| AD Number | 67-19-02 | Status | Active |
| Effective Date | July 10, 1967 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-434 |
| Product Type | ["Aircraft"] | Product Subtype | ["Large Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Airbus SAS |
| Model(s) | BAC 1-11 200 Series BAC 1-11 400 Series |
67-19-02 BRITISH AIRCRAFT: Amdt. 39-434, Part 39, Federal Register June 10, 1967. Applies to British Aircraft Corporation Model BAC 1-11, 200 and 400 Series Airplanes.
Compliance required as indicated, unless already accomplished.
To detect honeycomb delamination on all moveable control surfaces and tabs, accomplish the following:
(a) Within the next 600 hours' time in service after the effective date of this AD for airplanes with 1000 or more hours' time in service, or for airplanes with less than 1000 hours' time in service as of the effective date of this AD before the accumulation of 1500 hours' time in service, tap test all control surfaces and tabs for evidence of delamination of the skin from the honeycomb structure in accordance with British Aircraft Corporation Alert Service Bulletin No. 55/57-A-PM 2597, dated September 19, 1966, or later ARB-approved issue.
(b) If the control surfaces with delamination are within the permissible limits specified in BAC Structural Repair Manual, they may remain in service, but must be inspected in accordance with paragraph (a) at intervals not to exceed 300 hours' time in service from the date of the last inspection.
(c) Control surfaces with delaminations exceeding the permissible limits as specified in BAC Structural Repair Manual, must be repaired or replaced, before further flight, in accordance with this Structural Repair Manual, or later ARB-approved issue, or FAA-approved equivalent.
This amendment effective July 10, 1967.