| AD Number | 63-19-05 | Status | Active |
| Effective Date | September 16, 1963 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | N/A |
| Product Type | ["Aircraft"] | Product Subtype | ["Rotorcraft"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | Federal Register: September 10, 1963 | ||
| Manufacturer(s) | Airbus Helicopters |
| Model(s) | SE 3130-Alouette II |
63-19-05 SUD AVIATION: Amdt. 614 Part 507 Federal Register September 10, 1963. Applies to All SE 3130 Alouette II Aircraft.
Compliance required as indicated.
To prevent fatigue failure of the main rotor hub P/N 3130.12.20.001 the following must be accomplished:
(a) The main rotor hub must be replaced with a new hub prior to accumulating a total of more than 600 hours' time in service, except as provided for in (b).
(b) The service life of the main rotor hub may be extended to a maximum of 1,200 hours' time in service if the hubs are inspected by means of the ultrasonic method specified in Sud Service Bulletin No. AL.II 12.11.204/A, or an FAA approved equivalent method, as follows:
(1) Hubs which have accumulated less than 600 hours' time in service on the effective date of this AD shall be inspected prior to 600 hours' time in service and thereafter at intervals not exceeding 50 hours' time in service.
(2) Hubs which have accumulated more than 600 hours' time in service on the effective date of this AD shall be inspected within 10 hours' time in service after the effective date, and thereafter at intervals not exceeding 50 hours' time in service.
(3) Replace cracked hubs before further flight.
(Sud Service Bulletin No. AL.II 12.11.204/A dated April 18, 1962, covers the same subject.)
This directive effective September 16, 1963.