| AD Number | 64-27-03 | Status | Active |
| Effective Date | January 01, 1965 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-8 |
| Product Type | ["Aircraft"] | Product Subtype | ["Large Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Sud Aviation |
| Model(s) | Caravelle SE 210 Model VIR |
64-27-03 SUD AVIATION: Amdt. 39-8 Part 39 (New) Federal Register December 2, 1964. Applies to Model SE 210 Caravelle VIR Aircraft.
Compliance required as indicated.
In order to prevent fatigue failure of the main landing gear steel axle beams accomplish the following:
(a) Within 430 hours' time in service after the effective date of this AD and thereafter at intervals not exceeding 430 hours' time in service from the last inspection, visually inspect all main landing gear steel axle beams, P/N's 269028B and 269029B, for cracks around threaded holes, as specified in Hispano Suiza Aeroservice Bulletin No. 91 Section 1, No. 34 dated January 4, 1963. (Note: This inspection may be made without disassembly of tubing support components.)
(b) Within 860 hours' time in service after the effective date of this AD and thereafter at intervals not exceeding 860 hours' time in service from the last inspection, remove the lower tubing support shield and visually inspect witha magnifying glass the lower threaded holes in the main landing gear steel axle beams for cracks.
(c) Unless previously accomplished remove the lower tubing support shielding and inspect for cracks all lower threaded holes in the main landing gear steel axle beams and surrounding areas using fluorescent magnetic particle inspection or FAA approved equivalent at the following times:
(1) For landing gear with between 4,500 hours' and 5,100 hours' total time in service as of the effective date of this AD accomplish the inspection before the accumulation of 5,530 hours' total time in service.
(2) For landing gear with 5,100 or more hours' total time in service as of the effective date of this AD accomplish the inspection within 430 hours' total time in service after the effective date of this AD.
(d) Within 8,000 hours' total time in service rework all the lower threaded holes on axle beams as specified in Hispano Suiza Aero-service Bulletin No. 91 Section 1, No. 34dated January 4, 1963, or an FAA approved equivalent. The repetitive inspections specified in (b) and the inspection specified in (c) need not be performed after this rework has been accomplished.
(e) Within 12,000 hours' total time in service rework in accordance with Hispano Suiza Aeroservice Bulletin No. 91 Section 1, No. 34 dated January 4, 1963, or an FAA approved equivalent all holes in the landing gear which have not previously been reworked in accordance with (d). This AD no longer applies to aircraft on which this rework has been accomplished.
(f) Replace any parts found cracked before further flight.
(g) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Aircraft Certification Division, Paris, France, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase forsuch operator.
(Hispano Suiza Aeroservice Bulletin No. 91 Section 1, No. 34 dated January 4, 1963, covers this same subject.)
This directive effective January 1, 1965.