| AD Number | 90-10-01 | Status | Active |
| Effective Date | June 01, 1990 | Issue Date | Not specified |
| Docket Number | 90-NM-03-AD | Amendment | 39-6585 |
| 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 I Caravelle SE 210 Model III Caravelle SE 210 Model VIR |
90-10-01 AEROSPATIALE (FORMERLY SUD AVIATION/SUD-SERVICE): Amendment 39-6585. Docket No. 90-NM-03-AD.
Applicability: All Aerospatiale Caravelle Model SE 210 Model series airplanes, certificated in any category.
Compliance: Required as indicated, unless previously accomplished.
To detect fatigue cracks in the wing-to-fuselage junction and fuselage lower section components, accomplish the following:
A. Prior to the accumulation of 29,000 landings, or within 2,000 landings after the effective date of this AD, whichever occurs later, perform one of the following inspections in accordance with Aerospatiale Service Bulletin 53-51, Revision 6, dated July 31, 1986:
1. Visual inspection of the wing-to-fuselage junction fittings at Frames 31 and 35, in accordance with the service bulletin. Repeat this inspection thereafter at intervals not to exceed 2,500 landings; or
2. Visual and eddy current inspection of the wing-to-fuselage junction fittings at Frames 31and 35, and a magnetic particle inspection of all removed horizontal bolts, in accordance with the service bulletin. Repeat this inspection thereafter at intervals not to exceed 7,500 landings.
B. If cracks or sheared bolts or rivets are detected during the inspection required by paragraph A., above, replace with serviceable parts prior to further flight, in accordance with Aerospatiale Service Bulletin 53-51, Revision 6, dated July 31, 1986. Repeat inspections thereafter at intervals specified in paragraph A., above.
C. Prior to the accumulation of 29,000 landings, or within 2,000 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 2,500 landings, perform a visual and dye penetrant inspection of the fuselage lower section beam under Rib 52, the attachment fittings at the rear section of Rib 52, and the front pick-up fittings between the beam under Rib 52 and the canted frames at Frame 30, in accordance with Aerospatiale Service Bulletin 53-52, Revision 7, dated March 22, 1988.
D. If sheared-off attachment hardware is detected during the inspection required by paragraph C., above, prior to further flight replace with serviceable parts in accordance with the Structural Repair Manual, Chapter 57-1-33. Repeat the inspection identified in paragraph C., above, at intervals not to exceed 2,500 landings.
E. If cracks are detected during the inspection required by paragraph C., above, in Fittings 210.12.52.382/383 and 210.22.53.012 at the attachment level, prior to further flight, repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. Repeat the inspection identified in paragraph C., above, at an interval to be approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region.
F. If cracks are detected during the inspection required by paragraph C., above, in Fittings 210.12.52.382/383 and 210.22.53.012 outside the attachment areas, prior to further flight, replace with new fittings, in accordance with Aerospatiale Service Bulletin 53-52, Revision 7, dated March 22, 1988. Repeat the inspection identified in paragraph C., above, at intervals not to exceed 2,500 landings.
G. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM- 113, FAA, Northwest Mountain Region.
NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Standardization Branch, ANM-113.
H. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD.
All persons affected by this directive who have not already received the appropriate service documents from the manufacturer mayobtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington.
This amendment (39-6585, AD 90-10-01) becomes effective on June 1, 1990.