90-11-03 AEROSPATIALE (FORMERLY SUD AVIATION/SUD-SERVICE): Amendment 39-6604. Docket No. 90-NM-08-AD.
Applicability: Caravelle SE 210 Model III and VIR series airplanes, certificated in any category.
Compliance: Required as indicated, unless previously accomplished.
To prevent failure of the main landing gear diagonal brace struts and subsequent collapse of the main landing gear, accomplish the following:
A. Prior to the accumulation of 25,000 landings, or within 50 landings after the effective date of this AD, whichever occurs later, perform a visual and high frequency eddy current or rototest inspection of the main landing gear framework brace struts in the area of the 5 mm drain hole located 120 mm from the tapered end of Rib 38, in accordance with Aerospatiale Service Bulletin 32-122, dated November 10, 1988.
B. If no cracks are found, repeat the inspections required by paragraph A., above, at intervals not to exceed 4,500 landings.
C. If cracks found are more than 12 mm in length, prior to further flight, replace brace strut, in accordance with Aerospatiale Service Bulletin 32-122, dated November 10, 1988. Repeat the inspection required by paragraph A., above, at intervals not to exceed 4,500 landings.
D. If cracks found are 12 mm or less in length, accomplish the following in accordance with Aerospatiale Service Bulletin 32-122, dated November 10, 1988:
1. Cracks measuring 1 mm or less:
a. Ream the drain hole to 8 mm diameter in accordance with paragraph 5.C.(1) of the service bulletin.
b. Repeat the inspection required by paragraph A., above, at intervals not to exceed 3,400 flights.
2. Cracks measuring more than 1 mm but less than or equal to 7 mm:
a. Drill and ream a 5 mm diameter hole at the end of the cracks in accordance with paragraph 5.C.(2) of the service bulletin.
b. Repeat inspection required by paragraph A., above, at intervals not to exceed 550 landings.
3. Cracks measuring more than 7 mm but less than or equal to 12 mm:
a. Drill and ream a 5 mm diameter hole at the end of the cracks in accordance with paragraph 5.C.(2) of the service bulletin.
b. Repeat the inspection required by paragraph A., above, at intervals not to exceed 25 landings until replacement of brace strut. Upon replacement of brace strut, repeat inspections at intervals not to exceed 4,500 landings.
E. If recurring cracks are found during the repetitive inspections required by paragraph D., above, prior to further flight, replace the brace strut, in accordance with Aerospatiale Service Bulletin 32- 122, dated November 10, 1988. Upon the installation of a new brace strut, repeat inspections in accordance with paragraph A., above, at intervals not to exceed 4,500 landings.
F. 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.
G. 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 may obtain 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 (39-6604, AD 90-11-03) becomes effective on June 19, 1990.