AD 90-25-13

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AD Number:
90-25-13
Document Type:
AD Final Rules
Docket Number:
90-NM-159-AD
Subject Heading:
Airworthiness Directives; AEROSPATIALE Caravelle SE 210 Model I, III, and VIR Series Airplanes
Subject:
Rear Spar
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
01/07/1991
Make:
Sud Aviation
Model:
Caravelle SE 210 Model I | Caravelle SE 210 Model III | Caravelle SE 210 Model VIR
Product Type:
Aircraft
Product Subtype:
Large Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 90-25-13
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   90-NM-159-AD

AMENDMENT:   39-6820

AD NUMBER:   90-25-13

SUBJECT HEADING:   Airworthiness Directives; AEROSPATIALE Caravelle SE 210 Model I, III, and VIR Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective January 7, 1991.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
90-25-13 AEROSPATIALE (FORMERLY SUD AVIATION/SUD-SERVICE): Amendment 39-6820. Docket No. 90-NM-159-AD.
Applicability: All Caravelle SE 210 Model I, III, and VIR series airplanes, certificated in any category.

Compliance: Required as indicated, unless previously accomplished.

To detect cracks in the rear spar upper cap at Rib 49 and to prevent reduced structural integrity of the wings, accomplish the following:

A. Prior to the accumulation of 25,000 landings, or within 120 days after the effective date of this AD, whichever occurs later, perform an eddy current rototest inspection of hole No. 1 (left and right wings) at the level of the rear spar upper cap (angle extrusion) and the splice under Rib 49, in accordance with Aerospatiale Service Bulletin 57-69, dated March 12, 1990. If no crack is detected in hole No. 1, the airplane may be returned to service.

B. If a crack is detected in the angle extrusion for hole No. 1, accomplish the following in accordance with Aerospatiale Service Bulletin 57-69, dated March 12, 1990:

1. Prior to further flight, repair the crack and perform an eddy current rototest inspection of holes No. 2 and 3 (left and right wings), in accordance with the service bulletin.

2. If no crack is found in holes No. 2 and 3, the airplane may be returned to service. Repeat the eddy current rototest inspection of hole No. 2 at intervals not to exceed 1,500 landings in accordance with the service bulletin.

3. If a crack is detected in holes No. 2 or 3, prior to further flight, repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.

C. 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, Transport Airplane Directorate.

NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113.

D. 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, 1601 Lind Avenue S.W., Renton, Washington 98055-4056.

This amendment (39-6820, AD 90-25-13) becomes effective on January 7, 1991.

FOOTER: