AD 90-14-03

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AD Number:
90-14-03
Document Type:
AD Final Rules
Docket Number:
90-NM-38-AD
Subject Heading:
Airworthiness Directives; AEROSPATIALE Caravelle SE 210 Model III and VIR Series Airplanes
Subject:
Wing Spar
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
08/03/1990
Make:
Sud Aviation
Model:
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Superseded AD: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Superseded By: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:
Updated RGL applicability to match AD applicability; CAR C-11-185
AIRWORTHINESS DIRECTIVES FINAL RULES: 90-14-03
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   90-NM-38-AD

AMENDMENT:   39-6642

AD NUMBER:   90-14-03

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

ACTION:  

SUMMARY:  

DATES:   Effective August 3, 1990.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
90-14-03 AEROSPATIALE (FORMERLY SUD-SERVICE/SUD AVIATION): Amendment 39-6642. Docket No. 90-NM-38-AD.
Applicability: All Caravelle SE 210 Model III and VIR series airplanes, certificated in any category.

Compliance: Required as indicated, unless previously accomplished.

To identify and repair fatigue cracks in the wing spar box, which could result in reduced structural integrity of the wings, accomplish the following:

A. Perform an initial X-ray inspection on the left and right wing lower surface stiffeners located at the ends of the internal and external scalloped doublers between the rear and center spars of Ribs 42 and 43 (defined in the service bulletin as the "critical zone"), in accordance with Aerospatiale Service Bulletin 57-67, dated July 31, 1986, prior to the accumulation of 40,000 landings or within 1,000 landings after the effective date of this AD, whichever occurs later.

B. If no cracks are found as a result of the X-ray inspection required by paragraph A., above, repeat the inspection at intervals not to exceed 2,500 landings.

C. If cracks are suspected as a result of the X-ray inspection required by paragraph A., above, evaluate the extent of the damage by performing an ultrasonic inspection on the left and right wing lower surface stiffeners located at the ends of the internal and external scalloped doublers at the rear spar of Rib 43 (defined in the service bulletin as the "critical zone"), in accordance with Aerospatiale Service Bulletin 57-67, dated July 31, 1986.

1. If no cracks are found, repeat the X-ray inspection at intervals not to exceed 2,500 landings.

2. If cracks are found, accomplish the requirements of paragraph D., below.

D. If cracks are found, prior to further flight, perform an X-ray inspection of the expanded area to include splices at Ribs 45, 47, 50, and 51 (defined in the service bulletin as Zones B, C, D, E, F, and G), and the lower surface stiffeners between the front and center spars and between Ribs 42 and 43 (defined in the service bulletin as Zone A), in accordance with Aerospatiale Service Bulletin 57-67, dated July 31, 1986. Repair cracks prior to further flight, as follows:

1. If the cracks found are less than 8 mm in length, repair in accordance with Aerospatiale Service Bulletin 57-67, dated July 31, 1986. Repeat the X-ray inspection required by paragraph A., above, at intervals not to exceed 2,500 landings.

2. If the cracks found are equal to or greater than 8 mm in length, repair in a manner approved by the Manager, Standardization Branch, ANM 113, FAA, Northwest Mountain Region. Repeat the X-ray inspection required by paragraph A., above, at intervals approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region.

3. If no cracks are found, repeat the X-ray inspection required by paragraph A., above, at intervals not to exceed 5,000 landings.

E. 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 Maintenance Inspector (PMI). The PMI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113.

F. 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 (39-6642, AD 90-14-03) becomes effective on August 3, 1990.

FOOTER: