AD 93-05-12

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AD Number:
93-05-12
Document Type:
AD Final Rules
Docket Number:
92-NM-214-AD
Subject Heading:
Airworthiness Directives; AIRBUS INDUSTRIE Model A320 Series Airplanes
Subject:
Wing Rear Spar
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
05/05/1993
Make:
Airbus
Model:
A320-111 | A320-211 | A320-212 | A320-214 | A320-231 | A320-232 | A320-233
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Superseded AD: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Superseded By: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: 93-05-12
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   92-NM-214-AD

AMENDMENT:   39-8516

AD NUMBER:   93-05-12

SUBJECT HEADING:   Airworthiness Directives; AIRBUS INDUSTRIE Model A320 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective May 5, 1993.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
93-05-12 AIRBUS INDUSTRIE: Amendment 39-8516. Docket 92-NM-214-AD.

Applicability: Model A320 series airplanes; serial numbers 002 through 071, inclusive; certificated in any category.

Compliance: Required as indicated, unless accomplished previously.

To prevent reduced structural integrity of the wing, accomplish the following:

(a) Prior to the accumulation of 13,000 total landings, or within 1,000 landings after the effective date of this AD, whichever occurs later: Perform a detailed visual inspection to detect cracks in the left- and right-hand sides of the wing rear spar between ribs 1 and 2, in accordance with Airbus Industrie Service Bulletin A320-57-1020, dated September 5, 1991.
(1) If any crack is found, prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.
(2) If no cracks are found, repeat the inspection required by paragraph (a) of this AD thereafter at intervals not to exceed 3,000 landings.

(b) Within 3 years after the effective date of this AD, modify the outer wing rear spar forward face between ribs 1 and 2, in accordance with Airbus Industrie Service Bulletin A320-57-1021, dated September 5, 1991.

(c) Accomplishment of the modification required by paragraph (b) of this AD constitutes terminating action for the repetitive inspections required by paragraph (a) of this AD.

(d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113.

NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113.

(e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.

(f) The inspection shall be done in accordance with Airbus Industrie Service Bulletin A320-57-1020, dated September 5, 1991. The modification shall be done in accordance with Airbus Industrie Service Bulletin A320-57-1021, dated September 5, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

(g) This amendment becomes effective on May 5, 1993.

FOOTER: