AD 93-08-13

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AD Number:
93-08-13
Document Type:
AD Final Rules
Docket Number:
93-NM-30-AD
Subject Heading:
Airworthiness Directives; AIRBUS INDUSTRIE Model A300 Series Airplanes
Subject:
Inspect Fuselage Skin
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
05/27/1993
Make:
Airbus
Model:
A300 B2-1A | A300 B2-1C | A300 B2-203 | A300 B2K-3C | A300 B4-103 | A300 B4-203 | A300 B4-2C
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Superseded AD: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Superseded By: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: 93-08-13
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   93-NM-30-AD

AMENDMENT:   39-8561

AD NUMBER:   93-08-13

SUBJECT HEADING:   Airworthiness Directives; AIRBUS INDUSTRIE Model A300 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective May 27, 1993.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
93-08-13 AIRBUS INDUSTRIE: Amendment 39-8561. Docket 93-NM-30-AD.

Applicability: Model A300 series airplanes; MSN 003 through MSN 107, inclusive; that have been modified in accordance with Airbus Industrie Service Bulletin A300-53-216 (Airbus Industrie Modification No. 6699); certificated in any category.

Compliance: Required as indicated, unless accomplished previously.

To prevent rapid loss of cabin pressure, accomplish the following:

(a) Within 50 landings after the effective date of this AD, perform a low-frequency eddy current inspection from outside the fuselage skin above the modified lap joint at stringer 43 (left- and right-hand) between frames 37 and 39 to detect damage, in accordance with Airbus Industrie All Operator Telex (AOT) 53-04, dated January 20, 1993.
(b) If no damage is found as a result of the inspection required by paragraph (a) of this AD, accomplish paragraphs (b)(1) and (b)(2) of this AD in accordance with Airbus Industrie All Operator Telex (AOT) 53-04, dated January 20, 1993.

(1) Perform a detailed visual inspection from outside the fuselage skin to detect damage in this area thereafter at intervals not to exceed 50 landings until the requirements of paragraph (b)(2) of this AD are accomplished. Prior to further flight, repair any crack that is found.

(2) Within 250 landings after accomplishing the initial (external eddy current) inspection, perform a detailed visual inspection from inside the fuselage skin to detect damage in this area. If no damage is found, no further action is required by this AD. If any damage is found, prior to further flight, measure the length and depth of the damage, and accomplish paragraph (b)(2)(i) or (b)(2)(ii) of this AD, as applicable.
(i) If the damage found is less than or equal to 0.7 mm in depth and 130 mm in length, and if no damage is found in adjacent frame bays, perform a detailed visual inspection from outside the fuselage skin thereafter at intervals not to exceed 50 landings. Prior to the accumulation of 250 landings after accomplishing the internal visual inspection, repair the damaged area in accordance with the AOT. Repair of the damaged area constitutes terminating action for the repetitive inspections required by this paragraph.
(ii) If the damage found is greater than 0.7 mm in depth or 130 mm in length, or if damage is found in the adjacent frame bays, prior to further flight, repair the damaged area in accordance with the AOT.

(c) If any damage is found as a result of the initial (external eddy current) inspection required by paragraph (a) of this AD, prior to further flight, perform a detailed visual inspection from inside the fuselage skin above the modified lap joint at stringer 43 (left- and right-hand) between frames 37 and 39 to detect damage, and measure the damage found in accordance with Airbus Industrie All Operator Telex (AOT) 53-04, dated January 20, 1993.

(1) If the damage found is less than or equal to 0.7 mm in depth and 130 mm in length, and if no damage is found in adjacent frame bays, perform a detailed visual inspection from outside the fuselage skin in this area thereafter at intervals not to exceed 50 landings. Prior to the accumulation of 250 landings after accomplishing the initial (external eddy current) inspection required by paragraph (a) of this AD, repair the damaged area in accordance with the AOT. Repair of the damaged area constitutes terminating action for the repetitive inspections required by this paragraph.

(2) If the damage found is greater than 0.7 mm in depth or 130 mm in length, or if damage is found in the adjacent frame bays, prior to further flight, repair the damaged area in accordance with the AOT.

(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 inspections, measurement, and repair shall be done in accordance with Airbus Industrie All Operator Telex 53-04, dated January 20, 1993. 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, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 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 27, 1993.

FOOTER: