AD 93-05-04

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AD Number:
93-05-04
Document Type:
AD Final Rules
Docket Number:
92-NM-112-AD
Subject Heading:
AIRBUS INDUSTRIE Model A300 B2-1C, B2-203, B2K-3C, B4-2C, B4-103, and B4-203 Series Airplanes
Subject:
Inspect Pylon Panel Of Fire Extinguisher Access Doors
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
04/29/1993
Make:
Airbus SAS
Model:
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Superseded AD: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Superseded By: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: 93-05-04
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   92-NM-112-AD

AMENDMENT:   39-8509

AD NUMBER:   93-05-04

SUBJECT HEADING:   AIRBUS INDUSTRIE Model A300 B2-1C, B2-203, B2K-3C, B4-2C, B4-103, and B4-203 Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective April 29, 1993.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
93-05-04 AIRBUS INDUSTRIE: Amendment 39-8509. Docket 92-NM-112-AD.

Applicability: Model A300 B2-1C, B2-203, B2K-3C, B4-2C, B4-103, and B4-203 series airplanes; equipped with General Electric (GE) engines on which engine Pylon Modification No. 2434, as described in Airbus Industrie Service Bulletin A300-54-070, Revision 1, dated March 17, 1992, has not been installed; certificated in any category.

Compliance: Required as indicated, unless accomplished previously.

To prevent reduced structural integrity of the engine pylon, accomplish the following:

(a) Prior to the accumulation of 22,400 total hours time-in-service, or within 1,000 hours time-in-service after the effective date of this AD, whichever occurs later, perform an initial visual and eddy current inspection to detect wear or cracks of the inner doubler on the pylon side panel around the fire extinguisher access doors, in accordance with Airbus Industrie Service Bulletin A300-54-070, Revision 1, dated March 17, 1992. If cracks are detected, prior to further flight, accomplish the requirements of either paragraph (a)(1) or (a)(2) of this AD, as applicable:

(1) If cracks less than 5 mm (0.197 inch) are detected, prior to further flight, repair in an accordance with a method approved by the Manager, Standardization Branch, ANM- 113, FAA, Transport Airplane Directorate.
(2) If cracks greater than or equal to 5 mm (0.019 inch) are detected, accomplish either paragraph (a)(2)(i) or (a)(2)(ii), as applicable:
(i) For airplanes on which the modification described in Airbus Industrie Service Bulletin No. A300-54-046 (screwed doors) has been accomplished: Prior to further flight, replace the doubler. Replacement of the doubler constitutes terminating action for the inspections required by this AD.
(ii) For airplanes on which the modification described in Airbus Industrie Service Bulletin No. A300-54-046 (screwed doors) has not been accomplished: Prior to further flight, replace the doubler. Prior to the accumulation of 22,400 hours time-in-service after replacement of the doubler, perform the visual and eddy current inspections in accordance with paragraph (a) of this AD; and repeat those inspections thereafter in accordance with paragraphs (b), (c), (d), or (e) of this AD, as applicable.

(b) For airplanes having Configuration No. 1.A.: Repeat the visual and eddy current inspections to detect doubler wear and cracks, as required by paragraph (a) of this AD, in accordance with Airbus Industrie Service Bulletin A300-54-070, Revision 1, dated March 17, 1992, as follows:
(1) No further action is necessary for the following airplanes:
(i) Airplanes on which the modification described in Airbus Industrie Service Bulletin No. A300-54-046 (screwed doors) has been accomplished, and the measured doubler wear, as detected by any visual inspection required by this AD, is less than 0.5 mm (0.019 inch).
(ii) Airplanes on which the modification described in Airbus Industrie Service Bulletin No. A300-54-046 (screwed doors) has not been accomplished, and the measured doubler wear, as detected by any visual inspection required by this AD, is less than 0.1 mm (0.004 inch).

(2) For airplanes on which the modification described in Airbus Industrie Service Bulletin No. A300-54-046 (screwed doors) has not been accomplished, if the measured doubler wear, as detected by any visual inspection required by this AD, is equal to or greater than to 0.1 mm (0.004 inch) and less than 0.5 mm (0.019 inch): Repeat the visual and eddy current inspections at intervals not to exceed 4,400 hours time-in-service.
NOTE: Subsequent action to be taken (repetitive inspections or inner doubler replacement) will depend upon the "worst finding," defined as the area with the largest amount of measured doubler wear.

(3) For airplanes on which the measured doubler wear, as detected by any visual inspection required by this AD, is equal to or greater than 0.5 mm (0.019 inch) and less than 2 mm (0.078 inch): Repeat the visual and eddy current inspections at intervals not to exceed 4,400 hours time-in-service.

(4) For airplanes on which the measured doubler wear, as detected by any visual inspection required by this AD, is equal to or greater than 2 mm (0.078 inch) and less than 4 mm (0.157 inch): Repeat the visual and eddy current inspections at intervals not to exceed 1,800 hours time-in-service.

(5) For airplanes on which the measured doubler wear, as detected by any visual inspection required by this AD, is equal to or greater than 4 mm (0.157 inch) and less than 6 mm (0.236 inch): Accomplish either paragraph (b)(5)(i), (b)(5)(ii), or (b)(5)(iii) of this AD.
(i) Repeat the visual and eddy current inspection at intervals not to exceed 350 hours time-in-service. Or
(ii) If the modification described in Airbus Industrie Service Bulletin No. A300-54-046 (screwed doors) has been accomplished: Prior to further flight, replace the doubler. Replacement of the doubler constitutes terminating action for the inspections required by this AD. Or
(iii) If the modification described in Airbus Industrie Service Bulletin No. A300-54-046 (screwed doors) has not been accomplished: Prior to further flight, replace the doubler. Prior to the accumulation of 22,400 hours time-in-service after replacement of the doubler, perform the visual and eddy current inspections in accordance with paragraph (a) of this AD, and repeat those inspections thereafter in accordance with paragraph (b) of this AD.

(6) For airplanes on which the measured doubler wear, as detected by any visual inspection required by this AD, is equal to or greater than 6 mm (0.236 inch): Prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.

(c) For airplanes having Configuration No. 1.B: Repeat the visual and eddy current inspections for doubler wear and cracks, as required by paragraph (a) of this AD, in accordance with Airbus Industrie Service Bulletin A300-54-070, Revision 1, dated March 17, 1992, as follows:

(1) No further action is necessary for the following airplanes:
(i) Airplanes on which the modification described in Airbus Industrie Service Bulletin No. A300-54-046 (screwed doors) has been accomplished, and the measured doubler wear, as detected by any visual inspection required by this AD, is less than 0.5 mm (0.019 inch).
(ii) Airplanes on which the modification described in Airbus Industrie Service Bulletin No. A300-54-046 (screwed doors) has not been accomplished, and the measured doubler wear, as detected by any visual inspection required by this AD, is less than 0.1 mm (0.004 inch).

(2) For airplanes on which the modification described in Airbus Industrie Service Bulletin No. A300-54-046 (screwed doors) has not been accomplished, if the measured doubler wear, as detected by any visual inspection required by this AD, is equal to or greater than to 0.1 mm (0.004 inch) and less than 0.5 mm (0.019 inch): Repeat the visual and eddy current inspections at intervals not to exceed 3,400 hours time-in-service.
NOTE: Subsequent action to be taken (repetitive inspections or inner doubler replacement) will depend upon the "worst finding," defined as the area with the largest amount of measured doubler wear.

(3) For airplanes on which the measured doubler wear, as detected by any visual inspection required by this AD, is equal to or greater than 0.5 mm (0.019 inch) and less than 2 mm (0.078 inch): Repeat the visual and eddy current inspections at intervals not to exceed 3,400 hours time-in-service.

(4) For airplanes on which the measured doubler wear, as detected by any visual inspection required by this AD, is equal to or greater than 2 mm (0.078 inch) and less than 4 mm (0.157 inch): Accomplish either paragraph (c)(4)(i), (c)(4)(ii), or (c)(4)(iii) of this AD.
(i) Repeat the visual and eddy current inspection at intervals not to exceed 300 hours time-in-service. Or
(ii) If the modification described in Airbus Industrie Service Bulletin No. A300-54-046 (screwed doors) has been accomplished: Prior to further flight, replace the doubler. Replacement of the doubler constitutes terminating action for the inspections required by this AD. Or
(iii) If the modification described in Airbus Industrie Service Bulletin No. A300-54-046 (screwed doors) has not been accomplished: Prior to further flight, replace the doubler. Prior to the accumulation of 22,400 hours time-in-service after the replacement date of the doubler, perform the visual and eddy current inspections in accordance with paragraph (a) of this AD, and repeat those inspections thereafter in accordance with paragraph (c) of this AD.

(5) For airplanes on which the measured doubler wear, as detected by any visual inspection required by this AD, is greater than or equal to 4 mm (0.157 inch): Prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.

(d) For airplanes having Configuration No. 1.A. on which the modification described in Airbus Industrie Service Bulletin No. A300-54-008 (door with 4 latches) has been accomplished; and for airplanes having Configuration No. 2.A.: Repeat the visual and eddy current inspections for doubler wear and cracks at zones D1, D2, D3, and D4, as required by paragraph (a) of this AD, in accordance with Airbus Industrie Service Bulletin A300-54-070, Revision 1, dated March 17, 1992, as follows:

(1) No further action is necessary for the following airplanes:
(i) Airplanes on which the modification described in Airbus Industrie Service Bulletin No. A300-54-046 (screwed doors) has been accomplished, and the measured doubler wear, as detected by any visual inspection required by this AD, is less than 0.5 mm (0.019 inch).
(ii) Airplanes on which the modification described in Airbus Industrie Service Bulletin No. A300-54-046 (screwed doors) has not been accomplished, and the measured doubler wear, as detected by any visual inspection required by this AD, is less than 0.1 mm (0.004 inch).

(2) For airplanes on which the modification described in Airbus Industrie Service Bulletin No. A300-54-046 (screwed doors) has not been accomplished, if the measured doubler wear, as detected by any visual inspection required by this AD, is equal to or greater than to 0.1 mm (0.004 inch) and less than or equal to 0.5 mm (0.019 inch): Repeat the visual and eddy current inspections at intervals not to exceed 5,800 hours time-in-service.
NOTE: Subsequent action to be taken (repetitive inspections or inner doubler replacement) will depend upon the "worst finding," defined as the area with the largest amount of measured doubler wear.

(3) For airplanes on which the measured doubler wear, as detected by any visual inspection required by this AD, is greater than 0.5 mm (0.019 inch) and less than 2 mm (0.078 inch): Repeat the visual and eddy current inspections at intervals not to exceed 5,800 hours time-in-service.

(4) For airplanes on which the measured doubler wear, as detected by any visual inspection required by this AD, is greater than 2 mm (0.078 inch) and less than 4 mm (0.157 inch): Repeat the visual and eddy current inspections at intervals not to exceed 4,300 hours time-in-service.

(5) For airplanes on which the modification described in Airbus Industrie Service Bulletin No. A300-54-046 (screwed doors) has been accomplished, if the measured doubler wear, as detected by any visual inspection required by this AD, is greater than 4 mm (0.157 inch) and less than 6 mm (0.236 inch): Repeat the visual and eddy current inspection at intervals not to exceed 2,300 hours time-in-service.

(6) For airplanes on which the measured doubler wear, as detected by any visual inspection required by this AD, is greater than 6 mm (0.236 inch) and less than 8 mm (0.315 inch): Accomplish either paragraph (d)(6)(i), (d)(6)(ii), or (d)(6)(iii) of this AD.
(i) Repeat the visual and eddy current inspections at intervals not to exceed 450 hours time-in-service. Or
(ii) If the modification described in Airbus Industrie Service Bulletin No. A300-54-046 (screwed doors) has been accomplished: Prior to further flight, replace the doubler. Replacement of the doubler constitutes terminating action for the inspections required by this AD. Or
(iii) If the modification described in Airbus Industrie Service Bulletin No. A300-54-046 (screwed doors) has not been accomplished: Prior to further flight, replace the doubler. Prior to the accumulation of 22,400 hours time-in-service after replacement the doubler, perform the visual and eddy current inspections in accordance with paragraph (a) of this AD, and repeat those inspections thereafter in accordance with paragraph (d) of this AD.

(7) For airplanes on which the measured doubler wear, as detected by any visual inspection required by this AD, is greater than or equal to 8 mm (0.315 inch): Prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.

(e) For airplanes having Configuration No. 1.B. on which the modification described in Airbus Industrie Service Bulletin No. A300-54-008 (door with 4 latches) has been accomplished; and for airplanes having Configuration No. 2.B.: Repeat the visual and eddy current inspections for doubler wear and cracks at zones D1, D2, D3, and D4, as required by paragraph (a) of this AD, in accordance with Airbus Industrie Service Bulletin A300-54-070, Revision 1, dated March 17, 1992, as follows:

(1) No further action is necessary for the following airplanes:
(i) Airplanes on which the modification described in Airbus Industrie Service Bulletin No. A300-54-046 (screwed doors) has been accomplished, and the measured doubler wear, as detected by any visual inspection required by this AD, is less than 0.5 mm (0.019 inch).
(ii) Airplanes on which the modification described in Airbus Industrie Service Bulletin No. A300-54-046 (screwed doors) has not been accomplished, and the measured doubler wear, as detected by any visual inspection required by this AD, is less than 0.1 mm (0.004 inch).

(2) For airplanes on which the modification described in Airbus Industrie Service Bulletin No. A300-54-046 (screwed doors) has not been accomplished, if the measured doubler wear, as detected by any visual inspection required by this AD, is greater than 0.1 mm (0.004 inch) and less than 0.5 mm (0.019 inch): Repeat the visual and eddy current inspections at intervals not to exceed 4,500 hours time-in-service.

NOTE: Subsequent action to be taken (repetitive inspections or inner doubler replacement) will depend upon the "worst finding," defined as the area with the largest amount of measured doubler wear.

(3) For airplanes on which the measured doubler wear, as detected by any visual inspection required by this AD, is greater than 0.5 mm (0.019 inch) and less than 2 mm (0.078 inch): Repeat the visual and eddy current inspections at intervals not to exceed 4,500 hours time-in-service.

(4) For airplanes on which the measured doubler wear, as detected by any visual inspection required by this AD, is greater than 2 mm (0.078 inch) and less than 4 mm (0.157 inch): Repeat the visual and eddy current inspections at intervals not to exceed 3,300 hours time-in-service.

(5) For airplanes on which the measured doubler wear, as detected by any visual inspection required by this AD, is greater than 4 mm (0.157 inch) and less than 6 mm (0.236 inch): Repeat the visual and eddy current inspections at intervals not to exceed 1,800 hours time-in-service.

(6) For airplanes on which the measured doubler wear, as detected by any visual inspection required by this AD, is greater than 6 mm (0.236 inch) and less than 8 mm (0.315 inch): Accomplish either paragraph (e)(6)(i), (e)(6)(ii), or (e)(6)(iii) of this AD.
(i) Repeat the visual and eddy current inspections at intervals not to exceed 400 hours time-in-service. Or
(ii) If the modification described in Airbus Industrie Service Bulletin A300-54-046 (screwed doors) has been accomplished: Prior to further flight, replace the doubler. Replacement of the doubler constitutes terminating action for the inspections required by this AD. Or
(iii) If the modification described in Airbus Industrie Service Bulletin No. A300-54-046 (screwed doors) has not been accomplished: Prior to further flight, replace the doubler. Prior to the accumulation of 22,400 hours time-in-service after replacement of the doubler, perform the visual and eddy current inspections in accordance with paragraph (a) of this AD, and repeat those inspections thereafter in accordance with paragraph (e) of this AD.

(7) For airplanes on which the measured doubler wear, as detected by any visual inspection required by this AD, is greater than or equal to 8 mm (0.315 inch): Prior to further flight, repair in accordance with a method approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.

(f) Accomplishment of the replacement of the inner doubler on the pylon side panel around the fire extinguisher access doors; and installation of the modification (screwed doors) in accordance with Airbus Industrie Service Bulletin No. A300-54-046, dated June 24, 1982, and Change Notice, dated July 8, 1985; constitutes terminating action for the visual and eddy current inspections required by this AD.

(g) 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.

(h) 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.

(i) The modification shall be done in accordance with Airbus Industrie Service Bulletin No. A300-54-046, dated June 24, 1982; and Change Notice, dated July 8, 1985, for Airbus Industrie Service Bulletin No. A300-54-046, dated June 24, 1982. The inspections shall be done in accordance Airbus Industrie Service Bulletin No. A300-54-070, Revision 1, dated March 17, 1992, which contains the following list of effective pages:

Page Number
	
Revision Level
Shown on Page
	
Date
Shown on Page


1-10, 31-32
	
1
	
March 17, 1992


11-30, 33-34
	
Original
	
February 6, 1992

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.

(j) This amendment becomes effective on April 29, 1993.

FOOTER: