AD 99-16-07

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AD Number:
99-16-07
Document Type:
AD Final Rules
Docket Number:
99-NM-17-AD
Subject Heading:
Airworthiness Directives; Airbus Model A310 Series Airplanes
Subject:
Inspect Upper Wing-To-Fuselage Fairings
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
09/13/1999
Make:
Airbus SAS
Model:
A310-203 | A310-204 | A310-221 | A310-222 | A310-304 | A310-322 | A310-324 | A310-325
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Superseded AD: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Superseded By: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 [64 FR 43050 No. 152 08/09/1999]
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 99-16-07
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   99-NM-17-AD

AMENDMENT:   39-11242

AD NUMBER:   99-16-07

SUBJECT HEADING:   Airworthiness Directives; Airbus Model A310 Series Airplanes

ACTION:   Final rule.

SUMMARY:   This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 series airplanes, that requires repetitive inspections to detect cracked or broken support brackets of the upper wing-to-fuselage fairings, and replacement of any discrepant support brackets with new brackets. This amendment also requires replacement of the fairing seals with new, improved seals; modification of the fairing panels; and installation of new bulkheads; which constitutes terminating action for the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent reduced structural integrity of the fairing support brackets, which could result in loss of the wing-to-fuselage fairings during flight, and consequent structural damage to the airplane.

DATES:   Effective September 13, 1999.

ADDRESSES:   The service information referenced in this AD may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:   Norman B. Martenson, Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2110; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:  
A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain Airbus Model A310 series airplanes was published in the Federal Register on April 28, 1999 (64 FR 22816). That action proposed to require repetitive inspections to detect cracked or broken support brackets of the upper wing-to-fuselage fairings, and replacement of any discrepant support brackets with new brackets. That action also proposed to require replacement of the fairing seals with new, improved seals; modification of the fairing panels; and installation of new bulkheads; which would constitute terminating action for the repetitive inspections.

Comments
Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were submitted in response to the proposal or the FAA's determination of the cost to the public.

Conclusion
The FAA has determined that air safety and the public interest require the adoption of the rule as proposed.

Cost Impact
The FAA estimates that 47 airplanes of U.S. registry will be affected by this AD.

It will take approximately 2 work hours per airplane to accomplish the required inspection, at an average labor rate of $60 per work hour. Based on these figures, the cost impact of the inspection required by this AD on U.S. operators is estimated to be $5,640, or $120 per airplane, per inspection cycle.

It will take approximately 6 work hours per airplane to accomplish the required replacement, modification, and installation, at an average labor rate of $60 per work hour. Required parts will cost approximately $1,690 per airplane. Based on these figures, the cost impact of the replacement, modification and installation required by this AD on U.S. operators is estimated to be $96,350, or $2,050 per airplane.

The cost impact figures discussed above are based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted.

Regulatory Impact
The regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment.

For the reasons discussed above, I certify that this action (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption "ADDRESSES."

List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39 - AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13 [Amended]
2. Section 39.13 is amended by adding the following new airworthiness directive:

REGULATORY TEXT:  
99-16-07 AIRBUS INDUSTRIE: Amendment 39-11242; Docket 99-NM-17-AD.

Applicability: Model A310-200 series airplanes, on which Airbus Modification 4800 or 4906 has been accomplished; and Model A310-300 series airplanes on which Airbus Modification 11758 has not been accomplished; certificated in any category.

NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Compliance: Required as indicated, unless accomplished previously.

To prevent reduced structural integrity of the support brackets of the upper wing-to- fuselage fairing, which could result in loss of the wing-to-fuselage fairings during flight, and consequent structural damage to the airplane, accomplish the following:

Initial/Repetitive Inspections
(a) Prior to the accumulation of 5,000 total flight hours or within 1,200 flight hours after the effective date of this AD, whichever occurs later: Perform a detailed visual inspection to detect cracked or broken support brackets of the upper wing-to-fuselage fairings, in accordance with Airbus Service Bulletin A310-53-2078, Revision 1, dated March 24, 1997. Repeat the detailed visual inspection thereafter at intervals not to exceed 2,500 flight hours.

Corrective Action
(b) If any discrepancy is detected during any inspection required by paragraph (a) of this AD, prior to further flight, replace the discrepant support bracket with a new bracket in accordance with Airbus Service Bulletin A310-53-2078, Revision 1, dated March 24, 1997. Repeat the inspection required by paragraph (a) of this AD thereafter at intervals not to exceed 2,500 flight hours.

Terminating Action
(c) Within 2 years after the effective date of this AD, accomplish the requirements of paragraphs (c)(1) and (c)(2) of this AD.

(1) Perform the initial inspection required by paragraph (a) of this AD in accordance with Airbus Service Bulletin A310-53-2078, Revision 1, dated March 24, 1997.

(2) Replace the fairing seals with new, improved seals; modify the fairing panels; and install new bulkheads; in accordance with Airbus Service Bulletin A310-53-2083, Revision 02, dated May 5, 1998. Accomplishment of these actions constitutes terminating action for the repetitive inspection requirements of this AD.

Alternative Methods of Compliance
(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, International Branch, ANM-116, 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, International Branch, ANM-116.

NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116.

Special Flight Permits
(e) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished.

Incorporation by Reference
(f) The actions shall be done in accordance with Airbus Service Bulletin A310-53-2078, Revision 1, dated March 24, 1997, and Airbus Service Bulletin A310-53-2083, Revision 02, dated May 5, 1998. 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.

NOTE 3: The subject of this AD is addressed in French airworthiness directives 97-175- 228(B) R1 and 98-450-261(B), both dated November 18, 1998.

(g) This amendment becomes effective on September 13, 1999.

FOOTER: