[Federal Register Volume 64, Number 244 (Tuesday, December 21, 1999)]
[Rules and Regulations]
[Pages 71282-71283]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-32736]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-248-AD; Amendment 39-11475; AD 99-26-15]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and B4 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Airbus Model A300 B2 and B4 series airplanes, 
that requires repetitive inspections to detect cracking of the inner 
skin panel of the longitudinal lap joint; and repair, or modification 
and new repetitive inspections, if necessary. 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 detect and correct stress corrosion cracking of 
the inner skin panel of the longitudinal lap joint, which could result 
in rapid depressurization of the airplane.

DATES: Effective January 25, 2000.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 25, 2000.

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 A300 B2 and 
B4 series airplanes was published in the Federal Register on October 
21, 1999 (64 FR 56712). That action proposed to require repetitive 
inspections to detect cracking of the inner skin panel of the 
longitudinal lap joint; and repair, or modification and new repetitive 
inspections, if necessary.

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 3 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 4 work hours per 
airplane to accomplish the required eddy current inspection (either 
internal or external), and that the average labor rate is $60 per work 
hour. Based on these figures, the cost impact of this AD on U.S. 
operators is estimated to be $720, or $240 per airplane, per inspection 
cycle.
    The cost impact figure discussed above is 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 a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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.

[[Page 71283]]

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.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

99-26-15 AIRBUS: Amendment 39-11475. Docket 98-NM-248-AD.

    Applicability: Model A300 B2 and B4 series airplanes, 
manufacturer serial numbers 003 through 156 inclusive, certificated 
in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
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 (f) 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 detect and correct stress corrosion cracking of the inner 
skin panel of the longitudinal lap joint, which could result in 
rapid depressurization of the airplane, accomplish the following:

Initial Inspection

    (a) Within 400 flight cycles after the effective date of this 
AD, perform an external eddy current inspection for cracking of the 
inner skin panel of the longitudinal lap joint between frames 65 and 
72 at stringer 57, in accordance with Airbus Service Bulletin A300-
53-305, Revision 1, dated January 29, 1999.

Repetitive Inspections

    (b) If no cracking is detected during the inspection performed 
in accordance with paragraph (a) of this AD: Thereafter, perform an 
internal or external eddy current inspection, as specified in 
paragraphs (b)(1) and (b)(2) of this AD, as applicable; at intervals 
not to exceed 1,250 flight cycles or 7 months, whichever occurs 
first; in accordance with Airbus Service Bulletin A300-53-305, 
Revision 1, dated January 29, 1999; until the requirements of 
paragraph (e) of this AD have been accomplished.
    (1) If the most recent inspection was an internal eddy current 
inspection, perform an external eddy current inspection of the inner 
skin panel of the longitudinal lap joint.
    (2) If the most recent inspection was an external eddy current 
inspection, perform an internal eddy current inspection of the inner 
skin panel of the longitudinal lap joint.

Corrective Actions

    (c) If any cracking is detected during any inspection performed 
in accordance with paragraph (a) or (b) of this AD, prior to further 
flight, accomplish the actions required by either paragraph (c)(1) 
or paragraph (c)(2) of this AD.
    (1) Repair the inner skin panel of the longitudinal lap joint in 
accordance with Airbus Service Bulletin A300-53-305, Revision 1, 
dated January 29, 1999. Thereafter, repeat the inspection of areas 
in which no cracking is detected at the interval specified in, and 
in accordance with, paragraph (b) of this AD; and repeat the 
inspection of the repaired area at the intervals specified in the 
service bulletin, in accordance with the service bulletin. If any 
cracking is found in the repaired area during any repetitive 
inspection, prior to further flight, repair in accordance with the 
service bulletin.

    Note 2: Airbus Service Bulletin A300-53-305, Revision 1, dated 
January 29, 1999, references Airbus Structural Repair Manual Chapter 
53-17-00, as an additional source of service information to 
accomplish the repair specified in paragraph (c)(1) of this AD.

    (2) Modify the inner skin panel of the longitudinal lap joint in 
accordance with Airbus Service Bulletin A300-53-306, dated September 
5, 1995, and accomplish the requirements of paragraph (d) of this 
AD.
    (d) For airplanes modified in accordance with Airbus Service 
Bulletin A300-53-306, dated September 5, 1995: Inspect the modified 
inner skin panel of the longitudinal lap joint to detect cracking at 
the applicable threshold and repetitive intervals specified in Table 
1A, 1B, or 2 of Airbus Service Bulletin A300-53-211, Revision 5, 
dated April 29, 1999, in accordance with Airbus Service Bulletin 
A300-53-211, Revision 5. If any cracking is found during any 
repetitive inspection, prior to further flight, repair in accordance 
with Airbus Service Bulletin A300-53-211, Revision 5.

Optional Modification

    (e) Modification of the inner skin panel of the longitudinal lap 
joint in accordance with Airbus Service Bulletin A300-53-306, dated 
September 5, 1995, constitutes terminating action for the repetitive 
inspections required by paragraph (b) of this AD. Such modification 
does not terminate the repetitive inspections required by paragraph 
(d) of this AD.

Alternative Methods of Compliance

    (f) 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. 
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 3: 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

    (g) 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

    (h) The actions shall be done in accordance with Airbus Service 
Bulletin A300-53-306, dated September 5, 1995; Airbus Service 
Bulletin A300-53-211, Revision 5, dated April 29, 1999; and Airbus 
Service Bulletin A300-53-305, Revision 1, dated January 29, 1999, 
which contains the following list of effective pages:

------------------------------------------------------------------------
                                    Revision level
            Page No.                 shown on page    Date shown on page
------------------------------------------------------------------------
1-6, 8-12.......................  1.................  Jan. 29, 1999.
7...............................  Original..........  Sept. 5, 1995.
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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 4: The subject of this AD is addressed in French 
airworthiness directive 98-150-246(B), dated April 8, 1998.

    (i) This amendment becomes effective on January 25, 2000.

    Issued in Renton, Washington, on December 13, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-32736 Filed 12-20-99; 8:45 am]
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