[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:
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Revision level
Page No. shown on page Date shown on page
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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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