[Federal Register Volume 62, Number 186 (Thursday, September 25, 1997)]
[Rules and Regulations]
[Pages 50251-50253]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-25164]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-NM-170-AD; Amendment 39-10145; AD 97-20-07]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300-600 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 A300-600 series airplanes, that
requires repetitive inspections to detect fatigue cracking in the left
and right wings in the area where the top skin attaches to the center
spar; and repair or modification of this area, if necessary. This
amendment is prompted by a report from the manufacturer indicating
that, during full-scale fatigue testing of the airframe, fatigue
cracking was detected in this area. The actions specified by this AD
are intended to detect and correct this cracking, which could reduce
the residual strength of the top skin of the wings, and consequently
affect the structural integrity of the airframe.
DATES: Effective October 30, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of October 30, 1997.
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: Charles Huber, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2589; 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 A300-600
series airplanes was published in the Federal Register on
[[Page 50252]]
May 1, 1997 (62 FR 23697). That action proposed to require repetitive
inspections to detect fatigue cracking in the left and right wings in
the area where the top skin attaches to the center spar between ribs 1
and 7; and repair or modification of this area, if necessary.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the single comment received.
The commenter supports the proposed rule.
Conclusion
After careful review of the available data, including the comment
noted above, 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 35 Airbus Model A300-600 series airplanes of
U.S. registry will be affected by this AD.
For airplanes on which Airbus Modification 10089 has not been
installed, it will take approximately 2 work hours to accomplish each
detailed visual inspection or 3 work hours to accomplish each high
frequency eddy current (HFEC) inspection. The average labor rate is $60
per work hour. Based on these figures, the cost impact of each
inspection on U.S. operators is estimated to be either $120 or $180 per
airplane, depending on the type of inspection conducted.
For airplanes on which Airbus Modification 10089 has been
installed, it will take approximately 3 work hours to accomplish each
low frequency eddy current inspection. The average labor rate is $60
per work hour. Based on these figures, the cost impact of the each
inspection on U.S. operators is estimated to be $180 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.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
97-20-07 Airbus: Amendment 39-10145. Docket 96-NM-170-AD.
Applicability: Model A300-600 series airplanes on which Airbus
Modification 10160 has not been installed during production;
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 (c) 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 fatigue cracking in the left and right
wings in the area where the top skin attaches to the center spar,
which could reduce the residual strength of this skin, and
consequently affect the structural integrity of the airframe,
accomplish the following:
(a) For airplanes on which Airbus Modification 10089 has not
been installed: Prior to the accumulation of 18,000 total landings,
or within 1,500 landings after the effective date of this AD,
whichever occurs later, conduct either a detailed visual inspection
or a high frequency eddy current (HFEC) inspection to detect fatigue
cracking in the left and right wings in the area where the top skin
attaches to the center spar between ribs 1 and 7, in accordance with
Airbus Service Bulletin A300-57-6044, Revision 2, dated September 6,
1995, including Appendix 1.
(1) If no cracking is detected, conduct repetitive inspections
thereafter at the following intervals:
(i) If the immediately preceding inspection was conducted using
detailed visual techniques, conduct the next inspection within 5,000
landings.
(ii) If the immediately preceding inspection was conducted using
HFEC techniques, conduct the next inspection within 9,500 landings.
(2) If any cracking is detected or suspected during any detailed
visual inspection required by paragraph (a), (a)(1), or (a)(3)(i) of
this AD, prior to further flight, confirm this finding and the
length of this cracking by conducting a HFEC inspection, in
accordance with the service bulletin. If no cracking is confirmed
during the HFEC inspection, accomplish the repetitive inspection
required by paragraph (a)(1)(ii) of this AD at the time specified in
that paragraph.
(3) If any cracking is detected or confirmed during any HFEC
inspection required by paragraph (a), (a)(1), or (a)(2) of this AD:
(i) If the cracking is 75 mm or less per rib bay, prior to
further flight, repair in accordance with the service bulletin.
Thereafter, conduct repetitive detailed visual inspections of the
repaired area at intervals not to exceed 50 landings, in accordance
with the service bulletin.
(ii) If the cracking exceeds 75 mm per rib bay, prior to further
flight, install Airbus Modification 10089, in accordance with the
service bulletin. Thereafter, conduct a low frequency eddy current
inspection in accordance with the requirements of paragraph (b) of
this AD.
Note 2: The Airbus service bulletin references Airbus Service
Bulletin A300-57-6041, Revision 4, dated November 16, 1995, as an
additional source of service information for installing Airbus
Modification 10089.
(b) For airplanes on which Airbus Modification 10089 has been
installed: Prior to the accumulation of 22,000 total landings after
this modification has been installed, or within 1,500 landings after
the effective date of this AD, whichever occurs later, conduct a low
frequency eddy current inspection to detect fatigue cracking in the
inboard and rear edges of the top skin reinforcing plates, in
accordance with Airbus Service Bulletin A300-57-6044, Revision 2,
dated September 6, 1995, including Appendix 1.
(1) If no cracking is detected, repeat this inspection
thereafter at intervals not to exceed 11,000 landings.
[[Page 50253]]
(2) If any cracking is detected, prior to further flight, repair
in accordance with a method approved by the Manager, Standardization
Branch, ANM-113, FAA, Transport Airplane Directorate. Thereafter,
repeat this inspection at intervals not to exceed 11,000 landings.
(c) 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 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(d) 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.
(e) The inspections and installation shall be done in accordance
with Airbus Service Bulletin A300-57-6044, Revision 2, dated
September 6, 1995, including Appendix 1, which contains the
specified effective pages:
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Revision level
Page number shown on page shown on page Date shown on page
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1-8............................ 2.............. Sept. 6, 1995.
9, 10.......................... Original....... Mar. 1, 1993.
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Appendix 1
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1.............................. 1.............. Nov. 25, 1994.
2-6............................ Original....... Mar. 1, 1993.
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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.
(f) This amendment becomes effective on October 30, 1997.
Issued in Renton, Washington, on September 17, 1997.
James V. Devany,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-25164 Filed 9-24-97; 8:45 am]
BILLING CODE 4910-13-U