[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