[Federal Register Volume 63, Number 200 (Friday, October 16, 1998)]
[Rules and Regulations]
[Pages 55524-55526]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-27479]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-341-AD; Amendment 39-10842; AD 98-21-34]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300, A310, and 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 all Airbus Model A300, A310, and A300-600 series 
airplanes, that requires repetitive inspections to detect corrosion and 
cracks on the bottom area of the wing skin, and corrective action, 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 corrosion and cracks on the bottom area of the wing skin, which 
could result in reduced structural integrity of the airplane.

DATES: Effective November 20, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 20, 1998.

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 all Airbus Model A300, A310, and 
A300-600 series airplanes was published in the Federal Register on 
March 24, 1998 (63 FR 14044). That action proposed to require 
repetitive inspections to detect corrosion and cracks on the bottom 
area of the wing skin, and corrective action, if necessary.

Comments

    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.

Request to Clarify Certain Data in Table 3

    The commenter (the manufacturer) requests that the proposal be 
revised to specify the correct value for a certain inspection interval. 
The commenter notes that the compliance time listed in Table 3. of the 
proposed AD specifies that the nondestructive testing (NDT) high 
frequency eddy current (HFEC) inspection interval for area ``1, 2, 3a'' 
should read ``21,100 flight hours,'' instead of ``12,100 flight 
hours.''
    The FAA concurs. Based on a review of the information provided by 
the manufacturer, the FAA finds that, as published, the proposed AD 
contains a typographical error in Table 3. in the ``NDT (HFEC) 
Interval'' column for area ``1, 2, 3a.'' The FAA has revised Table 3. 
of the final rule to indicate the correct inspection interval of 21,100 
flight hours.

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 with the change described 
previously. The FAA has determined that this change will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    The FAA estimates that 49 Model A300 and A310 series airplanes, and 
51 Model A300-600 series airplanes, of U.S. registry will be affected 
by this AD, that it will take approximately 8 work hours per airplane 
per inspection cycle to accomplish the required actions, and that the 
average labor rate is $60 per work hour. Based on these figures, the 
cost impact of the AD on U.S. operators is estimated to be $48,000, or 
$480 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 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:

[[Page 55525]]

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:

98-21-34  Airbus Industrie: Amendment 39-10842. Docket 97-NM-341-AD.

    Applicability: All Model A300, A310, and A300-600 series 
airplanes; 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 (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 detect and correct corrosion and cracks on the bottom wing 
skin area, which could result in reduced structural integrity of the 
airplane, accomplish the following:
    (a) At the time specified in paragraph (a)(1), (a)(2), (a)(3), 
or (a)(4) of this AD, as applicable: Except as required by 
paragraphs (b) and (c) of this AD, perform an inspection for 
corrosion and cracks on the bottom wing skin area, and accomplish 
follow-on corrective actions, in accordance with Airbus Service 
Bulletin A300-57-0204, dated December 4, 1995 (for Model A300 series 
airplanes); A310-57-2061, dated December 4, 1995 (for Model A310 
series airplanes); or A300-57-6047, Revision 01, dated October 16, 
1996, as revised by Change Notice 1.A., dated February 24, 1997 (for 
Model A300-600 series airplanes); as applicable; subsequently 
referred to in this AD as the ``applicable'' service bulletins. 
Thereafter, repeat the inspection at intervals not to exceed 5 
years.
    (1) For airplanes with 5 years or less since date of 
manufacture: Prior to the accumulation of 5 years since date of 
manufacture or within 18 months after the effective date of this AD, 
whichever occurs later.
    (2) For airplanes with more than 5 years, but less than 15 years 
since date of manufacture: Within 18 months after the effective date 
of this AD.
    (3) For airplanes with more than 15 years, but less than 20 
years since date of manufacture: Within 12 months after the 
effective date of this AD.
    (4) For airplanes with more than 20 years since date of 
manufacture: Within 6 months after the effective date of this AD.
    (b) If any corrosion or crack is found during an inspection 
required by paragraph (a) of this AD, and the applicable service 
bulletin specifies to contact Airbus for an appropriate action: 
Prior to further flight, repair in accordance with a method approved 
by the Manager, International Branch, ANM-116, FAA, Transport 
Airplane Directorate.
    (c) If any crack is found during an inspection required by 
paragraph (a) of this AD, and the applicable service bulletin 
specifies to refer to Table B, Figure 4, of the service bulletin to 
determine the fatigue inspection threshold and interval: Use Table 
1, 2, 3, 4, or 5, of this AD, as applicable, to determine the 
fatigue inspection threshold and interval in flight cycles (FC) or 
flight hours (FH).

                Table 1.--Airbus Service Bulletin A300-57-204 (Model A300 B2) Fatigue Inspection
----------------------------------------------------------------------------------------------------------------
                                                                    Detailed visual      NDT (HFEC) Interval (FC
                 Area                    Threshold (FC or FH,     interval (FC or FH,    or FH, whichever occurs
                                       whichever occurs first)  whichever occurs first)           first)
----------------------------------------------------------------------------------------------------------------
1, 2, 3a \1\.........................  10,400 FC or 15,800 FH.  10,400 FC or 15,800 FH.  10,400 FC or 15,800 FH.
3b, 4a \2\...........................  7,200 FC or 11,000 FH..  2,500 FC or 3,800 FH...  6,300 FC or 9,600 FH.
4b...................................  10,400 FC or 15,800 FH.  10,400 FC or 15,800 FH.  10,400 FC or 15,800 FH.
5, 6.................................  9,900 FC or 15,100 FH..  8,700 FC or 13,200 FH..  9,900 FC or 15,100 FH.
7, 8.................................  6,600 FC or 10,000 FH..  5,000 FC or 7,700 FH...  6,400 FC or 9,700 FH.
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\1\ Area 3, as defined by Table B, Table 4, of SB A300-57-0204, has been split into areas 3a and 3b with a
  borderline between stiffener 43.2 and lattice flange 44 for Tables 1, 2, and 3 of this AD.
\2\ Area 4, as defined by Table B, Table 4, of SB A300-57-0204, has been split into areas 4a and 4b with a
  borderline between lattice flange 44 for stiffener 44.1 for Tables 1, 2, and 3 of this AD.


              Table 2.--Airbus Service Bulletin A300-57-204 (Model A300 B4-100) Fatigue Inspection
----------------------------------------------------------------------------------------------------------------
                                                                    Detailed visual      NDT (HFEC) interval (FC
                 Area                    Threshold (FC or FH,     interval (FC or FH,    or FH, whichever occurs
                                       whichever occurs first)  whichever occurs first)           first)
----------------------------------------------------------------------------------------------------------------
1, 2, 3a.............................  9,500 FC or 15,600 FH..  8,600 FC or 14,200 FH..  9,500 FC or 15,600 FH.
3b, 4a...............................  6,700 FC or 12,000 FH..  2,000 FC or 3,300 FH...  5,000 FC or 8,200 FH.
4b...................................  9,500 FC or 15,600 FH..  8,600 FC or 14,200 FH..  9,500 FC or 15,600 FH.
5, 6.................................  8,200 FC or 13,400 FH..  7,200 FC or 11,900 FH..  8,200 FC or 13,400 FH.
7, 8.................................  4,600 FC or 7,600 FH...  3,600 FC or 5,900 FH...  4,500 FC or 7,400 FH.
----------------------------------------------------------------------------------------------------------------


              Table 3.--Airbus Service Bulletin A300-57-204 (Model A300 B4-100) Fatigue Inspection
----------------------------------------------------------------------------------------------------------------
                                                                    Detailed visual      NDT (HFEC) interval (FC
                 Area                    Threshold (FC or FH,     interval (FC or FH,    or FH, whichever occurs
                                       whichever occurs first)  whichever occurs first)           first)
----------------------------------------------------------------------------------------------------------------
1, 2, 3a.............................  9,900 FC or 21,600 FH..  9,000 FC or 19,200 FH..  9,900 FC or 21,100 FH.
3b, 4a...............................  7,000 FC or 14,900 FH..  2,100 FC or 4,500 FH...  5,200 FC or 11,100 FH.
4b...................................  9,900 FC or 21,100 FH..  9,000 FC or 19,200 FH..  9,900 FC or 21,100 FH.
5, 6.................................  8,500 FC or 18,100 FH..  7,500 FC or 16,000 FH..  8,500 FC or 18,100 FH.
7, 8.................................  4,800 FC or 10,200 FH..  3,700 FC or 7,900 FH...  4,700 FC or 10,000 FH.
----------------------------------------------------------------------------------------------------------------


[[Page 55526]]


           Table 4.--Airbus Service Bulletin A330-57-2061 (Model A310 and A310-300) Fatigue Inspection
----------------------------------------------------------------------------------------------------------------
                                                                    Detailed visual      NDT (HFEC) interval (FC
                 Area                    Threshold (FC or FH,     interval (FC or FH,    or FH, whichever occurs
                                       whichever occurs first)  whichever occurs first)           first)
----------------------------------------------------------------------------------------------------------------
1....................................  12,800 FC or 36,600 FH.  10,500 FC or 29,900 FH.  12,800 FC or 36,600 FH.
2....................................  5,700 FC or 16,300 FH..  4,600 FC or 13,100 FH..  5,700 FC or 16,300 FH.
3, 5.................................  5,100 FC or 14,700 FH..  4,100 FC or 11,800 FH..  5,100 FC or 14,700 FH.
4....................................  4,500 FC or 12,800 FH..  1,800 FC or 5,100 FH...  4,500 FC or 12,800 FH.
6....................................  19,400 FC or 55,300 FH.  16,500 FC or 47,000 FH.  19,400 FC or 55,300 FH.
7....................................  16,300 FC or 46,500 FH.  13,800 FC or 39,500 FH.  16,300 FC or 46,500 FH.
----------------------------------------------------------------------------------------------------------------


               Table 5.--Airbus Service Bulletin A300-57-6047 (Model A300-600) Fatigue Inspection
----------------------------------------------------------------------------------------------------------------
                                                                    Detailed visual      NDT (HFEC) interval (FC
                 Area                    Threshold (FC or FH,     interval (FC or FH,    or FH, whichever occurs
                                       whichever occurs first)  whichever occurs first)           first)
----------------------------------------------------------------------------------------------------------------
1, 2.................................  13,600 FC or 42,900 FH.  11,800 FC or 37,000 FH.  15,500 FC or 48,800 FH.
3....................................  6,500 FC or 20,400 FH..  5,800 FC or 18,400 FH..  6,900 FC or 21,600 FH.
4, 6.................................  4,800 FC or 15,100 FH..  4,500 FC or 14,200 FH..  5,000 FC or 15,700 FH
5....................................  2,100 FC or 6,500 FH...  900 FC or 3,000 FH.....  2,100 FC or 6,500 FH.
7....................................  5,700 FC or 18,100 FH..  5,500 FC or 17,200 FH..  6,300 FC or 19,800 FH.
8....................................  2,400 FC or 7,400 FH...  2,100 FC or 6,500 FH...  2,400 FC or 7,400 FH.
----------------------------------------------------------------------------------------------------------------

    (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. 
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.

    (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.
    (f) Except as provided by paragraphs (b) and (c) of this AD, the 
actions shall be done in accordance with the following Airbus 
service bulletins, as applicable, which contain the specified 
effective pages:

----------------------------------------------------------------------------------------------------------------
  Service bulletin referenced and                          Revision level shown
               date                        Page No.               on page               Date shown on page
----------------------------------------------------------------------------------------------------------------
A300-57-0204, December 4, 1995....  1-101................  Original............  December 4, 1995.
A310-57-2061, December 4, 1995....  1-111................  Original............  December 4, 1995.
A300-57-6047, October 16, 1996....  1-3, 29, 30..........  01..................  October 16, 1996.
                                    4-29, 31-65..........  Original............  January 4, 1996.
Change Notice 1.A., February 24,    1, 2.................  Original............  February 24, 1997.
 1997, for Airbus Service Bulletin
 A300-57-6047, October 16, 1996.
----------------------------------------------------------------------------------------------------------------

    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 directive 97-006-210(B), dated January 2, 1997.

    (g) This amendment becomes effective on November 20, 1998.

    Issued in Renton, Washington, on October 7, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-27479 Filed 10-15-98; 8:45 am]
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