[Federal Register Volume 69, Number 190 (Friday, October 1, 2004)]
[Rules and Regulations]
[Pages 58828-58830]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-21816]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-254-AD; Amendment 39-13805; AD 2004-19-11]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A320 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Airbus Model A320 series airplanes, that 
currently requires modification of the rear spar web of the wing, cold 
expansion of certain attachment holes for the forward pintle fitting 
and certain holes at the actuating cylinder anchorage of the main 
landing gear (MLG), repetitive inspections for fatigue cracking in 
certain areas of the rear spar of the wing, and corrective action if 
necessary. That AD also provides for optional terminating action for 
the requirements of the AD. This amendment revises certain compliance 
times for the inspection. The actions specified by this AD are intended 
to detect and correct fatigue cracking, which may lead to reduced 
structural integrity of the wing and the MLG. This action is intended 
to address the identified unsafe condition.

DATES: Effective November 5, 2004.
    The incorporation by reference of a certain publication, as listed 
in the regulations, is approved by the Director of the Federal Register 
as of November 5, 2004.
    The incorporation by reference of certain other publications, as 
listed in the regulations, was approved previously by the Director of 
the Federal Register as of June 30, 2000 (65 FR 34069, May 26, 2000); 
February 14, 1994 (59 FR 1903, January 13, 1994); and June 11, 1993 (58 
FR 27923, May 12, 1993).

ADDRESSES: The service information referenced in this AD may be 
obtained from Airbus, 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 National Archives 
and Records Administration (NARA). For information on the availability 
of this material at NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2141; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 2000-10-15, 
amendment 39-11739 (65 FR 34069, May 26, 2000), which is applicable to 
certain Airbus Model A320 series airplanes, was published in the 
Federal Register on February 13, 2004 (69 FR 7176). The action proposed 
to retain the requirements of AD 2000-10-15 (modification of the rear 
spar web of the wing, cold expansion of certain attachment holes for 
the forward pintle fitting and certain holes at the actuating cylinder 
anchorage of the main landing gear (MLG), and repetitive inspections 
for fatigue cracking in certain areas of the rear spar of the wing; and 
corrective action if necessary; with optional terminating action for 
those requirements). The notice of proposed rulemaking (NPRM) proposed 
to revise the threshold and repetitive intervals for the inspection.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Support for the Proposed AD

    One commenter supports the AD as proposed.

Request To Revise Certain Compliance Time

    One commenter, an airline operator, suggests that the grace period 
(60 days) specified in paragraph (c)(1) of the proposed AD is overly 
restrictive. The operator requests that the grace period be changed to 
correspond to the next C-check (18 months for this operator). This 
recommended grace period would provide sufficient time for operators to 
do the optional terminating modification specified in the proposed AD. 
The operator reports that the modification (which has been done on 80 
percent of its fleet to date) has revealed only one cracked fastener 
hole, representing 0.05 percent of all fastener holes inspected. The 
operator asserts that its proposed grace period would still allow for 
the safe continued airworthiness of the affected airplanes.
    The FAA agrees with the commenter's request and rationale. We agree 
that the proposed 60-day grace period was unnecessarily restrictive. 
The commenter's proposed grace period approximates the grace periods 
mandated by the parallel French airworthiness directive. We have 
accordingly revised the grace period in paragraph (c)(1) of this final 
rule.

Additional Change to the Final Rule

    Because the language in Note 2 of the proposed AD is regulatory in 
nature, that note has been redesignated as paragraph (d) of this final 
rule.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes previously 
described. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    This AD will affect about 126 airplanes of U.S. registry. The 
following table provides the cost estimates of the actions currently 
required by AD 2000-10-15:

[[Page 58829]]



                                                 Cost Estimates
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                                                                  Hourly
                     Action                        Work hours   labor rate      Parts cost     Cost per airplane
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Modification....................................           60          $65                 $0             $3,900
Cold expansion..................................          600           65                  0             39,000
Inspection......................................           24           65                  0          \1\ 1,560
Optional terminating action.....................          750           65  \2\ 27,036-32,727     75,786-81,477
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\1\ Per inspection cycle.
\2\ Depending on airplane configuration.

    This AD will not add any new actions and therefore will not add any 
economic burden on operators--except for the additional cost associated 
with a potentially shortened inspection interval.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the requirements of this 
AD, and that no operator would accomplish those actions in the future 
if this AD were not adopted. The cost impact figures discussed in AD 
rulemaking actions represent only the time necessary to perform the 
specific actions actually required by the AD. These figures typically 
do not include incidental costs, such as the time required to gain 
access and close up, planning time, or time necessitated by other 
administrative actions.

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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
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

0
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]

0
2. Section 39.13 is amended by removing amendment 39-11739 (65 FR 
34069, May 26, 2000), and by adding a new airworthiness directive (AD), 
amendment 39-13805, to read as follows:

2004-19-11 Airbus: Amendment 39-13805. Docket 2001-NM-254-AD. 
Supersedes AD 2000-10-15, Amendment 39-11739.

    Applicability: Model A320 series airplanes, certificated in any 
category, except those modified in accordance with Airbus 
Modification 24591 (Airbus Service Bulletin A320-57-1089, dated 
December 22, 1996; Revision 01, dated April 17, 1997; Revision 02, 
dated November 6, 1998; or Revision 03, dated February 9, 2001).
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct fatigue cracking in certain areas of the 
rear spar of the wing, which may lead to reduced structural 
integrity of the wing and the main landing gear (MLG), accomplish 
the following:

Restatement of Certain Requirements of AD 2000-10-15

Modification

    (a) For airplanes having manufacturer's serial numbers (MSN) 003 
through 008 inclusive, and 010 through 021 inclusive: Prior to the 
accumulation of 12,000 total flight cycles, or within 500 flight 
cycles after June 11, 1993 (the effective date of AD 93-08-15, 
amendment 39-8563), whichever occurs later, modify the inner rear 
spar web of the wing in accordance with Airbus Service Bulletin 
A320-57-1004, Revision 1, dated September 24, 1992; or Revision 2, 
dated June 14, 1993.
    (b) For airplanes having MSNs 002 through 051 inclusive: Prior 
to the accumulation of 12,000 total flight cycles, or within 2,000 
flight cycles after February 14, 1994 (the effective date of AD 93-
25-13, amendment 39-8777), whichever occurs later, accomplish the 
requirements of paragraphs (b)(1) and (b)(2) of this AD in 
accordance with Airbus Service Bulletin A320-57-1060, dated December 
8, 1992; or Revision 2, dated December 16, 1994.
    (1) Perform a cold expansion of all the attachment holes for the 
forward pintle fitting of the MLG, except for the holes that are for 
taper-lok bolts.
    (2) Perform a cold expansion of the holes at the actuating 
cylinder anchorage of the MLG.

    Note 1: Accomplishment of the cold expansion in accordance with 
Airbus Service Bulletin A320-57-1060, Revision 1, dated April 26, 
1993, is also acceptable for compliance with the requirements of 
paragraph (b) of this AD.

New Requirements of This AD

Ultrasonic Inspection

    (c) Do an ultrasonic inspection for cracking of the rear spar of 
the wing, in accordance with Airbus Service Bulletin A320-57-1088, 
Revision 04, dated August 6, 2001. Inspect at the applicable time 
specified in paragraph 1.E. of the service bulletin, except as 
required by paragraphs (c)(1) and (c)(2) of this AD.
    (1) For any airplane that has not been inspected but has 
exceeded the applicable specified compliance time in paragraph 1.E. 
of the service bulletin as of the effective date of this AD: Inspect 
within 18 months after the effective date of this AD.
    (2) For any airplane that has been inspected before the 
effective date of this AD: Repeat the inspection within 3,600 flight 
cycles after the most recent inspection.
    (d) An inspection done before the effective date of this AD in 
accordance with Airbus Service Bulletin A320-57-1088, Revision 02, 
dated July 29, 1999; or Revision 03, dated February 9, 2001; is 
acceptable for compliance with the requirements of the initial 
inspection required by paragraph (c) of this AD.

Repetitive Inspections

    (e) Repeat the inspection required by paragraph (c) of this AD 
at intervals not to exceed 3,600 flight cycles or 6,700 flight 
hours, whichever occurs first, until the requirements of paragraph 
(g) have been done.

Corrective Action

    (f) If any crack is found during any inspection required by 
paragraph (c) or (e) of this AD: Before further flight, repair in 
accordance with a method approved by

[[Page 58830]]

either the Manager, International Branch, ANM-116, FAA, Transport 
Airplane Directorate; or the Direction Generale de l'Aviation Civile 
(or its delegated agent).

Optional Terminating Action

    (g) Modification of all specified fastener holes in the rear 
spar of the wing terminates the initial and repetitive inspections 
required by paragraphs (c) and (e) of this AD, if the modification 
is done in accordance with Airbus Service Bulletin A320-57-1089, 
Revision 02, dated November 6, 1998; or Revision 03, dated February 
9, 2001. If done before the airplane accumulates 12,000 total flight 
cycles, the modification also terminates the actions required by 
paragraphs (a) and (b) of this AD.

Incorporation by Reference

    (h) Unless otherwise specified in this AD, the actions must be 
done in accordance with the service bulletins listed in Table 1 of 
this AD.

          Table 1.--Service Bulletins Incorporated by Reference
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        Service bulletin            Revision level           Date
------------------------------------------------------------------------
Airbus Service Bulletin A320-57-  1.................  September 24,
 1004.                                                 1992.
Airbus Service Bulletin A320-57-  2.................  June 14, 1993.
 1004.
Airbus Service Bulletin A320-57-  Original..........  December 8, 1992.
 1060.
Airbus Service Bulletin A320-57-  2.................  December 16, 1994.
 1060.
Airbus Service Bulletin A320-57-  04................  August 6, 2001.
 1088.
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    (1) The incorporation by reference of Airbus Service Bulletin 
A320-57-1088, Revision 04, dated August 6, 2001, is approved by the 
Director of the Federal Register as of November 5, 2004.
    (2) The incorporation by reference of Airbus Service Bulletin 
A320-57-1004, Revision 2, dated June 14, 1993; and Airbus Service 
Bulletin A320-57-1060, Revision 2, dated December 16, 1994; was 
approved previously by the Director of the Federal Register as of 
June 30, 2000 (65 FR 34069, May 26, 2000).
    (3) The incorporation by reference of Airbus Service Bulletin 
A320-57-1060, dated December 8, 1992, was approved previously by the 
Director of the Federal Register as of February 14, 1994 (59 FR 
1903, January 13, 1994).
    (4) The incorporation by reference of Airbus Service Bulletin 
A320-57-1004, Revision 1, dated September 24, 1992, was approved 
previously by the Director of the Federal Register as of June 11, 
1993 (58 FR 27923, May 12, 1993).
    (5) Copies may be obtained from Airbus, 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 National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Note 2: The subject of this AD is addressed in French 
airworthiness directive 2001-249(B), dated June 27, 2001.

Effective Date

    (i) This amendment becomes effective on November 5, 2004.

    Issued in Renton, Washington, on September 21, 2004.
Kalene C. Yanamura,
Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 04-21816 Filed 9-30-04; 8:45 am]
BILLING CODE 4910-13-P