[Federal Register: October 1, 2004 (Volume 69, Number 190)]
[Rules and Regulations]
[Page 58828-58830]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr01oc04-7]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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
----------------------------------------------------------------------------------------------------------------
Hourly
Action Work hours labor rate Parts cost Cost per airplane
----------------------------------------------------------------------------------------------------------------
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
----------------------------------------------------------------------------------------------------------------
\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
------------------------------------------------------------------------
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.
------------------------------------------------------------------------
(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