[Federal Register: July 9, 2004 (Volume 69, Number 131)]
[Rules and Regulations]
[Page 41398-41401]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr09jy04-10]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-177-AD; Amendment 39-13718; AD 2004-14-09]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A320-111, -211, -212, and
-231 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 A320-111, -211, -212, and -231
series airplanes, that currently requires repetitive inspections to
detect fatigue cracking of the lower surface panel on the wing center
box, and repair if necessary. That AD also requires modification of the
lower surface panel on the wing center box, which constitutes
terminating action for the repetitive inspections. This amendment
reduces the compliance times for the inspections required by the
existing AD. The actions specified by this AD are intended to prevent
fatigue cracking of the lower surface panel on the wing center box,
which could result in reduced structural integrity of the airplane.
This action is intended to address the identified unsafe condition.
DATES: Effective August 13, 2004.
The incorporation by reference of Airbus Service Bulletin A320-57-
1082, Revision 03, dated April 30, 2002; and Airbus Service Bulletin
A320-57-1043, Revision 05, dated April 30, 2002; as listed in the
regulations; is approved by the Director of the Federal Register as of
August 13, 2004.
The incorporation by reference of Airbus Service Bulletin A320-57-
1082, Revision 01, dated December 10, 1997; and Airbus Service Bulletin
A320-57-1043, Revision 02, dated May 14, 1997; as listed in the
regulations; was approved previously by the Director of the Federal
Register as of November 27, 1998 (63 FR 56542, October 22, 1998).
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: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2125; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 98-22-05,
amendment 39-10851 (63 FR 56542, October 22, 1998), which is applicable
to certain Airbus Model A320 series airplanes, was published in the
Federal Register on February 6, 2004 (69 FR 5790). The action proposed
to continue to require repetitive inspections to detect fatigue
cracking of the lower surface panel on the wing center box, and repair
if necessary. That action also proposed to continue to require
modification of the lower surface panel on the wing center box, which
would constitute terminating action for the repetitive inspections.
That action also proposed to reduce the compliance times for the
inspections required by the existing AD.
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 from a single commenter.
Request To Remove Paragraph (c)(1) of the Proposed AD
The commenter states that paragraph (c)(1) of the proposed AD
(Restatement of Requirements of AD 98-22-05), conflicts with paragraph
(g) of the proposed AD (New Requirements of This AD). The commenter
notes that paragraph (c)(1) requires accomplishment of the modification
of the lower surface panel on the wing center box per Airbus Service
Bulletin A320-57-1043, Revision 02 or Revision 05, if no cracking is
found during the inspection required by paragraph (c) of the proposed
AD, but paragraph (g) specifies repeating the inspection per Airbus
Service Bulletin A320-57-1082, Revision 01 or Revision 03, if no
cracking is found. The commenter adds that French airworthiness
directive 2002-342(B), dated June 26, 2002 (referenced in the proposed
AD), and French airworthiness directive 97-309-104(B), dated October
27, 1997 (referenced in the existing AD), issued by the Direction
G[eacute]n[eacute]rale de l'Aviation Civile, which is the airworthiness
authority for France, require accomplishment of the actions specified
in Airbus Service Bulletin A320-57-1043, Revision 02 or Revision 05
only, if no cracking is found. The commenter asks that paragraph (c)(1)
be removed for the reasons stated above.
The FAA partially agrees. Paragraph (g) of this AD requires
repeating the inspection required by paragraph (a) or (f) of the AD if
no cracking is found during either of those inspections. The inspection
specified in paragraph (f) is
[[Page 41399]]
for airplanes on which the inspection required by paragraph (a) has not
been done as of the effective date of the AD, and accomplishment of the
inspection constitutes terminating action for the requirements of
paragraph (a). Paragraph (c)(1) specifies that accomplishment of the
modification per Airbus Service Bulletin A320-57-1043, Revision 02 or
Revision 05, also constitutes terminating action for the requirements
of paragraph (a). Therefore, if the commenter has done the modification
required by paragraph (c)(1), the repetitive inspections required by
paragraph (g) are not required. We have changed paragraphs (f) and (g)
for clarification, as follows: We have changed paragraph (f) to state
``For airplanes on which neither the inspection required by paragraph
(a) of this AD, nor the modification required by paragraph (c)(1) of
this AD has been done before the effective date of this AD:'' We have
changed paragraph (g) to add ``Accomplishment of the modification
required by paragraph (c)(1) of this AD terminates the requirements of
this paragraph.''
Additionally, the applicability of this AD is for Model A320 series
airplanes on which Airbus Modification 22418 (reference Airbus Service
Bulletin A320-57-1043) has not been done. French airworthiness
directive 2002-342(B), does not require accomplishment of the actions
specified in Airbus Service Bulletin A320-57-1043, but requires
accomplishment of the actions specified in Airbus Service Bulletin
A320-57-1082. French airworthiness directive 97-309-104(B), was
cancelled upon issuance of French airworthiness directive 2002-342(B).
The applicability in French airworthiness directive 2002-342(B), in
part, excludes airplanes on which the actions specified in Service
Bulletin A320-57-1043 have been done. No change to the AD is necessary
in this regard.
Request To Change Compliance Time
The commenter states that the compliance time for the inspection
required by paragraph (f)(2) of the proposed AD specifies ``Prior to
the accumulation of 20,000 total flight cycles, or within 3,500 flight
cycles after the effective date of this AD, whichever is first.'' The
commenter notes that the compliance time should be ``whichever occurs
later.'' No justification is provided for this comment.
We have coordinated this issue with the manufacturer and determined
that the compliance time required by paragraph (f)(2) of this AD should
specify ``Prior to the accumulation of 20,000 total flight cycles, or
within 3,500 flight cycles after the effective date of this AD,
whichever is later.'' The referenced French airworthiness directive and
service information did not provide this criterion. We have determined
that extending the compliance time for the inspection will continue to
provide an acceptable level of safety for the affected fleet. Paragraph
(f)(2) of this AD has been changed accordingly.
Request To Change Applicability
The commenter states that the models listed in French airworthiness
directive 2002-342(B), dated June 26, 2002 (referenced in the proposed
AD), are Airbus Model A320-111, -211, -212, and -231 series airplanes.
The commenter asks that the models listed in the proposed AD (Model
A320 series airplanes) be changed to match the models listed in the
referenced French airworthiness directive.
We agree. French airworthiness directive 97-309-104(B), dated
October 27, 1997 (referenced in the existing AD), listed Model A320
series airplanes and has since been cancelled. Therefore, we have
changed the models listed in this AD to specify Model A320-111, -211, -
212, and -231 series airplanes. This change corresponds with the models
specified in French airworthiness directive 2002-342(B).
Conclusion
We have carefully reviewed the available data, including the
comments noted above, and have determined that air safety and the
public interest require adopting the AD with the changes described
previously. These changes will neither increase the economic burden on
any operator nor increase the scope of the AD.
Cost Impact
There are approximately 60 airplanes of U.S. registry that will be
affected by this AD. This AD reduces the compliance time for the
inspections required by AD 98-22-05, and consequently adds no
additional costs or work. The current costs associated with that AD are
repeated as follows for the convenience of affected operators:
The inspections that are currently required by AD 98-22-05, and
retained in this AD, take about 2 work hours per airplane to
accomplish, at an average labor rate of $65 per work hour. Based on
these figures, the cost impact of the currently required inspections is
estimated to be $130 per airplane, per inspection cycle.
The modification that is currently required by AD 98-22-05, and
retained in this AD, will take about 2 work hours per airplane to
accomplish, at an average labor rate of $65 per work hours. There are
no parts necessary to accomplish the modification. Based on these
figures, the cost impact of the modification currently required is
estimated to be $130 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. 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:
[[Page 41400]]
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 39-10851 (63 FR
56542, October 22, 1998), and by adding a new airworthiness directive
(AD), amendment 39-13718, to read as follows:
2004-14-09 Airbus: Amendment 39-13718. Docket 2002-NM-177-AD.
Supersedes AD 98-22-05, Amendment 39-10851.
Applicability: Model A320-111, -211, -212, and -231 series
airplanes; certificated in any category, on which Airbus
Modification 22418 (reference Airbus Service Bulletin A320-57-1043)
has not been done.
Compliance: Required as indicated, unless accomplished
previously.
To prevent fatigue cracking of the lower surface panel on the
wing center box, which could result in reduced structural integrity
of the airplane, accomplish the following:
Restatement of Requirements of AD 98-22-05
Repetitive Inspections
(a) Except as provided by paragraph (e) of this AD: Prior to the
accumulation of 20,000 total flight cycles, or within 60 days after
November 27, 1998 (the effective date of AD 98-22-05, amendment 39-
10851), whichever occurs later, perform a high frequency eddy
current inspection to detect fatigue cracking of the lower surface
panel on the wing center box, in accordance with Airbus Service
Bulletin A320-57-1082, Revision 01, dated December 10, 1997; or
Revision 03, dated April 30, 2002. Repeat the eddy current
inspection thereafter at intervals not to exceed 7,500 flight cycles
until the actions required by paragraph (c) of this AD are
accomplished.
Repair
(b) Except as provided by paragraph (d) of this AD: If any
cracking is detected during any inspection required by paragraph (a)
of this AD, prior to further flight, repair in accordance with
Airbus Service Bulletin A320-57-1082, Revision 01, dated December
10, 1997; or Revision 03, dated April 30, 2002. Accomplishment of
the repair constitutes terminating action for the repetitive
inspections for the repaired area only.
Inspection/Modification/Repair
(c) Prior to the accumulation of 25,000 total flight cycles, or
within 60 days after November 27, 1998, whichever occurs later:
Perform a high frequency eddy current inspection to detect fatigue
cracking of the lower surface panel on the wing center box, in
accordance with Airbus Service Bulletin A320-57-1082, Revision 01,
dated December 10, 1997; or Revision 03, dated April 30, 2002.
(1) If no cracking is detected: Prior to further flight, modify
the lower surface panel on the wing center box, in accordance with
Airbus Service Bulletin A320-57-1043, Revision 02, dated May 14,
1997; or Revision 05, dated April 30, 2002. Accomplishment of the
modification constitutes terminating action for the requirements of
paragraph (a) of this AD.
(2) Except as provided by paragraph (d) of this AD, if any
cracking is detected: Prior to further flight, repair in accordance
with Airbus Service Bulletin A320-57-1082, Revision 01, dated
December 10, 1997; or Revision 03, dated April 30, 2002; and modify
any uncracked area in accordance with Airbus Service Bulletin A320-
57-1043, Revision 02, dated May 14, 1997; or Revision 05, dated
April 30, 2002. Accomplishment of the repair of cracked area(s) and
modification of uncracked area(s) constitutes terminating action for
the requirements of paragraph (a) of this AD.
(d) If any cracking is detected during any inspection required
by paragraph (b) or (c)(2) 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 either the Manager, International Branch, AMN-116, FAA, Transport
Airplane Directorate; or the Direction G[eacute]n[eacute]rale de
l'Aviation Civile (or its delegated agent).
(e) The actions required by paragraph (a) of this AD are not
required to be accomplished if the requirements of paragraph (c) of
this AD are accomplished at the time specified in paragraph (a) of
this AD.
New Requirements of this AD
Initial Inspection
(f) For airplanes on which neither the inspection required by
paragraph (a) of this AD, nor the modification required by paragraph
(c)(1) of this AD has been done before the effective date of this
AD: Perform a high frequency eddy current inspection to detect
fatigue cracking of the lower surface panel on the wing center box,
in accordance with Airbus Service Bulletin A320-57-1082, Revision
01, dated December 10, 1997; or Revision 03, dated April 30, 2002;
at the later of the times specified in paragraphs (f)(1) and (f)(2)
of this AD. Accomplishment of the inspection required by this
paragraph terminates the requirements of paragraph (a) of this AD.
(1) Prior to the accumulation of 13,200 total flight cycles or
39,700 total flight hours after the effective date of this AD,
whichever is first.
(2) Prior to the accumulation of 20,000 total flight cycles, or
within 3,500 flight cycles after the effective date of this AD,
whichever is later.
Repetitive Inspections
(g) If no cracking is detected during the inspection required by
paragraph (a) or (f) of this AD: Repeat the inspection at the
applicable time specified in paragraph (g)(1) or (g)(2) of this AD.
Accomplishment of the modification required by paragraph (c)(1) of
this AD terminates the requirements of this paragraph.
(1) For airplanes on which the inspections required by paragraph
(a) of this AD have been done before the effective date of this AD:
Do the next inspection within 5,700 flight cycles after
accomplishment of the last inspection, or within 1,800 flight cycles
after the effective date of this AD, whichever is later. Repeat the
inspection thereafter at intervals not to exceed 5,700 flight
cycles.
(2) For airplanes on which no inspection required by paragraph
(a) of this AD has been done before the effective date of this AD:
Do the next inspection within 5,700 flight cycles after
accomplishment of the inspection required by paragraph (f) of this
AD. Repeat the inspection thereafter at intervals not to exceed
5,700 flight cycles.
Repair/Modification
(h) If any cracking is detected during any inspection required
by paragraph (f) or (g) of this AD, prior to further flight, repair
in accordance with Airbus Service Bulletin A320-57-1082, Revision
01, dated December 10, 1997; or Revision 03, dated April 30, 2002;
and modify any uncracked area in accordance with Airbus Service
Bulletin A320-57-1043, Revision 02, dated May 14, 1997; or Revision
05, dated April 30, 2002. Where Airbus Service Bulletin A320-57-1082
specifies to contact Airbus for an appropriate repair action: Prior
to further flight, repair in accordance with a method approved by
either the Manager, International Branch, ANM-116, FAA, Transport
Airplane Directorate; or the Direction G[eacute]n[eacute]rale de
l'Aviation Civile (DGAC) (or its delegated agent). Accomplishment of
the repair of cracked area(s) and modification of uncracked area(s)
constitutes terminating action for the requirements of this AD.
Actions Done per Previous Issues of Service Bulletins
(i) Accomplishment of inspections and repairs before the
effective date of this AD in accordance with Airbus Service Bulletin
A320-57-1082, Revision 02, dated July 26, 1999; and accomplishment
of the modification before the effective date of this AD in
accordance with Airbus Service Bulletin Airbus Service Bulletin
A320-57-1043, dated February 16, 1993; Revision 01, dated June 14,
1996; Revision 03, dated October 24, 1997; or Revision 04, dated
March 15, 1999; are considered acceptable for compliance with the
applicable actions specified in this AD.
Alternative Methods of Compliance
(j) In accordance with 14 CFR 39.19, the Manager, International
Branch, ANM-116, is authorized to approve alternative methods of
compliance for this AD.
Incorporation by Reference
(k) Unless otherwise provided in this AD, the actions shall be
done in accordance with Airbus Service Bulletin A320-57-1082,
Revision 01, dated December 10, 1997; Airbus Service Bulletin A320-
57-1082, Revision 03, dated April 30, 2002; Airbus Service Bulletin
A320-57-1043, Revision 02, dated May 14, 1997; and Airbus Service
Bulletin A320-57-1043, Revision 05, dated April 30, 2002; as
applicable.
(1) The incorporation by reference of Airbus Service Bulletin
A320-57-1082,
[[Page 41401]]
Revision 03, dated April 30, 2002; and Airbus Service Bulletin A320-
57-1043, Revision 05, dated April 30, 2002; is approved by the
Director of the Federal Register in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51.
(2) The incorporation by reference of Airbus Service Bulletin
A320-57-1082, Revision 01, dated December 10, 1997; and Airbus
Service Bulletin A320-57-1043, Revision 02, dated May 14, 1997; was
approved previously by the Director of the Federal Register as of
November 27, 1998 (63 FR 56542, October 22, 1998).
(3) 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 1: The subject of this AD is addressed in French
airworthiness directive 2002-342(B), dated June 26, 2002.
Effective Date
(l) This amendment becomes effective on August 13, 2004.
Issued in Renton, Washington, on June 29, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-15372 Filed 7-8-04; 8:45 am]
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