[Federal Register: August 5, 2004 (Volume 69, Number 150)]
[Proposed Rules]
[Page 47391-47393]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr05au04-22]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-18773; Directorate Identifier 2002-NM-312-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A320 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) for certain Airbus Model A320 series airplanes. That AD
currently requires repetitive inspections to detect fatigue cracking in
certain areas of the fuselage, and corrective action if necessary. That
AD also provides for an optional terminating action for the repetitive
inspections. This proposed AD would reduce the compliance threshold and
repetitive intervals for the inspections required by the existing AD,
and would reduce the allowable time for the optional terminating
action. This proposed AD is prompted by a full-scale fatigue survey on
the Model A320 fleet. We are proposing this AD to detect and correct
fatigue cracking of the fuselage, which could result in reduced
structural integrity of the airplane.
DATES: We must receive comments on this proposed AD by September 7,
2004.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m.
and 5 p.m., Monday through Friday, except Federal holidays.
You can get the service information identified in this proposed AD
from Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex,
France.
You may examine the contents of this AD docket on the Internet at
http://dms.dot.gov, or at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street SW., room PL-401, on
the plaza level of the Nassif Building, Washington, DC.
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:
Docket Management System (DMS)
The FAA has implemented new procedures for maintaining AD dockets
electronically. As of May 17, 2004, new AD actions are posted on DMS
and assigned a docket number. We track each action and assign a
corresponding directorate identifier. The DMS AD docket number is in
the form ``Docket No. FAA-2004-99999.'' The Transport Airplane
Directorate identifier is in the form ``Directorate Identifier 2004-NM-
999-AD.'' Each DMS AD docket also lists the directorate identifier
(``Old Docket Number'') as a cross-reference for searching purposes.
Comments Invited
We invite you to submit any written relevant data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2004-18773;
Directorate Identifier 2002-NM-312-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to http://dms.dot.gov
, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of our
docket Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
may visit http://dms.dot.gov.
We are reviewing the writing style we currently use in regulatory
documents. We are interested in your comments on whether the style of
this document is clear, and your suggestions to improve the clarity of
our communications that affect you. You can get more information about
plain language at http://www.faa.gov/language and http://www.plainlanguage.gov.Examining
the Docket
You may examine the AD docket in person at the Docket Management
Facility office between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Management Facility office
(telephone (800) 647-5227) is located on the plaza level of the Nassif
Building at the DOT street address stated in the ADDRESSES section.
Comments will be available in the AD docket shortly after the DMS
receives them.
Discussion
On December 30, 1998, we issued AD 99-01-19, amendment 39-10987 (64
FR 1114, January 11, 1999), for certain Airbus Model A320 series
airplanes. That AD requires repetitive inspections to detect fatigue
cracking in certain areas of the fuselage, and corrective action if
necessary. That AD also provides for an optional terminating action for
the repetitive inspections. That AD was prompted by issuance of
mandatory continuing airworthiness information by a foreign civil
airworthiness authority. We issued that AD to detect and correct
fatigue cracking of the fuselage, which could result in reduced
structural integrity of the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 99-01-19, the Direction G[eacute]n[eacute]rale
de l'Aviation Civile (DGAC), which is the airworthiness authority for
France, advises that a full-scale fatigue survey on the Model A320
fleet revealed that the weight of fuel at landing and the average
flight duration are higher than those defined for the analysis of
fatigue-related tasks. This has led to an adjustment of the fatigue
mission for the A320 fleet, in that the
[[Page 47392]]
DGAC has required shorter compliance thresholds and repetitive
intervals for accomplishment of the inspections for fatigue cracking
than those required by AD 99-01-19. Fatigue-related cracking in certain
areas of the fuselage could result in reduced structural integrity of
the airplane.
Relevant Service Information
Airbus has issued Service Bulletin A320-53-1032, Revision 02, dated
December 5, 2001. The procedures specified in Revision 02 are
essentially the same as those in Revision 01 of the service bulletin,
which was referenced in the existing AD for accomplishment of the
inspections and corrective action. However, Revision 02 has a change
that recommends a reduction in the compliance threshold from 30,000
total flight cycles to 24,800 total flight cycles and in the repetitive
intervals from 6,000 flight cycles to 4,900 flight cycles. Airbus also
has issued Service Bulletin A320-53-1031, Revision 02, dated December
5, 2001. The procedures in Revision 02 are essentially the same as
those in the original issue of the service bulletin, which was
referenced in the existing AD for accomplishment of the optional
terminating action. However, Revision 02 recommends a reduction in the
compliance threshold from 20,000 flight cycles to 16,000 flight cycles.
We have determined that accomplishment of the actions specified in
the revised service information will adequately address the unsafe
condition. The DGAC mandated the service information and issued French
airworthiness directive 2002-259(B), dated May 15, 2002, to ensure the
continued airworthiness of these airplanes in France.
FAA's Determination and Requirements of the Proposed AD
This airplane model is manufactured in France and is type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, the DGAC has kept us informed of the
situation described above. We have examined the DGACs findings,
evaluated all pertinent information, and determined that AD action is
necessary for airplanes of this type design that are certificated for
operation in the United States.
Therefore, we are proposing this AD, to supersede AD 99-01-19 to
continue to require repetitive inspections to detect fatigue cracking
in certain areas of the fuselage, and corrective action if necessary.
This proposed AD would also continue to provide for an optional
terminating action for the repetitive inspections. This proposed AD
would reduce the compliance threshold and repetitive intervals for the
inspections required by the existing AD, and would reduce the allowable
time for the optional terminating action. The proposed AD would require
using the revised service information described previously to do these
actions.
Changes to Existing AD
The number of affected airplanes has changed since we issued the
existing AD; therefore, we have changed the Cost Impact section in this
proposed AD to reflect the correct number of airplanes.
We have changed all references to a ``visual inspection'' in the
existing AD to a ``detailed inspection'' in this action. Additionally,
we have added a note to define that inspection.
Revised Labor Rate
We have reviewed the figures we have used over the past several
years to calculate AD costs to operators. To account for various
inflationary costs in the airline industry, we find it necessary to
increase the labor rate used in these calculations from $60 per work
hour to $65 per work hour. The cost information, below, reflects this
increase in the hourly labor rate.
Costs of Compliance
This proposed AD would affect about 269 airplanes of U.S. registry.
The inspection that is required by AD 99-01-19 and retained in this
proposed AD takes about 19 work hours per airplane, at an average labor
rate of $65 per work hour. Based on these figures, the estimated cost
of the currently required inspection is $1,235 per airplane.
The optional terminating action specified in Airbus Service
Bulletin A320-53-1031, if done, would take about 1 work hour per
fastener hole, at an average labor rate of $65 per work hour. The cost
of required parts would be about $4,219 (for one modification kit).
Based on these figures, the cost of the optional terminating action
would be a minimum of $4,284 per airplane.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD. See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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. The FAA amends Sec. 39.13 by removing amendment 39-10987 (64 FR
1114, January 11, 1999) and adding the following new airworthiness
directive (AD):
Airbus: Docket No. FAA-2004-18773; Directorate Identifier 2002-NM-
312-AD.
Comments Due Date
(a) The Federal Aviation Administration must receive comments on
this AD action by September 7, 2004.
Affected ADs
(b) This AD supersedes AD 99-01-19, amendment 39-10987.
Applicability
(c) This AD applies to Airbus Model A320 A320-111, -211, -212,
and -231 series airplanes on which Airbus Modification 21346 has not
been done, certificated in any category.
Unsafe Condition
(d) This AD was prompted by a full-scale fatigue survey on the
Model A320 fleet. We are issuing this AD to detect and correct
fatigue cracking of the fuselage, which could result in reduced
structural integrity of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within
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the compliance times specified, unless the actions have already been
done.
Repetitive Inspections
(f) At the applicable time specified in paragraph (f)(1) or
(f)(2) of this AD: Do a detailed inspection to find cracking on the
outboard flanges around the fastener holes of frames 38 through 41,
between stringers 12 and 21, using Airbus Service Bulletin A320-53-
1032, Revision 02, dated December 5, 2001. Accomplishment of the
inspection required by this paragraph ends the requirements of AD
99-01-19.
(1) For airplanes on which the inspection specified in Airbus
Service Bulletin A320-53-1032, Revision 01, dated January 15, 1998,
or Revision 02, dated December 5, 2001; has been done as of the
effective date of this AD: Do the next inspection within 4,900
flight cycles after accomplishment of the last inspection, or within
1,100 flight cycles after the effective date of this AD, whichever
is later.
(2) For airplanes on which no inspection specified in Airbus
Service Bulletin A320-53-1032, Revision 01, dated January 15, 1998,
or Revision 02, dated December 5, 2001; has been done as of the
effective date of this AD: Do the inspection at the earlier of the
times specified in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD.
(i) Before the accumulation of 30,000 total flight cycles.
(ii) Before the accumulation of 24,800 total flight cycles, or
within 3,500 flight cycles after the effective date of this AD,
whichever is later.
(g) If no crack is found during the inspection required by
paragraph (f)(1) or (f)(2) of this AD: Repeat the inspection
thereafter at intervals not to exceed 4,900 flight cycles.
Note 1: For the purposes of this AD, a detailed inspection is
defined as: ``An intensive visual examination of a specific
structural area, system, installation, or assembly to detect damage,
failure, or irregularity. Available lighting is normally
supplemented with a direct source of good lighting at intensity
deemed appropriate by the inspector. Inspection aids such as mirror,
magnifying lenses, etc., may be used. Surface cleaning and elaborate
access procedures may be required.''
Corrective Action
(h) If any crack is found during any inspection required by
paragraph (f) of this AD, before further flight, repair using Airbus
Service Bulletin A320-53-1032, Revision 01, dated January 15, 1998,
or Revision 02, dated December 5, 2001. Accomplishment of a repair
using the service bulletin ends the repetitive inspection
requirements for the area repaired. If any crack is found during any
inspection required by this AD, and the service bulletin specifies
to contact Airbus for appropriate action:
Before further flight, repair using a method approved by the
Manager, International Branch, ANM-116, FAA, Transport Airplane
Directorate.
Optional Terminating Action
(i) Accomplishment of Airbus Modification 21346 using Airbus
Service Bulletin A320-53-1031, dated December 9, 1994, or Revision
02, dated December 5, 2001, constitutes terminating action for the
repetitive inspection requirements of this AD.
(j) Accomplishment of the optional terminating action specified
in AD 99-01-19 before the effective date of this AD, using Airbus
Service Bulletin A320-53-1031, dated December 9, 1994, or Revision
02, dated December 5, 2001, is considered acceptable for compliance
with paragraph (i) of this AD.
Alternative Methods of Compliance (AMOCs)
(k) The Manager, International Branch, ANM-116, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
Related Information
(l) French airworthiness directive 2002-259(B), dated May 15,
2002, also addresses the subject of this AD.
Issued in Renton, Washington, on July 29, 2004.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-17857 Filed 8-4-04; 8:45 am]
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