[Federal Register Volume 69, Number 150 (Thursday, August 5, 2004)]
[Proposed Rules]
[Pages 47391-47393]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-17857]


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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]
BILLING CODE 4910-13-P