[Federal Register Volume 71, Number 34 (Tuesday, February 21, 2006)]
[Rules and Regulations]
[Pages 8792-8796]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 06-1504]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23935; Directorate Identifier 2005-NM-060-AD; 
Amendment 39-14492; AD 2006-04-11]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A321-100 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to certain Airbus Model A321-111, -112, and -131 
series airplanes. That AD currently requires repetitive inspections to 
detect fatigue cracking in the area surrounding certain attachment 
holes of the forward pintle fittings of the main landing gear (MLG) and 
the actuating cylinder anchorage fittings on the inner rear spar; and 
repair, if necessary. The existing AD also provides for optional 
terminating action for the repetitive inspections. This AD adds 
inspections of three additional mounting holes and revises the 
thresholds for the currently required inspections. This AD results from 
manufacturer analysis of the fatigue and damage tolerance of the area 
surrounding certain mounting holes of the MLG. We are issuing this AD 
to detect and correct fatigue cracking on the inner rear spar of the 
wings, which could result in reduced structural integrity of the 
airplane.

DATES: This AD becomes effective March 8, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of March 8, 2006.
    The incorporation by reference of Airbus Service Bulletin A320-57-
1101, Revision 02, dated October 25, 2001, as listed in the 
regulations, was approved previously by the Director of the Federal 
Register as of April 21, 2004 (69 FR 17906, April 6, 2004).

[[Page 8793]]

    The incorporation by reference of Airbus Service Bulletin A320-57-
1101, dated July 24, 1997, as listed in the regulations, was approved 
previously by the Director of the Federal Register as of December 18, 
1998 (63 FR 66753, December 3, 1998).
    We must receive comments on this AD by April 24, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this 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.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this AD.

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:

Discussion

    On March 25, 2004, we issued AD 2004-07-15, amendment 39-13559 (69 
FR 17906, April 6, 2004), for certain Airbus Model A321-111, -112, and 
-131 series airplanes. That AD requires repetitive inspections to 
detect fatigue cracking in the area surrounding certain attachment 
holes of the forward pintle fittings of the main landing gear (MLG) and 
the actuating cylinder anchorage fittings on the inner rear spar; and 
repair, if necessary. That AD also provided for optional terminating 
action for the repetitive inspections. That AD resulted from a fleet 
survey by the manufacturer. We issued that AD to detect and correct 
fatigue cracking on the inner rear spar of the wings, which could 
result in reduced structural integrity of the airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 2004-07-15, Airbus conducted further analysis of 
the fatigue and damage tolerance of the mounting holes of the inner 
rear spar of the wing. The results of the analysis revealed that three 
more mounting holes require inspection and that it is necessary to 
decrease the thresholds of the repetitive inspections already required 
by AD 2004-07-15.

Relevant Service Information

    Airbus has issued Service Bulletin (SB) A320-57-1101, Revision 04, 
dated November 22, 2004. (AD 2004-07-15 refers to Airbus SB A320-57-
1101, dated July 24, 1997; and Revision 02, dated October 25, 2001; as 
appropriate sources of service information for the actions required by 
that AD.) SB A320-57-1101, Revision 04, describes procedures for 
performing repetitive ultrasonic inspections for fatigue cracking in 
the area around certain mounting holes on the inner rear spar of the 
wings. The thresholds specified in SB A320-57-1101, Revision 04, have 
been reduced from those specified in SB A320-57-1101, Revision 02; and 
from those thresholds specified in Airbus SB A320-57-1101, Revision 03, 
dated July 30, 2003, which added three additional mounting holes to the 
area subject to the repetitive inspections. The Direction 
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), which is the 
airworthiness authority for France, mandated SB A320-57-1101, Revision 
03, and issued French airworthiness directive F-2004-166, dated October 
13, 2004, to ensure the continued airworthiness of these airplanes in 
France. Airbus SB A320-57-1101, Revision 04--which was released after 
the issuance of French airworthiness directive F-2004-166--is also 
acceptable for accomplishing the requirements of this AD.
    We have reviewed later revisions of Airbus SB A320-57-1100, dated 
July 28, 1997, which is designated as the appropriate source of 
information for accomplishing the optional terminating action specified 
in paragraph (b) of AD 2004-07-15. Those later revisions are Airbus SB 
A320-57-1100, Revision 01, dated June 4, 1999; Revision 02, dated 
October 25, 2001; and Revision 03, dated January 16, 2003. Though not 
specified in AD 2004-07-15, SB A320-57-1100 includes Appendix 01 only, 
while SB A320-57-1100, Revisions 01, 02, and 03 include Appendices 01 
and 02. Any revision of SB A320-57-1100 is considered an acceptable 
source of service information for accomplishing the optional 
terminating action specified in paragraph (b) of AD 2004-07-15, which 
is restated as paragraph (g) of this AD.

FAA's Determination and Requirements of This 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 the FAA informed 
of the situation described above. We have examined the DGAC's findings, 
evaluated all pertinent information, and determined that we need to 
issue an AD for products of this type design that are certificated for 
operation in the United States.
    We are issuing this AD to supersede AD 2004-07-15. This new AD 
continues to require repetitive inspections to detect fatigue cracking 
in the area surrounding certain attachment holes of the forward pintle 
fittings of the MLG and the actuating cylinder anchorage fittings on 
the inner rear spar; and repair, if necessary; and additional 
inspections and repairs, if necessary; as specified in the service 
information described previously; except as discussed under 
``Difference Between French Airworthiness Directive and This AD'' and 
``Differences Between This AD and Service Information.''

Difference Between French Airworthiness Directive and This AD

    The applicability of French airworthiness directive F-2004-166 
excludes airplanes on which Airbus SB A320-57-1100 was accomplished in 
service. However, we have not excluded those airplanes in the 
applicability of this AD; rather, this AD includes a requirement to 
accomplish the actions specified in SB A320-57-1101, Revision 04, and 
provides for doing SB A320-57-1100 as an optional terminating action 
for the actions in SB A320-57-1101. This requirement will ensure that 
the actions specified in SB A320-57-1101, Revision 04, are accomplished 
on all affected airplanes. Operators must continue to operate the 
airplane in the configuration required by this AD unless an alternative 
method of compliance (AMOC) is approved.

Differences Between This AD and Service Information

    Airbus SB A320-57-1101, Revision 04, does not describe any method 
or service information to be used to repair any crack discovered during 
any inspection specified by the service information. Therefore, this AD 
requires operators to use a repair method that we

[[Page 8794]]

or the DGAC (or its delegated agent) approve.
    Although the service bulletins describe procedures for reporting 
inspection findings to Airbus, this AD does not require such a report.

Explanation of Change to Applicability

    We have revised the applicability of the existing AD to identify 
model designations as published in the most recent type certificate 
data sheet for the affected models.

Change to Existing AD

    This AD would retain certain requirements of AD 2004-07-15. Since 
AD 2004-07-15 was issued, the AD format has been revised, and certain 
paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers have changed in this AD, as listed in the 
following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                           Corresponding requirement in
      Requirement in  AD 2004-07-15              this proposed AD
------------------------------------------------------------------------
Paragraph (a)...........................  Paragraph (f).
Paragraph (b)...........................  Paragraph (g).
Paragraph (c)...........................  Paragraph (h).
Paragraph (d)...........................  Paragraph (i).
Paragraph (e)...........................  Paragraph (j).
Paragraph (f)...........................  Paragraph (m).
------------------------------------------------------------------------

Clarification of AMOC Paragraph

    We have revised this action to clarify the appropriate procedure 
for notifying the principal inspector before using any approved AMOC on 
any airplane to which the AMOC applies.

Costs of Compliance

    None of the airplanes affected by this action are on the U.S. 
Register. All airplanes included in the applicability of this AD 
currently are operated by non-U.S. operators under foreign registry; 
therefore, they are not directly affected by this AD action. However, 
we consider that this AD is necessary to ensure that the unsafe 
condition is addressed in the event that any of these subject airplanes 
are imported and placed on the U.S. Register in the future.
    If an affected airplane is imported and placed on the U.S. Register 
in the future, it would require approximately 22 work hours to 
accomplish the required actions at an average labor rate of $65 per 
work hour. Based on these figures, the cost impact of this AD would be 
$1,430 per airplane.
    If an operator elects to accomplish the optional terminating action 
provided by this AD, it would take approximately 520 work hours to 
accomplish, at an average labor rate of $65 per work hour. The cost of 
required parts would be approximately $17,540 per airplane. Based on 
these figures, the cost impact of the optional terminating action would 
be $51,340 per airplane.

FAA's Determination of the Effective Date

    No airplane affected by this AD is currently on the U.S. Register. 
Therefore, providing notice and opportunity for public comment is 
unnecessary before this AD is issued, and this AD may be made effective 
in less than 30 days after it is published in the Federal Register.

Comments Invited

    This AD is a final rule that involves requirements that affect 
flight safety and was not preceded by notice and an opportunity for 
public comment; however, we invite you to submit any relevant written 
data, views, or arguments regarding this AD. Send your comments to an 
address listed in the ADDRESSES section. Include ``Docket No. FAA-2006-
23935; Directorate Identifier 2005-NM-060-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the AD that might 
suggest a need to modify it.
    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 AD. Using the search function of that 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.

Examining the Docket

    You may examine the AD docket on the Internet at http://dms.dot.gov, or 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 Docket Management System 
receives them.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD 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.
    For the reasons discussed above, I certify that the 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 AD and placed it in the AD docket. 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:


[[Page 8795]]


    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-13559 (69 FR 17906, April 6, 2004) and by adding 
the following new airworthiness directive (AD):

2006-04-11 Airbus: Amendment 39-14492. Docket No. FAA-2006-23935; 
Directorate Identifier 2005-NM-060-AD.

Effective Date

    (a) This AD becomes effective March 8, 2006.

Affected ADs

    (b) This AD supersedes AD 2004-07-15.

Applicability

    (c) This AD applies to Airbus Model A321-111, -112, and -131 
airplanes, certificated in any category; all manufacturer serial 
numbers (MSN), except MSN 364 and 365; and except for those 
airplanes that have received Airbus Modification 24977 in 
production.

Unsafe Condition

    (d) This AD results from manufacturer analysis of the fatigue 
and damage tolerance of the area surrounding certain mounting holes 
of the main landing gear (MLG). The FAA is issuing this AD to detect 
and correct fatigue cracking on the inner rear spar of the wings, 
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 the compliance times specified, unless the 
actions have already been done.

Restatement of Requirements of AD 2004-07-15

Repetitive Inspections and Corrective Actions

    (f) Prior to the accumulation of 20,000 total flight cycles, or 
within 120 days after December 18, 1998 (the effective date of AD 
98-25-05, amendment 39-10928), whichever occurs later, perform an 
ultrasonic inspection to detect fatigue cracking in the area 
surrounding certain attachment holes of the forward pintle fittings 
of the MLG and the actuating cylinder anchorage fittings on the 
inner rear spar, in accordance with Airbus Service Bulletin A320-57-
1101, dated July 24, 1997; or Revision 02, dated October 25, 2001.
    (1) If no cracking is detected, prior to further flight, repair 
the sealant in the inspected areas and repeat the ultrasonic 
inspections thereafter at intervals not to exceed 7,700 flight 
cycles, until paragraph (g), (i), or (k) of this AD is accomplished.
    (2) If any cracking is detected, prior to further flight, repair 
in accordance with a method approved by either the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the Direction Generale de l'Aviation Civile (DGAC) (or its 
delegated agent).

Optional Terminating Action

    (g) Accomplishment of visual and eddy current inspections to 
detect cracking in the area surrounding certain attachment holes of 
the forward pintle fittings of the MLG and the actuating cylinder 
anchorage fittings on the inner rear spar; follow-on corrective 
actions, as applicable; and rework of the attachment holes; in 
accordance with Airbus Service Bulletin A320-57-1100, including 
Appendix 01, dated July 28, 1997; or Revision 03, including 
Appendices 01 and 02, dated January 16, 2003; constitutes 
terminating action for the repetitive inspection requirements of 
this AD. Actions accomplished in accordance with Airbus Service 
Bulletin A320-57-1100, Revision 01, including Appendices 01 and 02, 
dated June 4, 1999; or Revision 02, including Appendices 01 and 02, 
dated October 25, 2001; are considered acceptable for compliance 
with the optional terminating action specified in this paragraph. If 
any cracking is detected during accomplishment of any inspection 
described in the service bulletin, and the service bulletin 
specifies to contact Airbus for appropriate action: Prior to further 
flight, repair in accordance with a method approved by either the 
Manager, International Branch, ANM-116; or the DGAC (or its 
delegated agent).

Repetitive Inspections for Airplanes Not Previously Inspected Per 
Paragraph (f)

    (h) For airplanes on which the initial inspection required by 
paragraph (f) of this AD has not been accomplished as of April 21, 
2004 (the effective date of AD 2004-07-15): Accomplish the 
inspection required by paragraph (f) of this AD, at the earlier of 
the times specified in paragraphs (h)(1) and (h)(2) of this AD. If 
no cracking is found, repeat the inspection thereafter at intervals 
not to exceed 5,500 flight cycles or 10,200 flight hours, whichever 
occurs first, until paragraph (g) or (k) of this AD is accomplished. 
Accomplishment of this paragraph eliminates the need to accomplish 
repetitive inspections at the intervals required by paragraph (f)(1) 
of this AD.
    (1) Prior to the accumulation of 20,000 total flight cycles.
    (2) Prior to the accumulation of 37,300 total flight hours, or 
within 120 days after April 21, 2004, whichever occurs later.

Repetitive Inspections for Airplanes Previously Inspected Per 
Paragraph (f)

    (i) For airplanes on which the initial inspection required by 
paragraph (f) of this AD has been accomplished as of April 21, 2004, 
and no cracking was found: Do the next inspection at the earlier of 
the times specified in paragraphs (i)(1) and (i)(2) of this AD, and 
repeat the inspection thereafter at intervals not to exceed 5,500 
flight cycles or 10,200 flight hours, whichever occurs first, until 
paragraph (g) or (k) of this AD is accomplished. Accomplishment of 
this paragraph terminates the repetitive inspections required by 
paragraph (f)(1) of this AD.
    (1) Within 7,700 flight cycles since the most recent inspection.
    (2) At the later of the times specified in paragraph (i)(2)(i) 
or (i)(2)(ii) of this AD:
    (i) Within 5,500 flight cycles or 10,200 flight hours since the 
most recent inspection, whichever occurs first.
    (ii) Within 120 days after April 21, 2004.

Existing Repair

    (j) If any cracking is detected during any inspection required 
by paragraph (h) or (i) of this AD: Prior to further flight, repair 
in accordance with a method approved by either the Manager, 
International Branch, ANM-116; or the DGAC (or its delegated agent).

New Requirements of This AD

Initial and Repetitive Inspections

    (k) Within the applicable compliance times specified by 
paragraph (k)(1), (k)(2), or (k)(3) of this AD, perform an 
ultrasonic inspection for cracking of the attachment holes of the 
MLG pintle fittings in the inner rear spar in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-57-1101, 
Revision 03, dated July 30, 2003; or Revision 04, dated November 22, 
2004. If no cracking is found, repeat the inspection thereafter at 
intervals not to exceed 5,500 flight cycles or 10,200 flight hours, 
whichever occurs first, until paragraph (g) of this AD is 
accomplished. Accomplishment of this paragraph terminates the 
repetitive inspections required by paragraphs (f)(1), (h), and (i) 
of this AD.
    (1) For airplanes that have never been inspected in accordance 
with Airbus Service Bulletin A320-57-1101, dated July 24, 1997; or 
Revision 02, dated October 25, 2001: Before the accumulation of 
20,000 total flight cycles or 37,300 total flight hours, whichever 
occurs first; or within 120 days after the effective date of this 
AD; whichever occurs later.
    (2) For airplanes previously inspected in accordance with Airbus 
Service Bulletin A320-57-1101, dated July 24, 1997; or Revision 02, 
dated October 25, 2001, that have accumulated less than 18,900 total 
flight cycles or 35,300 total flight hours as of the effective date 
of this AD: Within 5,500 flight cycles or 10,200 flight hours, 
whichever occurs first, after the previous inspection performed in 
accordance with Airbus Service Bulletin A320-57-1101, Revision 02, 
dated October 25, 2001; or within 120 days after the effective date 
of this AD; whichever occurs later.
    (3) For airplanes previously inspected in accordance with Airbus 
Service Bulletin A320-57-1101, dated July 24, 1997; or Revision 02, 
dated October 25, 2001, that have accumulated 18,900 or more flight 
cycles or 35,300 or more flight hours as of the effective date of 
this AD: Before the accumulation of 24,400 total flight cycles or 
45,600 total flight hours, whichever occurs first; or within 120 
days after the effective date of this AD; whichever occurs later.

New Repair

    (l) If any crack is detected during any inspection required by 
paragraph (k) of this AD: Prior to further flight, repair in 
accordance with a method approved by either the Manager, 
International Branch, ANM-116; or the DGAC (or its delegated agent).

[[Page 8796]]

No Reporting Requirement

    (m) Although Airbus Service Bulletin A320-57-1101, Revision 02, 
dated October 25, 2001; and Revision 04, dated November 22, 2004; 
describe procedures for reporting inspection findings to Airbus, 
this AD does not require such a report.

Alternative Methods of Compliance (AMOCs)

    (n)(1) The Manager, International Branch, ANM-116, has the 
authority to approve AMOCs for this AD, if requested in accordance 
with the procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with 14 CFR 
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Related Information

    (o) French airworthiness directive F-2004-166, dated October 13, 
2004, also addresses the subject of this AD.

Material Incorporated by Reference

    (p) You must use the service information specified in Table 1 of 
this AD to perform the actions that are required by this AD, unless 
the AD specifies otherwise.

                                Table 1.--All Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
         Airbus service bulletin                  Revision level                           Date
----------------------------------------------------------------------------------------------------------------
A320-57-1100, including Appendix 01......  Original....................  July 28, 1997.
A320-57-1100, including Appendices 01 and  03..........................  January 16, 2003.
 02.
A320-57-1101.............................  Original....................  July 24, 1997.
A320-57-1101.............................  02..........................  October 25, 2001.
A320-57-1101.............................  03..........................  July 30, 2003.
A320-57-1101.............................  04..........................  November 22, 2004.
----------------------------------------------------------------------------------------------------------------

    The optional terminating action specified in paragraph (g) of 
this AD should be done in accordance with the service bulletins 
specified in Table 2 of this AD.

                                      Table 2.--Optional Service Bulletins
----------------------------------------------------------------------------------------------------------------
         Airbus service bulletin                  Revision level                           Date
----------------------------------------------------------------------------------------------------------------
A320-57-1100, including Appendix 01......  Original....................  July 28, 1997.
A320-57-1100, including Appendices 01 and  03..........................  January 16, 2003.
 02.
----------------------------------------------------------------------------------------------------------------

    (1) The Director of the Federal Register approved the 
incorporation by reference of the service bulletins specified in 
Table 3 of this AD, in accordance with 5 U.S.C. 552(a) and 1 CFR 
part 51.

                                Table 3.--New Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
         Airbus service bulletin                  Revision level                           Date
----------------------------------------------------------------------------------------------------------------
A320-57-1100, including Appendix 01......  Original....................  July 28, 1997.
A320-57-1100, including Appendices 01 and  03..........................  January 16, 2003.
 02.
A320-57-1101.............................  03..........................  July 30, 2003.
A320-57-1101.............................  04..........................  November 22, 2004.
----------------------------------------------------------------------------------------------------------------

    (2) The incorporation by reference of Airbus Service Bulletin 
A320-57-1101, Revision 02, dated October 25, 2001, was approved 
previously by the Director of the Federal Register as of April 21, 
2004 (69 FR 17906, April 6, 2004).
    (3) The incorporation by reference of Airbus Service Bulletin 
A320-57-1101, dated July 24, 1997, was approved previously by the 
Director of the Federal Register as of December 18, 1998 (63 FR 
66753, December 3, 1998).
    (4) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France, for a copy of this service information. You may 
review copies at the Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street SW., room PL-401, Nassif 
Building, Washington, DC; on the Internet at http://dms.dot.gov; or 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at the NARA, call 
(202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on February 9, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-1504 Filed 2-17-06; 8:45 am]
BILLING CODE 4910-13-P