Airworthiness Directives; Airbus Model A318-100 and A319-100 Series Airplanes; A320-111 Airplanes; A320-200 Series Airplanes; and A321-100 and A321-200 Series Airplanes, 6665-6667 [06-1151]

Download as PDF Federal Register / Vol. 71, No. 27 / Thursday, February 9, 2006 / Rules and Regulations Note 1: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ DEPARTMENT OF TRANSPORTATION Adjustment/Replacement of Wire Bundle Clamps and Installation of Protective Sleeve Airworthiness Directives; Airbus Model A318–100 and A319–100 Series Airplanes; A320–111 Airplanes; A320– 200 Series Airplanes; and A321–100 and A321–200 Series Airplanes (g) After performing the actions required by paragraph (f) of this AD: Before further flight, adjust and replace, as applicable, the wire bundle clamps located aft of station 540; and install a protective sleeve on the upper bundle of the bundle run at station 616, RBL and LBL 24.50; by accomplishing all of the applicable actions specified in the Accomplishment Instructions of Boeing Service Bulletin 737–28–1208, Revision 1, dated August 25, 2005. Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, Seattle Aircraft Certification Office, FAA, 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 § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Material Incorporated by Reference cprice-sewell on PROD1PC66 with RULES (i) You must use Boeing Service Bulletin 737–28–1208, Revision 1, dated August 25, 2005, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207, 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 January 30, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–1152 Filed 2–8–06; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 12:39 Feb 08, 2006 Jkt 208001 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22528; Directorate Identifier 2005–NM–125–AD; Amendment 39–14474; AD 2006–03–10] RIN 2120–AA64 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A318–100 and A319–100 series airplanes; A320–111 airplanes; A320–200 series airplanes; and A321– 100 and A321–200 series airplanes. This AD requires a one-time inspection of the horizontal hinge pin of the 103VU electrical panel in the avionics compartment to determine if the hinge pin can move out of the hinge, and related investigative and corrective actions if necessary. This AD results from a report indicating that electrical wire damage was found in the 103VU electrical panel due to contact between the hinge pin and the adjacent electrical wire harness. We are issuing this AD to prevent contact between the horizontal hinge pin and the adjacent electrical wire harness, which could result in damage to electrical wires, and consequent arcing and/or failure of associated systems. DATES: This AD becomes effective March 16, 2006. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of March 16, 2006. ADDRESSES: You may examine the AD docket on the Internet at http:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL–401, Washington, DC. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 6665 98055–4056; telephone (425) 227–2141; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (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 street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain Airbus Model A318– 100 and A319–100 series airplanes; A320–111 airplanes; A320–200 series airplanes; and A321–100 and A321–200 series airplanes. That NPRM was published in the Federal Register on September 27, 2005 (70 FR 56381). That NPRM proposed to require a one-time inspection of the horizontal hinge pin of the 103VU electrical panel in the avionics compartment to determine if the hinge pin can move out of the hinge, and related investigative and corrective actions if necessary. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comment received. Statement of Planned Revision to French Airworthiness Directive The commenter, the airplane manufacturer, notes that the French airworthiness directive F–2005–052 R1, dated April 13, 2005, which was cited in the NPRM, will be revised to add Airbus Modification 36115 as the final fix for the unsafe condition. The commenter notes that the purpose of Airbus Modification 36115 is to ensure that the hinge is manufactured to prevent hinge pin migration. We infer that the commenter is requesting that we consider mandating this modification when the Direction ´ ´ Generale de l’Aviation Civile (DGAC) revises French airworthiness directive F–2005–052. We will consider mandating this modification after the DGAC releases its revision. However, we will not delay issuing this AD pending release of the new French airworthiness directive and the applicable Airbus service bulletin. Operators may request an alternative method of compliance under the E:\FR\FM\09FER1.SGM 09FER1 6666 Federal Register / Vol. 71, No. 27 / Thursday, February 9, 2006 / Rules and Regulations provisions of paragraph (h) of this AD. Once the modification is approved and available, we may consider additional rulemaking. We have not changed the AD in this regard. Conclusion Costs of Compliance We have carefully reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD as proposed. The following table provides the estimated costs for U.S. operators to comply with this AD. ESTIMATED COSTS Action Work hours Average labor rate per hour Parts Cost per airplane Number of U.S.-registered airplanes Fleet cost Inspection .......................................................................................... 1 $65 None $65 696 $45,240 cprice-sewell on PROD1PC66 with RULES 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 this AD: (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. 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. VerDate Aug<31>2005 12:39 Feb 08, 2006 Jkt 208001 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): I 2006–03–10 Airbus: Amendment 39–14474. Docket No. FAA–2005–22528; Directorate Identifier 2005–NM–125–AD. Effective Date (a) This AD becomes effective March 16, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A318– 111 and –112; A319–111, –112, –113, –114, –115, –131, –132, and –133; A320–111, –211, –212, –214, –231, –232, and –233; and A321– 111, –112, –131, –211 and –231 airplanes; certificated in any category; serial numbers (S/Ns) 1 through 2396 inclusive, except S/Ns 2104, 2143, 2248, 2270, 2347, 2366, 2372, 2376, 2384, 2386, 2388, 2390, 2391, 2393, and 2395. Unsafe Condition (d) This AD results from a report indicating that electrical wire damage was found in the 103VU electrical panel due to contact between the hinge pin and the adjacent electrical wire harness. We are issuing this AD to prevent contact between the horizontal hinge pin and the adjacent electrical wire harness, which could result in damage to PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 electrical wires, and consequent arcing and/ or failure of associated systems. 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. Inspections and Corrective Actions (f) Within 600 flight hours after the effective date of this AD, do a general visual inspection of the horizontal hinge pin of the 103VU electrical panel in the avionics compartment to determine if the pin can move out of the hinge, and do any applicable related investigative and corrective actions, including repair of any damaged electrical wires, before further flight. Do all the actions in accordance with Airbus All Operators Telex 25A1440, dated February 15, 2005. Note 1: For the purposes of this AD, a general visual inspection is: ‘‘A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.’’ No Reporting (g) Although Airbus All Operators Telex 25A1440, dated February 15, 2005, specifies that operators should send the results of inspections to the manufacturer, that action is not required by this AD. Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, 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 § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. E:\FR\FM\09FER1.SGM 09FER1 Federal Register / Vol. 71, No. 27 / Thursday, February 9, 2006 / Rules and Regulations Related Information (i) French airworthiness directive F–2005– 052 R1, dated April 13, 2005, also addresses the subject of this AD. Material Incorporated by Reference (j) You must use Airbus All Operators Telex 25A1440, dated February 15, 2005, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 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 January 26, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–1151 Filed 2–8–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–23799; Directorate Identifier 2004–NM–141–AD; Amendment 39–14475; AD 2006–03–11] RIN 2120–AA64 Airworthiness Directives; British Aerospace Model HS 748 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. cprice-sewell on PROD1PC66 with RULES AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all British Aerospace Model HS 748 airplanes. This AD requires installing a baulking actuator system for the elevator gust lock; doing a functional test and an inspection of any previously installed baulking actuator system for wiring errors; doing repetitive inspections of the gust lock baulk lever for correct operation; and corrective action, if necessary. This AD results from incidents where an elevator gust lock reengaged without input from the flightcrew, and may have caused a flight VerDate Aug<31>2005 12:39 Feb 08, 2006 Jkt 208001 control restriction. We are issuing this AD to prevent uncommanded reengagement of the elevator gust lock, which could result in restriction of the elevator’s movement and consequent reduced controllability of the airplane. DATES: This AD becomes effective February 24, 2006. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of February 24, 2006. We must receive comments on this AD by April 10, 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 British Aerospace Regional Aircraft American Support, 13850 Mclearen Road, Herndon, Virginia 20171, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–1175; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion The Civil Aviation Authority (CAA), which is the airworthiness authority for the United Kingdom, notified us that an unsafe condition may exist on British Aerospace Model HS 748 airplanes. The CAA advises that there have been two incidents where re-engagement of the elevator gust lock without input by the flightcrew may have caused a flight control restriction. Uncommanded reengagement of the elevator gust lock, if not corrected, could result in restriction of the elevator’s movement and consequent reduced controllability of the airplane. Relevant Service Information British Aerospace has issued BAE Systems (Operations) Limited Service PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 6667 Bulletin HS748–27–135, Revision 2, dated October 2, 2003. The service bulletin describes procedures for installing a baulking actuator system for the elevator gust lock; doing a functional test of the actuator system for correct operation; and inspecting the gust lock baulk lever for correct operation. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The CAA mandated a previous revision of the service bulletin (which specified some wiring procedures incorrectly) and issued British airworthiness directive 003–12– 2002 to ensure the continued airworthiness of these airplanes in the United Kingdom. The CAA has also issued British airworthiness directive G–2004–0002, dated February 18, 2004, which supersedes British airworthiness directive 003–12–2002, and requires doing additional actions in accordance with Revision 2 of the service bulletin. Service Bulletin HS748–27–135 refers to BAE Systems (Operations) Limited Alert Service Bulletin HS748–A27–128, Revision 1, dated December 10, 2002, as an additional source of service information for accomplishing a check of the rigging of the gust lock system. Service Bulletin HS748–27–135 also refers to BAE Systems (Operations) Limited Service Bulletin HS748–A27– 76, Revision 3, dated December 20, 1996, as an additional source of service information for accomplishing an overlap check of the lever gate stop. FAA’s Determination and Requirements of This AD This airplane model is manufactured in the United Kingdom 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 CAA has kept the FAA informed of the situation described above. We have examined the CAA’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. Therefore, we are issuing this AD to prevent uncommanded re-engagement of the elevator gust lock, which could result in restriction of the elevator’s movement and consequent reduced controllability of the airplane. This AD requires accomplishing the actions specified in the service information described previously, except as described in ‘‘Difference Between This AD and the Service Bulletin.’’ E:\FR\FM\09FER1.SGM 09FER1

Agencies

[Federal Register Volume 71, Number 27 (Thursday, February 9, 2006)]
[Rules and Regulations]
[Pages 6665-6667]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-1151]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22528; Directorate Identifier 2005-NM-125-AD; 
Amendment 39-14474; AD 2006-03-10]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A318-100 and A319-100 
Series Airplanes; A320-111 Airplanes; A320-200 Series Airplanes; and 
A321-100 and A321-200 Series Airplanes

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

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Airbus Model A318-100 and A319-100 series airplanes; A320-111 
airplanes; A320-200 series airplanes; and A321-100 and A321-200 series 
airplanes. This AD requires a one-time inspection of the horizontal 
hinge pin of the 103VU electrical panel in the avionics compartment to 
determine if the hinge pin can move out of the hinge, and related 
investigative and corrective actions if necessary. This AD results from 
a report indicating that electrical wire damage was found in the 103VU 
electrical panel due to contact between the hinge pin and the adjacent 
electrical wire harness. We are issuing this AD to prevent contact 
between the horizontal hinge pin and the adjacent electrical wire 
harness, which could result in damage to electrical wires, and 
consequent arcing and/or failure of associated systems.

DATES: This AD becomes effective March 16, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of March 16, 
2006.

ADDRESSES: You may examine the AD docket on the Internet at http://
dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street SW., Nassif Building, 
room PL-401, Washington, DC.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this AD.

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:

Examining the Docket

    You may examine the airworthiness directive (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 street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that would apply to certain Airbus Model 
A318-100 and A319-100 series airplanes; A320-111 airplanes; A320-200 
series airplanes; and A321-100 and A321-200 series airplanes. That NPRM 
was published in the Federal Register on September 27, 2005 (70 FR 
56381). That NPRM proposed to require a one-time inspection of the 
horizontal hinge pin of the 103VU electrical panel in the avionics 
compartment to determine if the hinge pin can move out of the hinge, 
and related investigative and corrective actions if necessary.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comment received.

Statement of Planned Revision to French Airworthiness Directive

    The commenter, the airplane manufacturer, notes that the French 
airworthiness directive F-2005-052 R1, dated April 13, 2005, which was 
cited in the NPRM, will be revised to add Airbus Modification 36115 as 
the final fix for the unsafe condition. The commenter notes that the 
purpose of Airbus Modification 36115 is to ensure that the hinge is 
manufactured to prevent hinge pin migration.
    We infer that the commenter is requesting that we consider 
mandating this modification when the Direction G[eacute]n[eacute]rale 
de l'Aviation Civile (DGAC) revises French airworthiness directive F-
2005-052. We will consider mandating this modification after the DGAC 
releases its revision. However, we will not delay issuing this AD 
pending release of the new French airworthiness directive and the 
applicable Airbus service bulletin. Operators may request an 
alternative method of compliance under the

[[Page 6666]]

provisions of paragraph (h) of this AD. Once the modification is 
approved and available, we may consider additional rulemaking. We have 
not changed the AD in this regard.

Conclusion

    We have carefully reviewed the available data, including the 
comment received, and determined that air safety and the public 
interest require adopting the AD as proposed.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this AD.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                        Number of
                                                Average                   Cost per        U.S.-
             Action               Work hours  labor rate      Parts       airplane     registered    Fleet cost
                                               per hour                                 airplanes
----------------------------------------------------------------------------------------------------------------
Inspection......................          1         $65   None........          $65           696       $45,240
----------------------------------------------------------------------------------------------------------------

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 this AD:
    (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.
    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:

    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 
adding the following new airworthiness directive (AD):

2006-03-10 Airbus: Amendment 39-14474. Docket No. FAA-2005-22528; 
Directorate Identifier 2005-NM-125-AD.

Effective Date

    (a) This AD becomes effective March 16, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A318-111 and -112; A319-111, 
-112, -113, -114, -115, -131, -132, and -133; A320-111, -211, -212, 
-214, -231, -232, and -233; and A321-111, -112, -131, -211 and -231 
airplanes; certificated in any category; serial numbers (S/Ns) 1 
through 2396 inclusive, except S/Ns 2104, 2143, 2248, 2270, 2347, 
2366, 2372, 2376, 2384, 2386, 2388, 2390, 2391, 2393, and 2395.

Unsafe Condition

    (d) This AD results from a report indicating that electrical 
wire damage was found in the 103VU electrical panel due to contact 
between the hinge pin and the adjacent electrical wire harness. We 
are issuing this AD to prevent contact between the horizontal hinge 
pin and the adjacent electrical wire harness, which could result in 
damage to electrical wires, and consequent arcing and/or failure of 
associated systems.

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.

Inspections and Corrective Actions

    (f) Within 600 flight hours after the effective date of this AD, 
do a general visual inspection of the horizontal hinge pin of the 
103VU electrical panel in the avionics compartment to determine if 
the pin can move out of the hinge, and do any applicable related 
investigative and corrective actions, including repair of any 
damaged electrical wires, before further flight. Do all the actions 
in accordance with Airbus All Operators Telex 25A1440, dated 
February 15, 2005.

    Note 1: For the purposes of this AD, a general visual inspection 
is: ``A visual examination of an interior or exterior area, 
installation, or assembly to detect obvious damage, failure, or 
irregularity. This level of inspection is made from within touching 
distance unless otherwise specified. A mirror may be necessary to 
ensure visual access to all surfaces in the inspection area. This 
level of inspection is made under normally available lighting 
conditions such as daylight, hangar lighting, flashlight, or 
droplight and may require removal or opening of access panels or 
doors. Stands, ladders, or platforms may be required to gain 
proximity to the area being checked.''

No Reporting

    (g) Although Airbus All Operators Telex 25A1440, dated February 
15, 2005, specifies that operators should send the results of 
inspections to the manufacturer, that action is not required by this 
AD.

Alternative Methods of Compliance (AMOCs)

    (h)(1) The Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 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 Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

[[Page 6667]]

Related Information

    (i) French airworthiness directive F-2005-052 R1, dated April 
13, 2005, also addresses the subject of this AD.

Material Incorporated by Reference

    (j) You must use Airbus All Operators Telex 25A1440, dated 
February 15, 2005, to perform the actions that are required by this 
AD, unless the AD specifies otherwise. The Director of the Federal 
Register approved the incorporation by reference of this document in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 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 January 26, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-1151 Filed 2-8-06; 8:45 am]
BILLING CODE 4910-13-P