Airworthiness Directives; Airbus Model A330, A340-200, and A340-300 Series Airplanes, 13345-13347 [05-5297]

Download as PDF Federal Register / Vol. 70, No. 53 / Monday, March 21, 2005 / Rules and Regulations its place ‘‘in paragraph (e) of this section’’. I 4. In § 630.301, in newly redesignated paragraphs (g) and (i), remove the phrase ‘‘under paragraph (d) of this section’’ and add in its place ‘‘under paragraph (h) of this section’’ wherever it occurs. [FR Doc. 05–5508 Filed 3–18–05; 8:45 am] BILLING CODE 6325–39–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 13 Rules of Practice in FAA Civil Penalty Actions Federal Aviation Administration (FAA), DOT. ACTION: Final rule; technical amendment. AGENCY: The FAA amended the procedural regulations governing the assessment of civil penalties against persons other than individuals acting as pilots, flight engineers, mechanics or repairmen in a notice published in the Federal Register on February 18, 2005. We explained in the preamble of that notice that we were amending the procedural rules to provide the FAA Hearing Docket’s new address and new instructions on filing of documents. We inadvertently failed to amend the rule about filing an appeal, to include the new address informtion. We are now making that inadvertently omitted amendment. SUMMARY: This rule is effective on March 21, 2005. FOR FURTHER INFORMATION CONTACT: Vicki Leemon, Office of the Chief Counsel, Adjudication Branch, 800 Independence Avenue, SW., Washington, DC 20591; telephone 202/ 385–8227. SUPPLEMENTARY INFORMATION: DATES: Background The Administrator may impose a civil penalty against a person other than an individual acting as a pilot, flight engineer, mechanic, or repairman, after notice and an opportunity for a hearing on the record, for violations cited in 49 U.S.C. 46301(d)(2) or 47531. 49 U.S.C. 46301(d)(7)(A) and 47531. These violations, in general, involve aviation safety issues. Also, under 49 U.S.C. 5123 and 49 CFR 1.47(k), the Administrator may, after notice and an opportunity for a hearing, assess a civil penalty against any person who knowingly violates the Federal VerDate jul<14>2003 15:51 Mar 18, 2005 Jkt 205001 hazardous materials transportation law, 49 U.S.C. chapter 51, or any of its implementing regulations. The rules governing proceedings in these civil penalty cases are set forth in 14 CFR 13.16 and 14 CFR part 13, subpart G. We recently amended those rules to, among other things, provide the new address of the FAA Hearing Docket. 70 FR 8236, February 18, 2005. As we explained in the February 18, 2005, notice, the FAA Hearing Docket is now located in Room 2014 of the Wilbur Wright Building, 600 Independence Avenue, SW., Washington, DC 20591. Anyone handdelivering a document for filing should go to the Wilbur Wright Building at the above address. Packages sent by expedited courier to the Hearing Docket should be addressed as follows: Hearing Docket, Federal Aviation Administration, 600 Independence Avenue, SW., Wilbur Wright Building— Room 2014, Washington, DC 20591; Att: Hearing Docket Clerk, AGC–430. As explained further in the February 18, 2005, notice, all envelopes and packages sent by U.S. Mail to individuals in the Wilbur Wright Building are processed by the FAA Headquarters’ mail room staff located at 800 Independence Avenue, SW., Washington, DC 20591. Consequently, anyone using U.S. Mail to file a document should use the following address: Hearing Docket, Federal Aviation Administration, 800 Independence Avenue, SW., Washington, DC 20591; Att: Hearing Docket Clerk, AGC–430, Wilbur Wright Building—Room 2014. We explained in the February 18, 2005, notice that we were revising several sections of 14 CFR part 13, subpart G—including 14 CFR 13.233— to include this new information. However, we failed to include the actual revision in the notice. This technical amendment is intended to correct that omission from the previous revision. Procedural Matters In general, under the APA, 5 U.S.C. 533, agencies must publish regulations for public comment and give the public at least 30 days notice before adopting regulations. There is an exception to these requirements if the agency for good cause finds that notice and public procedure are impracticable, unnecessary, or contrary to the public interest. In this case, the FAA finds that notice and comment requirements are unnecessary due to the administrative nature of the changes. It is in the public interest that the revision to 14 CFR 13.233 takes effect promptly so that anyone appealing from an administrative law judge’s initial PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 13345 decision or order knows the correct address to use for the Hearing Docket. This revision was inadvertently omitted during the prevision revision. The amendments set forth in this notice do not affect the rights or duties of any regulated entity. List of Subjects in 14 CFR Part 13 Administrative practice and procedure, Air transportation, Aviation safety, Hazardous materials transportation, Investigations, Law enforcement, Penalties. The Amendments Accordingly, the Federal Aviation Administration amends part 13 of title 14, Code of Federal Regulations as follows: I PART 13—INVESTIGATIVE AND ENFORCEMENT PROCEDURES 1. The authority citation for part 13 continues to read as follows: I Authority: 18 U.S.C. 6002; 28 U.S.C. 2461 (note); 49 U.S.C. 106(g), 5121–5124, 40113– 40114, 44103–44106, 44702–44703, 44709– 44710, 44713, 46101–46110, 46301–46316, 46318, 46501–46502, 46504–46507, 47106, 47111, 47112, 47122, 47306, 47531–47532; 49 CFR 1.47. 2. Amend § 13.233 by revising the second sentence of paragraph (a) to read as follows: I § 13.233 Appeal from initial decision. (a) * * * A party must file the notice of appeal in the FAA Hearing Docket using the appropriate address listed in § 13.210(a). * * * * * * * * Issued in Washington, DC on March 15, 2005. Rebecca MacPherson, Assistant Chief Counsel for Regulations. [FR Doc. 05–5439 Filed 3–18–05; 8:45 am] BILLING CODE 4910–13–M DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20025; Directorate Identifier 2004–NM–208–AD; Amendment 39–14016; AD 2005–06–08] RIN 2120–AA64 Airworthiness Directives; Airbus Model A330, A340–200, and A340–300 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). AGENCY: E:\FR\FM\21MRR1.SGM 21MRR1 13346 ACTION: Federal Register / Vol. 70, No. 53 / Monday, March 21, 2005 / Rules and Regulations Final rule. SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A330, A340–200, and A340–300 series airplanes. This AD requires repetitive inspections of a certain bracket that attaches the flight deck instrument panel to the airplane structure; replacement of the bracket with a new, improved bracket; and related investigative and corrective actions if necessary. This AD is prompted by reports of cracking of a certain bracket that attaches the flight deck instrument panel to the airplane structure. We are issuing this AD to detect and correct a cracked bracket. Failure of this bracket, combined with failure of the horizontal beam, could result in collapse of the left part of the flight deck instrument panel, and consequent reduced controllability of the airplane. DATES: This AD becomes effective April 25, 2005. The incorporation by reference of certain publications listed in the AD is approved by the Director of the Federal Register as of April 25, 2005. ADDRESSES: For service information identified in this AD, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Docket: The AD docket contains the proposed AD, comments, and any final disposition. You can examine the AD docket on the Internet at https:// 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 U.S. Department of Transportation, 400 Seventh Street, SW., room PL–401, Washington, DC. This docket number is FAA–2005–20025; the directorate identifier for this docket is 2004–NM– 208–AD. FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2797; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR Part 39 with an AD for all Airbus Model A330, A340–200, and A340–300 series airplanes. That action, published in the Federal Register on January 12, 2005 (70 FR 2067), proposed to require repetitive inspections of a certain bracket that attaches the flight deck instrument panel to the airplane VerDate jul<14>2003 15:51 Mar 18, 2005 Jkt 205001 structure; replacement of the bracket with a new, improved bracket; and related investigative and corrective actions if necessary. Comments We provided the public the opportunity to participate in the development of this AD. No comments have been submitted on the proposed AD or on the determination of the cost to the public. Clarification of Final Rule We have revised paragraphs (i)(3)(i) and (i)(3)(ii) to clarify that the compliance times are relative to the replacement of a certain bracket that attaches the flight deck instrument panel to the airplane structure. Conclusion We have carefully reviewed the available data, and determined that air safety and the public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance This AD will affect about 19 Model A330 series airplanes of U.S. registry. The required inspection will take about 1 work hour per airplane, per inspection cycle, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the AD for U.S. operators is $1,235, or $65 per airplane, per inspection cycle. There are currently no affected Model A340–200 or –300 series airplanes of U.S. registry. However, if one of these airplanes is imported and put on the U.S. Register in the future, this cost estimate will also apply to those airplanes. 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. 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 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 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 PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): I 2005–06–08 Airbus: Amendment 39–14016. Docket No. FAA–2005–20025; Directorate Identifier 2004–NM–208–AD. Effective Date (a) This AD becomes effective April 25, 2005. Affected ADs (b) None. Applicability (c) This AD applies to all Airbus Model A330, A340–200, and A340–300 series airplanes; certificated in any category. E:\FR\FM\21MRR1.SGM 21MRR1 Federal Register / Vol. 70, No. 53 / Monday, March 21, 2005 / Rules and Regulations Unsafe Condition (d) This AD was prompted by reports of cracking of a certain bracket that attaches the flight deck instrument panel to the airplane structure. We are issuing this AD to detect and correct a cracked bracket. Failure of this bracket, combined with failure of the horizontal beam, could result in collapse of the left part of the flight deck instrument panel, and consequent reduced controllability 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. Service Bulletin Reference (f) The term ‘‘service bulletin,’’ as used in this AD, means the Accomplishment Instructions of Airbus Service Bulletins A330–25–3227 (for Model A330 series airplanes); and A340–25–4230 (for Model A340–200 and –300 series airplanes); both including Appendix 01; and both dated June 17, 2004; as applicable. Initial Inspection (g) At the applicable time specified in paragraph (g)(1) or (g)(2) of this AD, perform a detailed inspection of the bracket having part number (P/N) F2511012920000, which attaches the flight deck instrument panel to airplane structure, in accordance with the service bulletin. (1) For Model A330 series airplanes: Prior to the accumulation of 16,500 total flight cycles, or within 60 days after the effective date of this AD, whichever is later. (2) For Model A340–200 and –300 series airplanes: Prior to the accumulation of 9,700 total flight cycles, or within 2,700 flight cycles after the effective date of this AD, whichever is later. 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.’’ No Cracking/Repetitive Inspections (h) If no cracking is found during the initial inspection required by paragraph (g) of this AD: Repeat the inspection thereafter at the applicable interval specified in paragraph (h)(1) or (h)(2) of this AD. (1) For Model A330 series airplanes: Intervals not to exceed 13,800 flight cycles. (2) For Model A340–200 and –300 series airplanes: Intervals not to exceed 7,000 flight cycles. Crack Found/Replacement, Reporting, and Repetitive Inspections (i) If any cracking is found during any inspection required by paragraph (g) or (h) of this AD: Do the actions in paragraphs (i)(1), (i)(2), and (i)(3) of this AD, except as provided by paragraph (j) of this AD. VerDate jul<14>2003 15:51 Mar 18, 2005 Jkt 205001 (1) Before further flight: Replace the cracked bracket with a new, improved bracket having P/N F2511012920095, in accordance with the service bulletin. (2) Within 30 days after performing the inspection, or within 30 days after the effective date of this AD, whichever is later: Report the cracked fitting to Airbus, Department AI/SE–A21, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. The report must include the airplane serial number, the number of flight cycles and flight hours on the airplane, the date of the inspection, and whether both flanges of a bracket are broken. Submitting Appendix 01 of the applicable service bulletin is acceptable for compliance with this paragraph. Under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120–0056. (3) Inspect the replaced bracket at the time specified in paragraph (i)(3)(i) or (i)(3)(ii) of this AD. Then, do repetitive inspections or replace the bracket as specified in paragraph (h) or (i) of this AD, as applicable. (i) For Model A330 series airplanes: Within 16,500 flight cycles after replacing the bracket. (ii) For Model A340–200 and –300 series airplanes: Within 9,700 flight cycles after replacing the bracket. (j) If both flanges of a bracket are broken: Before further flight, replace the bracket as specified in paragraph (i)(1) and perform any applicable related investigative and corrective actions (which may include inspections for damage to surrounding structure caused by the broken bracket, and corrective actions for any damage that is found), in accordance with a method approved by the Manager, International Branch, ANM–116, Transport Airplane ´ ´ Directorate, FAA; or the Direction Generale de l’Aviation Civile (DGAC) (or its delegated agent). Alternative Methods of Compliance (AMOCs) (k) 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. Related Information (l) French airworthiness directives F– 2004–140 and F–2004–141, both dated August 18, 2004, also address the subject of this AD. Material Incorporated by Reference (m) You must use Airbus Service Bulletin A330–25–3227, including Appendix 01, dated June 17, 2004; or Airbus Service Bulletin A340–25–4230, including Appendix 01, dated June 17, 2004; as applicable; to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approves the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. For copies of the service information, contact Airbus, 1 Rond PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 13347 Point Maurice Bellonte, 31707 Blagnac Cedex, France. For information on the availability of this material at the National Archives and Records Administration (NARA), call (202) 741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. You may view the AD docket at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW, room PL–401, Nassif Building, Washington, DC. Issued in Renton, Washington, on March 8, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–5297 Filed 3–18–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2004–19945; Directorate Identifier 2004–NM–22–AD; Amendment 39– 14017; AD 2005–06–09] RIN 2120–AA64 Airworthiness Directives; Boeing Model 747–200B, 747–200C, 747–200F, 747–300, and 747SR Series Airplanes Equipped With General Electric (GE) CF6–45 or –50 Series Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747–200B, 747–200C, 747–200F, 747–300, and 747SR series airplanes, equipped with GE CF6–45 or –50 series engines. This AD requires modifying the side cowl assemblies on the engines by replacing existing wear plates with new extended wear plates and installing new stop fittings. This AD is prompted by reports of a gap at the interface of the lower portion of the side cowl and the aft flange of the thrust reverser. We are issuing this AD to prevent an excessive quantity of air from entering the fire zone that surrounds the engine, which, in the event of an engine fire, could result in an inability to control or extinguish the fire. DATES: This AD becomes effective April 25, 2005. The incorporation by reference of certain publications listed in the AD is approved by the Director of the Federal Register as of April 25, 2005. ADDRESSES: For service information identified in this AD, contact Boeing E:\FR\FM\21MRR1.SGM 21MRR1

Agencies

[Federal Register Volume 70, Number 53 (Monday, March 21, 2005)]
[Rules and Regulations]
[Pages 13345-13347]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-5297]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20025; Directorate Identifier 2004-NM-208-AD; 
Amendment 39-14016; AD 2005-06-08]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330, A340-200, and A340-
300 Series Airplanes

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

[[Page 13346]]


ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all 
Airbus Model A330, A340-200, and A340-300 series airplanes. This AD 
requires repetitive inspections of a certain bracket that attaches the 
flight deck instrument panel to the airplane structure; replacement of 
the bracket with a new, improved bracket; and related investigative and 
corrective actions if necessary. This AD is prompted by reports of 
cracking of a certain bracket that attaches the flight deck instrument 
panel to the airplane structure. We are issuing this AD to detect and 
correct a cracked bracket. Failure of this bracket, combined with 
failure of the horizontal beam, could result in collapse of the left 
part of the flight deck instrument panel, and consequent reduced 
controllability of the airplane.

DATES: This AD becomes effective April 25, 2005.
    The incorporation by reference of certain publications listed in 
the AD is approved by the Director of the Federal Register as of April 
25, 2005.

ADDRESSES: For service information identified in this AD, contact 
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
    Docket: The AD docket contains the proposed AD, comments, and any 
final disposition. You can examine the AD docket on the Internet at 
https://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 U.S. 
Department of Transportation, 400 Seventh Street, SW., room PL-401, 
Washington, DC. This docket number is FAA-2005-20025; the directorate 
identifier for this docket is 2004-NM-208-AD.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2797; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR Part 39 
with an AD for all Airbus Model A330, A340-200, and A340-300 series 
airplanes. That action, published in the Federal Register on January 
12, 2005 (70 FR 2067), proposed to require repetitive inspections of a 
certain bracket that attaches the flight deck instrument panel to the 
airplane structure; replacement of the bracket with a new, improved 
bracket; and related investigative and corrective actions if necessary.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. No comments have been submitted on the proposed 
AD or on the determination of the cost to the public.

Clarification of Final Rule

    We have revised paragraphs (i)(3)(i) and (i)(3)(ii) to clarify that 
the compliance times are relative to the replacement of a certain 
bracket that attaches the flight deck instrument panel to the airplane 
structure.

Conclusion

    We have carefully reviewed the available data, and determined that 
air safety and the public interest require adopting the AD with the 
changes described previously. We have determined that these changes 
will neither increase the economic burden on any operator nor increase 
the scope of the AD.

Costs of Compliance

    This AD will affect about 19 Model A330 series airplanes of U.S. 
registry. The required inspection will take about 1 work hour per 
airplane, per inspection cycle, at an average labor rate of $65 per 
work hour. Based on these figures, the estimated cost of the AD for 
U.S. operators is $1,235, or $65 per airplane, per inspection cycle.
    There are currently no affected Model A340-200 or -300 series 
airplanes of U.S. registry. However, if one of these airplanes is 
imported and put on the U.S. Register in the future, this cost estimate 
will also apply to those airplanes.

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. 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 FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2005-06-08 Airbus: Amendment 39-14016. Docket No. FAA-2005-20025; 
Directorate Identifier 2004-NM-208-AD.

Effective Date

    (a) This AD becomes effective April 25, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Airbus Model A330, A340-200, and 
A340-300 series airplanes; certificated in any category.

[[Page 13347]]

Unsafe Condition

    (d) This AD was prompted by reports of cracking of a certain 
bracket that attaches the flight deck instrument panel to the 
airplane structure. We are issuing this AD to detect and correct a 
cracked bracket. Failure of this bracket, combined with failure of 
the horizontal beam, could result in collapse of the left part of 
the flight deck instrument panel, and consequent reduced 
controllability 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.

Service Bulletin Reference

    (f) The term ``service bulletin,'' as used in this AD, means the 
Accomplishment Instructions of Airbus Service Bulletins A330-25-3227 
(for Model A330 series airplanes); and A340-25-4230 (for Model A340-
200 and -300 series airplanes); both including Appendix 01; and both 
dated June 17, 2004; as applicable.

Initial Inspection

    (g) At the applicable time specified in paragraph (g)(1) or 
(g)(2) of this AD, perform a detailed inspection of the bracket 
having part number (P/N) F2511012920000, which attaches the flight 
deck instrument panel to airplane structure, in accordance with the 
service bulletin.
    (1) For Model A330 series airplanes: Prior to the accumulation 
of 16,500 total flight cycles, or within 60 days after the effective 
date of this AD, whichever is later.
    (2) For Model A340-200 and -300 series airplanes: Prior to the 
accumulation of 9,700 total flight cycles, or within 2,700 flight 
cycles after the effective date of this AD, whichever is later.

    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.''

No Cracking/Repetitive Inspections

    (h) If no cracking is found during the initial inspection 
required by paragraph (g) of this AD: Repeat the inspection 
thereafter at the applicable interval specified in paragraph (h)(1) 
or (h)(2) of this AD.
    (1) For Model A330 series airplanes: Intervals not to exceed 
13,800 flight cycles.
    (2) For Model A340-200 and -300 series airplanes: Intervals not 
to exceed 7,000 flight cycles.

Crack Found/Replacement, Reporting, and Repetitive Inspections

    (i) If any cracking is found during any inspection required by 
paragraph (g) or (h) of this AD: Do the actions in paragraphs 
(i)(1), (i)(2), and (i)(3) of this AD, except as provided by 
paragraph (j) of this AD.
    (1) Before further flight: Replace the cracked bracket with a 
new, improved bracket having P/N F2511012920095, in accordance with 
the service bulletin.
    (2) Within 30 days after performing the inspection, or within 30 
days after the effective date of this AD, whichever is later: Report 
the cracked fitting to Airbus, Department AI/SE-A21, 1 Rond Point 
Maurice Bellonte, 31707 Blagnac Cedex, France. The report must 
include the airplane serial number, the number of flight cycles and 
flight hours on the airplane, the date of the inspection, and 
whether both flanges of a bracket are broken. Submitting Appendix 01 
of the applicable service bulletin is acceptable for compliance with 
this paragraph. Under the provisions of the Paperwork Reduction Act 
of 1980 (44 U.S.C. 3501 et seq.), the Office of Management and 
Budget (OMB) has approved the information collection requirements 
contained in this AD and has assigned OMB Control Number 2120-0056.
    (3) Inspect the replaced bracket at the time specified in 
paragraph (i)(3)(i) or (i)(3)(ii) of this AD. Then, do repetitive 
inspections or replace the bracket as specified in paragraph (h) or 
(i) of this AD, as applicable.
    (i) For Model A330 series airplanes: Within 16,500 flight cycles 
after replacing the bracket.
    (ii) For Model A340-200 and -300 series airplanes: Within 9,700 
flight cycles after replacing the bracket.
    (j) If both flanges of a bracket are broken: Before further 
flight, replace the bracket as specified in paragraph (i)(1) and 
perform any applicable related investigative and corrective actions 
(which may include inspections for damage to surrounding structure 
caused by the broken bracket, and corrective actions for any damage 
that is found), in accordance with a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) 
(or its delegated agent).

Alternative Methods of Compliance (AMOCs)

    (k) 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.

Related Information

    (l) French airworthiness directives F-2004-140 and F-2004-141, 
both dated August 18, 2004, also address the subject of this AD.

Material Incorporated by Reference

    (m) You must use Airbus Service Bulletin A330-25-3227, including 
Appendix 01, dated June 17, 2004; or Airbus Service Bulletin A340-
25-4230, including Appendix 01, dated June 17, 2004; as applicable; 
to perform the actions that are required by this AD, unless the AD 
specifies otherwise. The Director of the Federal Register approves 
the incorporation by reference of these documents in accordance with 
5 U.S.C. 552(a) and 1 CFR part 51. For copies of the service 
information, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France. For information on the availability of this 
material at the National Archives and Records Administration (NARA), 
call (202) 741-6030, or go to: https://www.archives.gov/federal_
register/code_of_federal_regulations/ibr_locations.html.
    You may view the AD docket at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street SW, room PL-
401, Nassif Building, Washington, DC.

    Issued in Renton, Washington, on March 8, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-5297 Filed 3-18-05; 8:45 am]
BILLING CODE 4910-13-P

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