Airworthiness Directives; Airbus Model A330, A340-200, and A340-300 Series Airplanes, 2067-2070 [05-612]

Download as PDF Federal Register / Vol. 70, No. 8 / Wednesday, January 12, 2005 / Proposed Rules 61772). The proposed rule would have required installing shield assemblies for power feeder cables in the forward and aft lower cargo compartments, and installing an additional shield for the power feeder cable of the auxiliary power unit in the aft lower cargo compartment. That action was prompted by several incidents of migration of power feeder cable troughs on McDonnell Douglas Model DC–9–81 (MD–81), DC–9–82 (MD–82), DC–9–83 (MD–83), DC–9–87 (MD–87), and MD– 88 airplanes. The proposed actions were intended to prevent a cable from chafing against an edge of a lightening hole, which could result in electrical arcing, and consequent smoke/fire in the lower cargo compartments. Response to Comments We have considered the comments that have been submitted on the proposed AD. One commenter points out that an existing AD, AD 94–09–02, amendment 39–8890 (59 FR 18720, April 20, 1994), currently requires accomplishment of the original issue of Boeing Service Bulletin MD80–24–100. The commenter further states that all affected airplanes listed in Revision 04 of that service bulletin (referenced as the appropriate source of service information in the proposed rule) were affected by the previous revisions of that service bulletin, and that the proposed rule contains no new requirements beyond those required by the existing AD. We agree. We have determined that the requirements of the proposed rule are included in the requirements of another existing AD. The existing AD, AD 94–09–02, is applicable to certain McDonnell Douglas Model DC–9–81 (MD–81), DC–9–82 (MD–82), DC–9–83 (MD–83), and DC–9–87 (MD–87) series airplanes; and Model MD–88 airplanes; as listed in McDonnell Douglas MD–80 Service Bulletin 24–94, Revision 1, dated May 28, 1987, and McDonnell Douglas Model MD–80 Service Bulletin 24–100, dated March 30, 1988. That AD requires an inspection to detect damage of the auxiliary power unit (APU) power feeder cable installation, repair of damaged cables, modification of the cable installation, and an inspection of previously modified airplanes to determine whether a spacer or ‘‘stand off’’ has been installed, and installation of those items, if necessary. That action was prompted by reports of generator power feeder cables electrically shorting to the airplane structure due to chafing. The requirements of that AD are intended to prevent the APU power feeder cable from chafing against adjacent structures, which could result VerDate jul<14>2003 17:43 Jan 11, 2005 Jkt 205001 in electrical shorting and arcing, and a fire below the cabin floor. Additionally, AD 94–09–02 references McDonnell Douglas MD–80 Service Bulletin 24–100, dated March 30, 1988, as the appropriate source of service information for accomplishing the modification. The proposed rule references McDonnell Douglas Alert Service Bulletin MD80–24A100, Revision 04, dated January 24, 2000, as the appropriate source of service information for accomplishing the modification (installing shield assemblies for power feeder cables). Revision 04 was issued merely to elevate the service bulletin to the ‘‘alert’’ status and to reference AD 94–09–02; no additional work is required. All airplanes affected by Revision 04 are also affected by the previous revisions of the service bulletin. The proposed rule does not contain any new requirements beyond those required by AD 94–09–02. Accomplishment of the requirements of AD 94–09–02 adequately addresses the identified unsafe condition. FAA’s Conclusions Upon further consideration, the FAA has determined that the proposed requirements are included in the requirements of another existing AD; the proposed rule does not contain any new requirements beyond those of the existing AD. Accordingly, the proposed rule is hereby withdrawn. Withdrawal of this NPRM constitutes only such action, and does not preclude the agency from issuing another action in the future, nor does it commit the agency to any course of action in the future. Regulatory Impact Since this action only withdraws a notice of proposed rulemaking, it is neither a proposed nor a final rule and therefore is not covered under Executive Order 12866, the Regulatory Flexibility Act, or DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979). List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Withdrawal Accordingly, the notice of proposed rulemaking, Docket 2000–NM–168–AD, published in the Federal Register on October 30, 2003 (68 FR 61772), is withdrawn. PO 00000 Frm 00041 Fmt 4702 Sfmt 4702 2067 Issued in Renton, Washington, on January 3, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–613 Filed 1–11–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20025; Directorate Identifier 2004–NM–208–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A330, A340–200, and A340–300 Series Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for all Airbus Model A330, A340–200, and A340–300 series airplanes. This proposed AD would 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. This proposed AD is prompted by reports of cracking of a certain bracket that attaches the flight deck instrument panel to the airplane structure. We are proposing 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: We must receive comments on this proposed AD by February 11, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://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. • By fax: (202) 493–2251. E:\FR\FM\12JAP1.SGM 12JAP1 2068 Federal Register / Vol. 70, No. 8 / Wednesday, January 12, 2005 / Proposed Rules • 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. For service information identified in this proposed AD, contact Airbus, 1 Rond Point Maurice Belonte, 31707 Blagnac Cedex, France. You can examine the contents of this AD docket on the Internet at https:// dms.dot.gov, or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., room PL–401, on the plaza level of the Nassif Building, Washington, DC. 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: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2005–20025; Directorate Identifier 2004–NM–208–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments submitted by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of our docket Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.) You can review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you can visit https:// dms.dot.gov. Examining the Docket You can examine the AD docket on the Internet at https://dms.dot.go, or in person at the Docket Management VerDate jul<14>2003 17:43 Jan 11, 2005 Jkt 205001 Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the DMS receives them. Discussion ´ ´ The Direction Genenrale de l’Aviation Civile (DGAC), which is the airworthiness authority for France, notified us that an unsafe condition may exist on all Airbus Model A330, A340– 200, and A340–300 series airplanes. The DGAC advises that a certain bracket, one of eight parts that attaches the flight deck instrument panel to airplane structure, has been found cracked on several airplanes. In one case, the bracket was completely broken. The cracking has been attributed to tightening of the bracket during assembly, combined with further effects of differential pressure and flight loads. Failure of the bracket cannot be detected without an inspection. If the horizontal beam also fails, failure of this bracket could lead to collapse of the left part of the flight deck instrument panel, and consequent reduced controllability of the airplane. Relevant Service Information Airbus has issued Service Bulletins A330–25–3227 and A340–25–4230, both including Appendix 01, both dated June 17, 2004. The service bulletins describe procedures for performing repetitive detailed visual inspections of a certain bracket that attaches the flight deck instrument panel to airplane structure, and replacing the bracket with a new, improved bracket if necessary. If both flanges of the bracket are cracked, the service bulletin recommends contacting Airbus for further action. The DGAC mandated the service information and issued French airworthiness directives F–2004–140 and F–2004–141, both dated August 18, 2004, to ensure the continued airworthiness of these airplanes in France. FAA’s Determination and Requirement of the Proposed AD These airplanes models are manufactured in France and are type certificated for operation in the United States under the provisions of § 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 PO 00000 Frm 00042 Fmt 4702 Sfmt 4702 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. Therefore, we are proposing this AD, which would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Among the Proposed AD, the French Airworthiness Directives, and the Service Information.’’ The proposed AD would also require sending the inspection results for any cracked bracket to Airbus. Differences Among the Proposed AD, the French Airworthiness Directives, and the Service Information If you find both flanges of a subject bracket broken, the service information and French airworthiness directives F– 2004–140 and F–2004–141 instruct you to contact Airbus. This proposed AD would require that, if you find both flanges of a bracket broken, before further flight, you replace the bracket and perform any applicable related investigative and corrective actions in accordance with a method approved by the FAA or the DGAC (or its delegated agent). These related investigative and corrective actions may include inspections for damage to surrounding structure caused by the broken bracket, and corrective actions for any damage that is found. For Model A330 series airplanes, Airbus Service Bulletins A330–25–3227 and French airworthiness directive F– 2004–140 specify an initial inspection threshold of 16,500 total flight cycles. This proposed AD would require you to perform the initial inspection prior to the accumulation of 16,500 total flight cycles or within 60 days after the effective date of the AD, whichever is later. We have included a 60-day grace period to ensure that any airplane that is close to or has passed the 16,500total-flight-cycle threshold is not grounded as of the effective date of the AD. Clarification of Inspection Terminology In this proposed AD, the ‘‘detailed visual inspection’’ specified in the Airbus service bulletins is referred to as a ‘‘detailed inspection.’’ We have included the definition for a detailed inspection in a note in the proposed AD. Interim Action We consider this proposed AD interim action. If final action is later identified, we may consider further rulemaking then. E:\FR\FM\12JAP1.SGM 12JAP1 Federal Register / Vol. 70, No. 8 / Wednesday, January 12, 2005 / Proposed Rules Costs of Compliance This proposed AD would affect about 19 Model A330 series airplanes of U.S. registry. The proposed inspection would 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 proposed AD for U.S. operators is $1,235, or $65 per airplane, per inspection cycle. There are currently no affected Model A340–200 and –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. this proposed AD. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Authority for This Rulemaking The FAA’s authority to issue rules regarding aviation safety is found in Title 49 of the United States Code. 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. This rulemaking is promulgated under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, the FAA is charged 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 proposed AD. Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with VerDate jul<14>2003 17:43 Jan 11, 2005 Jkt 205001 § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): Airbus: Docket No. FAA–2005–20025; Directorate Identifier 2004–NM–208–AD. Comments Due Date (a) The Federal Aviation Administration must receive comments on this AD action by February 11, 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. 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 PO 00000 Frm 00043 Fmt 4702 Sfmt 4702 2069 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 Round 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. (ii) For Model A340–200 and –300 series airplanes: Within 9,700 flight cycles. (j) If both flanges of a bracket are broken: Before further flight, replace the bracket and E:\FR\FM\12JAP1.SGM 12JAP1 2070 Federal Register / Vol. 70, No. 8 / Wednesday, January 12, 2005 / Proposed Rules 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. Issued in Renton, Washington, on December 30, 2004. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–612 Filed 1–11–05; 8:45 am] BILLING CODE 4910–13–M DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2004–19897; Directorate Identifier 2004–CE–45–AD] RIN 2120–AA64 Airworthiness Directives; Eagle Aircraft (Malaysia) Sdn. Bhd. Model Eagle 150B Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Eagle Aircraft (Malaysia) Sdn. Bhd. Model Eagle 150B airplanes. This proposed AD would require you to modify or replace the co-pilot rudder pedal assembly. This proposed AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Malaysia. We are issuing this proposed AD to prevent binding of the co-pilot rudder pedal assembly due to premature wear of the bushing, which could result in loss of co-pilot rudder and brake control. This failure could result in loss of control of the airplane. VerDate jul<14>2003 17:43 Jan 11, 2005 Jkt 205001 We must receive any comments on this proposed AD by February 11, 2005. ADDRESSES: Use one of the following to submit comments on this proposed AD: • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://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– 001. • Fax: 1–202–493–2251. • 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. To get the service information identified in this proposed AD, contact Eagle Aircraft (Malaysia) Sdn. Bhd., P.O. Box 1028, Pejabat Pos Besar, Melanka, Malaysia, 75150; telephone: 011 (606) 317–4105; facsimile: 011 (606) 317– 7213. To view the comments to this proposed AD, go to https://dms.dot.gov. This is docket number FAA–2004– 19897. FOR FURTHER INFORMATION CONTACT: Karl Schletzbaum, Aerospace Engineer, Small Airplane Directorate, ACE–112, 901 Locust, Rm 301, Kansas City, Missouri 64106; telephone: (816) 329– 4146; facsimile: (816) 329–4149. SUPPLEMENTARY INFORMATION: DATES: Comments Invited How do I comment on this proposed AD? We invite you to submit any written relevant data, views, or arguments regarding this proposal. Send your comments to an address listed under ADDRESSES. Include the docket number, ‘‘FAA–2004–19897; Directorate Identifier 2004–CE–45–AD’’ at the beginning of your comments. We will post all comments we receive, without change, to https://dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed rulemaking. Using the search function of our docket Web site, anyone can find and read the comments received into 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.). This is docket number FAA–2004–19897. You PO 00000 Frm 00044 Fmt 4702 Sfmt 4702 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 https:// dms.dot.gov. Are there any specific portions of this proposed AD I should pay attention to? We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. If you contact us through a nonwritten communication and that contact relates to a substantive part of this proposed AD, we will summarize the contact and place the summary in the docket. We will consider all comments received by the closing date and may amend this proposed AD in light of those comments and contacts. Docket Information Where can I go to view the docket information? You may view the AD docket that contains the proposal, any comments received, and any final disposition in person at the DMS Docket Offices between 9 a.m. and 5 p.m. (eastern standard time), Monday through Friday, except Federal holidays. The Docket Office (telephone 1–800– 647–5227) is located on the plaza level of the Department of Transportation NASSIF Building at the street address stated in ADDRESSES. You may also view the AD docket on the Internet at http:/ /dms.dot.gov. The comments will be available in the AD docket shortly after the DMS receives them. Discussion What events have caused this proposed AD? The Department of Civil Aviation, Malaysia (DCA), which is the airworthiness authority for Malaysia, recently notified FAA that an unsafe condition may exist on certain Eagle Aircraft Sdn. Bhd. Model Eagle 150B airplanes. The DCA reports two incidents of the co-pilot rudder pedal assembly, part number (P/N) 2720D07– 02, binding and becoming inoperable during flight. Investigation revealed that the two incidents resulted from premature wear of the bushing, P/N 2720D08–39, in the co-pilot rudder pedal assembly. Premature wear of the bushing allowed it to slide out of the housing resulting in excessive play between the co-pilot rudder pedal assembly and the shaft. That condition caused the co-pilot rudder control pushrod pivot, P/N 2720D08–31/04, to bind with the copilot pivot arms, P/N 2720D08–42. Stronger material is now used to manufacture the bushing and it has also been improved by including side stoppers. E:\FR\FM\12JAP1.SGM 12JAP1

Agencies

[Federal Register Volume 70, Number 8 (Wednesday, January 12, 2005)]
[Proposed Rules]
[Pages 2067-2070]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-612]


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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]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for all Airbus Model A330, A340-200, and A340-300 series airplanes. 
This proposed AD would 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. This 
proposed AD is prompted by reports of cracking of a certain bracket 
that attaches the flight deck instrument panel to the airplane 
structure. We are proposing 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: We must receive comments on this proposed AD by February 11, 
2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
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.
     By fax: (202) 493-2251.

[[Page 2068]]

     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.
    For service information identified in this proposed AD, contact 
Airbus, 1 Rond Point Maurice Belonte, 31707 Blagnac Cedex, France.
    You can examine the contents of this AD docket on the Internet at 
https://dms.dot.gov, or in person at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street, SW., room PL-
401, on the plaza level of the Nassif Building, Washington, DC. 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:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2005-20025; 
Directorate Identifier 2004-NM-208-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments submitted by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of our 
docket Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.) You can review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
can visit https://dms.dot.gov.

Examining the Docket

    You can examine the AD docket on the Internet at https://dms.dot.go, 
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 DMS receives them.

Discussion

    The Direction G[eacute]n[eacute]nrale de l'Aviation Civile (DGAC), 
which is the airworthiness authority for France, notified us that an 
unsafe condition may exist on all Airbus Model A330, A340-200, and 
A340-300 series airplanes. The DGAC advises that a certain bracket, one 
of eight parts that attaches the flight deck instrument panel to 
airplane structure, has been found cracked on several airplanes. In one 
case, the bracket was completely broken. The cracking has been 
attributed to tightening of the bracket during assembly, combined with 
further effects of differential pressure and flight loads. Failure of 
the bracket cannot be detected without an inspection. If the horizontal 
beam also fails, failure of this bracket could lead to collapse of the 
left part of the flight deck instrument panel, and consequent reduced 
controllability of the airplane.

Relevant Service Information

    Airbus has issued Service Bulletins A330-25-3227 and A340-25-4230, 
both including Appendix 01, both dated June 17, 2004. The service 
bulletins describe procedures for performing repetitive detailed visual 
inspections of a certain bracket that attaches the flight deck 
instrument panel to airplane structure, and replacing the bracket with 
a new, improved bracket if necessary. If both flanges of the bracket 
are cracked, the service bulletin recommends contacting Airbus for 
further action. The DGAC mandated the service information and issued 
French airworthiness directives F-2004-140 and F-2004-141, both dated 
August 18, 2004, to ensure the continued airworthiness of these 
airplanes in France.

FAA's Determination and Requirement of the Proposed AD

    These airplanes models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
Sec.  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.
    Therefore, we are proposing this AD, which would require 
accomplishing the actions specified in the service information 
described previously, except as discussed under ``Differences Among the 
Proposed AD, the French Airworthiness Directives, and the Service 
Information.'' The proposed AD would also require sending the 
inspection results for any cracked bracket to Airbus.

Differences Among the Proposed AD, the French Airworthiness Directives, 
and the Service Information

    If you find both flanges of a subject bracket broken, the service 
information and French airworthiness directives F-2004-140 and F-2004-
141 instruct you to contact Airbus. This proposed AD would require 
that, if you find both flanges of a bracket broken, before further 
flight, you replace the bracket and perform any applicable related 
investigative and corrective actions in accordance with a method 
approved by the FAA or the DGAC (or its delegated agent). These related 
investigative and corrective actions may include inspections for damage 
to surrounding structure caused by the broken bracket, and corrective 
actions for any damage that is found.
    For Model A330 series airplanes, Airbus Service Bulletins A330-25-
3227 and French airworthiness directive F-2004-140 specify an initial 
inspection threshold of 16,500 total flight cycles. This proposed AD 
would require you to perform the initial inspection prior to the 
accumulation of 16,500 total flight cycles or within 60 days after the 
effective date of the AD, whichever is later. We have included a 60-day 
grace period to ensure that any airplane that is close to or has passed 
the 16,500-total-flight-cycle threshold is not grounded as of the 
effective date of the AD.

Clarification of Inspection Terminology

    In this proposed AD, the ``detailed visual inspection'' specified 
in the Airbus service bulletins is referred to as a ``detailed 
inspection.'' We have included the definition for a detailed inspection 
in a note in the proposed AD.

Interim Action

    We consider this proposed AD interim action. If final action is 
later identified, we may consider further rulemaking then.

[[Page 2069]]

Costs of Compliance

    This proposed AD would affect about 19 Model A330 series airplanes 
of U.S. registry. The proposed inspection would 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 proposed 
AD for U.S. operators is $1,235, or $65 per airplane, per inspection 
cycle.
    There are currently no affected Model A340-200 and -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

    The FAA's authority to issue rules regarding aviation safety is 
found in Title 49 of the United States Code. 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.
    This rulemaking is promulgated under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, the FAA is charged 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 
proposed AD.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD. See the ADDRESSES section for a location 
to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13   [Amended]

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

Airbus: Docket No. FAA-2005-20025; Directorate Identifier 2004-NM-
208-AD.

Comments Due Date

    (a) The Federal Aviation Administration must receive comments on 
this AD action by February 11, 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.

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 Round 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.
    (ii) For Model A340-200 and -300 series airplanes: Within 9,700 
flight cycles.
    (j) If both flanges of a bracket are broken: Before further 
flight, replace the bracket and

[[Page 2070]]

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.

    Issued in Renton, Washington, on December 30, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-612 Filed 1-11-05; 8:45 am]
BILLING CODE 4910-13-M

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