Airworthiness Directives; Airbus Model A330 Airplanes, 66472-66474 [E6-19228]

Download as PDF 66472 Proposed Rules Federal Register Vol. 71, No. 220 Wednesday, November 15, 2006 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–26324; Directorate Identifier 2006–NM–214–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A330 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). rmajette on PROD1PC67 with PROPOSALS1 AGENCY: SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain Airbus Model 330–300 series airplanes. The existing AD currently requires reinforcement of the structure of the center fuselage by installing external stiffeners (butt straps) at frame (FR) 53.3 on the fuselage skin between left-hand (LH) and right-hand (RH) stringer (STR) 13, and related investigative and corrective actions. This proposed AD would require additional reinforcement of the structure of the center fuselage by installing external stiffeners (butt straps) at frame FR53.3 on the fuselage skin between LH and RH STR13, and related investigative and other specified actions. This proposed AD also adds airplanes to the applicability. This proposed AD results from cracking found at the circumferential joint of FR53.3. We are proposing this AD to prevent fatigue cracking of the fuselage, which could result in reduced structural integrity of the fuselage. DATES: We must receive comments on this proposed AD by December 15, 2006. 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. VerDate Aug<31>2005 14:55 Nov 14, 2006 Jkt 211001 • 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. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; 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 in the ADDRESSES section. Include the docket number ‘‘Docket No. FAA–2006–26324; Directorate Identifier 2006–NM–214– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to 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 that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https:// dms.dot.gov. PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 Examining the Docket You may 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 DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion On September 20, 2005, we issued AD 2005–20–07, amendment 39–14300 (70 FR 57732, October 4, 2005), for certain Airbus Model A330–300 series airplanes. That AD requires reinforcing the structure of the center fuselage by installing external stiffeners (butt straps) at frame (FR) 53.3 on the fuselage skin between left-hand (LH) and right-hand (RH) stringer (STR) 13, and doing related investigative and corrective actions. That AD resulted from a report that, during fatigue tests of the fuselage, cracks initiated and grew at the circumferential joint of FR53.3. We issued that AD to prevent fatigue cracking of the fuselage, which could result in reduced structural integrity of the fuselage. Actions Since Existing AD Was Issued Since we issued AD 2005–20–07, the European Aviation Safety Agency (EASA), which is the airworthiness authority for the European Union, notified us that further modification of Airbus Model A330–300 series airplanes is necessary to correct the unsafe condition identified in AD 2005–20–07. The EASA has also notified us that the same unsafe condition may also exist on Model A330–200 series airplanes. Relevant Service Information Airbus has issued Service Bulletin A330–53–3143, Revision 01, including Appendix 01, dated June 29, 2006. The service bulletin describes procedures for reinforcing the structure of the center fuselage by installing external doublers (butt straps) at FR53.3 on the fuselage skin between LH and RH STR13, and doing related investigative and other specified actions. The related investigative actions are rototests of certain fastener holes after fastener E:\FR\FM\15NOP1.SGM 15NOP1 Federal Register / Vol. 71, No. 220 / Wednesday, November 15, 2006 / Proposed Rules removal. If any crack is found during a rototest, the service bulletin specifies contacting Airbus for repair instructions. If no crack is found, the service bulletin specifies doing other specified actions, which include counter-drilling the fastener holes in the butt straps, cold-expanding the matching holes in the fuselage, reaming and deburring the holes, shimming, and applying sealant around the butt straps. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The EASA mandated the service information and issued airworthiness directive 2006–0266, dated August 30, 2006, to ensure the continued airworthiness of these airplanes in the European Union. rmajette on PROD1PC67 with PROPOSALS1 FAA’s Determination and Requirements of the Proposed AD These airplane models are manufactured in France and are 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. As described in FAA Order 8100.14A, ‘‘Interim Procedures for Working with the European Community on Airworthiness Certification and Continued Airworthiness,’’ dated August 12, 2005, the EASA has kept the FAA informed of the situation described above. We have examined the EASA’s findings, evaluated all pertinent information, and determined that AD action is necessary for airplanes of this type design that are certificated for operation in the United States. This proposed AD would supersede AD 2005–20–07 and would retain the requirements of the existing AD. This proposed AD would also add airplanes to the applicability. This proposed AD would also require accomplishing the actions specified in the service bulletin described previously, except as discussed under ‘‘Difference Between the Proposed AD and EASA Airworthiness Directive.’’ Difference Between the Proposed AD and EASA Airworthiness Directive The applicability of EASA airworthiness directive 2006–0266 excludes airplanes on which Airbus Service Bulletin A330–53–3127, Revision 01, dated November 21, 2003; or Airbus Service Bulletin A330–53– 3143, dated December 24, 2004; has been accomplished in service. However, we have not excluded those airplanes in the applicability of this proposed AD; rather, this proposed AD includes requirements to accomplish the actions VerDate Aug<31>2005 14:55 Nov 14, 2006 Jkt 211001 specified in those service bulletins, as applicable. These requirements would ensure that the actions specified in the service bulletins and required by this proposed AD are accomplished on all affected airplanes. Operators must continue to operate the airplane in the configuration required by this proposed AD unless an alternative method of compliance is approved. Explanation of Change Made to Requirements of Existing AD Paragraph (g) of the existing AD specifies making repairs using a method approved by either the FAA or the Direction Generale de l’Aviation Civile (DGAC) (or its delegated agent). The EASA has assumed responsibility for the airplane models that would be subject to this AD. Therefore, we have revised paragraph (g) of this proposed AD to specify making repairs using a method approved by the FAA, the DGAC (or its delegated agent), or the EASA (or its delegated agent). Clarification of Airbus Modification Number The applicability of AD 2005–20–07 exempts airplanes on which Airbus Modification 41652 had been incorporated in production. Airbus Modification 41652 is the abbreviated modification number of Airbus Modification 41652S11819. This proposed AD refers to Airbus Modification 41652S11819, as identified in EASA airworthiness directive 2006– 0266. Costs of Compliance Currently, the action required by AD 2005–20–07 and retained in this proposed AD affects 12 airplanes of U.S. registry. However, we have been advised that all affected U.S. operators have already accomplished that action. If an affected airplane is imported and placed on the U.S. Register in the future, the action required by AD 2005–20–07 takes about 315 work hours per airplane, at an average labor rate of $80 per work hour. Required parts cost about $8,920. Based on these figures, the estimated cost of the currently required action is $34,120 per airplane. The new proposed action would affect about 27 airplanes of U.S. registry. The new proposed action would take about 316 work hours per airplane, at an average labor rate of $80 per work hour. Required parts would cost about $9,160 per airplane. Based on these figures, the estimated cost of the new action specified in this proposed AD for U.S. operators is $929,880, or $34,440 per airplane. PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 66473 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 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 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, 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: E:\FR\FM\15NOP1.SGM 15NOP1 66474 Federal Register / Vol. 71, No. 220 / Wednesday, November 15, 2006 / Proposed Rules Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–14300 (70 FR 57732, October 4, 2005) and adding the following new airworthiness directive (AD): required by paragraph (f) of this AD, before further flight, repair the crack according to a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; the DGAC (or its delegated agent); or the EASA (or its delegated agent). DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 New Requirements of This AD [Docket No. FAA–2006–26323; Directorate Identifier 2006–NM–150–AD] Airbus: Docket No. FAA–2006–26324; Directorate Identifier 2006–NM–214–AD. Installation for Model A330–200 and –300 Series Airplanes RIN 2120–AA64 Comments Due Date (a) The FAA must receive comments on this AD action by December 15, 2006. (h) For all airplanes: At the later of the times in paragraphs (h)(1) and (h)(2) of this AD, install the butt straps at FR53.3 on the fuselage skin between LH and RH STR13; and do all related investigative and other specified actions before further flight, as applicable. Do all actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–53–3143, Revision 01, including Appendix 01, dated June 29, 2006; except if any crack is detected during a related investigative action (rototest), before further flight, repair the crack using a method approved by the Manager, International Branch, ANM–116; or the EASA (or its delegated agent). (1) Before the accumulation of 17,600 total flight cycles or 61,600 total flight hours, whichever occurs earlier. (2) Within 6 months after the effective date of this AD. Affected ADs (b) This AD supersedes AD 2005–20–07. Applicability (c) This AD applies to Airbus Model A330– 201, –202, –203, –223, –243, –301, –321, –322, –323, –341, –342, and –343 airplanes, certificated in any category; except those on which Airbus Modification 49202 has been incorporated in production. Unsafe Condition (d) This AD results from cracking found at the circumferential joint of frame (FR) 53.3. We are issuing this AD to prevent fatigue cracking of the fuselage, which could result in reduced structural integrity of the fuselage. 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. Requirements of AD 2005–20–07 rmajette on PROD1PC67 with PROPOSALS1 Installation for Model A330–300 Series Airplanes (f) For Airbus Model A330–301, –321, –322, –323, –341, –342, and –343 airplanes, except those on which Airbus Modification 41652S11819 has been incorporated in production: At the later of the times in paragraphs (f)(1) and (f)(2) of this AD, install the butt straps at FR53.3 on the fuselage skin between left-hand (LH) and right-hand (RH) stringer (STR) 13, and do all related investigative and corrective actions before further flight. Except as provided by paragraph (g) of this AD, do all actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330– 53–3127, Revision 01, dated November 21, 2003. (1) Before the accumulation of 14,700 total flight cycles or 51,400 total flight hours, whichever occurs earlier. (2) Within 6 months after October 19, 2005 (the effective date of AD 2005–20–07). ´ ´ Contact the FAA/Direction Generale de l’Aviation Civile (DGAC)/European Aviation Safety Agency (EASA) for Certain Repair Instructions (g) For Airbus Model A330–301, –321, –322, –323, –341, –342, and –343 airplanes, except those on which Airbus Modification 41652S11819 has been incorporated in production: If any crack is detected during the related investigative actions (rototest) VerDate Aug<31>2005 14:55 Nov 14, 2006 Jkt 211001 Credit for Actions Done in Accordance With Previous Service Bulletin (i) Actions done before the effective date of this AD in accordance with Airbus Service Bulletin A330–53–3143, including Appendix 01, dated December 24, 2004, are acceptable for compliance with the corresponding requirements of paragraph (h) of this AD. Alternative Methods of Compliance (AMOCs) (j)(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. Related Information (k) EASA airworthiness directive 2006– 0266, dated August 30, 2006, also addresses the subject of this AD. Issued in Renton, Washington, on November 7, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–19228 Filed 11–14–06; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 Airworthiness Directives; Boeing Model 737 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) that applies to all Boeing Model 737 airplanes. The existing AD currently requires installation of a new rudder control system and changes to the adjacent systems to accommodate that new rudder control system. For certain airplanes, this proposed AD would add, among other actions, repetitive tests of the force fight monitor of the main rudder power control unit (PCU), repetitive tests of the standby hydraulic actuation system, and corrective action; as applicable. For those airplanes, this proposed AD also would add, among other actions, replacement of both input control rods of the main rudder PCU and the input control rod of the standby rudder PCU with new input control rods, as applicable, which would end the repetitive tests. For certain other airplanes, this proposed AD would add installation of an enhanced rudder control system in accordance with new service information. This proposed AD results from a report of a fractured rod end on an input control rod of the main rudder PCU. We are proposing this AD to prevent failure of one of the two input control rods of main rudder PCU, which, under certain conditions, could result in reduced controllability of the airplane; and to prevent failure of any combination of two input control rods of the main rudder PCU and/or standby rudder PCU, which could result in loss of control of the airplane. We are also proposing this AD to prevent an uncommanded rudder hardover event and consequent loss of control of the airplane due to inherent failure modes, including single-jam modes, and certain latent failures or jams combined with a second failure or jam. DATES: We must receive comments on this proposed AD by January 2, 2007. E:\FR\FM\15NOP1.SGM 15NOP1

Agencies

[Federal Register Volume 71, Number 220 (Wednesday, November 15, 2006)]
[Proposed Rules]
[Pages 66472-66474]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-19228]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 71, No. 220 / Wednesday, November 15, 2006 / 
Proposed Rules

[[Page 66472]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-26324; Directorate Identifier 2006-NM-214-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330 Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to certain Airbus Model 330-300 series 
airplanes. The existing AD currently requires reinforcement of the 
structure of the center fuselage by installing external stiffeners 
(butt straps) at frame (FR) 53.3 on the fuselage skin between left-hand 
(LH) and right-hand (RH) stringer (STR) 13, and related investigative 
and corrective actions. This proposed AD would require additional 
reinforcement of the structure of the center fuselage by installing 
external stiffeners (butt straps) at frame FR53.3 on the fuselage skin 
between LH and RH STR13, and related investigative and other specified 
actions. This proposed AD also adds airplanes to the applicability. 
This proposed AD results from cracking found at the circumferential 
joint of FR53.3. We are proposing this AD to prevent fatigue cracking 
of the fuselage, which could result in reduced structural integrity of 
the fuselage.

DATES: We must receive comments on this proposed AD by December 15, 
2006.

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.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; 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 in the ADDRESSES section. Include the docket number ``Docket No. 
FAA-2006-26324; Directorate Identifier 2006-NM-214-AD'' at the 
beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of the 
proposed AD. We will consider all comments received by the closing date 
and may amend the proposed AD in light of those comments.
    We will post all comments we receive, without change, to 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 
that Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit https://dms.dot.gov.

Examining the Docket

    You may 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 DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

Discussion

    On September 20, 2005, we issued AD 2005-20-07, amendment 39-14300 
(70 FR 57732, October 4, 2005), for certain Airbus Model A330-300 
series airplanes. That AD requires reinforcing the structure of the 
center fuselage by installing external stiffeners (butt straps) at 
frame (FR) 53.3 on the fuselage skin between left-hand (LH) and right-
hand (RH) stringer (STR) 13, and doing related investigative and 
corrective actions. That AD resulted from a report that, during fatigue 
tests of the fuselage, cracks initiated and grew at the circumferential 
joint of FR53.3. We issued that AD to prevent fatigue cracking of the 
fuselage, which could result in reduced structural integrity of the 
fuselage.

Actions Since Existing AD Was Issued

    Since we issued AD 2005-20-07, the European Aviation Safety Agency 
(EASA), which is the airworthiness authority for the European Union, 
notified us that further modification of Airbus Model A330-300 series 
airplanes is necessary to correct the unsafe condition identified in AD 
2005-20-07. The EASA has also notified us that the same unsafe 
condition may also exist on Model A330-200 series airplanes.

Relevant Service Information

    Airbus has issued Service Bulletin A330-53-3143, Revision 01, 
including Appendix 01, dated June 29, 2006. The service bulletin 
describes procedures for reinforcing the structure of the center 
fuselage by installing external doublers (butt straps) at FR53.3 on the 
fuselage skin between LH and RH STR13, and doing related investigative 
and other specified actions. The related investigative actions are 
rototests of certain fastener holes after fastener

[[Page 66473]]

removal. If any crack is found during a rototest, the service bulletin 
specifies contacting Airbus for repair instructions. If no crack is 
found, the service bulletin specifies doing other specified actions, 
which include counter-drilling the fastener holes in the butt straps, 
cold-expanding the matching holes in the fuselage, reaming and 
deburring the holes, shimming, and applying sealant around the butt 
straps. Accomplishing the actions specified in the service information 
is intended to adequately address the unsafe condition. The EASA 
mandated the service information and issued airworthiness directive 
2006-0266, dated August 30, 2006, to ensure the continued airworthiness 
of these airplanes in the European Union.

FAA's Determination and Requirements of the Proposed AD

    These airplane models are manufactured in France and are 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. As described in FAA 
Order 8100.14A, ``Interim Procedures for Working with the European 
Community on Airworthiness Certification and Continued Airworthiness,'' 
dated August 12, 2005, the EASA has kept the FAA informed of the 
situation described above. We have examined the EASA's findings, 
evaluated all pertinent information, and determined that AD action is 
necessary for airplanes of this type design that are certificated for 
operation in the United States.
    This proposed AD would supersede AD 2005-20-07 and would retain the 
requirements of the existing AD. This proposed AD would also add 
airplanes to the applicability. This proposed AD would also require 
accomplishing the actions specified in the service bulletin described 
previously, except as discussed under ``Difference Between the Proposed 
AD and EASA Airworthiness Directive.''

Difference Between the Proposed AD and EASA Airworthiness Directive

    The applicability of EASA airworthiness directive 2006-0266 
excludes airplanes on which Airbus Service Bulletin A330-53-3127, 
Revision 01, dated November 21, 2003; or Airbus Service Bulletin A330-
53-3143, dated December 24, 2004; has been accomplished in service. 
However, we have not excluded those airplanes in the applicability of 
this proposed AD; rather, this proposed AD includes requirements to 
accomplish the actions specified in those service bulletins, as 
applicable. These requirements would ensure that the actions specified 
in the service bulletins and required by this proposed AD are 
accomplished on all affected airplanes. Operators must continue to 
operate the airplane in the configuration required by this proposed AD 
unless an alternative method of compliance is approved.

Explanation of Change Made to Requirements of Existing AD

    Paragraph (g) of the existing AD specifies making repairs using a 
method approved by either the FAA or the Direction Generale de 
l'Aviation Civile (DGAC) (or its delegated agent). The EASA has assumed 
responsibility for the airplane models that would be subject to this 
AD. Therefore, we have revised paragraph (g) of this proposed AD to 
specify making repairs using a method approved by the FAA, the DGAC (or 
its delegated agent), or the EASA (or its delegated agent).

Clarification of Airbus Modification Number

    The applicability of AD 2005-20-07 exempts airplanes on which 
Airbus Modification 41652 had been incorporated in production. Airbus 
Modification 41652 is the abbreviated modification number of Airbus 
Modification 41652S11819. This proposed AD refers to Airbus 
Modification 41652S11819, as identified in EASA airworthiness directive 
2006-0266.

Costs of Compliance

    Currently, the action required by AD 2005-20-07 and retained in 
this proposed AD affects 12 airplanes of U.S. registry. However, we 
have been advised that all affected U.S. operators have already 
accomplished that action. If an affected airplane is imported and 
placed on the U.S. Register in the future, the action required by AD 
2005-20-07 takes about 315 work hours per airplane, at an average labor 
rate of $80 per work hour. Required parts cost about $8,920. Based on 
these figures, the estimated cost of the currently required action is 
$34,120 per airplane.
    The new proposed action would affect about 27 airplanes of U.S. 
registry. The new proposed action would take about 316 work hours per 
airplane, at an average labor rate of $80 per work hour. Required parts 
would cost about $9,160 per airplane. Based on these figures, the 
estimated cost of the new action specified in this proposed AD for U.S. 
operators is $929,880, or $34,440 per airplane.

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 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 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, 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:


[[Page 66474]]


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


Sec.  39.13  [Amended]

    2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-14300 (70 FR 57732, October 4, 2005) and adding 
the following new airworthiness directive (AD):

Airbus: Docket No. FAA-2006-26324; Directorate Identifier 2006-NM-
214-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by December 
15, 2006.

Affected ADs

    (b) This AD supersedes AD 2005-20-07.

Applicability

    (c) This AD applies to Airbus Model A330-201, -202, -203, -223, 
-243, -301, -321, -322, -323, -341, -342, and -343 airplanes, 
certificated in any category; except those on which Airbus 
Modification 49202 has been incorporated in production.

Unsafe Condition

    (d) This AD results from cracking found at the circumferential 
joint of frame (FR) 53.3. We are issuing this AD to prevent fatigue 
cracking of the fuselage, which could result in reduced structural 
integrity of the fuselage.

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.

Requirements of AD 2005-20-07

Installation for Model A330-300 Series Airplanes

    (f) For Airbus Model A330-301, -321, -322, -323, -341, -342, and 
-343 airplanes, except those on which Airbus Modification 
41652S11819 has been incorporated in production: At the later of the 
times in paragraphs (f)(1) and (f)(2) of this AD, install the butt 
straps at FR53.3 on the fuselage skin between left-hand (LH) and 
right-hand (RH) stringer (STR) 13, and do all related investigative 
and corrective actions before further flight. Except as provided by 
paragraph (g) of this AD, do all actions in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-53-3127, 
Revision 01, dated November 21, 2003.
    (1) Before the accumulation of 14,700 total flight cycles or 
51,400 total flight hours, whichever occurs earlier.
    (2) Within 6 months after October 19, 2005 (the effective date 
of AD 2005-20-07).

Contact the FAA/Direction G[eacute]n[eacute]rale de l'Aviation 
Civile (DGAC)/European Aviation Safety Agency (EASA) for Certain 
Repair Instructions

    (g) For Airbus Model A330-301, -321, -322, -323, -341, -342, and 
-343 airplanes, except those on which Airbus Modification 
41652S11819 has been incorporated in production: If any crack is 
detected during the related investigative actions (rototest) 
required by paragraph (f) of this AD, before further flight, repair 
the crack according to a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
the DGAC (or its delegated agent); or the EASA (or its delegated 
agent).

New Requirements of This AD

Installation for Model A330-200 and -300 Series Airplanes

    (h) For all airplanes: At the later of the times in paragraphs 
(h)(1) and (h)(2) of this AD, install the butt straps at FR53.3 on 
the fuselage skin between LH and RH STR13; and do all related 
investigative and other specified actions before further flight, as 
applicable. Do all actions in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-53-3143, Revision 01, 
including Appendix 01, dated June 29, 2006; except if any crack is 
detected during a related investigative action (rototest), before 
further flight, repair the crack using a method approved by the 
Manager, International Branch, ANM-116; or the EASA (or its 
delegated agent).
    (1) Before the accumulation of 17,600 total flight cycles or 
61,600 total flight hours, whichever occurs earlier.
    (2) Within 6 months after the effective date of this AD.

Credit for Actions Done in Accordance With Previous Service 
Bulletin

    (i) Actions done before the effective date of this AD in 
accordance with Airbus Service Bulletin A330-53-3143, including 
Appendix 01, dated December 24, 2004, are acceptable for compliance 
with the corresponding requirements of paragraph (h) of this AD.

Alternative Methods of Compliance (AMOCs)

    (j)(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.

Related Information

    (k) EASA airworthiness directive 2006-0266, dated August 30, 
2006, also addresses the subject of this AD.

    Issued in Renton, Washington, on November 7, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-19228 Filed 11-14-06; 8:45 am]
BILLING CODE 4910-13-P

This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.