Airworthiness Directives; Airbus Model A330-200, A330-300, A340-200, and A340-300 Series Airplanes, 65906-65909 [E7-22925]

Download as PDF 65906 Federal Register / Vol. 72, No. 226 / Monday, November 26, 2007 / Proposed Rules DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–0230; Directorate Identifier 2007–NM–043–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A330–200, A330–300, A340–200, and A340–300 Series 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 Airbus Model A330–200, A330–300, A340–200, and A340–300 series airplanes. The existing AD currently requires an accelerated schedule of repetitive testing of the elevator servo control loops, and corrective actions if necessary. This proposed AD would retain the existing requirements, reduce the applicability of the existing AD, and add terminating actions. This proposed AD results from reports of failed elevator servo controls due to broken guides. We are proposing this AD to prevent failure of the elevator servo controls during certain phases of takeoff, which could result in an unannounced loss of elevator control and consequent reduced controllability of the airplane. DATES: We must receive comments on this proposed AD by December 26, 2007. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. 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 send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2007–0230; Directorate Identifier 2007–NM–043–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On October 31, 2005, we issued AD 2005–23–10, amendment 39–14368 (70 FR 69065, November 14, 2005), for all Airbus Model A330–200, A330–300, A340–200, and A340–300 series airplanes. That AD requires an accelerated schedule of repetitive testing of the elevator servo control loops, and corrective actions if necessary. That AD resulted from reports of failed elevator servo controls due to broken guides. We issued that AD to ensure proper functioning of the elevator servo controls. Failure of the elevator servo controls during certain phases of takeoff could result in an unannounced loss of elevator control and consequent reduced controllability of the airplane. Actions Since Existing AD Was Issued The preamble to AD 2005–23–10 explains that we consider the requirements ‘‘interim action’’ and were considering further rulemaking. We now have determined that further rulemaking is indeed necessary, and this proposed AD follows from that determination. Relevant Service Information Airbus has issued Revision 02 of Airbus Service Bulletins A330–27–3138 (for Model A330–200 and –300 series airplanes) and A340–27–4137 (for Model A340–200 and –300 series airplanes); both dated May 30, 2006. These service bulletins supersede, respectively, Revision 01 of Airbus All Operator Telexes (AOT) A330–27A3138 and A340–27A4137, both dated October 3, 2005. The AOTs are referenced in AD 2005–23–10 as the appropriate source of service information for accomplishing the required testing of the elevator servo control loops, and corrective actions if necessary. The procedures specified in Revision 02 of the service bulletins are identical to those in Revision 01 of the AOTs. No additional work is necessary for airplanes on which the actions specified in Revision 01 of the applicable AOT have been done. Airbus also has issued the following service bulletins: SERVICE BULLETINS ebenthall on PROD1PC69 with PROPOSALS Airbus service bulletins— Describe procedures for— And refer to— A330–27–3136, Revision 01, dated July 19, 2006 (for Model A330–200 and –300 series airplanes); and A340–27–4135, dated January 12, 2006 (for Model A340–200 and –300 series airplanes). Modification of four elevator servo controls by installing a new plug-guide assembly. Goodrich Actuation Systems Service Bulletin SC4800–27–18, Revision 1, dated May 19, 2006, as an additional source of service information for accomplishing the modification. VerDate Aug<31>2005 15:37 Nov 23, 2007 Jkt 214001 PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 E:\FR\FM\26NOP1.SGM 26NOP1 Federal Register / Vol. 72, No. 226 / Monday, November 26, 2007 / Proposed Rules 65907 SERVICE BULLETINS—Continued Airbus service bulletins— Describe procedures for— And refer to— A330–27–3134, Revision 01, dated May 12, 2006 (for Model A330–200 and –300 series airplanes); and A340–27–4132, dated October 13, 2005 (for Model A340–200 and –300 series airplanes). Modification of four elevator servo controls by replacing the o-ring of the solenoid valves with a new o-ring. Goodrich Actuation Systems Service Bulletin SC4800–27–17, Revision 2, dated May 19, 2006, as an additional source of service information for accomplishing the modification. Accomplishing the modification specified in the service bulletins eliminates the need for the repetitive inspection requirements of AD 2005– 23–10 and is intended to adequately address the unsafe condition. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, mandated the service information and issued airworthiness directive 2007–0008, dated January 9, 2007, to ensure the continued airworthiness of these airplanes in the European Union. FAA’s Determination and Requirements of the Proposed AD These airplanes 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 2005–23–10 and would retain the requirements of the existing AD. This proposed AD also would require accomplishing the actions specified in service information described previously. Accomplishing the modification specified in the service bulletins described previously eliminates the need for the retained requirements of 2005–23–10. This proposed AD also would remove airplanes from the applicability of the existing AD. Costs of Compliance The following table provides the estimated costs for U.S. operators of the affected Model A330–200 and A330– 300 series airplanes to comply with this proposed AD. ESTIMATED COSTS Average labor rate per hour Work hour(s) Action Inspection (required by AD 2005–23–10). Modifications (new proposed actions). None ........................... 28 $80 The manufacturer states that it will supply required parts to the operators at no cost. ebenthall on PROD1PC69 with PROPOSALS 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 Jkt 214001 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 PO 00000 Frm 00019 Number of U.S.-registered airplanes $80, per inspection cycle. $2,240 ......................... $80 Authority for This Rulemaking 15:37 Nov 23, 2007 Cost per airplane 1 Currently, there are no affected Model A340–200 and A340–300 series airplanes on the U.S. Register. However, if an affected airplane is imported and placed on the U.S. Register in the future, the proposed modification would take about 10 work hours, at an average labor rate of $80 per work hour. The manufacturer states that it would supply required parts to the operators at no cost. Based on these figures, we estimate the cost of this proposed AD for Model A340–200 and A340–300 series airplanes to be $800 per airplane. VerDate Aug<31>2005 Parts Fmt 4702 Sfmt 4702 18 18 Fleet cost $1,440, per inspection cycle. $40,320. 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 E:\FR\FM\26NOP1.SGM 26NOP1 65908 Federal Register / Vol. 72, No. 226 / Monday, November 26, 2007 / Proposed Rules 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 Airbus: Docket No. FAA–2007–0230; Directorate Identifier 2007–NM–043–AD. 1. The authority citation for part 39 continues to read as follows: Comments Due Date Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 (a) The FAA must receive comments on this AD action by December 26, 2007. Affected ADs [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–14368 (70 FR 69065, November 14, 2005) and adding the following new airworthiness directive (AD): (b) This AD supersedes AD 2005–23–10. Applicability (c) This AD applies to the airplanes identified in Table 1 of this AD, certificated in any category. TABLE 1.—APPLICABILITY Airbus model— Excluding those airplanes on which any of the following— Has been installed— A330–200, A330–300, A340–200, and A340–300 series airplanes. Airbus modification 54833 ..................................................................... In production. Airbus Service Bulletin A330–27–3136, Revision 01, dated July 19, 2006. Airbus Service Bulletin A340–27–4135, dated January 12, 2006 ........ In service. Unsafe Condition (d) This AD results from reports of failed elevator servo controls due to broken guides. We are proposing this AD to prevent failure of the elevator servo controls during certain phases of takeoff, which could result in an unannounced loss of elevator control 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. Requirements of AD 2005–23–10 Service Information (f) The term ‘‘AOT,’’ as used in paragraphs (g) through (i) of this AD, means section 4.2. ‘‘Description’’ of the following service information, as applicable: (1) For Model A330–200 and –300 series airplanes: Airbus All Operators Telex A330– 27A3138, Revision 01, dated October 3, 2005; and (2) For Model A340–200 and –300 series airplanes: Airbus All Operators Telex A340– 27A4137, Revision 01, dated October 3, 2005. ebenthall on PROD1PC69 with PROPOSALS Initial and Repetitive Elevator Servo-Loop Tests (g) Within 200 flight hours after November 29, 2005 (the effective date of AD 2005–23– 10): Test the elevator servo-loops, in accordance with the AOT, except as provided by paragraph (j) of this AD. If the test of the elevator servo-loops passes, repeat the test at intervals not to exceed 140 flight hours or 8 days, whichever occurs first. Failed Tests (h) If any test of the elevator servo-loops required by paragraph (g) of this AD fails: Before further flight, troubleshoot the cause of the test failure, and do the applicable corrective actions; in accordance with the AOT, except as provided by paragraph (j) of VerDate Aug<31>2005 15:37 Nov 23, 2007 Jkt 214001 this AD. Thereafter, repeat the test at the times specified in paragraph (g) of this AD. Reporting Requirement (i) Following each test required by paragraph (g) of this AD, submit a report of the findings of only failed elevator servo-loop tests to Airbus Customer Services, Engineering and Technical Support, Attention: Mr. J. Laurent, SEE53, fax +33/ (0)5.61.93.44.25; at the applicable time specified in paragraph (i)(1) or (i)(2) of this AD. The report must include the description of the failure experienced during the test, the identified cause of the failure, and the number of flight hours and flight cycles on the airplane. 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. (1) If the test was done after November 29, 2005: Submit the report within 10 days after the test. (2) If the test was done prior to November 29, 2005: Submit the report within 10 days after November 29, 2005. New Requirements of This AD New Service Information for Testing (j) As of the effective date of this AD, do the actions required by paragraphs (g) and (h) of this AD in accordance with the Accomplishment Instructions of the following service bulletins, as applicable. (1) For Model A330–200 and –300 series airplanes: Airbus Service Bulletin A330–27– 3138, Revision 02, dated May 30, 2006; and (2) For Model A340–200 and –300 series airplanes: Airbus Service Bulletin A340–27– 4137, Revision 02, dated May 30, 2006. Terminating Actions (k) Within 17 months after the effective date of this AD, modify the four elevator servo controls in accordance with the PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 In service. Accomplishment Instructions of Airbus Service Bulletin A330–27–3136, Revision 01, dated July 19, 2006 (for Model A330–200 and –300 series airplanes); or Airbus Service Bulletin A340–27–4135, dated January 12, 2006 (for Model A340–200 and –300 series airplanes); as applicable. Note 1: Airbus Service Bulletins A330–27– 3136 and A340–27–4135 refer to Goodrich Actuation Systems Service Bulletin SC4800– 27–18, Revision 1, dated May 19, 2006, as an additional source of service information for accomplishing the modification required by paragraph (k) of this AD. (l) Modifications done before the effective date of this AD in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–27–3136, dated January 12, 2006, are acceptable for compliance with the modification required by paragraph (k) of this AD. (m) Concurrently with the modification required by paragraph (k) of this AD, modify the four elevator servo controls in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–27–3134, Revision 01, dated May 12, 2006 (for Model A330–200 and –300 series airplanes); or Airbus Service Bulletin A340–27–4132, dated October 13, 2005 (for Model A340–200 and –300 series airplanes); as applicable. Note 2: Airbus Service Bulletins A330–27– 3134 and A340–27–4132 refer to Goodrich Actuation Systems Service Bulletin SC4800– 27–17, Revision 2, dated May 19, 2006, as an additional source of service information for accomplishing the modification required by paragraph (m) of this AD. (n) Modifications done before the effective date of this AD in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–27–3134, dated October 13, 2005, are acceptable for compliance with the modification required by paragraph (m) of this AD. (o) Accomplishment of the modifications required by paragraphs (k) and (m) of this AD constitutes terminating action for the E:\FR\FM\26NOP1.SGM 26NOP1 Federal Register / Vol. 72, No. 226 / Monday, November 26, 2007 / Proposed Rules requirements of paragraphs (f) through (i) of this AD. Parts Installation (p) As of the effective date of this AD, no person may install, on any airplane, an elevator servo control, unless it has been modified in accordance with paragraphs (k) and (m) of this AD. Alternative Methods of Compliance (AMOCs) (q)(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) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Related Information (r) EASA airworthiness directive 2007– 0008, dated January 9, 2007, also addresses the subject of this AD. Issued in Renton, Washington, on November 13, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–22925 Filed 11–23–07; 8:45 am] BILLING CODE 4910–13–P inspection requirements. This proposed AD results from reports of cracking due to fatigue and stress corrosion of the support fittings of the Krueger flap actuator. We are proposing this AD to prevent cracking of the support fittings, which could result in fracturing of the actuator attach lugs, separation of the actuator from the support fitting, severing of the hydraulic lines, resultant loss of hydraulic fluids, and consequent reduced controllability of the airplane. DATES: We must receive comments on this proposed AD by January 10, 2008. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. DEPARTMENT OF TRANSPORTATION Examining the AD Docket Federal Aviation Administration AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Boeing Model 737–200 series airplanes. This proposed AD would require repetitive inspections to detect cracking of the support fittings of the Krueger flap actuators, and corrective actions if necessary. This proposed AD also would require eventual replacement of any existing aluminum support fitting on each wing with a steel fitting, and modification of the aft attachment of the actuator. Doing these actions would terminate the repetitive You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6440; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Comments Invited 14 CFR Part 39 [Docket No. FAA–2007–0228; Directorate Identifier 2007–NM–107–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 737–200 Series Airplanes ebenthall on PROD1PC69 with PROPOSALS Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). VerDate Aug<31>2005 15:37 Nov 23, 2007 Jkt 214001 We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2007–0228; Directorate Identifier PO 00000 Frm 00021 Fmt 4702 Sfmt 4702 65909 2007–NM–107–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We have received reports of cracks in the support fitting of the Krueger flap actuator mounted on the front spar of eight affected airplanes. On one airplane, the lugs on the No. 1 Krueger flap actuator support fitting severed completely, the actuator separated from the front spar, and the hydraulic lines were severed. On another airplane, both actuator attach lugs of a No. 1 flap support fitting were also completely severed. The cracking is attributed to fatigue and stress corrosion, and it is suspected that high clamp-up stresses may be contributing to cracks in the actuator attach lugs. Cracking of the support fittings, if not corrected, could result in fracturing of the actuator attach lugs, separation of the actuator from the support fitting, severing of the hydraulic lines, resultant loss of hydraulic fluids, and consequent reduced controllability of the airplane. Other Relevant Rulemaking On July 31, 2000, we issued AD 2000– 15–18, amendment 39–11851 (65 FR 48371, August 8, 2000). That AD applies to certain Boeing Model 737–100 and –200 series airplanes, line numbers 001 through 813 inclusive. That AD requires inspections to detect cracking of the support fittings of the Krueger flap actuator; and, if necessary, replacement of existing fittings with new steel fittings and modification of the aft attachment of the actuator. That AD also requires eventual replacement of any existing aluminum Krueger flap actuator support fitting on each wing with a steel fitting, which terminates the repetitive inspection requirements. That AD resulted from reports of cracking due to fatigue and stress corrosion of the support fittings of the Krueger flap actuator. The actions in that AD are intended to prevent such cracking, which could result in fracturing of the actuator attach lugs, separation of the actuator from the support fitting, severing of the hydraulic lines, and E:\FR\FM\26NOP1.SGM 26NOP1

Agencies

[Federal Register Volume 72, Number 226 (Monday, November 26, 2007)]
[Proposed Rules]
[Pages 65906-65909]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-22925]



[[Page 65906]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0230; Directorate Identifier 2007-NM-043-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330-200, A330-300, A340-
200, and A340-300 Series 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 all Airbus Model A330-200, A330-300, 
A340-200, and A340-300 series airplanes. The existing AD currently 
requires an accelerated schedule of repetitive testing of the elevator 
servo control loops, and corrective actions if necessary. This proposed 
AD would retain the existing requirements, reduce the applicability of 
the existing AD, and add terminating actions. This proposed AD results 
from reports of failed elevator servo controls due to broken guides. We 
are proposing this AD to prevent failure of the elevator servo controls 
during certain phases of takeoff, which could result in an unannounced 
loss of elevator control and consequent reduced controllability of the 
airplane.

DATES: We must receive comments on this proposed AD by December 26, 
2007.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Airbus, 1 
Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (telephone 800-647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

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 send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2007-0230; 
Directorate Identifier 2007-NM-043-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On October 31, 2005, we issued AD 2005-23-10, amendment 39-14368 
(70 FR 69065, November 14, 2005), for all Airbus Model A330-200, A330-
300, A340-200, and A340-300 series airplanes. That AD requires an 
accelerated schedule of repetitive testing of the elevator servo 
control loops, and corrective actions if necessary. That AD resulted 
from reports of failed elevator servo controls due to broken guides. We 
issued that AD to ensure proper functioning of the elevator servo 
controls. Failure of the elevator servo controls during certain phases 
of takeoff could result in an unannounced loss of elevator control and 
consequent reduced controllability of the airplane.

Actions Since Existing AD Was Issued

    The preamble to AD 2005-23-10 explains that we consider the 
requirements ``interim action'' and were considering further 
rulemaking. We now have determined that further rulemaking is indeed 
necessary, and this proposed AD follows from that determination.

Relevant Service Information

    Airbus has issued Revision 02 of Airbus Service Bulletins A330-27-
3138 (for Model A330-200 and -300 series airplanes) and A340-27-4137 
(for Model A340-200 and -300 series airplanes); both dated May 30, 
2006. These service bulletins supersede, respectively, Revision 01 of 
Airbus All Operator Telexes (AOT) A330-27A3138 and A340-27A4137, both 
dated October 3, 2005. The AOTs are referenced in AD 2005-23-10 as the 
appropriate source of service information for accomplishing the 
required testing of the elevator servo control loops, and corrective 
actions if necessary. The procedures specified in Revision 02 of the 
service bulletins are identical to those in Revision 01 of the AOTs. No 
additional work is necessary for airplanes on which the actions 
specified in Revision 01 of the applicable AOT have been done.
    Airbus also has issued the following service bulletins:

                            Service Bulletins
------------------------------------------------------------------------
                               Describe procedures
 Airbus service bulletins--           for--            And refer to--
------------------------------------------------------------------------
A330-27-3136, Revision 01,    Modification of four  Goodrich Actuation
 dated July 19, 2006 (for      elevator servo        Systems Service
 Model A330-200 and -300       controls by           Bulletin SC4800-27-
 series airplanes); and A340-  installing a new      18, Revision 1,
 27-4135, dated January 12,    plug-guide assembly.  dated May 19, 2006,
 2006 (for Model A340-200                            as an additional
 and -300 series airplanes).                         source of service
                                                     information for
                                                     accomplishing the
                                                     modification.

[[Page 65907]]

 
A330-27-3134, Revision 01,    Modification of four  Goodrich Actuation
 dated May 12, 2006 (for       elevator servo        Systems Service
 Model A330-200 and -300       controls by           Bulletin SC4800-27-
 series airplanes); and A340-  replacing the o-      17, Revision 2,
 27-4132, dated October 13,    ring of the           dated May 19, 2006,
 2005 (for Model A340-200      solenoid valves       as an additional
 and -300 series airplanes).   with a new o-ring.    source of service
                                                     information for
                                                     accomplishing the
                                                     modification.
------------------------------------------------------------------------

    Accomplishing the modification specified in the service bulletins 
eliminates the need for the repetitive inspection requirements of AD 
2005-23-10 and is intended to adequately address the unsafe condition. 
The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, mandated the 
service information and issued airworthiness directive 2007-0008, dated 
January 9, 2007, to ensure the continued airworthiness of these 
airplanes in the European Union.

FAA's Determination and Requirements of the Proposed AD

    These airplanes 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 2005-23-10 and would retain the 
requirements of the existing AD. This proposed AD also would require 
accomplishing the actions specified in service information described 
previously. Accomplishing the modification specified in the service 
bulletins described previously eliminates the need for the retained 
requirements of 2005-23-10. This proposed AD also would remove 
airplanes from the applicability of the existing AD.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
of the affected Model A330-200 and A330-300 series airplanes to comply 
with this proposed AD.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                                     Number of
                                           Work       Average                                                          U.S.-
                Action                   hour(s)     labor rate            Parts              Cost per airplane      registered         Fleet cost
                                                      per hour                                                       airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection (required by AD 2005-23-              1          $80  None....................  $80, per inspection               18  $1,440, per inspection
 10).                                                                                       cycle.                                cycle.
Modifications (new proposed actions).           28          $80  The manufacturer states   $2,240.................           18  $40,320.
                                                                  that it will supply
                                                                  required parts to the
                                                                  operators at no cost.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    Currently, there are no affected Model A340-200 and A340-300 series 
airplanes on the U.S. Register. However, if an affected airplane is 
imported and placed on the U.S. Register in the future, the proposed 
modification would take about 10 work hours, at an average labor rate 
of $80 per work hour. The manufacturer states that it would supply 
required parts to the operators at no cost. Based on these figures, we 
estimate the cost of this proposed AD for Model A340-200 and A340-300 
series airplanes to be $800 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

[[Page 65908]]

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:

    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 39-14368 (70 FR 69065, November 14, 2005) and adding 
the following new airworthiness directive (AD):

Airbus: Docket No. FAA-2007-0230; Directorate Identifier 2007-NM-
043-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by December 
26, 2007.

Affected ADs

    (b) This AD supersedes AD 2005-23-10.

Applicability

    (c) This AD applies to the airplanes identified in Table 1 of 
this AD, certificated in any category.

                         Table 1.--Applicability
------------------------------------------------------------------------
                                    Excluding those
        Airbus model--          airplanes on which any      Has been
                                  of the following--       installed--
------------------------------------------------------------------------
A330-200, A330-300, A340-200,   Airbus modification     In production.
 and A340-300 series airplanes.  54833.
                                Airbus Service          In service.
                                 Bulletin A330-27-
                                 3136, Revision 01,
                                 dated July 19, 2006.
                                Airbus Service          In service.
                                 Bulletin A340-27-
                                 4135, dated January
                                 12, 2006.
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from reports of failed elevator servo 
controls due to broken guides. We are proposing this AD to prevent 
failure of the elevator servo controls during certain phases of 
takeoff, which could result in an unannounced loss of elevator 
control 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.

Requirements of AD 2005-23-10

Service Information

    (f) The term ``AOT,'' as used in paragraphs (g) through (i) of 
this AD, means section 4.2. ``Description'' of the following service 
information, as applicable:
    (1) For Model A330-200 and -300 series airplanes: Airbus All 
Operators Telex A330-27A3138, Revision 01, dated October 3, 2005; 
and
    (2) For Model A340-200 and -300 series airplanes: Airbus All 
Operators Telex A340-27A4137, Revision 01, dated October 3, 2005.

Initial and Repetitive Elevator Servo-Loop Tests

    (g) Within 200 flight hours after November 29, 2005 (the 
effective date of AD 2005-23-10): Test the elevator servo-loops, in 
accordance with the AOT, except as provided by paragraph (j) of this 
AD. If the test of the elevator servo-loops passes, repeat the test 
at intervals not to exceed 140 flight hours or 8 days, whichever 
occurs first.

Failed Tests

    (h) If any test of the elevator servo-loops required by 
paragraph (g) of this AD fails: Before further flight, troubleshoot 
the cause of the test failure, and do the applicable corrective 
actions; in accordance with the AOT, except as provided by paragraph 
(j) of this AD. Thereafter, repeat the test at the times specified 
in paragraph (g) of this AD.

Reporting Requirement

    (i) Following each test required by paragraph (g) of this AD, 
submit a report of the findings of only failed elevator servo-loop 
tests to Airbus Customer Services, Engineering and Technical 
Support, Attention: Mr. J. Laurent, SEE53, fax +33/(0)5.61.93.44.25; 
at the applicable time specified in paragraph (i)(1) or (i)(2) of 
this AD. The report must include the description of the failure 
experienced during the test, the identified cause of the failure, 
and the number of flight hours and flight cycles on the airplane. 
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.
    (1) If the test was done after November 29, 2005: Submit the 
report within 10 days after the test.
    (2) If the test was done prior to November 29, 2005: Submit the 
report within 10 days after November 29, 2005.

New Requirements of This AD

New Service Information for Testing

    (j) As of the effective date of this AD, do the actions required 
by paragraphs (g) and (h) of this AD in accordance with the 
Accomplishment Instructions of the following service bulletins, as 
applicable.
    (1) For Model A330-200 and -300 series airplanes: Airbus Service 
Bulletin A330-27-3138, Revision 02, dated May 30, 2006; and
    (2) For Model A340-200 and -300 series airplanes: Airbus Service 
Bulletin A340-27-4137, Revision 02, dated May 30, 2006.

Terminating Actions

    (k) Within 17 months after the effective date of this AD, modify 
the four elevator servo controls in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-27-3136, 
Revision 01, dated July 19, 2006 (for Model A330-200 and -300 series 
airplanes); or Airbus Service Bulletin A340-27-4135, dated January 
12, 2006 (for Model A340-200 and -300 series airplanes); as 
applicable.

    Note 1: Airbus Service Bulletins A330-27-3136 and A340-27-4135 
refer to Goodrich Actuation Systems Service Bulletin SC4800-27-18, 
Revision 1, dated May 19, 2006, as an additional source of service 
information for accomplishing the modification required by paragraph 
(k) of this AD.

    (l) Modifications done before the effective date of this AD in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-27-3136, dated January 12, 2006, are acceptable for 
compliance with the modification required by paragraph (k) of this 
AD.
    (m) Concurrently with the modification required by paragraph (k) 
of this AD, modify the four elevator servo controls in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A330-27-3134, Revision 01, dated May 12, 2006 (for Model A330-200 
and -300 series airplanes); or Airbus Service Bulletin A340-27-4132, 
dated October 13, 2005 (for Model A340-200 and -300 series 
airplanes); as applicable.

    Note 2: Airbus Service Bulletins A330-27-3134 and A340-27-4132 
refer to Goodrich Actuation Systems Service Bulletin SC4800-27-17, 
Revision 2, dated May 19, 2006, as an additional source of service 
information for accomplishing the modification required by paragraph 
(m) of this AD.

    (n) Modifications done before the effective date of this AD in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A330-27-3134, dated October 13, 2005, are acceptable for 
compliance with the modification required by paragraph (m) of this 
AD.
    (o) Accomplishment of the modifications required by paragraphs 
(k) and (m) of this AD constitutes terminating action for the

[[Page 65909]]

requirements of paragraphs (f) through (i) of this AD.

Parts Installation

    (p) As of the effective date of this AD, no person may install, 
on any airplane, an elevator servo control, unless it has been 
modified in accordance with paragraphs (k) and (m) of this AD.

Alternative Methods of Compliance (AMOCs)

    (q)(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) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.

Related Information

    (r) EASA airworthiness directive 2007-0008, dated January 9, 
2007, also addresses the subject of this AD.

    Issued in Renton, Washington, on November 13, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-22925 Filed 11-23-07; 8:45 am]
BILLING CODE 4910-13-P