Airworthiness Directives; Airbus Model A330-200 and -300, and A340-200 and -300 Series Airplanes, 40387-40389 [06-6180]

Download as PDF Federal Register / Vol. 71, No. 136 / Monday, July 17, 2006 / Rules and Regulations 40387 Compliance (e) To address this problem, you must do the following: Actions Compliance Procedures (1) Inspect, visually and using fluorescent dye penetrant, the support structures for the inboard and center aileron hinge fittings on both wings for cracks. (2) If you do not find cracks during the inspection required in paragraph (e)(1) of this AD, reinforce the support structures for the inboard and center aileron hinge fittings on both wings that are crack free. (3) If you find cracks during the inspection required in paragraph (e)(1) of this AD, replace and reinforce the cracked support structure. Within the next 150 hours time-in-service or 12 months after August 21, 2006 (the effective date of this AD), whichever occurs first. Before further flight after the inspection required in paragraph (e)(1) of this AD. After doing the reinforcement, no further action is required. Follow Twin Commander Aircraft LLC Alert Service Bulletin 236A and Alert Service Bulletin 238, both dated December 21, 2004, as applicable. Follow Twin Commander Aircraft LLC Alert Service Bulletin 236A and Alert Service Bulletin 238, both dated December 21, 2004, as applicable. Before further flight after the inspection required in paragraph (e)(1) of this AD. After doing the replacement and reinforcement, no further action is required. Follow Twin Commander Aircraft LLC Alert Service Bulletin 236A and Alert Service Bulletin 238, both dated December 21, 2004, as applicable. Alternative Methods of Compliance (AMOCs) DEPARTMENT OF TRANSPORTATION (f) The Manager, Seattle Aircraft Certification Office (ACO), FAA, ATTN: Vince Massey, Aerospace Engineer, Seattle, ACO, 1601 Lind Avenue SW., Renton, WA 98057; telephone: (425) 917–6475; facsimile: (425) 917–6590, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24522; Directorate Identifier 2006–NM–002–AD; Amendment 39–14680; AD 2006–14–09] RIN 2120–AA64 Material Incorporated by Reference rmajette on PROD1PC67 with RULES (g) You must do the actions required by this AD following Twin Commander Aircraft LLC Alert Service Bulletin 236A and Twin Commander Aircraft LLC Alert Service Bulletin 238, both dated December 21, 2004. The Director of the Federal Register approved the incorporation by reference of these service bulletins in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact Twin Commander Aircraft LLC, 19010 59th Drive NE., Arlington, WA 98223, telephone: (360) 435–9797; facsimile: (360) 435–1112. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html or call (202) 741–6030. To view the AD docket, go to the Docket Management Facility; US Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590–001 or on the Internet at http:// dms.dot.gov. The docket number is FAA– 2006–23785; Directorate Identifier 2006–CE– 10–AD. Issued in Kansas City, Missouri, on July 7, 2006. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–6225 Filed 7–14–06; 8:45 am] BILLING CODE 4910–13–M VerDate Aug<31>2005 15:22 Jul 14, 2006 Jkt 208001 Airworthiness Directives; Airbus Model A330–200 and –300, and A340–200 and –300 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330–200 and –300, and A340–200 and –300 series airplanes. This AD requires modifying certain rotary actuator assemblies for the leading edge slat. This AD results from a leak found at the seal of the torque limiter output shaft of the Type A rotary actuator of leading edge slat No. 1. We are issuing this AD to prevent a decrease in the torque limiter function, which could result in degradation and damage to the attachment bolts of the leading edge slat, loss of the slat, and consequent reduced control of the airplane. This AD becomes effective August 21, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of August 21, 2006. ADDRESSES: You may examine the AD docket on the Internet at http:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, DATES: PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 SW., Nassif Building, Room PL–401, Washington, DC. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for the service information identified in this AD. Tim Backman, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2797; fax (425) 227–1149. FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain Airbus Model A330– 200 and –300, and A340–200 and –300 series airplanes. That NPRM was published in the Federal Register on April 21, 2006 (71 FR 20599). That NPRM proposed to require modifying certain rotary actuator assemblies for the leading edge slat. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the single comment received. E:\FR\FM\17JYR1.SGM 17JYR1 40388 Federal Register / Vol. 71, No. 136 / Monday, July 17, 2006 / Rules and Regulations Request To Revise the Applicability Airbus requests that Model A330–302 and –303 airplanes be included in the applicability of paragraph (c) of the NPRM. Airbus states that those airplanes are in the process of being type certificated in the U.S. We agree. We have determined that Model A330–302 and –303 airplanes are subject to the identified unsafe condition of this AD. Therefore, we have revised the applicability of paragraph (c) of this AD to include those airplanes to ensure that the identified unsafe condition is addressed if any of those affected airplanes are imported and placed on the U.S. Register in the future. Conclusion We have carefully reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD with the change described previously. This change will neither increase the economic burden on any operator nor increase the scope of the AD. rmajette on PROD1PC67 with RULES Costs of Compliance This AD affects about 9 airplanes of U.S. registry. The modification (including operational test) takes about 4 work hours per airplane, at an average labor rate of $80 per work hour. Required parts are free of charge. Based on these figures, the estimated cost of the AD for U.S. operators is $2,880, or $320 per airplane. Currently, there are no affected Model A330–302 and –303 airplanes on the U.S. Register. However, if an affected airplane is imported and placed on the U.S. Register in the future, it would be subject to the same per-airplane cost specified above. 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 VerDate Aug<31>2005 15:22 Jul 14, 2006 Jkt 208001 that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): I 2006–14–09 Airbus: Amendment 39–14680. Docket No. FAA–2006–24522; Directorate Identifier 2006–NM–002–AD. Effective Date (a) This AD becomes effective August 21, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A330– 201, 202, –203, –223, and –243; A330–301, –302, –303, –321, –322, –323, –341, –342, PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 and –343; A340–211, –212, and –213; and A340–311, –312, and –313 airplanes, certificated in any category; except airplanes on which Airbus Modification 50138 was done during production. Unsafe Condition (d) This AD results from a leak found at the seal of the torque limiter output shaft of the Type A rotary actuator of leading edge slat No. 1. We are issuing this AD to prevent a decrease in the torque limiter function, which could result in degradation and damage to the attachment bolts of the leading edge slat, loss of the slat, and consequent reduced control 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. Modification (f) Within 38 months after the effective date of this AD: Modify any Type A rotary actuator assembly for the leading edge slat having part number (P/N) 954A0000–01 or 954A0000–02, or P/N 954B0000–01, as applicable, by doing all the applicable actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–27–3100, Revision 01, dated May 23, 2005; or A340–27–4106, Revision 01, dated May 23, 2005; as applicable. (g) Modification of any Type A rotary actuator assembly for the leading edge slat having P/N 954B0000–01, in accordance with Airbus Service Bulletin A330–27–3105 or A340–27–4110, both Revision 02, both dated October 10, 2005; as applicable; is acceptable for compliance with the corresponding modification specified in paragraph (f) of this AD. Note 1: Airbus Service Bulletins A330–27– 3100 and A340–27–4106 refer to Goodrich Actuation Systems Service Bulletin 954–27– M954–07, Revision 2, dated August 9, 2004; and Airbus Service Bulletins A330–27–3105 and A340–27–4110 refer to Goodrich Actuation Systems Service Bulletin 954–27– M954–06, Revision 2, dated May 20, 2004; as additional sources of service information for modifying the rotary actuator assembly for the leading edge slat. Parts Installation (h) As of the effective date of this AD, no Type A rotary actuator assembly for the leading edge slat having P/N 954A0000–01, –02, or 954B0000–01 may be installed unless the part has been modified in accordance with the actions required by paragraph (f) or (g) of this AD, as applicable. Actions Accomplished Previously (i) Modifications done before the effective date of this AD in accordance with Airbus Service Bulletins A330–27–3100, dated October 30, 2002; A330–27–3105, dated October 30, 2002, or Revision 01, dated March 27, 2003; A340–27–4106, dated October 30, 2002; or A340–27–4110, dated October 30, 2002, or Revision 01, dated March 27, 2003; as applicable; are acceptable E:\FR\FM\17JYR1.SGM 17JYR1 Federal Register / Vol. 71, No. 136 / Monday, July 17, 2006 / Rules and Regulations for compliance with the corresponding requirements of paragraphs (f) and (g) of this AD, as applicable. Alternative Methods of Compliance (AMOCs) Related Information (k) French airworthiness directives F– 2005–067 and F–2005–068, both dated April 27, 2005, also address the subject of this AD. Material Incorporated by Reference (l) You must use the applicable Airbus service bulletin identified in Table 1 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Room PL–401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to http:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. TABLE 1.—MATERIAL INCORPORATED BY REFERENCE rmajette on PROD1PC67 with RULES A330–27–3100 A330–27–3105 A340–27–4106 A340–27–4110 Revision level .. .. .. .. 01 02 01 02 Date May 23, 2005. Oct. 10, 2005. May 23, 2005. Oct. 10, 2005. Issued in Renton, Washington, on July 6, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–6180 Filed 7–14–06; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 15:22 Jul 14, 2006 Federal Aviation Administration 14 CFR Part 39 (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. Airbus Service Bulletin DEPARTMENT OF TRANSPORTATION Jkt 208001 [Docket No. FAA–2006–23644; Directorate Identifier 2006–CE–03–AD; Amendment 39– 14679; AD 2006–14–08] RIN 2120–AA64 Airworthiness Directives; Mitsubishi Heavy Industries MU–2B Series Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: The FAA adopts a new airworthiness directive (AD) for some Mitsubishi Heavy Industries (MHI) MU– 2B series airplanes. This AD requires you to verify that the current flight idle blade angles are set at 12 degrees. If not already set at that angle, set the flight idle blade angles to 12 degrees. This AD results from a recent safety evaluation that used a data-driven approach to analyze the design, operation, and maintenance of the MU–2B series airplanes in order to determine their safety and define what steps, if any, are necessary for their safe operation. Part of that evaluation was the identification of unsafe conditions that exist or could develop on the affected type design airplanes. We are issuing this AD to prevent incorrect flight idle blade angle settings. This unsafe condition, if not corrected, could lead to an asymmetric thrust situation in certain flight conditions, which could result in airplane controllability problems. DATES: This AD becomes effective on August 21, 2006. As of August 21, 2006, the Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulation. ADDRESSES: To get the service information identified in this AD, contact Mitsubishi Heavy Industries America, Inc., 4951 Airport Parkway, Suite 800, Addison, Texas 75001; telephone: 972–934–5480; facsimile: 972–934–5488. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 001 or on the Internet at http:// dms.dot.gov. The docket number is FAA–2006–23644; Directorate Identifier 2006–CE–03–AD. FOR FURTHER INFORMATION CONTACT: Rao Edupuganti, Aerospace Engineer, Fort Worth ACO, ASW–150, Rotorcraft PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 40389 Directorate, FAA, 2601 Meacham Boulevard, Fort Worth, Texas 76137– 4298; telephone: 817–222–5284; facsimile: 817–222–5960. SUPPLEMENTARY INFORMATION: Discussion On February 3, 2006, we issued a proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to some MHI MU–2B series airplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on February 9, 2006 (71 FR 6685). The NPRM proposed to require you to check the flight idle blade angle setting and set to 12 degrees if not already. Comments We provided the public the opportunity to participate in developing this AD. The following presents the comment received on the proposal and FAA’s response to the comment: Comment Issue: Need for Issuance of This AD After 25 Years Since the Issuance of the Service Bulletin Mitsubishi Heavy Industries America, Inc. questions the need for an AD 25 years after the service bulletin has been issued. In 1980, MHI (Mitsubishi Aircraft International, Inc. at the time of issuance) issued Service Bulletin No. SB016/61–001, dated March 18, 1980, to change the flight blade angles from 16 degrees to 12 degrees. The type certificate data sheet for the affected airplanes was also revised to incorporate this change, which included Note 3 to indicate a small group of airplanes that may not have incorporated Service Bulletin No. SB016/61–001. No Japanese AD was issued because no airplanes on the Japanese type certificate were affected by this change. The Japanese airplanes had already incorporated the intent of the service bulletin. At the time the service bulletin was issued, the FAA evaluated the available information and found that there were no reports of problems or incidents of flight idle blade angle settings with airplanes of U.S. registry. Therefore, we did not issue an airworthiness directive at that time. Based on information received from the safety evaluation done in 2005 for the MU–2B series airplanes, we identified flight idle blade angles set at 16 degrees instead of 12 degrees as a potential problem. After analyzing this issue using our risk-based methodology and the information received from the safety evaluation, we identified that an unsafe E:\FR\FM\17JYR1.SGM 17JYR1

Agencies

[Federal Register Volume 71, Number 136 (Monday, July 17, 2006)]
[Rules and Regulations]
[Pages 40387-40389]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-6180]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24522; Directorate Identifier 2006-NM-002-AD; 
Amendment 39-14680; AD 2006-14-09]
RIN 2120-AA64


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

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

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Airbus Model A330-200 and -300, and A340-200 and -300 series 
airplanes. This AD requires modifying certain rotary actuator 
assemblies for the leading edge slat. This AD results from a leak found 
at the seal of the torque limiter output shaft of the Type A rotary 
actuator of leading edge slat No. 1. We are issuing this AD to prevent 
a decrease in the torque limiter function, which could result in 
degradation and damage to the attachment bolts of the leading edge 
slat, loss of the slat, and consequent reduced control of the airplane.

DATES: This AD becomes effective August 21, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of August 21, 
2006.

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

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

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at http://dms.dot.gov or in person at the Docket Management 
Facility office between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Management Facility office 
(telephone (800) 647-5227) is located on the plaza level of the Nassif 
Building at the street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that would apply to certain Airbus Model 
A330-200 and -300, and A340-200 and -300 series airplanes. That NPRM 
was published in the Federal Register on April 21, 2006 (71 FR 20599). 
That NPRM proposed to require modifying certain rotary actuator 
assemblies for the leading edge slat.

Comments

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

[[Page 40388]]

Request To Revise the Applicability

    Airbus requests that Model A330-302 and -303 airplanes be included 
in the applicability of paragraph (c) of the NPRM. Airbus states that 
those airplanes are in the process of being type certificated in the 
U.S.
    We agree. We have determined that Model A330-302 and -303 airplanes 
are subject to the identified unsafe condition of this AD. Therefore, 
we have revised the applicability of paragraph (c) of this AD to 
include those airplanes to ensure that the identified unsafe condition 
is addressed if any of those affected airplanes are imported and placed 
on the U.S. Register in the future.

Conclusion

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

Costs of Compliance

    This AD affects about 9 airplanes of U.S. registry. The 
modification (including operational test) takes about 4 work hours per 
airplane, at an average labor rate of $80 per work hour. Required parts 
are free of charge. Based on these figures, the estimated cost of the 
AD for U.S. operators is $2,880, or $320 per airplane.
    Currently, there are no affected Model A330-302 and -303 airplanes 
on the U.S. Register. However, if an affected airplane is imported and 
placed on the U.S. Register in the future, it would be subject to the 
same per-airplane cost specified above.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

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


Sec.  39.13  [Amended]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

2006-14-09 Airbus: Amendment 39-14680. Docket No. FAA-2006-24522; 
Directorate Identifier 2006-NM-002-AD.

Effective Date

    (a) This AD becomes effective August 21, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A330-201, 202, -203, -223, 
and -243; A330-301, -302, -303, -321, -322, -323, -341, -342, and -
343; A340-211, -212, and -213; and A340-311, -312, and -313 
airplanes, certificated in any category; except airplanes on which 
Airbus Modification 50138 was done during production.

Unsafe Condition

    (d) This AD results from a leak found at the seal of the torque 
limiter output shaft of the Type A rotary actuator of leading edge 
slat No. 1. We are issuing this AD to prevent a decrease in the 
torque limiter function, which could result in degradation and 
damage to the attachment bolts of the leading edge slat, loss of the 
slat, and consequent reduced control 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.

Modification

    (f) Within 38 months after the effective date of this AD: Modify 
any Type A rotary actuator assembly for the leading edge slat having 
part number (P/N) 954A0000-01 or 954A0000-02, or P/N 954B0000-01, as 
applicable, by doing all the applicable actions in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A330-27-
3100, Revision 01, dated May 23, 2005; or A340-27-4106, Revision 01, 
dated May 23, 2005; as applicable.
    (g) Modification of any Type A rotary actuator assembly for the 
leading edge slat having P/N 954B0000-01, in accordance with Airbus 
Service Bulletin A330-27-3105 or A340-27-4110, both Revision 02, 
both dated October 10, 2005; as applicable; is acceptable for 
compliance with the corresponding modification specified in 
paragraph (f) of this AD.

    Note 1: Airbus Service Bulletins A330-27-3100 and A340-27-4106 
refer to Goodrich Actuation Systems Service Bulletin 954-27-M954-07, 
Revision 2, dated August 9, 2004; and Airbus Service Bulletins A330-
27-3105 and A340-27-4110 refer to Goodrich Actuation Systems Service 
Bulletin 954-27-M954-06, Revision 2, dated May 20, 2004; as 
additional sources of service information for modifying the rotary 
actuator assembly for the leading edge slat.

Parts Installation

    (h) As of the effective date of this AD, no Type A rotary 
actuator assembly for the leading edge slat having P/N 954A0000-01, 
-02, or 954B0000-01 may be installed unless the part has been 
modified in accordance with the actions required by paragraph (f) or 
(g) of this AD, as applicable.

Actions Accomplished Previously

    (i) Modifications done before the effective date of this AD in 
accordance with Airbus Service Bulletins A330-27-3100, dated October 
30, 2002; A330-27-3105, dated October 30, 2002, or Revision 01, 
dated March 27, 2003; A340-27-4106, dated October 30, 2002; or A340-
27-4110, dated October 30, 2002, or Revision 01, dated March 27, 
2003; as applicable; are acceptable

[[Page 40389]]

for compliance with the corresponding requirements of paragraphs (f) 
and (g) of this AD, as applicable.

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) French airworthiness directives F-2005-067 and F-2005-068, 
both dated April 27, 2005, also address the subject of this AD.

Material Incorporated by Reference

    (l) You must use the applicable Airbus service bulletin 
identified in Table 1 of this AD to perform the actions that are 
required by this AD, unless the AD specifies otherwise. The Director 
of the Federal Register approved the incorporation by reference of 
these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France, for a copy of this service information. You may 
review copies at the Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street SW., Room PL-401, Nassif 
Building, Washington, DC; on the Internet at http://dms.dot.gov; or 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at the NARA, call 
(202) 741-6030, or go to http://www.archives.gov/federal_register/
code_of_federal_regulations/ibr_locations.html.

              Table 1.--Material Incorporated by Reference
------------------------------------------------------------------------
                                      Revision
      Airbus Service Bulletin          level              Date
------------------------------------------------------------------------
A330-27-3100.......................         01  May 23, 2005.
A330-27-3105.......................         02  Oct. 10, 2005.
A340-27-4106.......................         01  May 23, 2005.
A340-27-4110.......................         02  Oct. 10, 2005.
------------------------------------------------------------------------


    Issued in Renton, Washington, on July 6, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-6180 Filed 7-14-06; 8:45 am]
BILLING CODE 4910-13-P