Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes; Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model A300 C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes); and Model A310-200 and -300 Series Airplanes, 50157-50160 [05-16749]

Download as PDF Federal Register / Vol. 70, No. 165 / Friday, August 26, 2005 / Rules and Regulations DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20794; Directorate Identifier 2004–NM–172–AD; Amendment 39–14235; AD 2005–17–14] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 B2 and B4 Series Airplanes; Model A300 B4–600, B4–600R, and F4– 600R Series Airplanes, and Model A300 C4–605R Variant F Airplanes (Collectively Called A300–600 Series Airplanes); and Model A310–200 and –300 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to all Airbus Model A300 B2 and B4 series airplanes; Model A300–600 series airplanes; and Model A310–200 and –300 series airplanes. That AD currently requires, among other actions, repetitive tests to detect desynchronization of the rudder servo actuators, and adjustment or replacement of the spring rods of the rudder servo actuators, if necessary. This new AD requires new repetitive tests/inspections/analyses of the rudder servo actuators, and related investigative/corrective actions if necessary. Accomplishment of the new actions ends the existing repetitive requirements. This AD is prompted by new reports of desynchronization of the rudder servo actuators. We are issuing this AD to prevent desynchronization of one of the three rudder servo actuators, which, if combined with an engine failure, could result in the loss of the related hydraulic system and could cause the loss of one of the two synchronized actuators. This condition could create additional fatigue loading and possible cracking on the attachment fittings and could result in the inability of the remaining synchronized actuator to maintain the commanded rudder deflection, which could result in reduced controllability of the airplane. DATES: This AD becomes effective September 30, 2005. The incorporation by reference of certain publications listed in the AD is approved by the Director of the Federal Register as of September 30, 2005. On July 30, 1998 (63 FR 34580, June 25, 1998), the Director of the Federal Register approved the incorporation by VerDate Aug<18>2005 16:11 Aug 25, 2005 Jkt 205001 reference of certain other publications listed in the AD. ADDRESSES: For service information identified in this AD, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Docket: The AD docket contains the proposed AD, comments, and any final disposition. You can examine the AD docket on the Internet at 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 U.S. Department of Transportation, 400 Seventh Street, SW., room PL–401, Washington, DC. This docket number is FAA–2005–20794; the directorate identifier for this docket is 2004–NM– 172–AD. FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2797; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: The FAA proposed to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) with an AD to supersede AD 98–13–33, amendment 39–10624 (63 FR 34580, June 25, 1998). The existing AD applies to all Airbus Model A300 B2 and B4 series airplanes; Model A300 B4–600, B4–600R, and F4–600R series airplanes, and Model A300 C4–605R Variant F airplanes (collectively called A300–600 series airplanes); and Model A310–200 and –300 series airplanes. The proposed AD was published in the Federal Register on April 5, 2005 (70 FR 17212), to continue to require repetitive tests to detect desynchronization of the rudder servo actuators, and adjustment or replacement of the spring rods of the rudder servo actuators, if necessary. The proposed AD would also require new repetitive tests/inspections/ analyses of the rudder servo actuators, and related investigative/corrective actions if necessary. The proposed AD states that accomplishing the new actions ends the existing repetitive requirements. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments that have been submitted on the proposed AD. Request To Withdraw the Proposed AD The commenter states that it can find no compelling reason for the proposed PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 50157 AD. The commenter notes that it has been accomplishing the requirements of AD 98–13–33 for several years and has had no significant findings. The commenter states that it has previously accomplished the actions in the parallel French airworthiness directive, F–2004– 092, dated June 23, 2004, which introduced the inspection for dead travel of the input lever of the rudder servo control due to an isolated incident with a single operator. The commenter asserts that this incident most likely resulted from improper assembly and testing of the servo control during repair and overhaul of the component. Therefore, the commenter does not see the value of or need for the inspection for dead travel. The commenter suggests that resolution of the discrepancy with the input lever of the rudder servo control should be addressed by revising the applicable component maintenance manual. We infer that the commenter is requesting that we withdraw the proposed AD. We do not agree. The information that we have received from the manufacturer and the Direction ´ ´ Generale de l’Aviation Civile (DGAC), which is the airworthiness authority for France, does not indicate that the malfunction or misadjustment of the spring rods of the rudder servo actuator is an isolated incident. We find that the new repetitive tests, inspections, and analyses of the rudder servo actuators that will be newly required by this AD are necessary to ensure that all potential causes of desynchronization of the rudder servo actuators are addressed. As explained previously, desynchronization of one of the three rudder servo actuators, if combined with an engine failure, could result in the loss of the related hydraulic system and, potentially, loss of one of the two synchronized actuators. This condition could create additional fatigue loading and possible cracking on the attachment fittings and could result in the inability of the remaining synchronized actuator to maintain the commanded rudder deflection, which could result in reduced controllability of the airplane. The tests, inspections, and analyses, as well as any necessary investigative and corrective actions, required by this AD are intended to address this unsafe condition. We have not changed the final rule in this regard. Request To Remove Reporting Requirement The commenter declares that the reporting requirement included in paragraph (n) of the proposed AD is unnecessary and does not enhance the value of the proposed requirements. The E:\FR\FM\26AUR1.SGM 26AUR1 50158 Federal Register / Vol. 70, No. 165 / Friday, August 26, 2005 / Rules and Regulations commenter states that reporting data at this point would not be relevant because there have been numerous opportunities to correct the unsafe condition prior to the proposed AD. We partially agree with the commenter’s request. Reporting any discrepancy will help to determine the extent of the unsafe condition in the affected fleet. Based on the results of these reports, we may determine that further investigative or corrective action is necessary. Reporting any discrepancy may also help us to determine if other conditions, as yet undetected, are present in the fleet, which could lead to desynchronization of the rudder servo actuators. For these reasons, this AD will continue to require reporting any discrepancy in accordance with the applicable referenced Airbus service bulletin. However, we have determined that it is not necessary to require reporting the inspection results in which there are no findings. Thus, we have revised paragraph (n) of this AD to specify that only positive findings must be reported. Explanation of Change to Applicability We have revised the applicability of this AD to identify model designations as published in the most recent type certificate data sheet for the affected models. Conclusion We have carefully reviewed the available data, including the comments that have been submitted, and determined that air safety and the public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance The following table provides the estimated costs for U.S. operators to comply with this AD. The average labor rate is $65 per hour. ESTIMATED COSTS Action Work hour Tests (required by AD 98–13–13) ......................................... Tests/inspections/analyses (new requirement) ..................... 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; VerDate Aug<18>2005 16:11 Aug 25, 2005 Jkt 205001 Parts 1 1 None ............ None ............ (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: ■ 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing amendment 39–10624 (63 FR 34580, June 25, 1998) and by adding the following new airworthiness directive (AD): ■ 2005–17–14 Airbus: Amendment 39–14235. Docket No. FAA–2005–20794; Directorate Identifier 2004–NM–172–AD. PO 00000 Frm 00010 Fmt 4700 Cost per airplane, per cycle Sfmt 4700 Number of U.S.-registered airplanes Fleet cost per cycle 179 179 $11,635 11,635 $65 65 Effective Date (a) This AD becomes effective September 30, 2005. Affected ADs (b) This AD supersedes AD 98–13–33, amendment 39–10624 (63 FR 34580, June 25, 1998). Applicability (c) This AD applies to all Airbus Model A300 B2–1A, B2–1C, B2K–3C, and B2–203 airplanes; Model A300 B4–2C, B4–103, and B4–203 airplanes; Model A300 B4–601, B4– 603, B4–605R, B4–620, B4–622, B4–622R, C4–605R Variant F, F4–605R, and F4–622R airplanes; and Model A310–203, –204, –221, –222, –304, –322, –324, and –325 airplanes; certificated in any category. Unsafe Condition (d) This AD was prompted by new reports of desynchronization of the rudder servo actuators. We are issuing this AD to prevent desynchronization of one of the three rudder servo actuators, which, if combined with an engine failure, could result in the loss of the related hydraulic system and could cause the loss of one of the two synchronized actuators. This condition could create additional fatigue loading and possible cracking on the attachment fittings and could result in the inability of the remaining synchronized actuator to maintain the commanded rudder deflection, which could result in 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. E:\FR\FM\26AUR1.SGM 26AUR1 Federal Register / Vol. 70, No. 165 / Friday, August 26, 2005 / Rules and Regulations Requirements of AD 98–13–33 Repetitive Tests and Adjustment or Replacement (f) Prior to accumulation of 1,300 total flight hours, or within 500 flight hours after July 30, 1998 (the effective date of AD 98– 13–33), whichever occurs later, and thereafter at intervals not to exceed 1,300 flight hours: Perform a test to detect desynchronization of the rudder servo actuators in accordance with Airbus Service Bulletin A300–27–0188, Revision 2, dated October 1, 1997 (for Model A300 series airplanes); A300–27–6036, Revision 2, dated October 1, 1997 (for Model A300–600 series airplanes); or A310–27–2082, Revision 2, dated October 1, 1997 (for Model A310–200 and –300 series airplanes); as applicable. If any desynchronization (rudder movement) is detected, prior to further flight, either adjust or replace, as applicable, the spring rod of the affected rudder servo actuator in accordance with the applicable service bulletin. Note 1: A test to detect desynchronization of the rudder servo actuators, if accomplished prior to the effective date of this AD in accordance with Airbus Service Bulletin A300–27–0188, dated October 24, 1996, or Revision 1, dated November 5, 1996 (for Model A300 series airplanes); A300–27– 6036, dated October 24, 1996, or Revision 1, dated November 5, 1996 (for Model A300– 600 series airplanes); or A310–27–2082, dated October 24, 1996, or Revision 1, dated November 5, 1996 (for Model A310–200 and –300 series airplanes); is considered acceptable for compliance with the initial test required by paragraph (f) of this AD. (g) Except as provided by paragraph (h) of this AD, if any desynchronization (rudder movement) greater than the limit specified in Paragraph B of the Accomplishment Instructions of the applicable service bulletin is detected during any test required by paragraph (f) of this AD, prior to further flight, accomplish either paragraph (g)(1) or (g)(2) of this AD, in accordance with Airbus Service Bulletin A300–55–0044, dated October 22, 1996 (for Model A300 series airplanes); A300–55–6023, dated October 22, 1996 (for Model A300–600 series airplanes); or A310–55–2026, dated October 22, 1996 (for Model A310 series airplanes); as applicable. (1) Conduct a visual inspection, high frequency eddy current inspection, or 50159 ultrasonic inspection, as applicable, to detect cracking of the rudder attachments; and repeat the inspection thereafter, as applicable, at the intervals specified in the applicable service bulletin. Or (2) Modify the rudder attachments to cold expand the rivet holes. (h) If any crack is found during any inspection or modification required by paragraph (g) of this AD, and the applicable service bulletin specifies to contact Airbus for an appropriate action: Prior to further flight, repair the affected structure in accordance with a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, or in accordance with a method approved by the ´ ´ Direction Generale de l’Aviation Civile (DGAC). New Requirements of This AD Service Bulletins (i) The term ‘‘primary service bulletin,’’ as hereafter used in this AD, means the Accomplishment Instructions of the applicable primary service bulletin in Table 1 of this AD. TABLE 1.—PRIMARY SERVICE BULLETINS Airbus service bulletin— For— (1) A300–27–0188, including Appendix 01 and Reporting Sheet, Revision 05, dated April 16, 2004. (2) A300–27–6036, including Appendix 01 and Reporting Sheet, Revision 08, dated April 16, 2004. (3) A310–27–2082, including Appendix 01 and Reporting Sheet, Revision 05, dated April 16, 2004. Model A300 B2 and B4 series airplanes. (j) The primary service bulletin refers to the applicable secondary service bulletin in related investigative actions for certain conditions. Table 2 of this AD as an additional source of service information for accomplishing the Model A300–600 series airplanes. Model A310–200 and –300 series airplanes. TABLE 2.—SECONDARY SERVICE BULLETINS Airbus service bulletin— For— (1) A300–55–0044, Revision 03, dated April 16, 2004 .................................................................. (2) A310–55–2026, Revision 02, dated April 16, 2004 .................................................................. (3) A300–55–6023, Revision 05, dated April 16, 2004 .................................................................. Model A300 B2 and B4 series airplanes. Model A310–200 and –300 series airplanes. Model A300–600 series airplanes. Compliance Times (k) Do the actions specified in paragraph (l) of this AD at the following times: (1) Within 700 flight hours after the effective date of this AD or within 1,300 flight hours after the last inspection required by either paragraph (f) or (g) of this AD, whichever occurs first; and (2) Thereafter at intervals not to exceed 1,300 flight hours. International Branch, ANM–116; or the DGAC (or its delegated agent). Tests/Inspections/Analyses and Related Investigative/Corrective Actions (l) Do the actions specified in paragraphs (l)(1) through (l)(4) of this AD and any applicable related investigative/corrective actions by doing all the actions in accordance with the primary service bulletin, except as required by paragraph (m) of this AD. Related investigative and corrective actions must be done before further flight. Accomplishing VerDate Aug<18>2005 16:11 Aug 25, 2005 Jkt 205001 these actions ends the requirements of paragraphs (f) through (h) of this AD. (1) Do an operational test of the rudder system with each hydraulic system pressurized in turn. (2) Do a static inspection for correct synchronization of the rudder servo controls with each hydraulic system. (3) Inspect to find dead travel of the input lever of the rudder servo control for each hydraulic system. (4) Analyze the results of the static inspection required by paragraph (l)(2) of this AD and the inspection to find dead travel required by paragraph (l)(3) of this AD. (m) If the primary/secondary service bulletin recommends contacting Airbus for appropriate action: Before further flight, repair any discrepancy in accordance with a method approved by either the Manager, PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 Reporting (n) At the applicable time specified in paragraph (n)(1) or (n)(2) of this AD, submit a report only of positive findings in accordance with the primary service bulletin. 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 action specified in the primary service bulletin was done after the effective date of this AD: Submit the report within 30 days after the inspection. (2) If the action specified in the primary service bulletin was accomplished before the E:\FR\FM\26AUR1.SGM 26AUR1 50160 Federal Register / Vol. 70, No. 165 / Friday, August 26, 2005 / Rules and Regulations effective date of this AD: Submit the report within 30 days after the effective date of this AD. (2) AMOCs approved previously according to AD 98–13–33 are not approved as AMOCs with this AD. Alternative Methods of Compliance (AMOCs) (o)(1) The Manager, International Branch, ANM–116, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Related Information (p) French airworthiness directive F–2004– 092, issued June 23, 2004, also addresses the subject of this AD. Material Incorporated by Reference (q) You must use the service information listed in Table 3 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. TABLE 3.—MATERIAL INCORPORATED BY REFERENCE Airbus service bulletin Revision level Date A300–27–0188 ......................................................................................................................... A300–27–0188, including Appendix 01 and Reporting Sheet ................................................ A300–27–6036 ......................................................................................................................... A300–27–6036, including Appendix 01 and Reporting Sheet ................................................ A300–55–0044 ......................................................................................................................... A300–55–6023 ......................................................................................................................... A310–27–2082 ......................................................................................................................... A310–27–2082, including Appendix 01 and Reporting Sheet ................................................ A310–55–2026 ......................................................................................................................... 2 ............................................. 05 ........................................... 2 ............................................. 08 ........................................... Original ................................... Original ................................... 2 ............................................. 05 ........................................... Original ................................... October 1, 1997. April 16, 2004. October 1, 1997. April 16, 2004. October 22, 1996. October 22, 1996. October 1, 1997. April 16, 2004. October 22, 1996. (1) The Director of the Federal Register approves th incorporatin by reference of the service information listed in Table 4 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. TABLE 4.—NEW MATERIAL INCORPORATED BY REFERENCE Airbus service bulletin Revision level A300–27–0188, including Appendix 01 and Reporting Sheet ................................................ A300–27–6036, including Appendix 01 and Reporting Sheet ................................................ A310–27–2082, including Appendix 01 and Reporting Sheet ................................................ 05 ........................................... 08 ........................................... 05 ........................................... (2) On July 30, 1998 (63 FR 34580, June 25, 1998), the Director of the Federal Register previously approved the incorporation by Date April 16, 2004. April 16, 2004. April 16, 2004. reference of the service information listed in Table 5 of this AD. TABLE 5.—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE Airbus service bulletin A300–27–0188 A300–27–6036 A300–55–0044 A300–55–6023 A310–27–2082 A310–55–2026 Revision level ......................................................................................................................... ......................................................................................................................... ......................................................................................................................... ......................................................................................................................... ......................................................................................................................... ......................................................................................................................... (3) To get copies of the service information, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. To view the AD docket, go to the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Nassif Building, Washington, DC. To review copies of the service information, go to 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/federalregister/cfr/ibr-locations.html. 2 ............................................. 2 ............................................. Original ................................... Original ................................... 2 ............................................. Original ................................... Issued in Renton, Washington, on August 12, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–16749 Filed 8–25–05; 8:45 am] BILLING CODE 4910–13–P Date October October October October October October 1, 1997. 1, 1997. 22, 1996. 22, 1996. 1, 1997. 22, 1996. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22168; Directorate Identifier 2005–NM–146–AD; Amendment 39–14234; AD 2005–17–13] RIN 2120–AA64 Airworthiness Directives; Short Brothers Model SD3–60 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). AGENCY: VerDate Aug<18>2005 16:11 Aug 25, 2005 Jkt 205001 PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 E:\FR\FM\26AUR1.SGM 26AUR1

Agencies

[Federal Register Volume 70, Number 165 (Friday, August 26, 2005)]
[Rules and Regulations]
[Pages 50157-50160]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-16749]



[[Page 50157]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20794; Directorate Identifier 2004-NM-172-AD; 
Amendment 39-14235; AD 2005-17-14]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2 and B4 Series 
Airplanes; Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, 
and Model A300 C4-605R Variant F Airplanes (Collectively Called A300-
600 Series Airplanes); and Model A310-200 and -300 Series Airplanes

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

ACTION: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to all Airbus Model A300 B2 and B4 series 
airplanes; Model A300-600 series airplanes; and Model A310-200 and -300 
series airplanes. That AD currently requires, among other actions, 
repetitive tests to detect desynchronization of the rudder servo 
actuators, and adjustment or replacement of the spring rods of the 
rudder servo actuators, if necessary. This new AD requires new 
repetitive tests/inspections/analyses of the rudder servo actuators, 
and related investigative/corrective actions if necessary. 
Accomplishment of the new actions ends the existing repetitive 
requirements. This AD is prompted by new reports of desynchronization 
of the rudder servo actuators. We are issuing this AD to prevent 
desynchronization of one of the three rudder servo actuators, which, if 
combined with an engine failure, could result in the loss of the 
related hydraulic system and could cause the loss of one of the two 
synchronized actuators. This condition could create additional fatigue 
loading and possible cracking on the attachment fittings and could 
result in the inability of the remaining synchronized actuator to 
maintain the commanded rudder deflection, which could result in reduced 
controllability of the airplane.

DATES: This AD becomes effective September 30, 2005.
    The incorporation by reference of certain publications listed in 
the AD is approved by the Director of the Federal Register as of 
September 30, 2005.
    On July 30, 1998 (63 FR 34580, June 25, 1998), the Director of the 
Federal Register approved the incorporation by reference of certain 
other publications listed in the AD.

ADDRESSES: For service information identified in this AD, contact 
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
    Docket: The AD docket contains the proposed AD, comments, and any 
final disposition. You can examine the AD docket on the Internet at 
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 U.S. 
Department of Transportation, 400 Seventh Street, SW., room PL-401, 
Washington, DC. This docket number is FAA-2005-20794; the directorate 
identifier for this docket is 2004-NM-172-AD.

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

SUPPLEMENTARY INFORMATION: The FAA proposed to amend part 39 of the 
Federal Aviation Regulations (14 CFR part 39) with an AD to supersede 
AD 98-13-33, amendment 39-10624 (63 FR 34580, June 25, 1998). The 
existing AD applies to all Airbus Model A300 B2 and B4 series 
airplanes; Model A300 B4-600, B4-600R, and F4-600R series airplanes, 
and Model A300 C4-605R Variant F airplanes (collectively called A300-
600 series airplanes); and Model A310-200 and -300 series airplanes. 
The proposed AD was published in the Federal Register on April 5, 2005 
(70 FR 17212), to continue to require repetitive tests to detect 
desynchronization of the rudder servo actuators, and adjustment or 
replacement of the spring rods of the rudder servo actuators, if 
necessary. The proposed AD would also require new repetitive tests/
inspections/ analyses of the rudder servo actuators, and related 
investigative/corrective actions if necessary. The proposed AD states 
that accomplishing the new actions ends the existing repetitive 
requirements.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
submitted on the proposed AD.

Request To Withdraw the Proposed AD

    The commenter states that it can find no compelling reason for the 
proposed AD. The commenter notes that it has been accomplishing the 
requirements of AD 98-13-33 for several years and has had no 
significant findings. The commenter states that it has previously 
accomplished the actions in the parallel French airworthiness 
directive, F-2004-092, dated June 23, 2004, which introduced the 
inspection for dead travel of the input lever of the rudder servo 
control due to an isolated incident with a single operator. The 
commenter asserts that this incident most likely resulted from improper 
assembly and testing of the servo control during repair and overhaul of 
the component. Therefore, the commenter does not see the value of or 
need for the inspection for dead travel. The commenter suggests that 
resolution of the discrepancy with the input lever of the rudder servo 
control should be addressed by revising the applicable component 
maintenance manual.
    We infer that the commenter is requesting that we withdraw the 
proposed AD. We do not agree. The information that we have received 
from the manufacturer and the Direction G[eacute]n[eacute]rale de 
l'Aviation Civile (DGAC), which is the airworthiness authority for 
France, does not indicate that the malfunction or misadjustment of the 
spring rods of the rudder servo actuator is an isolated incident. We 
find that the new repetitive tests, inspections, and analyses of the 
rudder servo actuators that will be newly required by this AD are 
necessary to ensure that all potential causes of desynchronization of 
the rudder servo actuators are addressed. As explained previously, 
desynchronization of one of the three rudder servo actuators, if 
combined with an engine failure, could result in the loss of the 
related hydraulic system and, potentially, loss of one of the two 
synchronized actuators. This condition could create additional fatigue 
loading and possible cracking on the attachment fittings and could 
result in the inability of the remaining synchronized actuator to 
maintain the commanded rudder deflection, which could result in reduced 
controllability of the airplane. The tests, inspections, and analyses, 
as well as any necessary investigative and corrective actions, required 
by this AD are intended to address this unsafe condition. We have not 
changed the final rule in this regard.

Request To Remove Reporting Requirement

    The commenter declares that the reporting requirement included in 
paragraph (n) of the proposed AD is unnecessary and does not enhance 
the value of the proposed requirements. The

[[Page 50158]]

commenter states that reporting data at this point would not be 
relevant because there have been numerous opportunities to correct the 
unsafe condition prior to the proposed AD.
    We partially agree with the commenter's request. Reporting any 
discrepancy will help to determine the extent of the unsafe condition 
in the affected fleet. Based on the results of these reports, we may 
determine that further investigative or corrective action is necessary. 
Reporting any discrepancy may also help us to determine if other 
conditions, as yet undetected, are present in the fleet, which could 
lead to desynchronization of the rudder servo actuators. For these 
reasons, this AD will continue to require reporting any discrepancy in 
accordance with the applicable referenced Airbus service bulletin.
    However, we have determined that it is not necessary to require 
reporting the inspection results in which there are no findings. Thus, 
we have revised paragraph (n) of this AD to specify that only positive 
findings must be reported.

Explanation of Change to Applicability

    We have revised the applicability of this AD to identify model 
designations as published in the most recent type certificate data 
sheet for the affected models.

Conclusion

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

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this AD. The average labor rate is $65 per hour.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                     Cost per     Number of U.S.-
            Action                Work hour          Parts         airplane, per    registered    Fleet cost per
                                                                       cycle         airplanes         cycle
----------------------------------------------------------------------------------------------------------------
Tests (required by AD 98-13-                1  None.............             $65             179         $11,635
 13).
Tests/inspections/analyses                  1  None.............              65             179          11,635
 (new requirement).
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing amendment 39-10624 (63 FR 
34580, June 25, 1998) and by adding the following new airworthiness 
directive (AD):

2005-17-14 Airbus: Amendment 39-14235. Docket No. FAA-2005-20794; 
Directorate Identifier 2004-NM-172-AD.

Effective Date

    (a) This AD becomes effective September 30, 2005.

Affected ADs

    (b) This AD supersedes AD 98-13-33, amendment 39-10624 (63 FR 
34580, June 25, 1998).

Applicability

    (c) This AD applies to all Airbus Model A300 B2-1A, B2-1C, B2K-
3C, and B2-203 airplanes; Model A300 B4-2C, B4-103, and B4-203 
airplanes; Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, B4-
622R, C4-605R Variant F, F4-605R, and F4-622R airplanes; and Model 
A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes; 
certificated in any category.

Unsafe Condition

    (d) This AD was prompted by new reports of desynchronization of 
the rudder servo actuators. We are issuing this AD to prevent 
desynchronization of one of the three rudder servo actuators, which, 
if combined with an engine failure, could result in the loss of the 
related hydraulic system and could cause the loss of one of the two 
synchronized actuators. This condition could create additional 
fatigue loading and possible cracking on the attachment fittings and 
could result in the inability of the remaining synchronized actuator 
to maintain the commanded rudder deflection, which could result in 
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.

[[Page 50159]]

Requirements of AD 98-13-33

Repetitive Tests and Adjustment or Replacement

    (f) Prior to accumulation of 1,300 total flight hours, or within 
500 flight hours after July 30, 1998 (the effective date of AD 98-
13-33), whichever occurs later, and thereafter at intervals not to 
exceed 1,300 flight hours: Perform a test to detect 
desynchronization of the rudder servo actuators in accordance with 
Airbus Service Bulletin A300-27-0188, Revision 2, dated October 1, 
1997 (for Model A300 series airplanes); A300-27-6036, Revision 2, 
dated October 1, 1997 (for Model A300-600 series airplanes); or 
A310-27-2082, Revision 2, dated October 1, 1997 (for Model A310-200 
and -300 series airplanes); as applicable. If any desynchronization 
(rudder movement) is detected, prior to further flight, either 
adjust or replace, as applicable, the spring rod of the affected 
rudder servo actuator in accordance with the applicable service 
bulletin.

    Note 1: A test to detect desynchronization of the rudder servo 
actuators, if accomplished prior to the effective date of this AD in 
accordance with Airbus Service Bulletin A300-27-0188, dated October 
24, 1996, or Revision 1, dated November 5, 1996 (for Model A300 
series airplanes); A300-27-6036, dated October 24, 1996, or Revision 
1, dated November 5, 1996 (for Model A300-600 series airplanes); or 
A310-27-2082, dated October 24, 1996, or Revision 1, dated November 
5, 1996 (for Model A310-200 and -300 series airplanes); is 
considered acceptable for compliance with the initial test required 
by paragraph (f) of this AD.

    (g) Except as provided by paragraph (h) of this AD, if any 
desynchronization (rudder movement) greater than the limit specified 
in Paragraph B of the Accomplishment Instructions of the applicable 
service bulletin is detected during any test required by paragraph 
(f) of this AD, prior to further flight, accomplish either paragraph 
(g)(1) or (g)(2) of this AD, in accordance with Airbus Service 
Bulletin A300-55-0044, dated October 22, 1996 (for Model A300 series 
airplanes); A300-55-6023, dated October 22, 1996 (for Model A300-600 
series airplanes); or A310-55-2026, dated October 22, 1996 (for 
Model A310 series airplanes); as applicable.
    (1) Conduct a visual inspection, high frequency eddy current 
inspection, or ultrasonic inspection, as applicable, to detect 
cracking of the rudder attachments; and repeat the inspection 
thereafter, as applicable, at the intervals specified in the 
applicable service bulletin. Or
    (2) Modify the rudder attachments to cold expand the rivet 
holes.
    (h) If any crack is found during any inspection or modification 
required by paragraph (g) of this AD, and the applicable service 
bulletin specifies to contact Airbus for an appropriate action: 
Prior to further flight, repair the affected structure in accordance 
with a method approved by the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA, or in accordance with a 
method approved by the Direction G[eacute]n[eacute]rale de 
l'Aviation Civile (DGAC).

New Requirements of This AD

Service Bulletins

    (i) The term ``primary service bulletin,'' as hereafter used in 
this AD, means the Accomplishment Instructions of the applicable 
primary service bulletin in Table 1 of this AD.

                                       Table 1.--Primary Service Bulletins
----------------------------------------------------------------------------------------------------------------
        Airbus service bulletin--                                          For--
----------------------------------------------------------------------------------------------------------------
(1) A300-27-0188, including Appendix 01    Model A300 B2 and B4 series airplanes.
 and Reporting Sheet, Revision 05, dated
 April 16, 2004.
(2) A300-27-6036, including Appendix 01    Model A300-600 series airplanes.
 and Reporting Sheet, Revision 08, dated
 April 16, 2004.
(3) A310-27-2082, including Appendix 01    Model A310-200 and -300 series airplanes.
 and Reporting Sheet, Revision 05, dated
 April 16, 2004.
----------------------------------------------------------------------------------------------------------------

    (j) The primary service bulletin refers to the applicable 
secondary service bulletin in Table 2 of this AD as an additional 
source of service information for accomplishing the related 
investigative actions for certain conditions.

                                      Table 2.--Secondary Service Bulletins
----------------------------------------------------------------------------------------------------------------
        Airbus service bulletin--                                          For--
----------------------------------------------------------------------------------------------------------------
(1) A300-55-0044, Revision 03, dated       Model A300 B2 and B4 series airplanes.
 April 16, 2004.
(2) A310-55-2026, Revision 02, dated       Model A310-200 and -300 series airplanes.
 April 16, 2004.
(3) A300-55-6023, Revision 05, dated       Model A300-600 series airplanes.
 April 16, 2004.
----------------------------------------------------------------------------------------------------------------

Compliance Times

    (k) Do the actions specified in paragraph (l) of this AD at the 
following times:
    (1) Within 700 flight hours after the effective date of this AD 
or within 1,300 flight hours after the last inspection required by 
either paragraph (f) or (g) of this AD, whichever occurs first; and
    (2) Thereafter at intervals not to exceed 1,300 flight hours.

Tests/Inspections/Analyses and Related Investigative/Corrective 
Actions

    (l) Do the actions specified in paragraphs (l)(1) through (l)(4) 
of this AD and any applicable related investigative/corrective 
actions by doing all the actions in accordance with the primary 
service bulletin, except as required by paragraph (m) of this AD. 
Related investigative and corrective actions must be done before 
further flight. Accomplishing these actions ends the requirements of 
paragraphs (f) through (h) of this AD.
    (1) Do an operational test of the rudder system with each 
hydraulic system pressurized in turn.
    (2) Do a static inspection for correct synchronization of the 
rudder servo controls with each hydraulic system.
    (3) Inspect to find dead travel of the input lever of the rudder 
servo control for each hydraulic system.
    (4) Analyze the results of the static inspection required by 
paragraph (l)(2) of this AD and the inspection to find dead travel 
required by paragraph (l)(3) of this AD.
    (m) If the primary/secondary service bulletin recommends 
contacting Airbus for appropriate action: Before further flight, 
repair any discrepancy in accordance with a method approved by 
either the Manager, International Branch, ANM-116; or the DGAC (or 
its delegated agent).

Reporting

    (n) At the applicable time specified in paragraph (n)(1) or 
(n)(2) of this AD, submit a report only of positive findings in 
accordance with the primary service bulletin. 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 action specified in the primary service bulletin was 
done after the effective date of this AD: Submit the report within 
30 days after the inspection.
    (2) If the action specified in the primary service bulletin was 
accomplished before the

[[Page 50160]]

effective date of this AD: Submit the report within 30 days after 
the effective date of this AD.

Alternative Methods of Compliance (AMOCs)

    (o)(1) The Manager, International Branch, ANM-116, has the 
authority to approve AMOCs for this AD, if requested in accordance 
with the procedures found in 14 CFR 39.19.
    (2) AMOCs approved previously according to AD 98-13-33 are not 
approved as AMOCs with this AD.

Related Information

    (p) French airworthiness directive F-2004-092, issued June 23, 
2004, also addresses the subject of this AD.

Material Incorporated by Reference

    (q) You must use the service information listed in Table 3 of 
this AD to perform the actions that are required by this AD, unless 
the AD specifies otherwise.

              Table 3.--Material Incorporated by Reference
------------------------------------------------------------------------
    Airbus service bulletin      Revision level            Date
------------------------------------------------------------------------
A300-27-0188..................  2..............  October 1, 1997.
A300-27-0188, including         05.............  April 16, 2004.
 Appendix 01 and Reporting
 Sheet.
A300-27-6036..................  2..............  October 1, 1997.
A300-27-6036, including         08.............  April 16, 2004.
 Appendix 01 and Reporting
 Sheet.
A300-55-0044..................  Original.......  October 22, 1996.
A300-55-6023..................  Original.......  October 22, 1996.
A310-27-2082..................  2..............  October 1, 1997.
A310-27-2082, including         05.............  April 16, 2004.
 Appendix 01 and Reporting
 Sheet.
A310-55-2026..................  Original.......  October 22, 1996.
------------------------------------------------------------------------

    (1) The Director of the Federal Register approves th 
incorporatin by reference of the service information listed in Table 
4 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.

            Table 4.--New Material Incorporated by Reference
------------------------------------------------------------------------
    Airbus service bulletin      Revision level            Date
------------------------------------------------------------------------
A300-27-0188, including         05.............  April 16, 2004.
 Appendix 01 and Reporting
 Sheet.
A300-27-6036, including         08.............  April 16, 2004.
 Appendix 01 and Reporting
 Sheet.
A310-27-2082, including         05.............  April 16, 2004.
 Appendix 01 and Reporting
 Sheet.
------------------------------------------------------------------------

    (2) On July 30, 1998 (63 FR 34580, June 25, 1998), the Director 
of the Federal Register previously approved the incorporation by 
reference of the service information listed in Table 5 of this AD.

         Table 5.--Material Previously Incorporated by Reference
------------------------------------------------------------------------
    Airbus service bulletin      Revision level            Date
------------------------------------------------------------------------
A300-27-0188..................  2..............  October 1, 1997.
A300-27-6036..................  2..............  October 1, 1997.
A300-55-0044..................  Original.......  October 22, 1996.
A300-55-6023..................  Original.......  October 22, 1996.
A310-27-2082..................  2..............  October 1, 1997.
A310-55-2026..................  Original.......  October 22, 1996.
------------------------------------------------------------------------

    (3) To get copies of the service information, contact Airbus, 1 
Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. To view 
the AD docket, go to the Docket Management Facility, U.S. Department 
of Transportation, 400 Seventh Street SW., room PL-401, Nassif 
Building, Washington, DC. To review copies of the service 
information, go to 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/cfr/ibr-locations.html.

    Issued in Renton, Washington, on August 12, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-16749 Filed 8-25-05; 8:45 am]
BILLING CODE 4910-13-P