Airworthiness Directives; Airbus Model A318-100 and A319-100 Series Airplanes; Model A320-111 Airplanes; Model A320-200, A321-200, A330-200, A330-300, A340-200, and A340-300 Series Airplanes; Model A340-541 Airplanes; and Model A340-642 Airplanes; Equipped With Certain Sogerma-Services Powered Seats, 3021-3023 [E6-532]

Download as PDF 3021 Proposed Rules Federal Register Vol. 71, No. 12 Thursday, January 19, 2006 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–23633; Directorate Identifier 2005–NM–242–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A318–100 and A319–100 Series Airplanes; Model A320–111 Airplanes; Model A320–200, A321–200, A330–200, A330–300, A340–200, and A340–300 Series Airplanes; Model A340–541 Airplanes; and Model A340–642 Airplanes; Equipped With Certain Sogerma-Services Powered Seats Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). hsrobinson on PROD1PC70 with PROPOSALS AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Airbus transport category airplanes. This proposed AD would require inspecting to determine if a certain actuator is installed in the pilot’s or co-pilot’s seat, and doing applicable corrective actions if necessary. For certain actuators, the proposed AD also would require replacing rotors on both vertical and horizontal movements with new rotors, and replacing the clutch cap with a new cap. This proposed AD results from a report of heavy wear at the driving gear of the rotor shaft end of the electrical driven motor on certain actuators of the pilot’s and co-pilot’s seats. We are proposing this AD to prevent uncommanded movement of the pilot’s or co-pilot’s seat during takeoff or landing, which could result in interference with the operation of the airplane and consequent temporary loss of airplane control. DATES: We must receive comments on this proposed AD by February 21, 2006. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. VerDate Aug<31>2005 13:29 Jan 18, 2006 Jkt 208001 • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Sogerma-Services, 109–17303 Rochefort, Cedex, France; and MessierBugatti, 45 Avenue Victor Hugo, 93538 Aubervilleirs, Cedex, France; for service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘FAA–2006–23633; Directorate Identifier 2005–NM–242–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https:// dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at https://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion ´ ´ The Direction Generale de l’Aviation Civile (DGAC), which is the airworthiness authority for France, notified us that an unsafe condition may exist on certain Airbus Model A318–100 and A319–100 series airplanes; Model A320–111 airplanes; Model A320–200, A321–200, A330–200, A330–300, A340– 200, and A340–300 series airplanes; Model A340–541 airplanes; and Model A340–642 airplanes; equipped with certain Sogerma-Services pilot’s and copilot’s seats. The DGAC advises that, during overhaul of the pilot’s and copilot’s seats, repair stations found heavy wear at the driving gear of the rotor shaft end of the electrical driven motor on certain actuators. The electrical driven motor controls the horizontal and vertical movements of the seats. Investigation revealed that a manufacturing process error resulted in a batch of defective rotor shafts on certain actuators. This condition, if not corrected, could result in uncommanded movement of the pilot’s or co-pilot’s seat during takeoff or landing, which could result in interference with the operation of the airplane and consequent temporary loss of airplane control. Relevant Service Information Sogerma-Services has issued Service Bulletin TAAI1–25–617, dated February 1, 2005. The service bulletin describes procedures for inspecting to determine if a certain actuator is installed in the pilot’s or co-pilot’s seat, and doing applicable corrective actions if E:\FR\FM\19JAP1.SGM 19JAP1 3022 Federal Register / Vol. 71, No. 12 / Thursday, January 19, 2006 / Proposed Rules necessary. The corrective actions include: • Replacing certain actuators with new actuators; • Installing a new identification label for any replaced actuator; and • Installing a new amendment label and writing the new amendment on it. Messier-Bugatti has issued Service Bulletins 4136290004–25–05 and 4136290005–25–02, both dated April 2005. For certain airplanes, the service bulletins describe procedures for replacing rotors on both vertical and horizontal movements with new rotors, and replacing the clutch cap with a new cap. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The DGAC mandated the service information and issued French airworthiness directive F–2005–164, dated September 28, 2005, to ensure the continued airworthiness of these airplanes in France. FAA’s Determination and Requirements of the Proposed AD These airplane models are manufactured in France and are type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the DGAC has kept the FAA informed of the situation described above. We have examined the DGAC’s findings, evaluated all pertinent information, and determined that we need to issue an AD for airplanes of this type design that are certificated for operation in the United States. Therefore, we are proposing this AD, which would require accomplishing the actions specified in the service information described previously. hsrobinson on PROD1PC70 with PROPOSALS Costs of Compliance This proposed AD would affect about 743 airplanes of U.S. registry. The proposed inspection would take about 1 work hour per airplane, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the proposed AD for U.S. operators is $48,295, or $65 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. VerDate Aug<31>2005 13:29 Jan 18, 2006 Jkt 208001 We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: 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): Airbus: Docket No. FAA–2006–23633; Directorate Identifier 2005–NM–242–AD. PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 Comments Due Date (a) The FAA must receive comments on this AD action by February 21, 2006. Affected ADs (b) None. Applicability (c) This AD applies to the airplanes identified in table 1 of this AD, certificated in any category; equipped with any SogermaServices pilot or co-pilot seat identified in Sogerma-Services Service Bulletin TAAI1– 25–617, dated February 1, 2005, excluding any seat having part number (P/N) TAAI3– 03PE00–01, TAAI3–03PE01–01, TAAI3– 03CE00–01, and TAAI3–03CE01–01, with a serial number (S/N) higher than 791, on which the actuator has been replaced after the date of issuance of the original standard airworthiness certificate or date of issuance of the original export certificate of airworthiness. TABLE 1.—APPLICABILITY Airbus model (1) A318–111 and –112 airplanes. (2) A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. (3) A320–111 airplanes. (4) A320–211, –212, –214, –231, –232, and –233 airplanes. (5) A321–211 and –231 airplanes. (6) A330–201, –202, –203, –223, and –243 airplanes. (7) A330–301, –321, –322, –323, –341, –342, and –343 airplanes. (8) A340–211, –212, and –213 airplanes. (9) A340–311, –312, and –313 airplanes. (10) A340–541 airplanes. (11) A340–642 airplanes. Unsafe Condition (d) This AD results from a report of heavy wear at the driving gear of the rotor shaft end of the electrical driven motor on certain actuators of the pilot’s and co-pilot’s seats. We are issuing this AD to prevent uncommanded movement of the pilot’s or copilot’s seat during takeoff or landing, which could result in interference with the operation of the airplane and consequent temporary loss of airplane control. 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. Inspection for the P/N of the Actuator (f) Within 56 months after the effective date of this AD, inspect to determine if an actuator identified in table 2 of this AD is installed in the pilot’s or co-pilot’s seat, in accordance with paragraph D., ‘‘DESCRIPTION’’ of Sogerma-Services Service Bulletin TAAI1–25–617, dated February 1, 2005. If any actuator identified in table 2 of this AD is found installed, within 56 months after the effective date of this AD, do the applicable corrective actions in accordance with paragraph 3., ‘‘OPERATING INSTRUCTIONS,’’ of the service bulletin. E:\FR\FM\19JAP1.SGM 19JAP1 Federal Register / Vol. 71, No. 12 / Thursday, January 19, 2006 / Proposed Rules TABLE 2.—AFFECTED ACTUATORS Manufacturer (1) (2) (3) (4) Messier-Bugatti ........... Messier-Bugatti ........... Aviac ........................... Artus ............................ Actuator P/N 4136290004 4136290005 6147–6 AD8552502–1 Concurrent Replacements (g) For Messier-Bugatti actuators identified in table 2 of this AD: Concurrently with the applicable corrective action required by paragraph (f) of this AD, replace the rotors on both vertical and horizontal movements with new rotors, and replace the clutch cap with a new cap, in accordance with MessierBugatti Service Bulletin 4136290004–25–05 or 4136290005–25–02, both dated April 2005, as applicable. Parts Installation (h) After the effective date of this AD, no actuator identified in table 2 of this AD may be installed on any airplane. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (j) French airworthiness directive F–2005– 164, issued September 28, 2005, also addresses the subject of this AD. Issued in Renton, Washington, on January 10, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–532 Filed 1–18–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–23635; Directorate Identifier 2005–NM–245–AD] hsrobinson on PROD1PC70 with PROPOSALS RIN 2120–AA64 Airworthiness Directives; Aerospatiale Model ATR42 Airplanes and Model ATR72 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: VerDate Aug<31>2005 13:29 Jan 18, 2006 Jkt 208001 SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Aerospatiale Model ATR42 airplanes and Model ATR72 airplanes. This proposed AD would require installing protective ramps on trim panel 110VU; and inspecting the protective guard of the standby pitch trim switch to determine if it is missing, damaged, or ineffective, and doing the corrective action if necessary. This proposed AD results from a finding that the protective guard of the standby pitch trim switch, which is installed on the center pedestal, could be damaged or missing. We are proposing this AD to prevent inadvertent activation of the standby pitch trim, which could result in pitch trim runaway and consequent reduced controllability of the airplane. DATES: We must receive comments on this proposed AD by February 21, 2006. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France, for service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘FAA–2006–23635; Directorate Identifier 2005–NM–245–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 3023 the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https:// dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at https://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion ´ ´ The Direction Generale de l’Aviation Civile (DGAC), which is the airworthiness authority for France, notified us that an unsafe condition may exist on certain Aerospatiale Model ATR42 and Model ATR72 airplanes. The DGAC advises that the protective guard of the standby pitch trim switch (18CG), which is installed on the center pedestal, could be damaged or missing. In some cases, a damaged protective guard, even if engaged, may not prevent inadvertent activation of the standby pitch trim. This condition, if not corrected, could result in pitch trim runaway and consequent reduced controllability of the airplane. Relevant Service Information Aerospatiale has issued Avions de Transport Regional Service Bulletin ATR42–92–0010, Revision 1, dated March 11, 2003 (for Model ATR42 airplanes); and Service Bulletin ATR72– 92–1010, Revision 1, dated March 11, 2003 (for Model ATR72 airplanes). The service bulletins describe the following procedures: E:\FR\FM\19JAP1.SGM 19JAP1

Agencies

[Federal Register Volume 71, Number 12 (Thursday, January 19, 2006)]
[Proposed Rules]
[Pages 3021-3023]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-532]


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

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

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


Federal Register / Vol. 71, No. 12 / Thursday, January 19, 2006 / 
Proposed Rules

[[Page 3021]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23633; Directorate Identifier 2005-NM-242-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A318-100 and A319-100 
Series Airplanes; Model A320-111 Airplanes; Model A320-200, A321-200, 
A330-200, A330-300, A340-200, and A340-300 Series Airplanes; Model 
A340-541 Airplanes; and Model A340-642 Airplanes; Equipped With Certain 
Sogerma-Services Powered Seats

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Airbus transport category airplanes. This proposed AD would 
require inspecting to determine if a certain actuator is installed in 
the pilot's or co-pilot's seat, and doing applicable corrective actions 
if necessary. For certain actuators, the proposed AD also would require 
replacing rotors on both vertical and horizontal movements with new 
rotors, and replacing the clutch cap with a new cap. This proposed AD 
results from a report of heavy wear at the driving gear of the rotor 
shaft end of the electrical driven motor on certain actuators of the 
pilot's and co-pilot's seats. We are proposing this AD to prevent 
uncommanded movement of the pilot's or co-pilot's seat during takeoff 
or landing, which could result in interference with the operation of 
the airplane and consequent temporary loss of airplane control.

DATES: We must receive comments on this proposed AD by February 21, 
2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Sogerma-Services, 109-17303 Rochefort, Cedex, France; and 
Messier-Bugatti, 45 Avenue Victor Hugo, 93538 Aubervilleirs, Cedex, 
France; for service information identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``FAA-2006-
23633; Directorate Identifier 2005-NM-242-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of 
that Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit https://dms.dot.gov.

Examining the Docket

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

Discussion

    The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), 
which is the airworthiness authority for France, notified us that an 
unsafe condition may exist on certain Airbus Model A318-100 and A319-
100 series airplanes; Model A320-111 airplanes; Model A320-200, A321-
200, A330-200, A330-300, A340-200, and A340-300 series airplanes; Model 
A340-541 airplanes; and Model A340-642 airplanes; equipped with certain 
Sogerma-Services pilot's and co-pilot's seats. The DGAC advises that, 
during overhaul of the pilot's and co-pilot's seats, repair stations 
found heavy wear at the driving gear of the rotor shaft end of the 
electrical driven motor on certain actuators. The electrical driven 
motor controls the horizontal and vertical movements of the seats. 
Investigation revealed that a manufacturing process error resulted in a 
batch of defective rotor shafts on certain actuators. This condition, 
if not corrected, could result in uncommanded movement of the pilot's 
or co-pilot's seat during takeoff or landing, which could result in 
interference with the operation of the airplane and consequent 
temporary loss of airplane control.

Relevant Service Information

    Sogerma-Services has issued Service Bulletin TAAI1-25-617, dated 
February 1, 2005. The service bulletin describes procedures for 
inspecting to determine if a certain actuator is installed in the 
pilot's or co-pilot's seat, and doing applicable corrective actions if

[[Page 3022]]

necessary. The corrective actions include:
     Replacing certain actuators with new actuators;
     Installing a new identification label for any replaced 
actuator; and
     Installing a new amendment label and writing the new 
amendment on it.
    Messier-Bugatti has issued Service Bulletins 4136290004-25-05 and 
4136290005-25-02, both dated April 2005. For certain airplanes, the 
service bulletins describe procedures for replacing rotors on both 
vertical and horizontal movements with new rotors, and replacing the 
clutch cap with a new cap.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. The DGAC mandated 
the service information and issued French airworthiness directive F-
2005-164, dated September 28, 2005, to ensure the continued 
airworthiness of these airplanes in France.

FAA's Determination and Requirements of the Proposed AD

    These airplane models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. We have examined the DGAC's findings, 
evaluated all pertinent information, and determined that we need to 
issue an AD for airplanes of this type design that are certificated for 
operation in the United States.
    Therefore, we are proposing this AD, which would require 
accomplishing the actions specified in the service information 
described previously.

Costs of Compliance

    This proposed AD would affect about 743 airplanes of U.S. registry. 
The proposed inspection would take about 1 work hour per airplane, at 
an average labor rate of $65 per work hour. Based on these figures, the 
estimated cost of the proposed AD for U.S. operators is $48,295, or $65 
per airplane.

Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

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

Airbus: Docket No. FAA-2006-23633; Directorate Identifier 2005-NM-
242-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by February 
21, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to the airplanes identified in table 1 of 
this AD, certificated in any category; equipped with any Sogerma-
Services pilot or co-pilot seat identified in Sogerma-Services 
Service Bulletin TAAI1-25-617, dated February 1, 2005, excluding any 
seat having part number (P/N) TAAI3-03PE00-01, TAAI3-03PE01-01, 
TAAI3-03CE00-01, and TAAI3-03CE01-01, with a serial number (S/N) 
higher than 791, on which the actuator has been replaced after the 
date of issuance of the original standard airworthiness certificate 
or date of issuance of the original export certificate of 
airworthiness.

                         Table 1.--Applicability
------------------------------------------------------------------------
                              Airbus model
-------------------------------------------------------------------------
(1) A318-111 and -112 airplanes.
(2) A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes.
(3) A320-111 airplanes.
(4) A320-211, -212, -214, -231, -232, and -233 airplanes.
(5) A321-211 and -231 airplanes.
(6) A330-201, -202, -203, -223, and -243 airplanes.
(7) A330-301, -321, -322, -323, -341, -342, and -343 airplanes.
(8) A340-211, -212, and -213 airplanes.
(9) A340-311, -312, and -313 airplanes.
(10) A340-541 airplanes.
(11) A340-642 airplanes.
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from a report of heavy wear at the driving 
gear of the rotor shaft end of the electrical driven motor on 
certain actuators of the pilot's and co-pilot's seats. We are 
issuing this AD to prevent uncommanded movement of the pilot's or 
co-pilot's seat during takeoff or landing, which could result in 
interference with the operation of the airplane and consequent 
temporary loss of airplane control.

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.

Inspection for the P/N of the Actuator

    (f) Within 56 months after the effective date of this AD, 
inspect to determine if an actuator identified in table 2 of this AD 
is installed in the pilot's or co-pilot's seat, in accordance with 
paragraph D., ``DESCRIPTION'' of Sogerma-Services Service Bulletin 
TAAI1-25-617, dated February 1, 2005. If any actuator identified in 
table 2 of this AD is found installed, within 56 months after the 
effective date of this AD, do the applicable corrective actions in 
accordance with paragraph 3., ``OPERATING INSTRUCTIONS,'' of the 
service bulletin.

[[Page 3023]]



                      Table 2.--Affected Actuators
------------------------------------------------------------------------
                     Manufacturer                         Actuator P/N
------------------------------------------------------------------------
(1) Messier-Bugatti...................................        4136290004
(2) Messier-Bugatti...................................        4136290005
(3) Aviac.............................................            6147-6
(4) Artus.............................................       AD8552502-1
------------------------------------------------------------------------

Concurrent Replacements

    (g) For Messier-Bugatti actuators identified in table 2 of this 
AD: Concurrently with the applicable corrective action required by 
paragraph (f) of this AD, replace the rotors on both vertical and 
horizontal movements with new rotors, and replace the clutch cap 
with a new cap, in accordance with Messier-Bugatti Service Bulletin 
4136290004-25-05 or 4136290005-25-02, both dated April 2005, as 
applicable.

Parts Installation

    (h) After the effective date of this AD, no actuator identified 
in table 2 of this AD may be installed on any airplane.

Alternative Methods of Compliance (AMOCs)

    (i)(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

    (j) French airworthiness directive F-2005-164, issued September 
28, 2005, also addresses the subject of this AD.

    Issued in Renton, Washington, on January 10, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E6-532 Filed 1-18-06; 8:45 am]
BILLING CODE 4910-13-P

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