Airworthiness Directives; Airbus Model A318-111 Airplanes; A319-100 Series Airplanes; A320-111 Airplanes; A320-200 Series Airplanes; and A321-100 and -200 Series Airplanes, 7878-7880 [E6-2172]

Download as PDF 7878 Federal Register / Vol. 71, No. 31 / Wednesday, February 15, 2006 / Proposed Rules Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, Los Angeles Aircraft Certification Office (ACO), 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 (i) None. Issued in Renton, Washington, on February 7, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–2173 Filed 2–14–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–23889; Directorate Identifier 2005–NM–252–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A318–111 Airplanes; A319–100 Series Airplanes; A320–111 Airplanes; A320– 200 Series Airplanes; and A321–100 and –200 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). cprice-sewell on PROD1PC66 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 the part number of the twin motor actuators, and related investigative and corrective actions if necessary. This proposed AD results from a report of a low pressure valve of the twin motor actuator found partially open, although the valve detection system indicated that the valve was closed. Investigation revealed that the locating pin in the actuator was too short to engage with the valve slot, resulting in incorrect alignment of the actuator and the drive assembly, causing the valve to remain partially open. We are proposing this AD to ensure that, in the event of an engine fire, the valve actuator functions properly to delay or block the fuel flow to the engine and prevent an uncontrollable fire. VerDate Aug<31>2005 15:04 Feb 14, 2006 Jkt 208001 We must receive comments on this proposed AD by March 17, 2006. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: 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: DATES: 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–2006–23889; Directorate Identifier 2005–NM–252–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 http:// 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 PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 published on April 11, 2000 (65 FR 19477–78), or you may visit http:// dms.dot.gov. Examining the Docket You may 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 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 transport category airplanes. The DGAC advises that it received a report of a low pressure valve of the twin motor actuator found partially open, although the valve detection system indicated that the valve was closed. Investigation revealed that the locating pin in the actuator was too short to engage with the valve slot, resulting in incorrect alignment. The cause of the defective locating pin was erroneous manufacturing tolerances. In the event of an engine fire, proper functioning of the valve actuator will delay or block the fuel flow to the engine and prevent an uncontrollable fire. Relevant Service Information Airbus has issued Service Bulletin A320–28–1122, including Appendix 01, dated November 19, 2004. The service bulletin describes procedures for inspecting to determine the part number of the twin motor actuators, and related investigative and corrective actions if necessary. If there is no affected actuator, the service bulletin specifies that no further action is required. If there is any affected actuator, the service bulletin specifies that operators should do the related investigative action of inspecting the locating pin of the valve of the twin-motor actuator for damage or misalignment, and accomplish all necessary corrective actions. The corrective action includes replacing any defective pin and repairing any damage to the actuator or drive assembly to ensure correct alignment can be attained. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The DGAC mandated the E:\FR\FM\15FEP1.SGM 15FEP1 Federal Register / Vol. 71, No. 31 / Wednesday, February 15, 2006 / Proposed Rules service information and issued French airworthiness directive F–2005–189, dated November 23, 2005, to ensure the continued airworthiness of these airplanes in France. The Airbus service bulletin refers to FR–HITEMP Service Bulletin HTE190001–28–003, dated March 30, 2004, as an additional source of service information for determining the part number of the twin motor actuators and accomplishing any related investigative and corrective actions. 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 Airbus service information described previously. Clarification of Inspection Language The French airworthiness directive and the service bulletin request that operators ‘‘inspect’’ the twin motor actuators to determine the part number. This proposed AD defines that inspection as a ‘‘general visual inspection.’’ This inspection is defined in Note 1 of this proposed AD. cprice-sewell on PROD1PC66 with PROPOSALS Costs of Compliance This proposed AD would affect about 719 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 $46,735, 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, VerDate Aug<31>2005 15:04 Feb 14, 2006 Jkt 208001 ‘‘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–2006–23889; Directorate Identifier 2005–NM–252–AD. PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 7879 Comments Due Date (a) The FAA must receive comments on this AD action by March 17, 2006. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A318– 111; A319–111, –112, –113, –114, –115, –131, –132, and –133; A320–111, –211, –212, –214, –231, –232, and –233; and A321–111, –112, –131, –211 and –231 airplanes; certificated in any category. Unsafe Condition (d) This AD results from a report of a low pressure valve of the twin motor actuator found partially open, although the valve detection system indicated that the valve was closed. Investigation revealed that the locating pin in the actuator was too short to engage with the valve slot, resulting in incorrect alignment of the actuator and the drive assembly, causing the valve to remain partially open. We are issuing this AD to ensure that, in the event of an engine fire, the valve actuator functions properly to delay or block the fuel flow to the engine and prevent an uncontrollable fire. 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 (f) Within 6,000 flight hours or 24 months after the effective date of this AD, whichever is first: Accomplish a one-time general visual inspection to determine the part number (P/ N) of the twin motor actuators in accordance with Airbus Service Bulletin A320–28–1122, including Appendix 01, dated November 19, 2004. (1) For airplanes having any actuator with P/N FRH010041 or P/N FRH010034, no further action is required by this paragraph. (2) For airplanes having any actuator with P/N HTE190001–2, where the actuator serial number is not identified in Appendix 01 of the service bulletin, no further action is required by this paragraph. (3) For airplanes having any actuator with P/N HTE190001, HTE190001–1, or HTE190001–2, where the actuator serial number is identified in Appendix 01 of the service bulletin, do all applicable related investigative and corrective actions before further flight, in accordance with the service bulletin. Note 1: For the purposes of this AD, a general visual inspection is: ‘‘A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, E:\FR\FM\15FEP1.SGM 15FEP1 7880 Federal Register / Vol. 71, No. 31 / Wednesday, February 15, 2006 / Proposed Rules cprice-sewell on PROD1PC66 with PROPOSALS ladders, or platforms may be required to gain proximity to the area being checked.’’ directive (AD) that applies to certain McDonnell Douglas Model MD–11 series airplanes. The existing AD Note 2: Airbus Service Bulletin A320–28– 1122, dated November 19, 2004, refers to FR– currently requires a revision of the HITEMP Service Bulletin HTE190001–28– airplane flight manual (AFM) to alert 003, dated March 30, 2004, as an additional the flightcrew that both flight source of service information for determining management computers (FMC) must be the part number of the twin motor actuators installed and operational. The existing and accomplishing any related investigative AD also requires an inspection to and corrective actions. determine the serial number of the FMCs; and follow-on corrective actions, Parts Installation if necessary, which terminate the AFM (g) As of the effective date of this AD: No revision. The existing AD also requires person may install an actuator with P/N HTE190001, HTE190001–1, or HTE190001–2, an inspection to verify if a certain and a serial number identified in Appendix modification is on the identification 01 of Airbus Service Bulletin A320–28–1122, plates of the FMCs; and applicable dated November 19, 2004, on any airplane follow-on and corrective actions. This unless all applicable related investigative and proposed AD would require installation corrective actions have been done in of upgraded flight management accordance with the requirements of computer software, which would paragraph (f)(3) of this AD. terminate the existing AD. This Alternative Methods of Compliance proposed AD would also add airplanes (AMOCs) to the applicability, including adding (h)(1) The Manager, International Branch, Model MD–10–10F and MD–10–30F ANM–116, Transport Airplane Directorate, airplanes. This proposed AD results FAA, has the authority to approve AMOCs from a report that the FMC does not for this AD, if requested in accordance with acknowledge the pre-set glareshield the procedures found in 14 CFR 39.19. control panel (GCP) altitude when (2) Before using any AMOC approved in profile (PROF) mode is engaged in accordance with § 39.19 on any airplane to descent mode. We are proposing this which the AMOC applies, notify the AD to prevent the un-commanded appropriate principal inspector in the FAA Flight Standards Certificate Holding District descent of an airplane below the Office. selected level-off altitude, which could result in an unacceptable reduction in Related Information the separation between the airplane and (i) French airworthiness directive F–2005– nearby air traffic or terrain. 189, dated November 23, 2005, also DATES: We must receive comments on addresses the subject of this AD. Issued in Renton, Washington, on February this proposed AD by April 3, 2006. ADDRESSES: Use one of the following 6, 2006. addresses to submit comments on this Kalene C. Yanamura, proposed AD. Acting Manager, Transport Airplane • DOT Docket Web site: Go to Directorate, Aircraft Certification Service. http://dms.dot.gov and follow the [FR Doc. E6–2172 Filed 2–14–06; 8:45 am] instructions for sending your comments BILLING CODE 4910–13–P electronically. • Government-wide rulemaking Web site: Go to http://www.regulations.gov DEPARTMENT OF TRANSPORTATION and follow the instructions for sending your comments electronically. Federal Aviation Administration • Mail: Docket Management Facility; U.S. Department of Transportation, 400 14 CFR Part 39 Seventh Street SW., Nassif Building, [Docket No. FAA–2006–23850; Directorate room PL–401, Washington, DC 20590. Identifier 2005–NM–126–AD] • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on RIN 2120–AA64 the plaza level of the Nassif Building, Airworthiness Directives; McDonnell 400 Seventh Street SW., Washington, Douglas Model MD–10–10F and MD– DC, between 9 a.m. and 5 p.m., Monday 10–30F Airplanes and Model MD–11 through Friday, except Federal holidays. and MD–11F Airplanes Contact Boeing Commercial Airplanes, Long Beach Division, 3855 AGENCY: Federal Aviation Lakewood Boulevard, Long Beach, Administration (FAA), Department of California 90846, Attention: Data and Transportation (DOT). Service Management, Dept. C1–L5A ACTION: Notice of proposed rulemaking (D800–0024), for service information (NPRM). identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: SUMMARY: The FAA proposes to Natalie Phan-Tran, Aerospace Engineer, supersede an existing airworthiness VerDate Aug<31>2005 15:04 Feb 14, 2006 Jkt 208001 PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 Systems and Equipment Branch, ANM– 130L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5343; fax (562) 627–5210. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘Docket No. FAA–2006–23850; Directorate Identifier 2005–NM–126– 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 http:// 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 visit http://dms.dot.gov. Examining the Docket You may 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 DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion On October 15, 2001, we issued AD 2001–21–05, amendment 39–12476 (66 FR 53335, October 22, 2001), for certain McDonnell Douglas Model MD–11 series airplanes. That AD requires a revision of the airplane flight manual (AFM) to alert the flightcrew that both flight management computers (FMC) must be installed and operational. That AD also requires an inspection to E:\FR\FM\15FEP1.SGM 15FEP1

Agencies

[Federal Register Volume 71, Number 31 (Wednesday, February 15, 2006)]
[Proposed Rules]
[Pages 7878-7880]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-2172]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23889; Directorate Identifier 2005-NM-252-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A318-111 Airplanes; A319-
100 Series Airplanes; A320-111 Airplanes; A320-200 Series Airplanes; 
and A321-100 and -200 Series Airplanes

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 the part number of the twin motor 
actuators, and related investigative and corrective actions if 
necessary. This proposed AD results from a report of a low pressure 
valve of the twin motor actuator found partially open, although the 
valve detection system indicated that the valve was closed. 
Investigation revealed that the locating pin in the actuator was too 
short to engage with the valve slot, resulting in incorrect alignment 
of the actuator and the drive assembly, causing the valve to remain 
partially open. We are proposing this AD to ensure that, in the event 
of an engine fire, the valve actuator functions properly to delay or 
block the fuel flow to the engine and prevent an uncontrollable fire.

DATES: We must receive comments on this proposed AD by March 17, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: 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-
23889; Directorate Identifier 2005-NM-252-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 http://
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 http://dms.dot.gov.

Examining the Docket

    You may 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 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 transport category 
airplanes. The DGAC advises that it received a report of a low pressure 
valve of the twin motor actuator found partially open, although the 
valve detection system indicated that the valve was closed. 
Investigation revealed that the locating pin in the actuator was too 
short to engage with the valve slot, resulting in incorrect alignment. 
The cause of the defective locating pin was erroneous manufacturing 
tolerances. In the event of an engine fire, proper functioning of the 
valve actuator will delay or block the fuel flow to the engine and 
prevent an uncontrollable fire.

Relevant Service Information

    Airbus has issued Service Bulletin A320-28-1122, including Appendix 
01, dated November 19, 2004. The service bulletin describes procedures 
for inspecting to determine the part number of the twin motor 
actuators, and related investigative and corrective actions if 
necessary. If there is no affected actuator, the service bulletin 
specifies that no further action is required. If there is any affected 
actuator, the service bulletin specifies that operators should do the 
related investigative action of inspecting the locating pin of the 
valve of the twin-motor actuator for damage or misalignment, and 
accomplish all necessary corrective actions. The corrective action 
includes replacing any defective pin and repairing any damage to the 
actuator or drive assembly to ensure correct alignment can be attained. 
Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. The DGAC mandated 
the

[[Page 7879]]

service information and issued French airworthiness directive F-2005-
189, dated November 23, 2005, to ensure the continued airworthiness of 
these airplanes in France.
    The Airbus service bulletin refers to FR-HITEMP Service Bulletin 
HTE190001-28-003, dated March 30, 2004, as an additional source of 
service information for determining the part number of the twin motor 
actuators and accomplishing any related investigative and corrective 
actions.

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 Airbus service information 
described previously.

Clarification of Inspection Language

    The French airworthiness directive and the service bulletin request 
that operators ``inspect'' the twin motor actuators to determine the 
part number. This proposed AD defines that inspection as a ``general 
visual inspection.'' This inspection is defined in Note 1 of this 
proposed AD.

Costs of Compliance

    This proposed AD would affect about 719 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 $46,735, 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-2006-23889; Directorate Identifier 2005-NM-
252-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by March 17, 
2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A318-111; A319-111, -112, -
113, -114, -115, -131, -132, and -133; A320-111, -211, -212, -214, -
231, -232, and -233; and A321-111, -112, -131, -211 and -231 
airplanes; certificated in any category.

Unsafe Condition

    (d) This AD results from a report of a low pressure valve of the 
twin motor actuator found partially open, although the valve 
detection system indicated that the valve was closed. Investigation 
revealed that the locating pin in the actuator was too short to 
engage with the valve slot, resulting in incorrect alignment of the 
actuator and the drive assembly, causing the valve to remain 
partially open. We are issuing this AD to ensure that, in the event 
of an engine fire, the valve actuator functions properly to delay or 
block the fuel flow to the engine and prevent an uncontrollable 
fire.

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

    (f) Within 6,000 flight hours or 24 months after the effective 
date of this AD, whichever is first: Accomplish a one-time general 
visual inspection to determine the part number (P/N) of the twin 
motor actuators in accordance with Airbus Service Bulletin A320-28-
1122, including Appendix 01, dated November 19, 2004.
    (1) For airplanes having any actuator with P/N FRH010041 or P/N 
FRH010034, no further action is required by this paragraph.
    (2) For airplanes having any actuator with P/N HTE190001-2, 
where the actuator serial number is not identified in Appendix 01 of 
the service bulletin, no further action is required by this 
paragraph.
    (3) For airplanes having any actuator with P/N HTE190001, 
HTE190001-1, or HTE190001-2, where the actuator serial number is 
identified in Appendix 01 of the service bulletin, do all applicable 
related investigative and corrective actions before further flight, 
in accordance with the service bulletin.


    Note 1: For the purposes of this AD, a general visual inspection 
is: ``A visual examination of an interior or exterior area, 
installation, or assembly to detect obvious damage, failure, or 
irregularity. This level of inspection is made from within touching 
distance unless otherwise specified. A mirror may be necessary to 
ensure visual access to all surfaces in the inspection area. This 
level of inspection is made under normally available lighting 
conditions such as daylight, hangar lighting, flashlight, or 
droplight and may require removal or opening of access panels or 
doors. Stands,

[[Page 7880]]

ladders, or platforms may be required to gain proximity to the area 
being checked.''


    Note 2: Airbus Service Bulletin A320-28-1122, dated November 19, 
2004, refers to FR-HITEMP Service Bulletin HTE190001-28-003, dated 
March 30, 2004, as an additional source of service information for 
determining the part number of the twin motor actuators and 
accomplishing any related investigative and corrective actions.

Parts Installation

    (g) As of the effective date of this AD: No person may install 
an actuator with P/N HTE190001, HTE190001-1, or HTE190001-2, and a 
serial number identified in Appendix 01 of Airbus Service Bulletin 
A320-28-1122, dated November 19, 2004, on any airplane unless all 
applicable related investigative and corrective actions have been 
done in accordance with the requirements of paragraph (f)(3) of this 
AD.

Alternative Methods of Compliance (AMOCs)

    (h)(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

    (i) French airworthiness directive F-2005-189, dated November 
23, 2005, also addresses the subject of this AD.

    Issued in Renton, Washington, on February 6, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-2172 Filed 2-14-06; 8:45 am]
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