Airworthiness Directives; Goodrich Evacuation Systems Approved Under Technical Standard Order (TSO) TSO-C69b and Installed on Airbus Model A330-200 and -300 Series Airplanes; Model A340-200 and -300 Series Airplanes; and Model A340-541 and -642 Airplanes, 7876-7878 [E6-2173]

Download as PDF 7876 Federal Register / Vol. 71, No. 31 / Wednesday, February 15, 2006 / Proposed Rules 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– 066, dated April 27, 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. E6–2175 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–2006–23890; Directorate Identifier 2005–NM–229–AD] RIN 2120–AA64 Airworthiness Directives; Goodrich Evacuation Systems Approved Under Technical Standard Order (TSO) TSO– C69b and Installed on Airbus Model A330–200 and –300 Series Airplanes; Model A340–200 and –300 Series Airplanes; and Model A340–541 and –642 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for Goodrich Evacuation Systems approved under TSO–C69b and installed on certain Airbus Model A330–200 and –300 series airplanes; Model A340–200 and –300 series airplanes; and Model A340–541 and –642 airplanes. This proposed AD would require inspecting to determine the part number of the pressure relief valves on the affected Goodrich evacuation systems, and corrective action if necessary. This proposed AD results from a report indicating that, during maintenance testing, the pressure relief valves on the affected Goodrich evacuation systems did not seal when activated, which caused the pressure in the escape slide/ cprice-sewell on PROD1PC66 with PROPOSALS SUMMARY: VerDate Aug<31>2005 15:04 Feb 14, 2006 Jkt 208001 raft to drop below the minimum allowable raft mode pressure. We are proposing this AD to prevent loss of pressure in the escape slides/rafts after an emergency evacuation, which could result in inadequate buoyancy to support the raft’s passenger capacity during ditching, and increase the chance for injury to raft passengers. 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 Goodrich, Aircraft Interior Products, ATTN: Technical Publications, 3414 South Fifth Street, Phoenix, AZ 85040, for service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Tracy Ton, Aerospace Engineer, Cabin Safety/Mechanical and Environmental Systems Branch, ANM–150L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5352; 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 ‘‘FAA–2006–23890; Directorate Identifier 2005–NM–229–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 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 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 We have received a report indicating that an unsafe condition may exist on certain Airbus Model A330–200 and –300 series airplanes; Model A340–200 and –300 series airplanes; and Model A340–541 and –642 airplanes; equipped with certain Goodrich evacuation systems. During maintenance testing, the pressure relief valves of the affected Goodrich evacuation systems did not seal when activated, which caused the pressure in the slide/raft to drop below the minimum allowable operating pressure. The affected Goodrich evacuation systems have certain part numbers (P/Ns) and are approved under Technical Standard Order (TSO) TSO– C69b. A review of service data indicates that there have been similar problems with pressure relief valves on multiple transport category airplane models. Loss of pressure in the escape slides/rafts after an emergency evacuation could result in inadequate buoyancy to support the raft’s passenger capacity during ditching, and increase the chance for injury to raft passengers. Relevant Service Information We have reviewed Goodrich Service Bulletin 25–355, dated July 25, 2005. The service bulletin describes procedures for inspecting to determine the P/N of the pressure relief valves on affected Goodrich evacuation systems, and corrective actions if necessary. The service bulletin also describes E:\FR\FM\15FEP1.SGM 15FEP1 Federal Register / Vol. 71, No. 31 / Wednesday, February 15, 2006 / Proposed Rules procedures for permanently marking the service bulletin number on the girt adjacent to the system identification placard to indicate compliance with the bulletin. The corrective action involves replacing any affected pressure relief valve on the affected evacuation system with a new valve. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. 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. Therefore, we are proposing this AD, which would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Difference Between This Proposed AD and the Service Bulletin.’’ cprice-sewell on PROD1PC66 with PROPOSALS Difference Between This Proposed AD and the Service Bulletin Although the service bulletin recommends accomplishing the inspection ‘‘at the next scheduled shop visit of the unit,’’ we have determined that this imprecise compliance time might not address the identified unsafe condition soon enough to ensure an adequate level of safety for the affected fleet. In developing an appropriate compliance time for this AD, we considered the manufacturer’s recommendation, the degree of urgency associated with the subject unsafe condition, and the average utilization of the affected fleet. In light of all of these factors, we find that a compliance time of 36 months for the inspection represents an appropriate interval of time for affected airplanes to continue to operate without compromising safety. Costs of Compliance This proposed AD would affect about 27 airplanes of U.S. registry. The proposed actions 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 $1,755, 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, VerDate Aug<31>2005 15:04 Feb 14, 2006 Jkt 208001 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. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 7877 by adding the following new airworthiness directive (AD): Airbus: Docket No. FAA–2006–23890; Directorate Identifier 2005–NM–229–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 Goodrich Evacuation Systems Approved Under Technical Standard Order (TSO) TSO–C69b and having any part number identified in Goodrich Service Bulletin 25–355, dated July 25, 2005, as installed on Airbus Model A330–201, –202, –203, –223, –243, –301, –321, –322, –323, –341, –342, and –343 airplanes; Model A340–211, –212, –213, –311, –312, and –313 airplanes; and Model A340–541 and –642 airplanes; certificated in any category. Unsafe Condition (d) This AD results from a report indicating that, during maintenance testing, the pressure relief valves of certain Goodrich evacuation systems did not seal when activated, which allowed the pressure in the slide/raft to drop below the minimum allowable raft mode pressure. We are issuing this AD to prevent loss of pressure in the escape slides/rafts after an emergency evacuation, which could result in inadequate buoyancy to support the raft’s passenger capacity during ditching, and increase the chance for injury to raft passengers. 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 36 months after the effective date of this AD: Perform an inspection to determine the part number (P/N) of the pressure relief valve on the Goodrich evacuation systems in accordance with the Accomplishment Instructions of Goodrich Service Bulletin 25–355, dated July 25, 2005. (1) If any pressure relief valve having P/N 4A3791–3 is installed, before further flight, replace the valve with a new or serviceable valve having P/N 4A3641–1 and mark the girt adjacent to the placard, in accordance with the Accomplishment Instructions of the service bulletin. (2) If any pressure release valve having P/ N 4A3641–1 is installed, before further flight, mark the girt adjacent to the placard in accordance with the Accomplishment Instructions of the service bulletin. Part Installation (g) As of the effective date of this AD, no person may install a pressure relief valve having P/N 4A3791–3, on any airplane equipped with Goodrich evacuation systems identified in Goodrich Service Bulletin 25– 355, dated July 25, 2005. E:\FR\FM\15FEP1.SGM 15FEP1 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

Agencies

[Federal Register Volume 71, Number 31 (Wednesday, February 15, 2006)]
[Proposed Rules]
[Pages 7876-7878]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-2173]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23890; Directorate Identifier 2005-NM-229-AD]
RIN 2120-AA64


Airworthiness Directives; Goodrich Evacuation Systems Approved 
Under Technical Standard Order (TSO) TSO-C69b and Installed on Airbus 
Model A330-200 and -300 Series Airplanes; Model A340-200 and -300 
Series Airplanes; and Model A340-541 and -642 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 Goodrich Evacuation Systems approved under TSO-C69b and installed 
on certain Airbus Model A330-200 and -300 series airplanes; Model A340-
200 and -300 series airplanes; and Model A340-541 and -642 airplanes. 
This proposed AD would require inspecting to determine the part number 
of the pressure relief valves on the affected Goodrich evacuation 
systems, and corrective action if necessary. This proposed AD results 
from a report indicating that, during maintenance testing, the pressure 
relief valves on the affected Goodrich evacuation systems did not seal 
when activated, which caused the pressure in the escape slide/raft to 
drop below the minimum allowable raft mode pressure. We are proposing 
this AD to prevent loss of pressure in the escape slides/rafts after an 
emergency evacuation, which could result in inadequate buoyancy to 
support the raft's passenger capacity during ditching, and increase the 
chance for injury to raft passengers.

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 Goodrich, Aircraft Interior Products, ATTN: Technical 
Publications, 3414 South Fifth Street, Phoenix, AZ 85040, for service 
information identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: Tracy Ton, Aerospace Engineer, Cabin 
Safety/Mechanical and Environmental Systems Branch, ANM-150L, FAA, Los 
Angeles Aircraft Certification Office, 3960 Paramount Boulevard, 
Lakewood, California 90712-4137; telephone (562) 627-5352; 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 ``FAA-2006-
23890; Directorate Identifier 2005-NM-229-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

    We have received a report indicating that an unsafe condition may 
exist on certain Airbus Model A330-200 and -300 series airplanes; Model 
A340-200 and -300 series airplanes; and Model A340-541 and -642 
airplanes; equipped with certain Goodrich evacuation systems. During 
maintenance testing, the pressure relief valves of the affected 
Goodrich evacuation systems did not seal when activated, which caused 
the pressure in the slide/raft to drop below the minimum allowable 
operating pressure. The affected Goodrich evacuation systems have 
certain part numbers (P/Ns) and are approved under Technical Standard 
Order (TSO) TSO-C69b. A review of service data indicates that there 
have been similar problems with pressure relief valves on multiple 
transport category airplane models. Loss of pressure in the escape 
slides/rafts after an emergency evacuation could result in inadequate 
buoyancy to support the raft's passenger capacity during ditching, and 
increase the chance for injury to raft passengers.

Relevant Service Information

    We have reviewed Goodrich Service Bulletin 25-355, dated July 25, 
2005. The service bulletin describes procedures for inspecting to 
determine the P/N of the pressure relief valves on affected Goodrich 
evacuation systems, and corrective actions if necessary. The service 
bulletin also describes

[[Page 7877]]

procedures for permanently marking the service bulletin number on the 
girt adjacent to the system identification placard to indicate 
compliance with the bulletin. The corrective action involves replacing 
any affected pressure relief valve on the affected evacuation system 
with a new valve. Accomplishing the actions specified in the service 
information is intended to adequately address the unsafe condition.

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.
    Therefore, we are proposing this AD, which would require 
accomplishing the actions specified in the service information 
described previously, except as discussed under ``Difference Between 
This Proposed AD and the Service Bulletin.''

Difference Between This Proposed AD and the Service Bulletin

    Although the service bulletin recommends accomplishing the 
inspection ``at the next scheduled shop visit of the unit,'' we have 
determined that this imprecise compliance time might not address the 
identified unsafe condition soon enough to ensure an adequate level of 
safety for the affected fleet. In developing an appropriate compliance 
time for this AD, we considered the manufacturer's recommendation, the 
degree of urgency associated with the subject unsafe condition, and the 
average utilization of the affected fleet. In light of all of these 
factors, we find that a compliance time of 36 months for the inspection 
represents an appropriate interval of time for affected airplanes to 
continue to operate without compromising safety.

Costs of Compliance

    This proposed AD would affect about 27 airplanes of U.S. registry. 
The proposed actions 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 $1,755, 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-2006-23890; Directorate Identifier 2005-NM-
229-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 Goodrich Evacuation Systems Approved 
Under Technical Standard Order (TSO) TSO-C69b and having any part 
number identified in Goodrich Service Bulletin 25-355, dated July 
25, 2005, as installed on Airbus Model A330-201, -202, -203, -223, -
243, -301, -321, -322, -323, -341, -342, and -343 airplanes; Model 
A340-211, -212, -213, -311, -312, and -313 airplanes; and Model 
A340-541 and -642 airplanes; certificated in any category.

Unsafe Condition

    (d) This AD results from a report indicating that, during 
maintenance testing, the pressure relief valves of certain Goodrich 
evacuation systems did not seal when activated, which allowed the 
pressure in the slide/raft to drop below the minimum allowable raft 
mode pressure. We are issuing this AD to prevent loss of pressure in 
the escape slides/rafts after an emergency evacuation, which could 
result in inadequate buoyancy to support the raft's passenger 
capacity during ditching, and increase the chance for injury to raft 
passengers.

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 36 months after the effective date of this AD: 
Perform an inspection to determine the part number (P/N) of the 
pressure relief valve on the Goodrich evacuation systems in 
accordance with the Accomplishment Instructions of Goodrich Service 
Bulletin 25-355, dated July 25, 2005.
    (1) If any pressure relief valve having P/N 4A3791-3 is 
installed, before further flight, replace the valve with a new or 
serviceable valve having P/N 4A3641-1 and mark the girt adjacent to 
the placard, in accordance with the Accomplishment Instructions of 
the service bulletin.
    (2) If any pressure release valve having P/N 4A3641-1 is 
installed, before further flight, mark the girt adjacent to the 
placard in accordance with the Accomplishment Instructions of the 
service bulletin.

Part Installation

    (g) As of the effective date of this AD, no person may install a 
pressure relief valve having P/N 4A3791-3, on any airplane equipped 
with Goodrich evacuation systems identified in Goodrich Service 
Bulletin 25-355, dated July 25, 2005.

[[Page 7878]]

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 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) 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