Airworthiness Directives; Airbus Model A321 Series Airplanes, 32542-32544 [05-11061]

Download as PDF 32542 Federal Register / Vol. 70, No. 106 / Friday, June 3, 2005 / Proposed Rules Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): Saab Aircraft AB: Docket No. FAA–2005– 21341; Directorate Identifier 2003–NM– 026–AD. Comments Due Date (a) The Federal Aviation Administration must receive comments on this AD action by July 5, 2005. Affected ADs (b) None. Applicability (c) This AD applies to certain Saab Model SAAB 2000 series airplanes having Serial Numbers 004 through 063 inclusive; certificated in any category. Unsafe Condition (d) This AD was prompted by a report of cracking of certain fastener holes in the lower spar cap of the rear spar and in the lower skin at the front spar. We are issuing this AD to prevent cracking of the front and rear spar, which could result in fuel leakage and consequent reduced structural integrity of the wing structure. 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) Prior to the accumulation of 20,000 total flight cycles, perform non-destructive tests for cracking of the fastener holes in the lower spar cap of the rear spar and in the lower skin at the left-hand and right-hand sides of the front spar, between WS20 and WS83 inclusive; by accomplishing all the actions specified in Parts A, B, and C of the Accomplishment Instructions of Saab Service Bulletin 2000–57–038, dated December 18, 2002. If any cracking is detected, before further flight, repair the cracking according to a method approved by the Manager, International Branch, ANM–116, FAA, Transport Airplane Directorate, or the Luftfartsverket (LFV) (or its delegated agent). Modification (g) Prior to the accumulation of 20,000 total flight cycles, modify the fastener holes of the front and rear spars and the rear spar web, including related investigative actions, by accomplishing all the actions specified in Part D of the Accomplishment Instructions of Saab Service Bulletin 2000–57–38, dated December 18, 2002. If 1⁄4-inch fasteners are needed for holes No. 7 and No. 8, before further flight, contact the Manager, International Branch, ANM116, FAA, Transport Airplane Directorate for further actions, or the LFV (or its delegated agent). If any scratches or other damage is detected on the skin surface or the surface of the front spar, before further flight, repair in accordance with a method approved by the VerDate jul<14>2003 17:25 Jun 02, 2005 Jkt 205001 Manager, International Branch, ANM–116, FAA, Transport Airplane Directorate, or the Luftfartsverket (LFV) (or its delegated agent.) Alternative Methods of Compliance (AMOCs) (h) 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. Related Information (i) Swedish airworthiness directive 1–182, dated December 20, 2002, also addresses the subject of this AD. Issued in Renton, Washington, on May 26, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–11060 Filed 6–2–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–21342; Directorate Identifier 2004–NM–15–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A321 Series 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 certain Airbus Model A321 series airplanes. This proposed AD would require repetitive measurements for correct control rod gap of the hold-open mechanism of all emergency doors, and corrective actions if necessary. This proposed AD would also require replacing the control rods with new, improved control rods, which would terminate the repetitive measurements. This proposed AD is prompted by a report that an operator found it impossible to lock emergency doors 2 and 3 in the open position. We are proposing this AD to prevent failure of the emergency doors to lock in the open position, which could interfere with passenger evacuation during an emergency. SUMMARY: We must receive comments on this proposed AD by July 5, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. DATES: PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 • 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. • By 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. For service information identified in this proposed AD, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. You can examine the contents of this AD docket on the Internet at http:// dms.dot.gov, or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, on the plaza level of the Nassif Building, Washington, DC. This docket number is FAA–2005– 21342; the directorate identifier for this docket is 2004–NM–15–AD. FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2141; 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 under ADDRESSES. Include ‘‘Docket No. FAA– 2005–21342; Directorate Identifier 2004–NM–15–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 submitted 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 our docket Web site, anyone can find and read the comments in any of our dockets, including the name of the individual E:\FR\FM\03JNP1.SGM 03JNP1 Federal Register / Vol. 70, No. 106 / Friday, June 3, 2005 / Proposed Rules who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You can review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you can visit http:// dms.dot.gov. Examining the Docket You can examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the DMS 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 A321 series airplanes. The DGAC advises that an operator found it impossible to lock emergency doors 2 and 3 in the open position due to an incorrect gap of the polyamide control rods of the hold-open release mechanisms. Investigation revealed that the polyamide control rod had lengthened due to water absorption and kept the hold-open mechanism constantly activated in the release position. This condition, if not corrected, could lead to failure of the emergency doors to lock in the open position, which could interfere with passenger evacuation during an emergency. Relevant Service Information Airbus has issued All Operators Telex (AOT) A320–52A1120, Revision 2, dated July 10, 2003. The AOT describes procedures for repetitive measurements to determine correct control rod gap of the hold-open mechanism of the emergency doors, and corrective actions if necessary. Corrective actions include shortening the polyamide control rod if it is too long or, if it is too short, replacing the rod with a new polyamide control rod or an aluminum control rod. Airbus has issued Service Bulletin A320–52–1121, dated December 12, 2003. The service bulletin describes procedures for replacing the polyamide or interim aluminum control rods with new, improved, water-resistant control rods. Interim or final replacement of the polyamide control rod eliminates the need for the repetitive measurements VerDate jul<14>2003 17:25 Jun 02, 2005 Jkt 205001 described by the AOT for that control rod. 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–2004–040, dated March 31, 2004, to ensure the continued airworthiness of these airplanes in France. FAA’s Determination and Requirements of the Proposed AD This airplane model is manufactured in France and is type certificated for operation in the United States under the provisions of § 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 products 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, except as discussed under ‘‘Differences Between French Airworthiness Directive and This Proposed AD.’’ Differences Between French Airworthiness Directive and This Proposed AD The applicability of French airworthiness directive F–2004–040 excludes airplanes on which Airbus Service Bulletin A320–52–1121 was done in service. However, we have not excluded those airplanes in the applicability of this proposed AD; rather, this proposed AD includes a requirement to accomplish the actions specified in that service bulletin. This requirement would ensure that the actions specified in the service bulletin and required by this proposed AD are accomplished on all affected airplanes. Operators must continue to operate the airplane in the configuration required by this proposed AD unless an alternative method of compliance is approved. This difference has been coordinated with the DGAC. French airworthiness directive F– 2004–040 specifies to ‘‘inspect’’ the hold-open mechanism. To prevent any confusion, rather than an ‘‘inspection’’ of the hold-open mechanism, this proposed AD would require a ‘‘measurement’’ to determine the control PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 32543 rod gap of the hold-open mechanism, as specified in the AOT. Clarification of Service Information The service information specifies procedures for reporting measurement results and accomplishment of the control rod replacement to the manufacturer; however, this proposed AD would not make this requirement. The FAA does not need this information from operators. Costs of Compliance This proposed AD would affect about 28 airplanes of U.S. registry. The measurement to determine control rod gap would take about 2 work hours per airplane, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the proposed measurement for U.S. operators is $3,640, or $130 per airplane, per measurement cycle. The replacement of the control rods with new, improved, water-resistant control rods would take about 9 work hours per airplane, at an average labor rate of $65 per work hour. Required parts would cost about $400 per airplane. Based on these figures, the estimated cost of the proposed replacement for U.S. operators is $27,580, or $985 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 E:\FR\FM\03JNP1.SGM 03JNP1 32544 Federal Register / Vol. 70, No. 106 / Friday, June 3, 2005 / Proposed Rules 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. 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 FAA amends § 39.13 by adding the following new airworthiness directive (AD): Airbus: Docket No. FAA–2005–21342; Directorate Identifier 2004–NM–15–AD. Comments Due Date (a) The Federal Aviation Administration must receive comments on this AD action by July 5, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A321 series airplanes, certificated in any category; except for those airplanes that have received Airbus Modification 33426 in production. Unsafe Condition (d) This AD was prompted by a report that an operator found it impossible to lock emergency doors 2 and 3 in the open position. We are issuing this AD to prevent failure of the emergency doors to lock in the open position, which could interfere with passenger evacuation during an emergency. 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. VerDate jul<14>2003 17:25 Jun 02, 2005 Jkt 205001 Inspection of Emergency Exit Doors (f) Within 600 flight hours after the effective date of this AD and thereafter at intervals not to exceed 600 flight hours, perform a measurement for correct gap of the control rod of the hold-open mechanism of all emergency doors, in accordance with Airbus All Operators Telex (AOT) A320– 52A1120, Revision 2, dated July 10, 2003. If the gap of any control rod is not correct, prior to further flight, apply all necessary corrective actions in accordance with the AOT. Optional Interim Terminating Action (g) Replacing the polyamide control rod of any mechanism with an aluminum control rod prior to accomplishing paragraph (h) of this AD, as specified in AOT A320–52A1120, Revision 2, dated July 10, 2003, terminates the repetitive measurement required by paragraph (f) of this AD for that mechanism. Final Terminating Action (h) Within 18 months after the effective date of this AD, replace the polyamide or interim aluminum control rods of the release mechanisms with new, improved, waterresistant control rods according to the Accomplishment Instructions of Airbus Service Bulletin A320–52–1121, dated December 12, 2003. This replacement terminates the repetitive measurement required by paragraph (f) of this AD. Actions Accomplished Per Previous Issue of Service Bulletin (i) Actions accomplished before the effective date of this AD according to Airbus AOT A320–52A1120, dated June 5, 2003, or Revision 1, dated June 19, 2003, are considered acceptable for compliance with the corresponding actions specified in this AD. No Reporting Requirement (j) Although the service information specifies procedures for reporting measurement results and control rod replacement to the manufacturer, this AD does not require these reports. Alternative Methods of Compliance (AMOCs) (k) 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. Related Information (l) French airworthiness directive F–2004– 040, dated March 31, 2004, also addresses the subject of this AD. Issued in Renton, Washington, on May 26, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–11061 Filed 6–2–05; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00021 Fmt 4702 Sfmt 4702 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–21345; Directorate Identifier 2005–NM–005–AD] RIN 2120–AA64 Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model ERJ 170 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for all EMBRAER Model ERJ 170 series airplanes. This proposed AD would require inspecting the hydraulic pressure tubes at the outlet of the engine-driven hydraulic pumps to determine the part and serial numbers; and replacing hydraulic pressure tubes having certain serial numbers with new hydraulic pressure tubes. This proposed AD is prompted by failure of a hydraulic system due to leakage of hydraulic fluid from a crack in the pipe coming from the pressure side of the engine driven pump. We are proposing this AD to prevent cracking of the hydraulic pressure pipes, which could result in failure of hydraulic system 1 or 2 or both, and consequent reduced controllability of the airplane. DATES: We must receive comments on this proposed AD by July 5, 2005. 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. • By 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. For service information identified in this proposed AD, contact Empresa Brasileira de Aeronautica S.A. (EMBRAER), P.O. Box 343—CEP 12.225, Sao Jose dos Campos—SP, Brazil. E:\FR\FM\03JNP1.SGM 03JNP1

Agencies

[Federal Register Volume 70, Number 106 (Friday, June 3, 2005)]
[Proposed Rules]
[Pages 32542-32544]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-11061]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21342; Directorate Identifier 2004-NM-15-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A321 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 Model A321 series airplanes. This proposed AD would 
require repetitive measurements for correct control rod gap of the 
hold-open mechanism of all emergency doors, and corrective actions if 
necessary. This proposed AD would also require replacing the control 
rods with new, improved control rods, which would terminate the 
repetitive measurements. This proposed AD is prompted by a report that 
an operator found it impossible to lock emergency doors 2 and 3 in the 
open position. We are proposing this AD to prevent failure of the 
emergency doors to lock in the open position, which could interfere 
with passenger evacuation during an emergency.

DATES: We must receive comments on this proposed AD by July 5, 2005.

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.
     By 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.
    For service information identified in this proposed AD, contact 
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
    You can examine the contents of this AD docket on the Internet at 
http://dms.dot.gov, or in person at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, 
on the plaza level of the Nassif Building, Washington, DC. This docket 
number is FAA-2005-21342; the directorate identifier for this docket is 
2004-NM-15-AD.

FOR FURTHER INFORMATION CONTACT: Tim Dulin, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2141; 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 under ADDRESSES. Include ``Docket No. FAA-2005-21342; 
Directorate Identifier 2004-NM-15-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 submitted 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 our 
docket Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual

[[Page 32543]]

who sent the comment (or signed the comment on behalf of an 
association, business, labor union, etc.). You can review the DOT's 
complete Privacy Act Statement in the Federal Register published on 
April 11, 2000 (65 FR 19477-78), or you can visit http://dms.dot.gov.

Examining the Docket

    You can examine the AD docket on the Internet at http://
dms.dot.gov, or in person at the Docket Management Facility office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the DMS 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 A321 series 
airplanes. The DGAC advises that an operator found it impossible to 
lock emergency doors 2 and 3 in the open position due to an incorrect 
gap of the polyamide control rods of the hold-open release mechanisms. 
Investigation revealed that the polyamide control rod had lengthened 
due to water absorption and kept the hold-open mechanism constantly 
activated in the release position. This condition, if not corrected, 
could lead to failure of the emergency doors to lock in the open 
position, which could interfere with passenger evacuation during an 
emergency.

Relevant Service Information

    Airbus has issued All Operators Telex (AOT) A320-52A1120, Revision 
2, dated July 10, 2003. The AOT describes procedures for repetitive 
measurements to determine correct control rod gap of the hold-open 
mechanism of the emergency doors, and corrective actions if necessary. 
Corrective actions include shortening the polyamide control rod if it 
is too long or, if it is too short, replacing the rod with a new 
polyamide control rod or an aluminum control rod.
    Airbus has issued Service Bulletin A320-52-1121, dated December 12, 
2003. The service bulletin describes procedures for replacing the 
polyamide or interim aluminum control rods with new, improved, water-
resistant control rods. Interim or final replacement of the polyamide 
control rod eliminates the need for the repetitive measurements 
described by the AOT for that control rod.
    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-
2004-040, dated March 31, 2004, to ensure the continued airworthiness 
of these airplanes in France.

FAA's Determination and Requirements of the Proposed AD

    This airplane model is manufactured in France and is type 
certificated for operation in the United States under the provisions of 
Sec.  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 products 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, except as discussed under ``Differences Between 
French Airworthiness Directive and This Proposed AD.''

Differences Between French Airworthiness Directive and This Proposed AD

    The applicability of French airworthiness directive F-2004-040 
excludes airplanes on which Airbus Service Bulletin A320-52-1121 was 
done in service. However, we have not excluded those airplanes in the 
applicability of this proposed AD; rather, this proposed AD includes a 
requirement to accomplish the actions specified in that service 
bulletin. This requirement would ensure that the actions specified in 
the service bulletin and required by this proposed AD are accomplished 
on all affected airplanes. Operators must continue to operate the 
airplane in the configuration required by this proposed AD unless an 
alternative method of compliance is approved. This difference has been 
coordinated with the DGAC.
    French airworthiness directive F-2004-040 specifies to ``inspect'' 
the hold-open mechanism. To prevent any confusion, rather than an 
``inspection'' of the hold-open mechanism, this proposed AD would 
require a ``measurement'' to determine the control rod gap of the hold-
open mechanism, as specified in the AOT.

Clarification of Service Information

    The service information specifies procedures for reporting 
measurement results and accomplishment of the control rod replacement 
to the manufacturer; however, this proposed AD would not make this 
requirement. The FAA does not need this information from operators.

Costs of Compliance

    This proposed AD would affect about 28 airplanes of U.S. registry.
    The measurement to determine control rod gap would take about 2 
work hours per airplane, at an average labor rate of $65 per work hour. 
Based on these figures, the estimated cost of the proposed measurement 
for U.S. operators is $3,640, or $130 per airplane, per measurement 
cycle.
    The replacement of the control rods with new, improved, water-
resistant control rods would take about 9 work hours per airplane, at 
an average labor rate of $65 per work hour. Required parts would cost 
about $400 per airplane. Based on these figures, the estimated cost of 
the proposed replacement for U.S. operators is $27,580, or $985 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

[[Page 32544]]

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. 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 FAA amends Sec.  39.13 by adding the following new 
airworthiness directive (AD):

Airbus: Docket No. FAA-2005-21342; Directorate Identifier 2004-NM-
15-AD.

Comments Due Date

    (a) The Federal Aviation Administration must receive comments on 
this AD action by July 5, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A321 series airplanes, 
certificated in any category; except for those airplanes that have 
received Airbus Modification 33426 in production.

Unsafe Condition

    (d) This AD was prompted by a report that an operator found it 
impossible to lock emergency doors 2 and 3 in the open position. We 
are issuing this AD to prevent failure of the emergency doors to 
lock in the open position, which could interfere with passenger 
evacuation during an emergency.

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 of Emergency Exit Doors

    (f) Within 600 flight hours after the effective date of this AD 
and thereafter at intervals not to exceed 600 flight hours, perform 
a measurement for correct gap of the control rod of the hold-open 
mechanism of all emergency doors, in accordance with Airbus All 
Operators Telex (AOT) A320-52A1120, Revision 2, dated July 10, 2003. 
If the gap of any control rod is not correct, prior to further 
flight, apply all necessary corrective actions in accordance with 
the AOT.

Optional Interim Terminating Action

    (g) Replacing the polyamide control rod of any mechanism with an 
aluminum control rod prior to accomplishing paragraph (h) of this 
AD, as specified in AOT A320-52A1120, Revision 2, dated July 10, 
2003, terminates the repetitive measurement required by paragraph 
(f) of this AD for that mechanism.

Final Terminating Action

    (h) Within 18 months after the effective date of this AD, 
replace the polyamide or interim aluminum control rods of the 
release mechanisms with new, improved, water-resistant control rods 
according to the Accomplishment Instructions of Airbus Service 
Bulletin A320-52-1121, dated December 12, 2003. This replacement 
terminates the repetitive measurement required by paragraph (f) of 
this AD.

Actions Accomplished Per Previous Issue of Service Bulletin

    (i) Actions accomplished before the effective date of this AD 
according to Airbus AOT A320-52A1120, dated June 5, 2003, or 
Revision 1, dated June 19, 2003, are considered acceptable for 
compliance with the corresponding actions specified in this AD.

No Reporting Requirement

    (j) Although the service information specifies procedures for 
reporting measurement results and control rod replacement to the 
manufacturer, this AD does not require these reports.

Alternative Methods of Compliance (AMOCs)

    (k) 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.

Related Information

    (l) French airworthiness directive F-2004-040, dated March 31, 
2004, also addresses the subject of this AD.

    Issued in Renton, Washington, on May 26, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-11061 Filed 6-2-05; 8:45 am]
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