Airworthiness Directives; Airbus Model A320-111 Airplanes and Model A320-200 Series Airplanes, 41946-41948 [05-14087]

Download as PDF 41946 Federal Register / Vol. 70, No. 139 / Thursday, July 21, 2005 / Rules and Regulations Service Bulletin Reference (f) The term ‘‘service bulletin,’’ as used in this AD, means the Accomplishment Instructions of Boeing Service Bulletin MD11–52–044, Revision 1 (for Model MD–11 and MD–11F airplanes), and Service Bulletin DC10–52–219, Revision 1 (for Model DC–10– 10, DC–10–10F, DC–10–15, DC–10–30, DC– 10–30F (KC–10A and KDC–10), DC–10–40, DC–10–40F, MD–10–10F, and MD–10–30F airplanes); both dated September 3, 2004; as applicable. Functional Test (g) Within 6,000 flight hours or 18 months after the effective date of this AD, whichever occurs later, perform a functional test of the exterior emergency control handle assemblies of the mid, overwing, and aft passenger doors; by doing all actions specified in the applicable service bulletin, except as provided by paragraph (i) of this AD. (1) If the functional test reveals no noisy operation or binding: Repeat the functional test at intervals not to exceed 6,000 flight hours or 18 months, whichever occurs later, until the terminating action of paragraph (h) of this AD has been accomplished. (2) If any functional test required by this AD reveals noisy operation or binding: Prior to further flight, replace the steel bearings with bearings made from corrosion-resistant material, in accordance with the applicable service bulletin. Optional Terminating Action (h) Accomplishment of the actions required by paragraph (g)(2) of this AD constitutes terminating action for the repetitive tests required by paragraph (g)(1) of this AD only for the modified doors. Inoperable Doors (i) Any mid, overwing, or aft passenger door that has been fastened shut and rendered inoperable according to an approved airplane freighter configuration is not subject to the requirements of this AD. Alternative Methods of Compliance (AMOCs) (j) 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. Material Incorporated by Reference (k) You must use Boeing Service Bulletin DC10–52–219, Revision 1, dated September 3, 2004; or Boeing Service Bulletin MD11– 52–044, Revision 1, dated September 3, 2004; as applicable, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1–L5A (D800–0024), for copies of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh VerDate jul<14>2003 17:10 Jul 20, 2005 Jkt 205001 Street SW., Room PL–401, Nassif Building, Washington, DC; on the internet at https:// dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on July 8, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–14088 Filed 7–20–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20500; Directorate Identifier 2004–NM–235–AD; Amendment 39–14191; AD 2005–15–02] RIN 2120–AA64 Airworthiness Directives; Airbus Model A320–111 Airplanes and Model A320– 200 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) that applies to certain Airbus Model A320– 111 airplanes and Model A320–200 series airplanes. This AD requires postmaintenance bleeding of accumulated air from, or ground functional testing of, the ram air turbine (RAT) system; modifying and reidentifying the airborne ground check module of the RAT system; and replacing the RAT reducer assembly if applicable. This AD is prompted by reports of unsuccessful in-flight RAT tests during which a deployed RAT failed to pressurize the blue hydraulic circuit of the RAT system. We are issuing this AD to prevent failure of the RAT during an inflight emergency, which could lead to loss of hydraulic and electrical power and reduced controllability of the airplane. DATES: This AD becomes effective August 25, 2005. The incorporation by reference of certain publications listed in the AD is approved by the Director of the Federal Register as of August 25, 2005. ADDRESSES: For service information identified in this AD, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 Docket: The AD docket contains the proposed AD, comments, and any final disposition. You can examine the AD docket on the Internet at https:// dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the U.S. Department of Transportation, 400 Seventh Street, SW., room PL–401, Washington, DC. This docket number is FAA–2005–20500; the directorate identifier for this docket is 2004–NM– 235–AD. 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. FOR FURTHER INFORMATION CONTACT: The FAA proposed to amend 14 CFR part 39 with an AD for Airbus Model A320 series airplanes. That action, published in the Federal Register on March 8, 2005 (70 FR 11170), proposed to require postmaintenance bleeding of accumulated air from, or ground functional testing of, the ram air turbine (RAT) system; modifying and reidentifying the airborne ground check module of the RAT system; and replacing the RAT reducer assembly if applicable. SUPPLEMENTARY INFORMATION: Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments that have been submitted on the proposed AD. Support for the Proposed AD One commenter supports the proposed AD. Request To Revise Applicability One commenter requests that we change a part number that was incorrectly referenced in the applicability of the proposed AD. The commenter states that part number (P/N) 760106 is incorrect and that it should be changed to P/N 769106. We agree with this request. P/N 760106 is a part number that is not referenced by the Airbus service bulletin; it appeared due to a typographical error. We have corrected paragraph (c) of the final rule to read P/N 769106, as specified in the Airbus service bulletin and the French airworthiness directive. E:\FR\FM\21JYR1.SGM 21JYR1 Federal Register / Vol. 70, No. 139 / Thursday, July 21, 2005 / Rules and Regulations Request To Revise Requirement for Bleeding of Blue Hydraulic Circuit The same commenter requests that we revise the wording of paragraphs (f) and (g) of the proposed AD. The commenter asserts that the statement ‘‘after performing any maintenance on the blue hydraulic circuit’’ that appears in paragraphs (f) and (g) is too vague and can be taken as requiring unnecessary bleeding of the blue hydraulic circuit. The commenter suggests that we revise this wording to read ‘‘after performing any maintenance that would normally require bleeding of the blue hydraulic circuit (as instructed by the related AMM procedure).’’ The commenter states that such wording would eliminate any unneeded maintenance introduced by the proposed AD and still ensure that, during any in-flight emergency, a RAT system failure does not occur. We agree with this request. We always seek to use unambiguous language and the specified statement could be taken as requiring unnecessary bleeding of the blue hydraulic circuit. Therefore, to ensure that bleeding of the blue hydraulic circuit must be performed only as a necessary part of a maintenance action, we have revised paragraphs (f) and (g) of the final rule to reflect the commenter’s wording. Explanation of Change to Applicability The FAA has revised the applicability of the proposed AD to identify model designations as published in the most recent type certificate data sheet for the affected models. Conclusion We have carefully reviewed the available data, including the comments that have been submitted, and determined that air safety and the public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance This AD will affect about 130 airplanes of U.S. registry. The system bleed/functional test will 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 required actions for U.S. operators is $8,450, or $65 per airplane. The airborne ground check module (AGCM) replacement will take about 2 work hours per airplane, at an average labor rate of $65 per work hour. Required parts will be supplied at no VerDate jul<14>2003 17:10 Jul 20, 2005 Jkt 205001 charge. Based on these figures, the estimated cost of this action for U.S. operators is $16,900, or $130 per airplane. The reducer replacement, for subject airplanes, will take about 1 work hour per airplane, at an average labor rate of $65 per work hour. Required parts will be supplied at no charge. Based on these figures, the estimated cost of this action for U.S. operators is $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 AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 41947 Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I 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): I 2005–15–02 Airbus: Amendment 39–14191. Docket No. FAA–2005–20500; Directorate Identifier 2004–NM–235–AD. Effective Date (a) This AD becomes effective August 25, 2005. Affected ADs (b) None. Applicability: (c) This AD applies to Airbus Model A320–111 airplanes and Model A320– 200 series airplanes, certificated in any category; equipped with Hamilton Sundstrand airborne ground check module (AGCM) having part number 769104, 769105, or 769106 installed; except those airplanes on which Airbus Modification 27189 has been done in production and on which Airbus Modification 28413 has not been done. Unsafe Condition (d) This AD was prompted by reports of unsuccessful in-flight ram air turbine (RAT) tests during which a deployed RAT failed to pressurize the blue hydraulic circuit of the RAT system. We are issuing this AD to prevent failure of the RAT system during an in-flight emergency, which could lead to loss of hydraulic and electrical power and reduced controllability of the airplane. Compliance: (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. RAT System Bleeding/Functional Test (f) For airplanes on which maintenance has been performed on the blue hydraulic circuit as of the effective date of this AD: Within 3 days or 20 flight hours after the effective date of this AD, whichever occurs first, bleed accumulated air from, or perform a ground functional test of, the RAT system; by accomplishing all the actions specified in Airbus All Operators Telex (AOT) A320– 29A1112, Revision 01, dated April 8, 2004. Thereafter, bleed the blue hydraulic circuit as specified in the AOT within 3 days or 20 flight hours after performing any maintenance that would normally require bleeding of the blue hydraulic circuit, (as instructed by the related aircraft maintenance manual (AMM) procedure). (g) For airplanes on which maintenance has not been performed on the blue hydraulic E:\FR\FM\21JYR1.SGM 21JYR1 41948 Federal Register / Vol. 70, No. 139 / Thursday, July 21, 2005 / Rules and Regulations circuit as of the effective date of this AD: Within 3 days or 20 flight hours after performing any maintenance that would normally require bleeding of the blue hydraulic circuit (as instructed by the related AMM procedure), bleed the blue hydraulic circuit by accomplishing all the actions specified in Airbus AOT A320–29A1112, Revision 01, dated April 8, 2004. DEPARTMENT OF TRANSPORTATION Replacement of AGCM and Reducer RIN 2120–AA64 (h) Within 35 months after the effective date of this AD, replace the AGCM with a modified and reidentified AGCM; and replace the reducer with a new reducer if applicable; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–29–1111, dated June 29, 2004. Replacing the AGCM, and the reducer if applicable, ends the actions required by paragraphs (f) and (g) of this AD. Note 1: Airbus Service Bulletin A320–29– 1111 refers to Hamilton Sundstrand Service Bulletin ERPS13GCM–29–5, dated June 29, 2004, as an additional source of service information for modifying and reidentifying the AGCM. Alternative Methods of Compliance (AMOCs) (i) 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 (j) French airworthiness directive F–2004– 150, dated September 1, 2004, also addresses the subject of this AD. Material Incorporated by Reference (k) You must use All Operators Telex (Airbus) A320–29A1112, Revision 01, dated April 8, 2004; and Airbus Service Bulletin A320–29–1111, dated June 29, 2004; as applicable, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approves the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of the service information, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. To view the AD docket, go to the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Nassif Building, Washington, DC. To review copies of the service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741– 6030, or go to https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on July 8, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–14087 Filed 7–20–05; 8:45 am] BILLING CODE 4910–13–P VerDate jul<14>2003 17:10 Jul 20, 2005 Jkt 205001 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–21598; Directorate Identifier 2005–NM–121–AD; Amendment 39–14159; AD 2005–13–22] Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB–135 Airplanes, and Model EMB–145, –145ER, –145MR, –145LR, –145XR, –145MP, and –145EP Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; correction. AGENCY: SUMMARY: The FAA is correcting a typographical error in an existing airworthiness directive (AD) that was published in the Federal Register on June 22, 2005 (70 FR 36011). The error resulted in an incomplete listing of the affected airplanes. This AD applies to all EMBRAER Model EMB–135 airplanes, and all Model EMB–145, –145ER, –145MR, –145LR, –145XR, –145MP, and –145EP airplanes. This AD requires repetitive inspections of the electrical connectors of the electric fuel pumps to detect discrepancies, application of anti-corrosion spray, replacement of all fuel pumps with improved fuel pumps, repetitive inspections after all six fuel pumps are replaced, and applicable corrective actions. Effective July 7, 2005. The AD docket contains the proposed AD, comments, and any final disposition. You may examine the AD docket on the Internet at https:// dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the U.S. Department of Transportation, 400 Seventh Street SW., Room PL–401, Washington, DC. This docket number is FAA–2005–21598; the directorate identifier for this docket is 2005–NM– 121–AD. FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–1175; fax (425) 227–1149. DATES: ADDRESSES: PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 On June 15, 2005, the FAA issued AD 2005–13– 22, amendment 39–14159 (70 FR 36011, June 22, 2005), for all EMBRAER Model EMB–135 airplanes, and all Model EMB–145, –145ER, –145MR, –145LR, –145XR, –145MP, and –145EP airplanes. The AD requires repetitive inspections of the electrical connectors of the electric fuel pumps to detect discrepancies, application of anticorrosion spray, replacement of all fuel pumps with improved fuel pumps, repetitive inspections after all six fuel pumps are replaced, and applicable corrective actions. As published, the AD includes an incomplete applicability. Paragraph (c) of the AD omits Models EMB–145XR, –145MP, and –145EP airplanes, although those three models were included in all other references to the applicability throughout the preamble and regulatory language of the AD. No other part of the regulatory information has been changed; therefore, the final rule is not republished in the Federal Register. The effective date of this AD remains July 7, 2005. SUPPLEMENTARY INFORMATION: PART 39—[AMENDED] § 39.13 [Corrected] I In the Federal Register of June 22, 2005, on page 36012, in the 3rd column, paragraph (c) of AD 2005–13–22 is corrected to read as follows: * * * * * (c) This AD applies to all EMBRAER Model EMB–135BJ, –135ER, –135KE, –135KL, and –135LR airplanes; and Model EMB–145, –145ER, –145MR, –145LR, –145XR, –145MP, and –145EP airplanes. * * * * * Issued in Renton, Washington, on July 11, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–14169 Filed 7–20–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2005–21103; Airspace Docket No. 05–AEA–10] Amendment of Class E Airspace; Blairstown, NJ Federal Aviation Administration (FAA) DOT. AGENCY: E:\FR\FM\21JYR1.SGM 21JYR1

Agencies

[Federal Register Volume 70, Number 139 (Thursday, July 21, 2005)]
[Rules and Regulations]
[Pages 41946-41948]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-14087]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20500; Directorate Identifier 2004-NM-235-AD; 
Amendment 39-14191; AD 2005-15-02]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A320-111 Airplanes and 
Model A320-200 Series Airplanes

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

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) that 
applies to certain Airbus Model A320-111 airplanes and Model A320-200 
series airplanes. This AD requires post-maintenance bleeding of 
accumulated air from, or ground functional testing of, the ram air 
turbine (RAT) system; modifying and reidentifying the airborne ground 
check module of the RAT system; and replacing the RAT reducer assembly 
if applicable. This AD is prompted by reports of unsuccessful in-flight 
RAT tests during which a deployed RAT failed to pressurize the blue 
hydraulic circuit of the RAT system. We are issuing this AD to prevent 
failure of the RAT during an in-flight emergency, which could lead to 
loss of hydraulic and electrical power and reduced controllability of 
the airplane.

DATES: This AD becomes effective August 25, 2005.
    The incorporation by reference of certain publications listed in 
the AD is approved by the Director of the Federal Register as of August 
25, 2005.

ADDRESSES: For service information identified in this AD, contact 
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
    Docket: The AD docket contains the proposed AD, comments, and any 
final disposition. You can examine the AD docket on the Internet at 
https://dms.dot.gov, or in person at the Docket Management Facility 
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the U.S. 
Department of Transportation, 400 Seventh Street, SW., room PL-401, 
Washington, DC. This docket number is FAA-2005-20500; the directorate 
identifier for this docket is 2004-NM-235-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: The FAA proposed to amend 14 CFR part 39 
with an AD for Airbus Model A320 series airplanes. That action, 
published in the Federal Register on March 8, 2005 (70 FR 11170), 
proposed to require post-maintenance bleeding of accumulated air from, 
or ground functional testing of, the ram air turbine (RAT) system; 
modifying and reidentifying the airborne ground check module of the RAT 
system; and replacing the RAT reducer assembly if applicable.

Comments

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

Support for the Proposed AD

    One commenter supports the proposed AD.

Request To Revise Applicability

    One commenter requests that we change a part number that was 
incorrectly referenced in the applicability of the proposed AD. The 
commenter states that part number (P/N) 760106 is incorrect and that it 
should be changed to P/N 769106.
    We agree with this request. P/N 760106 is a part number that is not 
referenced by the Airbus service bulletin; it appeared due to a 
typographical error. We have corrected paragraph (c) of the final rule 
to read P/N 769106, as specified in the Airbus service bulletin and the 
French airworthiness directive.

[[Page 41947]]

Request To Revise Requirement for Bleeding of Blue Hydraulic Circuit

    The same commenter requests that we revise the wording of 
paragraphs (f) and (g) of the proposed AD. The commenter asserts that 
the statement ``after performing any maintenance on the blue hydraulic 
circuit'' that appears in paragraphs (f) and (g) is too vague and can 
be taken as requiring unnecessary bleeding of the blue hydraulic 
circuit. The commenter suggests that we revise this wording to read 
``after performing any maintenance that would normally require bleeding 
of the blue hydraulic circuit (as instructed by the related AMM 
procedure).'' The commenter states that such wording would eliminate 
any unneeded maintenance introduced by the proposed AD and still ensure 
that, during any in-flight emergency, a RAT system failure does not 
occur.
    We agree with this request. We always seek to use unambiguous 
language and the specified statement could be taken as requiring 
unnecessary bleeding of the blue hydraulic circuit. Therefore, to 
ensure that bleeding of the blue hydraulic circuit must be performed 
only as a necessary part of a maintenance action, we have revised 
paragraphs (f) and (g) of the final rule to reflect the commenter's 
wording.

Explanation of Change to Applicability

    The FAA has revised the applicability of the proposed AD to 
identify model designations as published in the most recent type 
certificate data sheet for the affected models.

Conclusion

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

Costs of Compliance

    This AD will affect about 130 airplanes of U.S. registry.
    The system bleed/functional test will 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 required actions for U.S. operators 
is $8,450, or $65 per airplane.
    The airborne ground check module (AGCM) replacement will take about 
2 work hours per airplane, at an average labor rate of $65 per work 
hour. Required parts will be supplied at no charge. Based on these 
figures, the estimated cost of this action for U.S. operators is 
$16,900, or $130 per airplane.
    The reducer replacement, for subject airplanes, will take about 1 
work hour per airplane, at an average labor rate of $65 per work hour. 
Required parts will be supplied at no charge. Based on these figures, 
the estimated cost of this action for U.S. operators is $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 AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD. See the ADDRESSES section for a location to 
examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2005-15-02 Airbus: Amendment 39-14191. Docket No. FAA-2005-20500; 
Directorate Identifier 2004-NM-235-AD.

Effective Date

    (a) This AD becomes effective August 25, 2005.

Affected ADs

    (b) None.
    Applicability: (c) This AD applies to Airbus Model A320-111 
airplanes and Model A320-200 series airplanes, certificated in any 
category; equipped with Hamilton Sundstrand airborne ground check 
module (AGCM) having part number 769104, 769105, or 769106 
installed; except those airplanes on which Airbus Modification 27189 
has been done in production and on which Airbus Modification 28413 
has not been done.

Unsafe Condition

    (d) This AD was prompted by reports of unsuccessful in-flight 
ram air turbine (RAT) tests during which a deployed RAT failed to 
pressurize the blue hydraulic circuit of the RAT system. We are 
issuing this AD to prevent failure of the RAT system during an in-
flight emergency, which could lead to loss of hydraulic and 
electrical power and reduced controllability of the airplane.
    Compliance: (e) You are responsible for having the actions 
required by this AD performed within the compliance times specified, 
unless the actions have already been done.

RAT System Bleeding/Functional Test

    (f) For airplanes on which maintenance has been performed on the 
blue hydraulic circuit as of the effective date of this AD: Within 3 
days or 20 flight hours after the effective date of this AD, 
whichever occurs first, bleed accumulated air from, or perform a 
ground functional test of, the RAT system; by accomplishing all the 
actions specified in Airbus All Operators Telex (AOT) A320-29A1112, 
Revision 01, dated April 8, 2004. Thereafter, bleed the blue 
hydraulic circuit as specified in the AOT within 3 days or 20 flight 
hours after performing any maintenance that would normally require 
bleeding of the blue hydraulic circuit, (as instructed by the 
related aircraft maintenance manual (AMM) procedure).
    (g) For airplanes on which maintenance has not been performed on 
the blue hydraulic

[[Page 41948]]

circuit as of the effective date of this AD: Within 3 days or 20 
flight hours after performing any maintenance that would normally 
require bleeding of the blue hydraulic circuit (as instructed by the 
related AMM procedure), bleed the blue hydraulic circuit by 
accomplishing all the actions specified in Airbus AOT A320-29A1112, 
Revision 01, dated April 8, 2004.

Replacement of AGCM and Reducer

    (h) Within 35 months after the effective date of this AD, 
replace the AGCM with a modified and reidentified AGCM; and replace 
the reducer with a new reducer if applicable; in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-29-1111, 
dated June 29, 2004. Replacing the AGCM, and the reducer if 
applicable, ends the actions required by paragraphs (f) and (g) of 
this AD.

    Note 1: Airbus Service Bulletin A320-29-1111 refers to Hamilton 
Sundstrand Service Bulletin ERPS13GCM-29-5, dated June 29, 2004, as 
an additional source of service information for modifying and 
reidentifying the AGCM.

Alternative Methods of Compliance (AMOCs)

    (i) 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

    (j) French airworthiness directive F-2004-150, dated September 
1, 2004, also addresses the subject of this AD.

Material Incorporated by Reference

    (k) You must use All Operators Telex (Airbus) A320-29A1112, 
Revision 01, dated April 8, 2004; and Airbus Service Bulletin A320-
29-1111, dated June 29, 2004; as applicable, to perform the actions 
that are required by this AD, unless the AD specifies otherwise. The 
Director of the Federal Register approves the incorporation by 
reference of these documents in accordance with 5 U.S.C. 552(a) and 
1 CFR part 51. To get copies of the service information, contact 
Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. 
To view the AD docket, go to the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street SW., room PL-401, 
Nassif Building, Washington, DC. To review copies of the service 
information, go to the National Archives and Records Administration 
(NARA). For information on the availability of this material at the 
NARA, call (202) 741-6030, or go to https://www.archives.gov/federal
_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on July 8, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-14087 Filed 7-20-05; 8:45 am]
BILLING CODE 4910-13-P
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