Airworthiness Directives; Airbus Model A380-841, -842, and -861 Airplanes, 35780-35782 [E9-16763]

Download as PDF 35780 Federal Register / Vol. 74, No. 138 / Tuesday, July 21, 2009 / Rules and Regulations Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-mail: account.airwortheas@airbus.com; Internet https:// www.airbus.com. (4) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. (5) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at 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 2, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–17122 Filed 7–20–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0644; Directorate Identifier 2009–NM–059–AD; Amendment 39–15972; AD 2009–15–09] RIN 2120–AA64 Airworthiness Directives; Airbus Model A380–841, –842, and –861 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: erowe on DSK5CLS3C1PROD with RULES SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: During inspections in production and on in-service aircraft, a number of Overheat Detection System (OHDS) installation nonconformities have been identified along the bleed air ducting. Some installation issues which may lead to a degraded leak detection capability have been reported. In case of hot air leakage, the potential degradation of the OHDS would not allow preventing damages to structure or components * * *. * * * VerDate Nov<24>2008 * * 15:23 Jul 20, 2009 Jkt 217001 Nonconforming installation or a failure of the OHDS could allow undetected leakage of bleed air from the hot engine/auxiliary power unit causing damage to the airplane structure and various airplane components and systems. This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective August 5, 2009. The Director of the Federal Register approved the incorporation by reference of a certain publication, listed in the AD as of August 5, 2009. We must receive comments on this AD by August 20, 2009. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–40, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1175; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2009–0066, dated March 19, 2009 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 During inspections in production and on in-service aircraft, a number of Overheat Detection System (OHDS) installation nonconformities have been identified along the bleed air ducting. Some installation issues which may lead to a degraded leak detection capability have been reported. In case of hot air leakage, the potential degradation of the OHDS would not allow preventing damages to structure or components, and therefore could lead to an unsafe condition. To ensure that in-service aircraft are free of such non-conformities, this AD requires an inspection of the OHDS installation along the bleed air ducting and, in case of findings [any sensing element or insulation muff installed incorrectly], to bring back the installation into the compliant configuration. Nonconforming installation or a failure of the OHDS could allow undetected leakage of bleed air from the hot engine/ auxiliary power unit causing damage to the airplane structure and various airplane components and systems. The inspection of the OHDS installation, for certain airplanes, consists of inspecting the APU overheat sensing elements APU 1 Loop A and B, the APU overheat sensing elements APU 2 Loop A and B, the crossbleed overheat sensing element, the forward cargo compartment heating element, and the sensing element of the overheat detection unit of the wing. For certain other airplanes, inspecting the OHDS installation consists of inspecting the forward cargo compartment heating element. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Airbus has issued Service Bulletin A380–36–8004, dated February 13, 2009. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of This AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. There are no products of this type currently registered in the United States. However, this rule is necessary to ensure that the described unsafe condition is addressed if any of these E:\FR\FM\21JYR1.SGM 21JYR1 Federal Register / Vol. 74, No. 138 / Tuesday, July 21, 2009 / Rules and Regulations products are placed on the U.S. Register in the future. Differences Between the AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have required different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a Note within the AD. FAA’s Determination of the Effective Date Since there are currently no domestic operators of this product, notice and opportunity for public comment before issuing this AD are unnecessary. erowe on DSK5CLS3C1PROD with RULES Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2009–0644; Directorate Identifier 2009–NM–059– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. 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 VerDate Nov<24>2008 15:23 Jul 20, 2009 Jkt 217001 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 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 this AD: 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 AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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 AD: ■ 2009–15–09 Airbus: Amendment 39–15972. Docket No. FAA–2009–0644; Directorate Identifier 2009–NM–059–AD. Effective Date (a) This airworthiness directive (AD) becomes effective August 5, 2009. Affected ADs (b) None. PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 35781 Applicability (c) This AD applies to Airbus Model A380– 841, –842, and –861 airplanes, certificated in any category, serial numbers 3, 5, 6, 8, 10, 11, 12, 13, 14, 15, 16, 20, and 22. Subject (d) Air Transport Association (ATA) of America Code 36: Pneumatic. Reason (e) The mandatory continued airworthiness information (MCAI) states: During inspections in production and on in-service aircraft, a number of Overheat Detection System (OHDS) installation nonconformities have been identified along the bleed air ducting. Some installation issues which may lead to a degraded leak detection capability have been reported. In case of hot air leakage, the potential degradation of the OHDS would not allow preventing damages to structure or components, and therefore could lead to an unsafe condition. To ensure that in-service aircraft are free of such non-conformities, this AD requires an inspection of the OHDS installation along the bleed air ducting and, in case of findings [any sensing element or insulation muff installed incorrectly], to bring back the installation into the compliant configuration. Nonconforming installation or a failure of the OHDS could allow undetected leakage of bleed air from the hot engine/auxiliary power unit causing damage to the airplane structure and various airplane components and systems. The inspection of the OHDS installation, for certain airplanes, consists of inspecting the APU overheat sensing elements APU 1 Loop A and B, the APU overheat sensing elements APU 2 Loop A and B, the crossbleed overheat sensing element, the forward cargo compartment heating element, and the sensing element of the overheat detection unit of the wing. For certain other airplanes, inspecting the OHDS installation consists of inspecting the forward cargo compartment heating element. Actions and Compliance (f) Unless already done, do the following actions. (1) Within 90 days after the effective date of this AD, do a one-time detailed visual inspection to determine whether the OHDS sensing elements and insulation muffs have been correctly installed, in accordance with Airbus Service Bulletin A380–36–8004, dated February 13, 2009. (2) If, during any inspection required by paragraph (f)(1) of this AD, any sensing element or insulation muff is found to have been installed incorrectly, before further flight, bring the installation into compliant configuration, in accordance with Airbus Service Bulletin A380–36–8004, dated February 13, 2009. (3) Submit a report of the findings (both positive and negative) of the inspection required by paragraph (f)(1) of this AD to Airbus, Customer Services Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex France, as specified in Figures A– GBCAA and A–GBDAA of Airbus Service Bulletin A380–36–8004, dated February 13, E:\FR\FM\21JYR1.SGM 21JYR1 35782 Federal Register / Vol. 74, No. 138 / Tuesday, July 21, 2009 / Rules and Regulations 2009, at the applicable time specified in paragraph (f)(3)(i) or (f)(3)(ii) of this AD. (i) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection. (ii) If the inspection was accomplished prior to the effective date of this AD: Submit the report within 30 days after the effective date of this AD. FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–1175; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAAapproved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. erowe on DSK5CLS3C1PROD with RULES Related Information (h) Refer to Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency (EASA) Airworthiness Directive 2009–0066, dated March 19, 2009; and Airbus Service Bulletin A380–36–8004, dated February 13, 2009; for related information. Material Incorporated by Reference (i) You must use Airbus Service Bulletin A380–36–8004, dated February 13, 2009, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Airbus SAS—EANA (Airworthiness Office); 1 Rond Point Maurice VerDate Nov<24>2008 15:23 Jul 20, 2009 Jkt 217001 Bellonte, 31707 Blagnac Cedex, France; telephone +33 562 110 253; Fax +33 562 110 307; e-mail account.airworthA380@airbus.com; Internet https:// www.airbus.com. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at 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 6, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–16763 Filed 7–20–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–1311; Directorate Identifier 2007–NE–48–AD; Amendment 39– 15976; AD 2009–15–13] RIN 2120–AA64 Airworthiness Directives; Honeywell International Inc., T5313 and T5317 Series Turboshaft Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: The FAA is adopting a new airworthiness directive (AD) for Honeywell International Inc., T5313 and T5317 series turboshaft engines. This AD requires initial and repetitive visual inspections and initial and repetitive ultrasonic inspections of combustion chamber housings (CCHs) for cracks. This AD results from eight instances of cracks in CCHs. Two of the instances resulted in an engine shutdown during flight. We are issuing this AD to detect cracks in the CCH, which could result in rupture of the CCH, leading to loss of engine power and damage to the helicopter. This AD becomes effective August 25, 2009. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of August 25, 2009. DATES: PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 ADDRESSES: You can get the service information identified in this AD from Honeywell International Inc., P.O. Box 52181, Phoenix, AZ 85072–2181, U.S.A.; telephone (800) 601–3099 (U.S.A.) or (602) 365–3099 (International), Web site: https:// portal.honeywell.com/wps/portal/aero. The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. FOR FURTHER INFORMATION CONTACT: Robert Baitoo, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 90712–4137; e-mail: robert.baitoo@faa.gov; telephone (562) 627–5245; fax (562) 627–5210. The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to Honeywell International Inc., T5313 and T5317 series turboshaft engines. We published the proposed AD in the Federal Register on December 16, 2008 (73 FR 76291). That action proposed to require initial and repetitive visual inspections and initial and repetitive ultrasonic inspections of CCHs for cracks. SUPPLEMENTARY INFORMATION: Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. Comments We provided the public the opportunity to participate in the development of this AD. We received no comments on the proposal or on the determination of the cost to the public. Change to Optional Terminating Action Paragraph We changed optional terminating action paragraph (k) to state that installation of a CCH P/N 1–130–610–19 or 1–130–610R16 terminates the inspection requirements of this AD. These CCHs eliminate the failure mode that cause cracking. E:\FR\FM\21JYR1.SGM 21JYR1

Agencies

[Federal Register Volume 74, Number 138 (Tuesday, July 21, 2009)]
[Rules and Regulations]
[Pages 35780-35782]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-16763]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0644; Directorate Identifier 2009-NM-059-AD; 
Amendment 39-15972; AD 2009-15-09]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A380-841, -842, and -861 
Airplanes

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

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This AD results from mandatory continuing 
airworthiness information (MCAI) originated by an aviation authority of 
another country to identify and correct an unsafe condition on an 
aviation product. The MCAI describes the unsafe condition as:

    During inspections in production and on in-service aircraft, a 
number of Overheat Detection System (OHDS) installation non-
conformities have been identified along the bleed air ducting.
    Some installation issues which may lead to a degraded leak 
detection capability have been reported. In case of hot air leakage, 
the potential degradation of the OHDS would not allow preventing 
damages to structure or components * * *.
* * * * *
    Nonconforming installation or a failure of the OHDS could allow 
undetected leakage of bleed air from the hot engine/auxiliary power 
unit causing damage to the airplane structure and various airplane 
components and systems. This AD requires actions that are intended to 
address the unsafe condition described in the MCAI.

DATES: This AD becomes effective August 5, 2009.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication, listed in the AD as of August 5, 
2009.
    We must receive comments on this AD by August 20, 2009.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New 
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1175; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2009-0066, dated March 19, 2009 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    During inspections in production and on in-service aircraft, a 
number of Overheat Detection System (OHDS) installation non-
conformities have been identified along the bleed air ducting.
    Some installation issues which may lead to a degraded leak 
detection capability have been reported. In case of hot air leakage, 
the potential degradation of the OHDS would not allow preventing 
damages to structure or components, and therefore could lead to an 
unsafe condition.
    To ensure that in-service aircraft are free of such non-
conformities, this AD requires an inspection of the OHDS 
installation along the bleed air ducting and, in case of findings 
[any sensing element or insulation muff installed incorrectly], to 
bring back the installation into the compliant configuration.

Nonconforming installation or a failure of the OHDS could allow 
undetected leakage of bleed air from the hot engine/auxiliary power 
unit causing damage to the airplane structure and various airplane 
components and systems. The inspection of the OHDS installation, for 
certain airplanes, consists of inspecting the APU overheat sensing 
elements APU 1 Loop A and B, the APU overheat sensing elements APU 2 
Loop A and B, the crossbleed overheat sensing element, the forward 
cargo compartment heating element, and the sensing element of the 
overheat detection unit of the wing. For certain other airplanes, 
inspecting the OHDS installation consists of inspecting the forward 
cargo compartment heating element. You may obtain further information 
by examining the MCAI in the AD docket.

Relevant Service Information

    Airbus has issued Service Bulletin A380-36-8004, dated February 13, 
2009. The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are issuing this AD because we 
evaluated all pertinent information and determined the unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.
    There are no products of this type currently registered in the 
United States. However, this rule is necessary to ensure that the 
described unsafe condition is addressed if any of these

[[Page 35781]]

products are placed on the U.S. Register in the future.

Differences Between the AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have required different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a Note within the AD.

FAA's Determination of the Effective Date

    Since there are currently no domestic operators of this product, 
notice and opportunity for public comment before issuing this AD are 
unnecessary.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2009-0644; Directorate 
Identifier 2009-NM-059-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD because of 
those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

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 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 this AD:
    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 AD and placed it in the AD docket.

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 AD:

2009-15-09 Airbus: Amendment 39-15972. Docket No. FAA-2009-0644; 
Directorate Identifier 2009-NM-059-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective August 
5, 2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A380-841, -842, and -861 
airplanes, certificated in any category, serial numbers 3, 5, 6, 8, 
10, 11, 12, 13, 14, 15, 16, 20, and 22.

Subject

    (d) Air Transport Association (ATA) of America Code 36: 
Pneumatic.

Reason

    (e) The mandatory continued airworthiness information (MCAI) 
states:

    During inspections in production and on in-service aircraft, a 
number of Overheat Detection System (OHDS) installation non-
conformities have been identified along the bleed air ducting.
    Some installation issues which may lead to a degraded leak 
detection capability have been reported. In case of hot air leakage, 
the potential degradation of the OHDS would not allow preventing 
damages to structure or components, and therefore could lead to an 
unsafe condition.
    To ensure that in-service aircraft are free of such non-
conformities, this AD requires an inspection of the OHDS 
installation along the bleed air ducting and, in case of findings 
[any sensing element or insulation muff installed incorrectly], to 
bring back the installation into the compliant configuration.

    Nonconforming installation or a failure of the OHDS could allow 
undetected leakage of bleed air from the hot engine/auxiliary power 
unit causing damage to the airplane structure and various airplane 
components and systems. The inspection of the OHDS installation, for 
certain airplanes, consists of inspecting the APU overheat sensing 
elements APU 1 Loop A and B, the APU overheat sensing elements APU 2 
Loop A and B, the crossbleed overheat sensing element, the forward 
cargo compartment heating element, and the sensing element of the 
overheat detection unit of the wing. For certain other airplanes, 
inspecting the OHDS installation consists of inspecting the forward 
cargo compartment heating element.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) Within 90 days after the effective date of this AD, do a 
one-time detailed visual inspection to determine whether the OHDS 
sensing elements and insulation muffs have been correctly installed, 
in accordance with Airbus Service Bulletin A380-36-8004, dated 
February 13, 2009.
    (2) If, during any inspection required by paragraph (f)(1) of 
this AD, any sensing element or insulation muff is found to have 
been installed incorrectly, before further flight, bring the 
installation into compliant configuration, in accordance with Airbus 
Service Bulletin A380-36-8004, dated February 13, 2009.
    (3) Submit a report of the findings (both positive and negative) 
of the inspection required by paragraph (f)(1) of this AD to Airbus, 
Customer Services Directorate, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex France, as specified in Figures A-GBCAA and A-GBDAA of 
Airbus Service Bulletin A380-36-8004, dated February 13,

[[Page 35782]]

2009, at the applicable time specified in paragraph (f)(3)(i) or 
(f)(3)(ii) of this AD.
    (i) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (ii) If the inspection was accomplished prior to the effective 
date of this AD: Submit the report within 30 days after the 
effective date of this AD.

FAA AD Differences

    Note 1:  This AD differs from the MCAI and/or service 
information as follows: No differences.

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. Send information to ATTN: Todd 
Thompson, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
Washington 98057-3356; telephone (425) 227-1175; fax (425) 227-1149. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office. 
The AMOC approval letter must specifically reference this AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act, the 
Office of Management and Budget (OMB) has approved the information 
collection requirements and has assigned OMB Control Number 2120-
0056.

Related Information

    (h) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European Aviation Safety Agency (EASA) Airworthiness 
Directive 2009-0066, dated March 19, 2009; and Airbus Service 
Bulletin A380-36-8004, dated February 13, 2009; for related 
information.

Material Incorporated by Reference

    (i) You must use Airbus Service Bulletin A380-36-8004, dated 
February 13, 2009, to do the actions required by this AD, unless the 
AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Airbus SAS--EANA (Airworthiness Office); 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 562 110 253; 
Fax +33 562 110 307; e-mail account.airworth-A380@airbus.com; 
Internet https://www.airbus.com.
    (3) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221 or 425-227-1152.
    (4) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at 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 6, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-16763 Filed 7-20-09; 8:45 am]
BILLING CODE 4910-13-P
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.