Airworthiness Directives; Airbus Airplanes, 4762-4764 [2015-01178]

Download as PDF 4762 Federal Register / Vol. 80, No. 19 / Thursday, January 29, 2015 / Rules and Regulations In the rule, the FAA amended certain airworthiness regulations for transport category airplanes to eliminate regulatory differences between the airworthiness standards of the FAA and European Aviation Safety Agency (EASA). It does not add new requirements beyond what manufacturers currently meet for EASA certification and does not affect current industry design practices. This final rule revises the pitch maneuver design loads criteria; revises the gust and turbulence design loads criteria; revises the application of gust loads to engine mounts, high lift devices, and other control surfaces; adds a ‘‘round-theclock’’ discrete gust criterion and a multi-axis discrete gust criterion for airplanes equipped with wing-mounted engines; revises the engine torque loads criteria; adds an engine failure dynamic load condition; revises the ground gust design loads criteria; revises the criteria used to establish the rough air design speed; and requires the establishment of a rough air Mach number. This document corrects three errors in the Greek letters and subscripts contained in various equations in the regulatory text. In one case, the ‘‘U’’ in the equation is changed from subscript to regular, uppercase text. In another ¯ case, instead of ‘‘PL = PL–1g ± UsA’’, the ¯ equation should be ‘‘PL = PL–1g ± UsA’’. In two cases, the three Greek letters ‘‘rej’’ after sigma ‘‘s’’ in the subscript of ‘‘U’’ are changed to ‘‘ref’’. In these cases, ‘‘Usrej’’ should be ‘‘Usref’’. This correction also corrects the statement in the rule’s preamble that the FAA received 33 comments to the Advisory Circulars, rather than none. tkelley on DSK3SPTVN1PROD with RULES Corrections In FR Doc. 2014–28938, beginning on page 73464, in the Federal Register of December 11, 2014, make the following corrections: 1. On Page 73464, second column, under the heading ‘‘C. Advisory Material’’, the sentence, ‘‘The FAA did not receive any comments on the proposed ACs’’ is corrected to read ‘‘The FAA received 33 comments on the proposed ACs. These comments did not have an impact on the regulatory requirements’’. 2. On page 73467, second column, ¯ line 11, the equation ‘‘PL = PL–1g ± UsA’’ ¯ is corrected to read ‘‘PL = PL–1g ± UsA’’. 3. On page 73467, second column, fifth line from the bottom, the equation ‘‘Us = UsrejFg’’ is corrected to read ‘‘Us = Usref Fg’’. 4. On page 73467, second column, third line from the bottom, the text ‘‘Usrej’’ is corrected to read ‘‘Usref’’. VerDate Sep<11>2014 16:36 Jan 28, 2015 Jkt 235001 Issued in Washington, DC, on January 16, 2015. Lirio Liu, Director, Office of Rulemaking. [FR Doc. 2015–01205 Filed 1–28–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0078; Directorate Identifier 2014–NM–235–AD; Amendment 39–18084; AD 2015–02–17] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for all Airbus Model A330–200, A330–200 Freighter, and A330–300 series airplanes. This AD requires revising the electrical emergency configuration procedure in the Emergency Procedures section of the airplane flight manual (AFM) to include procedures for deploying the ram air turbine manually to provide sufficient hydraulic power and avoid constant speed motor/ generator (CSM/G) shedding. This AD was prompted by an electrical load analysis that revealed that hydraulic power might not be sufficient to supply the CSM/G during slat/flap extension when only one engine is running. We are issuing this AD to prevent such a condition which, in conjunction with the loss of the main electrical system, could lead to the scenario where the flightcrew is not clearly warned that the electrical system has switched on the battery and thus has a limited duration that would allow a safe landing. DATES: This AD becomes effective February 13, 2015. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of February 13, 2015. We must receive comments on this AD by March 16, 2015. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. SUMMARY: PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 • 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 W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330–A340@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 0078; 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; 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 Union, has issued EASA Airworthiness Directive 2014–0281, dated December 22, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition on all Airbus Model A330–200, A330–200 Freighter, and A330–300 series airplanes. The MCAI states: The Constant Speed Motor/Generator (CSM/G), as installed on Airbus A330 E:\FR\FM\29JAR1.SGM 29JAR1 Federal Register / Vol. 80, No. 19 / Thursday, January 29, 2015 / Rules and Regulations aeroplanes, is qualified for an overload condition of 9.5kVA [kilovolt-ampere] for 30 minutes. This duration is sufficient to perform safe landing and a GO–AROUND. However, electrical load analysis revealed that the hydraulic power might not be sufficient to supply the CSM/G during slat/ flap extension when only one engine is running. This condition, if not corrected, and in conjunction with the loss of main electrical system, could lead to the scenario where the crew is not clearly warned that the electrical system has switched on the battery and thus has a limited duration that would allow a safe landing. To address this potential unsafe condition, Airbus issued an Aircraft Flight Manual (AFM) Temporary Revision (TR) on A330 aeroplane to update the electrical emergency configuration ‘‘ELEC EMER CONFIG’’ procedure to require the pilot to deploy the ram air turbine manually before setting the Landing Recovery to ON position to provide sufficient hydraulic power and avoid CSM/ G shedding under worst-case operational conditions. Consequently, EASA issued AD 2014–0273 (http://ad.easa.europa.eu/blob/easa_ad_ 2014_0273_superseded.pdf/AD_2014-0273_ 1) to require amendment of the AFM by incorporating the applicable Airbus TR. After that [EASA] AD was issued, EASA became aware that the reference to Airbus modification (mod) 47930 was insufficient to define which AFM TR is applicable to which aeroplane (configuration), as this mod can be embodied in service with Airbus Service Bulletin (SB) A330–28–3067. For the reason described above, this [EASA] AD retains the requirements of EASA AD 2014–0273, which is superseded, and corrects the information included in Table 1. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2015–0078. tkelley on DSK3SPTVN1PROD with RULES Related Service Information Airbus has issued A330/A340 Airplane Flight Manual (AFM) Temporary Revision (TR) TR427, UPDATE OF ELEC—EMER CONFIG PROCEDURE, Issue 1.0, dated November 7, 2014 (for airplanes in Airbus pre-modification 47930 configuration or pre-Airbus Service Bulletin A330–28–3067 configuration); and A330/A340 AFM TR TR428, UPDATE OF ELEC—EMER CONFIG PROCEDURE, Issue 1.0, dated November 7, 2014 (for airplanes in Airbus post-modification 47930 configuration or post-Airbus Service Bulletin A330–28–3067 configuration). This service information describes updated electrical emergency configuration procedures in the AFM. You can find this information at http://www.regulations.gov by searching for and locating Docket No. FAA–2015– 0078. VerDate Sep<11>2014 16:36 Jan 28, 2015 Jkt 235001 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. FAA’s Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because hydraulic power might not be sufficient to supply the CSM/G during slat/flap extension when only one engine is running. This condition, in conjunction with the loss of the main electrical system, could lead to the scenario where the flightcrew is not clearly warned that the electrical system has switched on the battery and thus has a limited duration that would allow a safe landing. Therefore, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days. 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–2015–0078; Directorate Identifier 2014–NM–235– 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 based on those comments. We will post all comments we receive, without change, to http:// 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. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 4763 Costs of Compliance We estimate that this AD affects 91 airplanes of U.S. registry. We also estimate that it will take about 1 work-hour per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $7,735, or $85 per product. 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 that 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); 3. Will not affect intrastate aviation in Alaska; and 4. 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. E:\FR\FM\29JAR1.SGM 29JAR1 4764 Federal Register / Vol. 80, No. 19 / Thursday, January 29, 2015 / Rules and Regulations 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 airworthiness directive (AD): ■ 2015–02–17 Airbus: Amendment 39–18084. Docket No. FAA–2015–0078; Directorate Identifier 2014–NM–235–AD. (a) Effective Date This AD becomes effective February 13, 2015. (b) Affected ADs None. (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category, all manufacturer serial numbers. (1) Airbus Model A330–201, –202, –203, –223, –223F, –243, and –243F airplanes. (2) Airbus Model A330–301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes. (d) Subject Air Transport Association (ATA) of America Code 24, Electrical Power. (e) Reason This AD was prompted by an electrical load analysis that revealed that hydraulic power might not be sufficient to supply the constant speed motor/generator (CSM/G) during slat/flap extension when only one engine is running. We are issuing this AD to prevent such a condition which, in conjunction with the loss of the main electrical system, could lead to the scenario where the flightcrew is not clearly warned that the electrical system has switched on the battery and thus has a limited duration that would allow a safe landing. tkelley on DSK3SPTVN1PROD with RULES (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Revise Airplane Flight Manual (AFM) Within 15 days after the effective date of this AD, revise the Emergency Procedures section of the Airbus A330 AFM to include the information in the applicable Airbus temporary revision (TR) specified in paragraph (g)(1) or (g)(2) of this AD. This may be done by inserting a copy of the applicable TR specified in paragraph (g)(1) or (g)(2) of this AD into the AFM. Operate the airplane according to the procedures in the applicable VerDate Sep<11>2014 16:36 Jan 28, 2015 Jkt 235001 TR. When the information in the applicable TR has been included in the general revisions of the AFM, the general revisions may be inserted into the AFM, provided the relevant information in the general revision is identical to that in the TR, and the TR may be removed. (1) For airplanes in Airbus premodification 47930 configuration and preAirbus Service Bulletin A330–28–3067 configuration: Airbus A330/A340 AFM TR TR427, UPDATE OF ELEC—EMER CONFIG PROCEDURE, Issue 1.0, dated November 7, 2014. (2) For airplanes in Airbus postmodification 47930 configuration or postAirbus Service Bulletin A330–28–3067 configuration: Airbus A330/A340 AFM TR TR428, UPDATE OF ELEC—EMER CONFIG PROCEDURE, Issue 1.0, dated November 7, 2014. (h) Other FAA AD Provisions 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. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (i) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0281, dated December 22, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2015–0078. (j) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus A330/A340 Airplane Flight Manual (AFM) Temporary Revision TR427, UPDATE OF ELEC—EMER CONFIG PROCEDURE, Issue 1.0, dated November 7, 2014. (ii) Airbus A330/A340 AFM Temporary Revision TR428, UPDATE OF ELEC—EMER CONFIG PROCEDURE, Issue 1.0, dated November 7, 2014. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may view this 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: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on January 9, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–01178 Filed 1–28–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0683; Directorate Identifier 2010–NE–25–AD; Amendment 39– 18065; AD 2015–02–01] RIN 2120–AA64 Airworthiness Directives; Technify Motors GmbH (Type Certificate Previously Held by Thielert Aircraft Engines GmbH) Reciprocating Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are superseding airworthiness directive (AD) 2011–23– 01 for all Technify Motors GmbH (TMG) models TAE 125–01 and TAE 125–02– 99 reciprocating engines with certain part number (P/N) and serial number (S/ N) clutch assemblies installed. AD 2011–23–01 required replacement of certain P/N and S/N clutch assemblies. This AD requires the same actions but SUMMARY: E:\FR\FM\29JAR1.SGM 29JAR1

Agencies

[Federal Register Volume 80, Number 19 (Thursday, January 29, 2015)]
[Rules and Regulations]
[Pages 4762-4764]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-01178]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0078; Directorate Identifier 2014-NM-235-AD; 
Amendment 39-18084; AD 2015-02-17]
RIN 2120-AA64


Airworthiness Directives; Airbus 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 all 
Airbus Model A330-200, A330-200 Freighter, and A330-300 series 
airplanes. This AD requires revising the electrical emergency 
configuration procedure in the Emergency Procedures section of the 
airplane flight manual (AFM) to include procedures for deploying the 
ram air turbine manually to provide sufficient hydraulic power and 
avoid constant speed motor/generator (CSM/G) shedding. This AD was 
prompted by an electrical load analysis that revealed that hydraulic 
power might not be sufficient to supply the CSM/G during slat/flap 
extension when only one engine is running. We are issuing this AD to 
prevent such a condition which, in conjunction with the loss of the 
main electrical system, could lead to the scenario where the flightcrew 
is not clearly warned that the electrical system has switched on the 
battery and thus has a limited duration that would allow a safe 
landing.

DATES: This AD becomes effective February 13, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of February 13, 
2015.
    We must receive comments on this AD by March 16, 2015.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://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 W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this AD, contact Airbus SAS, 
Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; 
email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0078; 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: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; 
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 Union, has issued EASA 
Airworthiness Directive 2014-0281, dated December 22, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition on all Airbus Model A330-
200, A330-200 Freighter, and A330-300 series airplanes. The MCAI 
states:

    The Constant Speed Motor/Generator (CSM/G), as installed on 
Airbus A330

[[Page 4763]]

aeroplanes, is qualified for an overload condition of 9.5kVA 
[kilovolt-ampere] for 30 minutes. This duration is sufficient to 
perform safe landing and a GO-AROUND. However, electrical load 
analysis revealed that the hydraulic power might not be sufficient 
to supply the CSM/G during slat/flap extension when only one engine 
is running.
    This condition, if not corrected, and in conjunction with the 
loss of main electrical system, could lead to the scenario where the 
crew is not clearly warned that the electrical system has switched 
on the battery and thus has a limited duration that would allow a 
safe landing.
    To address this potential unsafe condition, Airbus issued an 
Aircraft Flight Manual (AFM) Temporary Revision (TR) on A330 
aeroplane to update the electrical emergency configuration ``ELEC 
EMER CONFIG'' procedure to require the pilot to deploy the ram air 
turbine manually before setting the Landing Recovery to ON position 
to provide sufficient hydraulic power and avoid CSM/G shedding under 
worst-case operational conditions.
    Consequently, EASA issued AD 2014-0273 (http://ad.easa.europa.eu/blob/easa_ad_2014_0273_superseded.pdf/AD_2014-0273_1) to require amendment of the AFM by incorporating the 
applicable Airbus TR.
    After that [EASA] AD was issued, EASA became aware that the 
reference to Airbus modification (mod) 47930 was insufficient to 
define which AFM TR is applicable to which aeroplane 
(configuration), as this mod can be embodied in service with Airbus 
Service Bulletin (SB) A330-28-3067.
    For the reason described above, this [EASA] AD retains the 
requirements of EASA AD 2014-0273, which is superseded, and corrects 
the information included in Table 1.

You may examine the MCAI on the Internet at http://www.regulations.gov 
by searching for and locating Docket No. FAA-2015-0078.

Related Service Information

    Airbus has issued A330/A340 Airplane Flight Manual (AFM) Temporary 
Revision (TR) TR427, UPDATE OF ELEC--EMER CONFIG PROCEDURE, Issue 1.0, 
dated November 7, 2014 (for airplanes in Airbus pre-modification 47930 
configuration or pre-Airbus Service Bulletin A330-28-3067 
configuration); and A330/A340 AFM TR TR428, UPDATE OF ELEC--EMER CONFIG 
PROCEDURE, Issue 1.0, dated November 7, 2014 (for airplanes in Airbus 
post-modification 47930 configuration or post-Airbus Service Bulletin 
A330-28-3067 configuration). This service information describes updated 
electrical emergency configuration procedures in the AFM. You can find 
this information at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2015-0078.

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.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because 
hydraulic power might not be sufficient to supply the CSM/G during 
slat/flap extension when only one engine is running. This condition, in 
conjunction with the loss of the main electrical system, could lead to 
the scenario where the flightcrew is not clearly warned that the 
electrical system has switched on the battery and thus has a limited 
duration that would allow a safe landing. Therefore, we determined that 
notice and opportunity for public comment before issuing this AD are 
impracticable and that good cause exists for making this amendment 
effective in fewer than 30 days.

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-2015-0078; Directorate 
Identifier 2014-NM-235-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 based on 
those comments.
    We will post all comments we receive, without change, to http://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.

Costs of Compliance

    We estimate that this AD affects 91 airplanes of U.S. registry.
    We also estimate that it will take about 1 work-hour per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Based on these figures, we estimate the cost of 
this AD on U.S. operators to be $7,735, or $85 per product.

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 that 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);
    3. Will not affect intrastate aviation in Alaska; and
    4. 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.

List of Subjects in 14 CFR Part 39

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

[[Page 4764]]

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

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):

2015-02-17 Airbus: Amendment 39-18084. Docket No. FAA-2015-0078; 
Directorate Identifier 2014-NM-235-AD.

(a) Effective Date

    This AD becomes effective February 13, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
and (c)(2) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Airbus Model A330-201, -202, -203, -223, -223F, -243, and -
243F airplanes.
    (2) Airbus Model A330-301, -302, -303, -321, -322, -323, -341, -
342, and -343 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 24, Electrical 
Power.

(e) Reason

    This AD was prompted by an electrical load analysis that 
revealed that hydraulic power might not be sufficient to supply the 
constant speed motor/generator (CSM/G) during slat/flap extension 
when only one engine is running. We are issuing this AD to prevent 
such a condition which, in conjunction with the loss of the main 
electrical system, could lead to the scenario where the flightcrew 
is not clearly warned that the electrical system has switched on the 
battery and thus has a limited duration that would allow a safe 
landing.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Revise Airplane Flight Manual (AFM)

    Within 15 days after the effective date of this AD, revise the 
Emergency Procedures section of the Airbus A330 AFM to include the 
information in the applicable Airbus temporary revision (TR) 
specified in paragraph (g)(1) or (g)(2) of this AD. This may be done 
by inserting a copy of the applicable TR specified in paragraph 
(g)(1) or (g)(2) of this AD into the AFM. Operate the airplane 
according to the procedures in the applicable TR. When the 
information in the applicable TR has been included in the general 
revisions of the AFM, the general revisions may be inserted into the 
AFM, provided the relevant information in the general revision is 
identical to that in the TR, and the TR may be removed.
    (1) For airplanes in Airbus pre-modification 47930 configuration 
and pre-Airbus Service Bulletin A330-28-3067 configuration: Airbus 
A330/A340 AFM TR TR427, UPDATE OF ELEC--EMER CONFIG PROCEDURE, Issue 
1.0, dated November 7, 2014.
    (2) For airplanes in Airbus post-modification 47930 
configuration or post-Airbus Service Bulletin A330-28-3067 
configuration: Airbus A330/A340 AFM TR TR428, UPDATE OF ELEC--EMER 
CONFIG PROCEDURE, Issue 1.0, dated November 7, 2014.

(h) Other FAA AD Provisions

    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. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. Information 
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.

(i) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
EASA Airworthiness Directive 2014-0281, dated December 22, 2014, for 
related information. This MCAI may be found in the AD docket on the 
Internet at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2015-0078.

(j) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus A330/A340 Airplane Flight Manual (AFM) Temporary 
Revision TR427, UPDATE OF ELEC--EMER CONFIG PROCEDURE, Issue 1.0, 
dated November 7, 2014.
    (ii) Airbus A330/A340 AFM Temporary Revision TR428, UPDATE OF 
ELEC--EMER CONFIG PROCEDURE, Issue 1.0, dated November 7, 2014.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; 
Internet http://www.airbus.com.
    (4) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (5) You may view this 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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on January 9, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-01178 Filed 1-28-15; 8:45 am]
BILLING CODE 4910-13-P