Airworthiness Directives; Airbus Airplanes, 33045-33048 [2014-12444]

Download as PDF Federal Register / Vol. 79, No. 111 / Tuesday, June 10, 2014 / Rules and Regulations have been submitted in response to the prior opportunities for comment described above. List of Subjects in 14 CFR Part 25 Aircraft, Aviation safety, Reporting and recordkeeping requirements. The authority citation for these special conditions is as follows: Authority: 49 U.S.C. 106(g), 40113, 44701, 44702, 44704. emcdonald on DSK67QTVN1PROD with RULES The Special Conditions Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the type certification basis for the Embraer S.A. Model EMB–550 airplane. Installation of Rechargeable Lithium Batteries In lieu of the requirements of § 25.1353(b)(1) through (b)(4) at Amendment 25–123, all rechargeable lithium batteries and battery system installations on the Model EMB–550 must be designed and installed as follows: (1) Safe cell temperatures and pressures must be maintained during any foreseeable charging or discharging condition and during any failure of the charging or battery monitoring system not shown to be extremely remote. The rechargeable lithium battery installation must preclude explosion in the event of those failures. (2) Design of the rechargeable lithium batteries must preclude the occurrence of self-sustaining, uncontrolled increases in temperature or pressure. (3) No explosive or toxic gases emitted by any rechargeable lithium battery in normal operation, or as the result of any failure of the battery charging system, monitoring system, or battery installation that is not shown to be extremely remote, may accumulate in hazardous quantities within the airplane. (4) Installations of rechargeable lithium batteries must meet the requirements of 14 CFR 25.863(a) through (d). (5) No corrosive fluids or gases that may escape from any rechargeable lithium battery may damage surrounding structure or any adjacent systems, equipment, or electrical wiring of the airplane in such a way as to cause a major or more severe failure condition, in accordance with § 25.1309(b) and applicable regulatory guidance. (6) Each rechargeable lithium battery installation must have provisions to prevent any hazardous effect on structure or essential systems caused by the maximum amount of heat the VerDate Mar<15>2010 16:04 Jun 09, 2014 Jkt 232001 battery can generate during a short circuit of the battery or of its individual cells. (7) Rechargeable lithium battery installations must have a system to control the charging rate of the battery automatically, so as to prevent battery overheating or overcharging, and, (i) A battery temperature sensing and over-temperature warning system with a means for automatically disconnecting the battery from its charging source in the event of an over-temperature condition, or, (ii) A battery failure sensing and warning system with a means for automatically disconnecting the battery from its charging source in the event of battery failure. (8) Any rechargeable lithium battery installation, the function of which is required for safe operation of the airplane, must incorporate a monitoring and warning feature that will provide an indication to the appropriate flight crewmembers whenever the state-ofcharge of the batteries has fallen below levels considered acceptable for dispatch of the airplane. (9) The Instructions for Continued Airworthiness required by § 25.1529 must contain maintenance requirements to assure that the battery is sufficiently charged at appropriate intervals specified by the battery manufacturer and the equipment manufacturer that contain the rechargeable lithium battery or rechargeable lithium battery system. This is required to ensure that lithium rechargeable batteries and lithium rechargeable battery systems will not degrade below specified ampere-hour levels sufficient to power the aircraft system, for intended applications. The Instructions for Continued Airworthiness must also contain procedures for the maintenance of batteries in spares storage to prevent the replacement of batteries with batteries that have experienced degraded charge retention ability or other damage due to prolonged storage at a low state of charge. Replacement batteries must be of the same manufacturer and part number as approved by the FAA. Precautions should be included in the Instructions for Continued Airworthiness maintenance instructions to prevent mishandling of the rechargeable lithium battery and rechargeable lithium battery systems that could result in short-circuit or other unintentional impact damage caused by dropping or other destructive means that could result in personal injury or property damage. Note 1: The electrical wiring interconnection systems (EWIS) maintenance PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 33045 and inspection tasks required by § 25.1729 must ensure that EWIS components associated with the batteries and battery systems are sufficient to detect degradation of any EWIS component that is designed and installed to support compliance with special conditions 1 through 8. Note 2: The term ‘‘sufficiently charged’’ means that the battery will retain enough of a charge, expressed in ampere-hours, to ensure that the battery cells will not be damaged. A battery cell may be damaged by lowering the charge below a point where there is a reduction in the ability to charge and retain a full charge. This reduction would be greater than the reduction that may result from normal operational degradation. Note 3: These special conditions are not intended to replace § 25.1353(b) at Amendment 25–123 in the certification basis of the Embraer Model EMB–550. These special conditions apply only to rechargeable lithium batteries and rechargeable lithium battery systems and their installations. The requirements of § 25.1353(b) at Amendment 25–123 remain in effect for batteries and battery installations on the Embraer Model EMB–550 that do not use rechargeable lithium batteries. Issued in Renton, Washington, on June 2, 2014. Michael Kaszycki, Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–13530 Filed 6–9–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–1031; Directorate Identifier 2013–NM–155–AD; Amendment 39–17854; AD 2014–11–04] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330–200, A330–200 Freighter, and A330–300 series airplanes; and Model A340–200, A340– 300, A340–500, and A340–600 series airplanes. This AD was prompted by a non-connection of the constant speed motor/generator (CSM/G) during a final assembly operational test. This AD requires a detailed inspection of the connector wires for connector 1XE–A of the generator control unit (GCU)–CSM/ SUMMARY: E:\FR\FM\10JNR1.SGM 10JNR1 33046 Federal Register / Vol. 79, No. 111 / Tuesday, June 10, 2014 / Rules and Regulations emcdonald on DSK67QTVN1PROD with RULES G for discrepancies (evidence of arcing or overheating damage), and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct incorrect locking of contacts into connector 1XE–A of the GCU–CSM/G, which could result in a loss of contact continuity and lead to the CSM/G not operating, which, in conjunction with an emergency electrical configuration loss of the main electrical system or total engine flameout, could adversely affect the airplane’s safe flight. DATES: This AD becomes effective July 15, 2014. The Director of the Federal Register approved the incorporation by reference of a certain publications listed in this AD as of July 15, 2014. ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov/ #!docketDetail;D=FAA-2013-1031; or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. 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 https://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. 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 We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Airbus Model A330– 200, A330–200 Freighter, and A330–300 series airplanes; and Model A340–200, A340–300, A340–500, and A340–600 series airplanes. The NPRM published in the Federal Register on December 26, 2013 (78 FR 78294). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA VerDate Mar<15>2010 16:04 Jun 09, 2014 Jkt 232001 Airworthiness Directive 2013–0175, dated August 2, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: During Final Assembly Line tests on an A330 aeroplane, the Generator Control Unit—Constant Speed Motor/Generator (GCU–CSM/G) failed the operational test. Investigations revealed that it is due to incorrect locking of some contacts (pins) into the GCU–CSM/G connector 1XE–A. An inspection of other aeroplanes confirmed this production quality issue. Among the 26 pins used in GCU–CSM/G connector 1XE–A, 6 pins have been identified as potentially affected by this issue. A badly locked contact could result in a loss of continuity [non-connection] and lead to the non-operation of the CSM/G. This condition, if not detected and corrected, and in conjunction with either an emergency electrical configuration loss of main electrical system or total engine flame out, could jeopardize the aeroplane’s safe flight. To address this condition, Airbus developed Alert Operator Transmission (AOT) A24L001–13, to provide instructions for a one-time inspection. For the reasons described above, this AD requires a one-time [detailed] inspection of the potentially affected connector wires of GCU–CSM/G connector 1XE–A and, depending on [the] finding, accomplishment of [a related investigative action] and applicable corrective actions. You may examine the MCAI in the AD docket on the Internet at https:// www.regulations.gov/ #!documentDetail;D=FAA-2013-10310002. Revised Service Information Since the NPRM (78 FR 78294, December 26, 2013) was published, we have received Airbus Alert Operators Transmission A24L001–13, Revision 01, dated March 6, 2014. We have determined that this service information does not add any additional actions to those proposed in the NPRM, therefore, we have revised paragraph (g) of this AD to refer to that service information. We have also added a new paragraph (h) to this AD to provide credit for actions performed before the effective date of this AD using Airbus Alert Operators Transmission A24L001–13, dated July 25, 2013, and redesignated the subsequent paragraphs accordingly. Additionally, we have added paragraph (k), Material Incorporated by Reference, to the end of this AD. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comment PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 received on the NPRM (78 FR 78294, December 26, 2013) and the FAA’s response to that comment. Request To Clarify What Prompted the NPRM (78 FR 78294, December 26, 2013) Airbus requested clarification in the SUMMARY section and paragraph (e) of the NPRM (78 FR 78294, December 26, 2013). Airbus stated that it was not ‘‘failure of the generator control unitconstant speed motor/generator during a final assembly operational test’’ that caused the unsafe condition, but a nonconnection of the CSM/G during an operational test in the final assembly line. Investigations revealed an incorrect locking of some contacts into connector 1XE–A of the GCU–CSM/G. We agree to revise the SUMMARY section and paragraph (e) of this final rule to state that this AD was prompted by a non-connection of the CSM/G during a final assembly operational test. Changes to This Final Rule Paragraphs (g)(1) and (g)(2) in the NPRM (78 FR 78294, December 26, 2013) have been combined into paragraph (g) in this final rule. Conclusion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (78 FR 78294, December 26, 2013) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (78 FR 78294, December 26, 2013). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Costs of Compliance We estimate that this AD affects 76 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. Required parts will cost about $0 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $6,460, or $85 per product. In addition, we estimate that any necessary follow-on actions will take about 1 work-hour and require parts costing up to $17,314, for a cost of up E:\FR\FM\10JNR1.SGM 10JNR1 Federal Register / Vol. 79, No. 111 / Tuesday, June 10, 2014 / Rules and Regulations to $17,399 per product. We have no way of determining the number of aircraft that might need this action. 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. emcdonald on DSK67QTVN1PROD with RULES 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. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov/ #!docketDetail;D=FAA-2013-1031; or in person at the Docket Management Facility 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. VerDate Mar<15>2010 16:04 Jun 09, 2014 Jkt 232001 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 airworthiness directive (AD): ■ 2014–11–04 Airbus: Amendment 39–17854. Docket No. FAA–2013–1031; Directorate Identifier 2013–NM–155–AD. (a) Effective Date This AD becomes effective July 15, 2014. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A330– 201, –202, –203, –223, –223F, –243, –243F, –301, –302, –303, –321, –322, –323, –341, –342, –343 airplanes; and A340–211, –212, –213, –311, –312, –313, –541, and –642 airplanes; certificated in any category; manufacturer serial numbers (MSNs) 1 through 1391 inclusive, except MSNs 0925 and 1382. (d) Subject Air Transport Association (ATA) of America Code 24, Electrical Power. (e) Reason This AD was prompted by a nonconnection of the constant speed motor/ generator (CSM/G) during a final assembly operational test. We are issuing this AD to detect and correct incorrect locking of contacts into connector 1XE–A of the generator control unit (GCU)–CSM/G, which could result in a loss of contact continuity and lead to the CSM/G not operating, which, in conjunction with an emergency electrical configuration loss of the main electrical system or total engine flameout, could adversely affect the airplane’s safe flight. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspections and Corrective Actions Within 1,000 flight hours after the effective date of this AD: Do a detailed inspection for discrepancies (proper engagement and evidence of arcing or overheating) of the affected connector wires of connector 1XE– A of the GCU–CSM/G, in accordance with PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 33047 Airbus Alert Operators Transmission A24L001–13, Revision 01, dated March 6, 2014. If any discrepancy is detected during the inspection, before further flight, do all applicable related investigative and corrective actions, in accordance with Airbus Alert Operators Transmission A24L001–13, Revision 01, dated March 6, 2014. (h) Credit for Previous Actions This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Airbus Alert Operators Transmission A24L001–13, dated July 25, 2013, which is not incorporated by reference in this AD. (i) 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) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they were approved by the State of Design Authority (or its delegated agent, or the Design Approval Holder with a State of Design Authority’s design organization approval, as applicable). You are required to ensure the product is airworthy before it is returned to service. (j) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency Airworthiness Directive 2013–0175, dated August 2, 2013, for related information. This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov/ #!documentDetail;D=FAA-2013-1031-0002. (2) Service information identified in this AD that is not incorporated by reference may be viewed at the addresses specified in paragraphs (k)(3) and (k)(4) of this AD. (k) 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. E:\FR\FM\10JNR1.SGM 10JNR1 33048 Federal Register / Vol. 79, No. 111 / Tuesday, June 10, 2014 / Rules and Regulations (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Alert Operators Transmission A24L001–13, Revision 01, dated March 6, 2014. (ii) Reserved. (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 https://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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on May 16, 2014. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–12444 Filed 6–9–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–1088; Directorate Identifier 2008–NE–15–AD; Amendment 39– 17831; AD 2008–21–07R1] RIN 2120–AA64 Airworthiness Directives; Dowty Propellers Propellers Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are revising airworthiness directive (AD) 2008–21–07 for certain Dowty Propellers model R408/6–123–F/ 17 propellers. AD 2008–21–07 required initial and repetitive inspections of the blade bonded metallic leading edge (L/ E) guards for correct bonding until they accumulate more than 1,200 flight hours (FH) time-in-service. This AD requires the same inspection and replacement requirements of AD 2008–21–07. This AD also provides an optional terminating action to those requirements. This AD was prompted by updated service bulletins that identify terminating action to the requirements of AD 2008–21–07. We are issuing this AD to prevent the loss of the bonded emcdonald on DSK67QTVN1PROD with RULES SUMMARY: VerDate Mar<15>2010 16:04 Jun 09, 2014 Jkt 232001 metallic L/E guard of the propeller, which could result in damage to the propeller or to the airplane, or injury to personnel. DATES: This AD is effective July 15, 2014. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of July 15, 2014. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of October 31, 2008 (73 FR 61346, October 16, 2008). ADDRESSES: For service information identified in this AD, contact Dowty Propellers, Anson Business Park, Cheltenham Road East, Gloucester GL2 9QN, UK; phone: 44 (0) 1452 716000; fax: 44 (0) 1452 716001. You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781– 238–7125. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2008– 1088; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the mandatory continuing airworthiness information (MCAI), the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590 FOR FURTHER INFORMATION CONTACT: Michael Schwetz, Aerospace Engineer, Boston Aircraft Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781– 238–7761; fax: 781–238–7170; email: michael.schwetz@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to revise AD 2008–21–07, Amendment 39–15691 (73 FR 61346, October 16, 2008), (‘‘AD 2008–21–07’’). AD 2008–21–07 applied to the specified products. The NPRM published in the Federal Register on December 26, 2013 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 (78 FR 78290). The NPRM proposed to continue to require the inspection and replacement requirements of AD 2008– 21–07 and provide an optional terminating action to those requirements. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (78 FR 78290, December 26, 2013). Since we issued the NPRM we received information that propeller blade, part number (P/N) 697071278–18, has not been implemented and that no parts were manufactured using this P/N. We removed propeller blade, P/N 697071278–18, from this AD. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting this AD with the changes described previously. We determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Costs of Compliance We estimate that this AD affects 174 propellers installed on airplanes of U.S. registry. We also estimate that it will take about 4 hours per propeller to comply with this AD. The average labor rate is $85 per hour. Required parts cost about $352 per propeller. Based on these figures, we estimate the cost of this AD to U.S. operators is $120,408. 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 This AD will not have federalism implications under Executive Order E:\FR\FM\10JNR1.SGM 10JNR1

Agencies

[Federal Register Volume 79, Number 111 (Tuesday, June 10, 2014)]
[Rules and Regulations]
[Pages 33045-33048]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-12444]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-1031; Directorate Identifier 2013-NM-155-AD; 
Amendment 39-17854; AD 2014-11-04]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus Model A330-200, A330-200 Freighter, and A330-300 series 
airplanes; and Model A340-200, A340-300, A340-500, and A340-600 series 
airplanes. This AD was prompted by a non-connection of the constant 
speed motor/generator (CSM/G) during a final assembly operational test. 
This AD requires a detailed inspection of the connector wires for 
connector 1XE-A of the generator control unit (GCU)-CSM/

[[Page 33046]]

G for discrepancies (evidence of arcing or overheating damage), and 
related investigative and corrective actions if necessary. We are 
issuing this AD to detect and correct incorrect locking of contacts 
into connector 1XE-A of the GCU-CSM/G, which could result in a loss of 
contact continuity and lead to the CSM/G not operating, which, in 
conjunction with an emergency electrical configuration loss of the main 
electrical system or total engine flameout, could adversely affect the 
airplane's safe flight.

DATES: This AD becomes effective July 15, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publications listed in this AD as of July 15, 
2014.

ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2013-1031; or in person at the 
Docket Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC.
    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 https://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.

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

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain Airbus Model A330-
200, A330-200 Freighter, and A330-300 series airplanes; and Model A340-
200, A340-300, A340-500, and A340-600 series airplanes. The NPRM 
published in the Federal Register on December 26, 2013 (78 FR 78294).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2013-0175, dated August 2, 2013 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    During Final Assembly Line tests on an A330 aeroplane, the 
Generator Control Unit--Constant Speed Motor/Generator (GCU-CSM/G) 
failed the operational test.
    Investigations revealed that it is due to incorrect locking of 
some contacts (pins) into the GCU-CSM/G connector 1XE-A. An 
inspection of other aeroplanes confirmed this production quality 
issue. Among the 26 pins used in GCU-CSM/G connector 1XE-A, 6 pins 
have been identified as potentially affected by this issue.
    A badly locked contact could result in a loss of continuity 
[non-connection] and lead to the non-operation of the CSM/G.
    This condition, if not detected and corrected, and in 
conjunction with either an emergency electrical configuration loss 
of main electrical system or total engine flame out, could 
jeopardize the aeroplane's safe flight.
    To address this condition, Airbus developed Alert Operator 
Transmission (AOT) A24L001-13, to provide instructions for a one-
time inspection.
    For the reasons described above, this AD requires a one-time 
[detailed] inspection of the potentially affected connector wires of 
GCU-CSM/G connector 1XE-A and, depending on [the] finding, 
accomplishment of [a related investigative action] and applicable 
corrective actions.

    You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2013-1031-0002.

Revised Service Information

    Since the NPRM (78 FR 78294, December 26, 2013) was published, we 
have received Airbus Alert Operators Transmission A24L001-13, Revision 
01, dated March 6, 2014. We have determined that this service 
information does not add any additional actions to those proposed in 
the NPRM, therefore, we have revised paragraph (g) of this AD to refer 
to that service information. We have also added a new paragraph (h) to 
this AD to provide credit for actions performed before the effective 
date of this AD using Airbus Alert Operators Transmission A24L001-13, 
dated July 25, 2013, and redesignated the subsequent paragraphs 
accordingly. Additionally, we have added paragraph (k), Material 
Incorporated by Reference, to the end of this AD.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comment received on the NPRM (78 FR 
78294, December 26, 2013) and the FAA's response to that comment.

Request To Clarify What Prompted the NPRM (78 FR 78294, December 26, 
2013)

    Airbus requested clarification in the SUMMARY section and paragraph 
(e) of the NPRM (78 FR 78294, December 26, 2013). Airbus stated that it 
was not ``failure of the generator control unit-constant speed motor/
generator during a final assembly operational test'' that caused the 
unsafe condition, but a non-connection of the CSM/G during an 
operational test in the final assembly line. Investigations revealed an 
incorrect locking of some contacts into connector 1XE-A of the GCU-CSM/
G.
    We agree to revise the SUMMARY section and paragraph (e) of this 
final rule to state that this AD was prompted by a non-connection of 
the CSM/G during a final assembly operational test.

Changes to This Final Rule

    Paragraphs (g)(1) and (g)(2) in the NPRM (78 FR 78294, December 26, 
2013) have been combined into paragraph (g) in this final rule.

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (78 FR 78294, December 26, 2013) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 78294, December 26, 2013).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 76 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. Required parts will cost about $0 per product. 
Based on these figures, we estimate the cost of this AD on U.S. 
operators to be $6,460, or $85 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 1 work-hour and require parts costing up to $17,314, for a 
cost of up

[[Page 33047]]

to $17,399 per product. We have no way of determining the number of 
aircraft that might need this action.

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.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2013-1031; or in person at the 
Docket Management Facility 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.

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

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):

2014-11-04 Airbus: Amendment 39-17854. Docket No. FAA-2013-1031; 
Directorate Identifier 2013-NM-155-AD.

(a) Effective Date

    This AD becomes effective July 15, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A330-201, -202, -203, -223, -
223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342, -
343 airplanes; and A340-211, -212, -213, -311, -312, -313, -541, and 
-642 airplanes; certificated in any category; manufacturer serial 
numbers (MSNs) 1 through 1391 inclusive, except MSNs 0925 and 1382.

(d) Subject

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

(e) Reason

    This AD was prompted by a non-connection of the constant speed 
motor/generator (CSM/G) during a final assembly operational test. We 
are issuing this AD to detect and correct incorrect locking of 
contacts into connector 1XE-A of the generator control unit (GCU)-
CSM/G, which could result in a loss of contact continuity and lead 
to the CSM/G not operating, which, in conjunction with an emergency 
electrical configuration loss of the main electrical system or total 
engine flameout, could adversely affect the airplane's safe flight.

(f) Compliance

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

(g) Inspections and Corrective Actions

    Within 1,000 flight hours after the effective date of this AD: 
Do a detailed inspection for discrepancies (proper engagement and 
evidence of arcing or overheating) of the affected connector wires 
of connector 1XE-A of the GCU-CSM/G, in accordance with Airbus Alert 
Operators Transmission A24L001-13, Revision 01, dated March 6, 2014. 
If any discrepancy is detected during the inspection, before further 
flight, do all applicable related investigative and corrective 
actions, in accordance with Airbus Alert Operators Transmission 
A24L001-13, Revision 01, dated March 6, 2014.

(h) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Alert Operators Transmission 
A24L001-13, dated July 25, 2013, which is not incorporated by 
reference in this AD.

(i) 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) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer, use these actions if they 
are FAA-approved. Corrective actions are considered FAA-approved if 
they were approved by the State of Design Authority (or its 
delegated agent, or the Design Approval Holder with a State of 
Design Authority's design organization approval, as applicable). You 
are required to ensure the product is airworthy before it is 
returned to service.

(j) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European Aviation Safety Agency Airworthiness Directive 2013-
0175, dated August 2, 2013, for related information. This MCAI may 
be found in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2013-1031-0002.
    (2) Service information identified in this AD that is not 
incorporated by reference may be viewed at the addresses specified 
in paragraphs (k)(3) and (k)(4) of this AD.

(k) 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.

[[Page 33048]]

    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Alert Operators Transmission A24L001-13, Revision 01, 
dated March 6, 2014.
    (ii) Reserved.
    (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 https://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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.


    Issued in Renton, Washington, on May 16, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-12444 Filed 6-9-14; 8:45 am]
BILLING CODE 4910-13-P
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