Airworthiness Directives; Airbus Airplanes, 52935-52937 [2015-21475]

Download as PDF 52935 Rules and Regulations Federal Register Vol. 80, No. 170 Wednesday, September 2, 2015 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. Prices of new books are listed in the first FEDERAL REGISTER issue of each week. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0085; Directorate Identifier 2014–NM–078–AD; Amendment 39–18255; AD 2015–17–22] 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 all Airbus Model A330–243, A330–243F, A330–341, A330–342, and A330–343 airplanes. This AD was prompted by reports indicating that certain hinge sleeves on the cowl doors of the thrust reverser units (TRUs) were not heat treated. This AD requires replacing the sleeves of certain hinges on the cowl doors of the TRUs with new parts. We are issuing this AD to prevent, in the event of a fan-blade-off event due to high vibration, in-flight loss of TRU heavy components, which might damage airplane structure or control surfaces and consequently reduce controllability of the airplane. DATES: This AD becomes effective October 7, 2015. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of October 7, 2015. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2015-0085 or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room asabaliauskas on DSK5VPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 19:00 Sep 01, 2015 Jkt 235001 W12–140, 1200 New Jersey Avenue SE., Washington, DC. For Airbus 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. For Aircelle service information identified in this AD, contact Aircelle Customer support Center, BP 50042, 50, rue Pierre Curie, 78371 Plaisir Cedex, France: telephone +33 (0)1 64 14 80 33; fax +33 (0)1 64 14 84 10. 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2015–0085. 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 all Airbus Model A330–243, A330–243F, A330–341, A330–342, and A330–343 airplanes. The NPRM published in the Federal Register on February 13, 2015 (80 FR 7986). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0062, dated March 11, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A330–243, A330–243F, A330– 341, A330–342, and A330–343 airplanes. The MCAI states: A manufacturing discrepancy (lack of heat treatment) on a batch of the N°3 and N°4 hinge sleeves installed on [a] Thrust Reverser Unit (TRU) was identified. Those parts are only installed on A330 aeroplanes equipped with Rolls-Royce (RR) Trent 700 engines. This condition, if not corrected, in case of a Fan Blade Off event due to high vibration PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 level, could cause in-flight loss of some heavy components of the TRU, possibly resulting in injury to persons on the ground [or damage to airplane structure or control surfaces, and consequent reduced controllability of the airplane]. As current hinge sleeves are not serialized, it is not possible to identify the TRU hinge sleeves which did not receive the heat treatment. The part supplier has developed an identification procedure for these TRU hinge sleeves in order to identify the affected hinge sleeves, and to allow a better part traceability in the future. For the reason described above, this [EASA] AD requires identification and replacement of the affected TRU hinge sleeves. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/#!documentDetail; D=FAA-2015-0085-0002. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (80 FR 7986, February 13, 2015) or on the determination of the cost to the public. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (80 FR 7986, February 13, 2015) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (80 FR 7986, February 13, 2015). Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A330–78–3021, Revision 03, dated October 15, 2014. Aircelle has issued Service Bulletin 78–AG924, dated September 26, 2012. This service information describes procedures for modifying and marking the sleeves for hinges number 3 and number 4 on the cowl doors of Rolls-Royce Trent 700 engines. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this AD. E:\FR\FM\02SER1.SGM 02SER1 52936 Federal Register / Vol. 80, No. 170 / Wednesday, September 2, 2015 / Rules and Regulations Costs of Compliance We estimate that this AD affects 24 airplanes of U.S. registry. We also estimate that it will take about 29 work-hours 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 $59,160, or $2,465 per product. In addition, we estimate that any necessary follow-on action will take up to 1 work-hour and require parts costing $0, for a cost of $85 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. asabaliauskas on DSK5VPTVN1PROD 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. VerDate Sep<11>2014 19:00 Sep 01, 2015 Jkt 235001 Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov/#!docketDetail;D= FAA-015-0085; 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 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): ■ 2015–17–22 Airbus: Amendment 39–18255. Docket No. FAA–2015–0085; Directorate Identifier 2014–NM–078–AD. (a) Effective Date This AD becomes effective October 7, 2015. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus Model A330– 243, A330–243F, A330–341, A330–342, and A330–343 airplanes, certificated in any category, all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 78, Exhaust. (e) Reason This AD was prompted by reports indicating that certain hinge sleeves on the cowl doors of the thrust reverser units (TRUs) were not heat treated. We are issuing this AD to prevent, in the event of a fan-blade-off event due to high vibration, in-flight loss of TRU heavy components, which might damage airplane structure or control surfaces and consequently reduce controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 (g) Identification of TRU Part Number Within 12 months after the effective date of this AD: Identify the part number of the TRUs, in accordance with the information in Aircelle Service Bulletin 78–AG924, dated September 26, 2012. (h) Replacement of TRU Hinge Sleeves If the results of the part identification required by paragraph (g) of this AD reveal that the TRUs are affected: Within the compliance time defined in paragraph (g) of this AD, replace hinge sleeves numbers 3 and 4 of each TRU cowl door, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–78–3021, Revision 03, dated October 15, 2014. Note 1 to paragraph (h) of this AD: RollsRoyce Alert Service Bulletin RB.211–78– AG924, dated September 26, 2012, is an additional source of guidance for replacing the TRUs and is not incorporated by reference in this AD. (i) Optional Terminating Action for Paragraphs (g) and (h) of this AD Modifying an airplane by incorporating Airbus Modification 202463 in production terminates the requirements specified in paragraphs (g) and (h) of this AD for that airplane. (j) Parts Installation Limitation As of the effective date of this AD, no person may install a TRU on any airplane unless it has been determined, using Aircelle Service Bulletin 78–AG924, dated September 26, 2012, that the cowl door hinge sleeves installed on the TRU are not affected by the requirements of this AD. (k) Credit for Previous Actions This paragraph provides credit for the actions required by paragraph (h) of this AD if those actions were performed before the effective date of this AD using the service information identified in paragraphs (k)(1), (k)(2), or (k)(3) of this AD, which are not incorporated by reference in this AD. (1) Airbus Service Bulletin A330–78–3021, dated October 17, 2012. (2) Airbus Service Bulletin A330–78–3021, Revision 01, dated July 30, 2013. (3) Airbus Service Bulletin A330–78–3021, Revision 02, dated April 17, 2014. (l) 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- E:\FR\FM\02SER1.SGM 02SER1 Federal Register / Vol. 80, No. 170 / Wednesday, September 2, 2015 / Rules and Regulations 5 61 93 45 80; email airworthiness.A330– A340@airbus.com; Internet http:// www.airbus.com. (4) For Aircelle service information identified in this AD, contact Aircelle Customer support Center, BP 50042, 50, rue Pierre Curie, 78371 Plaisir Cedex, France: telephone +33 (0)1 64 14 80 33; fax +33 (0)1 64 14 84 10. (5) 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. (6) 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. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2014–0062, dated March 11, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http:// www.regulations.gov/#!document Detail;D=FAA-2015-0085-0002. (2) Airbus service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (n)(3) and (n)(5) of this AD. (3) Rolls-Royce service information identified in this AD that is not incorporated by reference is available at Rolls-Royce plc, P.O. Box 31, Derby, DE24 8BJ, England; phone: 011–44–1332–242424; fax: 011–244– 1332–249936; email: http://www.rollsroyce.com/contact/civil_team.jsp; Internet: https://www.aeromanager.com. asabaliauskas on DSK5VPTVN1PROD with RULES 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. (3) Required for Compliance (RC): Where Airbus Service Bulletin A330–78–3021, Revision 03, dated October 15, 2014, contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures and tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operators’ maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in a serviceable condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. 14 CFR Part 39 (n) 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 Service Bulletin A330–78–3021, Revision 03, dated October 15, 2014. (ii) Aircelle Service Bulletin 78–AG924, dated September 26, 2012. (3) For Airbus 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 VerDate Sep<11>2014 19:00 Sep 01, 2015 Jkt 235001 Issued in Renton, Washington, on August 21, 2015. Kevin Hull, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–21475 Filed 9–1–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration [Docket No. FAA–2015–0680; Directorate Identifier 2014–NM–165–AD; Amendment 39–18236; AD 2015–17–03] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC–8–400, –401, and –402 airplanes. This AD was prompted by a report of a main landing gear (MLG) parking brake becoming dislodged from its mounting bracket due to an improperly installed quick release pin of the hand pump lever. This AD requires removing the hand pump lever of the parking brake from the right-hand side nacelle. We are issuing this AD to prevent an unsecured lever from migrating from its stowed position, fouling against the MLG, and subsequently puncturing the nacelle structure, which could adversely affect the safe landing of the airplane. DATES: This AD becomes effective October 7, 2015. The Director of the Federal Register approved the incorporation by reference SUMMARY: PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 52937 of a certain publication listed in this AD as of October 7, 2015. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2015-0680 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 Bombardier, Inc., QSeries Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375–4000; fax 416–375–4539; email thd.qseries@ aero.bombardier.com; Internet http:// www.bombardier.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. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 0680. FOR FURTHER INFORMATION CONTACT: Cesar Gomez, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7318; fax 516–794–5531. 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 Bombardier, Inc. Model DHC–8–400, -401, and -402 airplanes. The NPRM published in the Federal Register on April 1, 2015 (80 FR 17366). The Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2014–18, dated June 19, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Bombardier, Inc. Model DHC–8–400, –401, and –402 airplanes. The MCAI states: There has been one (1) reported in-service incident where the main landing gear (MLG) parking brake hand pump lever was not properly secured in the right-hand (RH) side nacelle and became dislodged from its mounting bracket. During extension of the MLG, the unsecured lever shifted causing a fouling condition with the nacelle and subsequently puncturing the nacelle structure. E:\FR\FM\02SER1.SGM 02SER1

Agencies

[Federal Register Volume 80, Number 170 (Wednesday, September 2, 2015)]
[Rules and Regulations]
[Pages 52935-52937]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-21475]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 
Prices of new books are listed in the first FEDERAL REGISTER issue of each 
week.

========================================================================


Federal Register / Vol. 80, No. 170 / Wednesday, September 2, 2015 / 
Rules and Regulations

[[Page 52935]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0085; Directorate Identifier 2014-NM-078-AD; 
Amendment 39-18255; AD 2015-17-22]
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 all 
Airbus Model A330-243, A330-243F, A330-341, A330-342, and A330-343 
airplanes. This AD was prompted by reports indicating that certain 
hinge sleeves on the cowl doors of the thrust reverser units (TRUs) 
were not heat treated. This AD requires replacing the sleeves of 
certain hinges on the cowl doors of the TRUs with new parts. We are 
issuing this AD to prevent, in the event of a fan-blade-off event due 
to high vibration, in-flight loss of TRU heavy components, which might 
damage airplane structure or control surfaces and consequently reduce 
controllability of the airplane.

DATES: This AD becomes effective October 7, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of October 7, 
2015.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-0085 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 Airbus 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. For Aircelle service information identified in this AD, 
contact Aircelle Customer support Center, BP 50042, 50, rue Pierre 
Curie, 78371 Plaisir Cedex, France: telephone +33 (0)1 64 14 80 33; fax 
+33 (0)1 64 14 84 10. 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0085.

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 all Airbus Model A330-243, 
A330-243F, A330-341, A330-342, and A330-343 airplanes. The NPRM 
published in the Federal Register on February 13, 2015 (80 FR 7986).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0062, dated March 11, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A330-243, A330-243F, A330-341, A330-342, and A330-343 airplanes. The 
MCAI states:

    A manufacturing discrepancy (lack of heat treatment) on a batch 
of the N[deg]3 and N[deg]4 hinge sleeves installed on [a] Thrust 
Reverser Unit (TRU) was identified. Those parts are only installed 
on A330 aeroplanes equipped with Rolls-Royce (RR) Trent 700 engines.
    This condition, if not corrected, in case of a Fan Blade Off 
event due to high vibration level, could cause in-flight loss of 
some heavy components of the TRU, possibly resulting in injury to 
persons on the ground [or damage to airplane structure or control 
surfaces, and consequent reduced controllability of the airplane].
    As current hinge sleeves are not serialized, it is not possible 
to identify the TRU hinge sleeves which did not receive the heat 
treatment. The part supplier has developed an identification 
procedure for these TRU hinge sleeves in order to identify the 
affected hinge sleeves, and to allow a better part traceability in 
the future.
    For the reason described above, this [EASA] AD requires 
identification and replacement of the affected TRU hinge sleeves.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015-0085-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (80 FR 7986, February 13, 
2015) or on the determination of the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this AD as proposed except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (80 FR 7986, February 13, 2015) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (80 FR 7986, February 13, 2015).

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A330-78-3021, Revision 03, dated 
October 15, 2014. Aircelle has issued Service Bulletin 78-AG924, dated 
September 26, 2012. This service information describes procedures for 
modifying and marking the sleeves for hinges number 3 and number 4 on 
the cowl doors of Rolls-Royce Trent 700 engines. This service 
information is reasonably available because the interested parties have 
access to it through their normal course of business or by the means 
identified in the ADDRESSES section of this AD.

[[Page 52936]]

Costs of Compliance

    We estimate that this AD affects 24 airplanes of U.S. registry.
    We also estimate that it will take about 29 work-hours 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 $59,160, or $2,465 per product.
    In addition, we estimate that any necessary follow-on action will 
take up to 1 work-hour and require parts costing $0, for a cost of $85 
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 http://www.regulations.gov/#!docketDetail;D=FAA-015-0085; 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):

2015-17-22 Airbus: Amendment 39-18255. Docket No. FAA-2015-0085; 
Directorate Identifier 2014-NM-078-AD.

(a) Effective Date

    This AD becomes effective October 7, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus Model A330-243, A330-243F, A330-
341, A330-342, and A330-343 airplanes, certificated in any category, 
all manufacturer serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 78, Exhaust.

(e) Reason

    This AD was prompted by reports indicating that certain hinge 
sleeves on the cowl doors of the thrust reverser units (TRUs) were 
not heat treated. We are issuing this AD to prevent, in the event of 
a fan-blade-off event due to high vibration, in-flight loss of TRU 
heavy components, which might damage airplane structure or control 
surfaces and consequently reduce controllability of the airplane.

(f) Compliance

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

(g) Identification of TRU Part Number

    Within 12 months after the effective date of this AD: Identify 
the part number of the TRUs, in accordance with the information in 
Aircelle Service Bulletin 78-AG924, dated September 26, 2012.

(h) Replacement of TRU Hinge Sleeves

    If the results of the part identification required by paragraph 
(g) of this AD reveal that the TRUs are affected: Within the 
compliance time defined in paragraph (g) of this AD, replace hinge 
sleeves numbers 3 and 4 of each TRU cowl door, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A330-78-
3021, Revision 03, dated October 15, 2014.

    Note 1 to paragraph (h) of this AD: Rolls-Royce Alert Service 
Bulletin RB.211-78-AG924, dated September 26, 2012, is an additional 
source of guidance for replacing the TRUs and is not incorporated by 
reference in this AD.

(i) Optional Terminating Action for Paragraphs (g) and (h) of this AD

    Modifying an airplane by incorporating Airbus Modification 
202463 in production terminates the requirements specified in 
paragraphs (g) and (h) of this AD for that airplane.

(j) Parts Installation Limitation

    As of the effective date of this AD, no person may install a TRU 
on any airplane unless it has been determined, using Aircelle 
Service Bulletin 78-AG924, dated September 26, 2012, that the cowl 
door hinge sleeves installed on the TRU are not affected by the 
requirements of this AD.

(k) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraph (h) of this AD if those actions were performed before the 
effective date of this AD using the service information identified 
in paragraphs (k)(1), (k)(2), or (k)(3) of this AD, which are not 
incorporated by reference in this AD.
    (1) Airbus Service Bulletin A330-78-3021, dated October 17, 
2012.
    (2) Airbus Service Bulletin A330-78-3021, Revision 01, dated 
July 30, 2013.
    (3) Airbus Service Bulletin A330-78-3021, Revision 02, dated 
April 17, 2014.

(l) 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-

[[Page 52937]]

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.
    (3) Required for Compliance (RC): Where Airbus Service Bulletin 
A330-78-3021, Revision 03, dated October 15, 2014, contains 
procedures or tests that are identified as RC, those procedures and 
tests must be done to comply with this AD; any procedures and tests 
that are not identified as RC are recommended. Those procedures and 
tests that are not identified as RC may be deviated from using 
accepted methods in accordance with the operators' maintenance or 
inspection program without obtaining approval of an AMOC, provided 
the procedures and tests identified as RC can be done and the 
airplane can be put back in a serviceable condition. Any 
substitutions or changes to procedures or tests identified as RC 
require approval of an AMOC.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2014-0062, dated March 11, 2014, for related 
information. This MCAI may be found in the AD docket on the Internet 
at http://www.regulations.gov/#!documentDetail;D=FAA-2015-0085-0002.
    (2) Airbus service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (n)(3) and (n)(5) of this AD.
    (3) Rolls-Royce service information identified in this AD that 
is not incorporated by reference is available at Rolls-Royce plc, 
P.O. Box 31, Derby, DE24 8BJ, England; phone: 011-44-1332-242424; 
fax: 011-244-1332-249936; email: http://www.rolls-royce.com/contact/civil_team.jsp; Internet: https://www.aeromanager.com.

(n) 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 Service Bulletin A330-78-3021, Revision 03, dated 
October 15, 2014.
    (ii) Aircelle Service Bulletin 78-AG924, dated September 26, 
2012.
    (3) For Airbus 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) For Aircelle service information identified in this AD, 
contact Aircelle Customer support Center, BP 50042, 50, rue Pierre 
Curie, 78371 Plaisir Cedex, France: telephone +33 (0)1 64 14 80 33; 
fax +33 (0)1 64 14 84 10.
    (5) 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.
    (6) 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 August 21, 2015.
Kevin Hull,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-21475 Filed 9-1-15; 8:45 am]
BILLING CODE 4910-13-P