Airworthiness Directives; Airbus Airplanes, 51325-51328 [2016-18168]

Download as PDF Federal Register / Vol. 81, No. 150 / Thursday, August 4, 2016 / Rules and Regulations (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office (ACO), ANE–170, 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 ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; fax 516–794–5531. 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, New York ACO, ANE–170, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.’s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. ehiers on DSK5VPTVN1PROD with RULES (k) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2015–25, dated September 10, 2015, for related information. This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2016–5459. (l) 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) Bombardier, Inc. Service Bulletin 700– 35–013, Revision 01, dated July 22, 2015. (ii) Bombardier, Inc. Service Bulletin 700– 35–5001, Revision 01, dated July 22, 2015. (iii) Bombardier Service Bulletin 700–35– 6001, Revision 01, dated July 22, 2015. (iv) Bombardier Service Bulletin 700– 1A11–35–012, Revision 01, dated July 22, 2015. (3) For service information identified in ˆ this AD, contact Bombardier, Inc., 400 Cote´ Vertu Road West, Dorval, Quebec H4S 1Y9, Canada; telephone 514–855–5000; fax 514– 855–7401; email thd.crj@ aero.bombardier.com; Internet https:// www.bombardier.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 VerDate Sep<11>2014 13:37 Aug 03, 2016 Jkt 238001 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 July 21, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–18172 Filed 8–3–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–5460; Directorate Identifier 2015–NM–188–AD; Amendment 39–18599; AD 2016–16–01] 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 Freighter, –200, and –300 series airplanes. This AD was prompted by a report of a manufacturing defect that affects the durability of affected parts in the cargo and cabin compartment. This AD requires an inspection of affected structural parts in the cargo and cabin compartments to determine if proper heat treatment has been done, and replacement if necessary. We are issuing this AD to prevent crack initiation and propagation, which could result in reduced structural integrity of the fuselage. SUMMARY: This AD is effective September 8, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of September 8, 2016. ADDRESSES: For service information identified in this final rule, 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. DATES: PO 00000 Frm 00029 Fmt 4700 Sfmt 4700 51325 For information on the availability of this material at the FAA, call 425–227– 1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2016–5460. 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–2016– 5460; 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 Office (telephone 800–647– 5527) is 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 20590. 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 A330–200 Freighter, –200, and –300 series airplanes. The NPRM published in the Federal Register on April 12, 2016 (81 FR 21486) (‘‘the NPRM’’). The NPRM was prompted by a report of a manufacturing defect that affects the durability of affected parts in the cargo and cabin compartment. The NPRM proposed to require an inspection of affected structural parts in the cargo and cabin compartments to determine if proper heat treatment has been done, and replacement if necessary. We are issuing this AD to prevent crack initiation and propagation, which could result in reduced structural integrity of the fuselage. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued European Airworthiness Directive 2015–0212, dated November 4, 2015, to correct an unsafe condition for all Airbus Model A330–200 Freighter, –200, and –300 series airplanes. The MCAI states: Airbus quality controls identified that several structural parts, intended for cargo or E:\FR\FM\04AUR1.SGM 04AUR1 51326 Federal Register / Vol. 81, No. 150 / Thursday, August 4, 2016 / Rules and Regulations cabin compartment installation, were manufactured from improperly heat-treated materials. Subsequent review identified that some of those parts were installed on airplanes manufactured between November 2011 and February 2013. From February 2013, Airbus implemented measures into manufacturing processes to ensure detection and to prevent installation of such nonconforming parts. A detailed safety assessment was accomplished to identify the possible impact of affected parts on the airplane structure. The result of this structural analysis demonstrated the capability of the affected structure to sustain static limit loads, but failed to confirm that the affected structures met the certified fatigue life. This condition, if not detected and corrected, could lead to crack initiation and propagation, possibly resulting in reduced structural integrity of the fuselage. To address this potentially unsafe condition, Airbus issued Service Bulletin (SB) SB A330–53–3227 and SB A330–53– 3228 to provide inspection instructions for affected cargo and cabin structural parts respectively. For the reasons described above, this [EASA] AD requires a one-time Special Detailed Inspection (SDI) [eddy current inspection] to measure the electrical conductivity of affected structural parts, to identify the presence or absence of heat treatment, and, depending on findings, corrective action [replacement]. Related Service Information Under 1 CFR Part 51 You may examine the MCAI in the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 5460. Airbus has issued the following service information: • Airbus Service Bulletin A330–53– 3227, dated August 18, 2015. The service information describes procedures to inspect affected structural parts in the cargo compartment to determine if proper heat treatment has been done, and replacement of parts; and • Airbus Service Bulletin A330–53– 3228, dated August 18, 2015. The service information describes procedures to inspect affected structural parts in the cabin compartment to determine if proper heat treatment has been done, and replacement of parts. 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. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM 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 for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Costs of Compliance We estimate that this AD affects 20 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Parts cost Cost per product Cost on U.S. operators Inspection ........................................................ 11 work-hours × $85 per hour = $935 ........... $0 $935 $18,700 We estimate the following costs to do any necessary replacements that will be required based on the results of the required inspection. We have received no definitive data that will enable us to provide the cost of replacement parts for the on-condition actions specified in this AD, nor the cost of repairs. We have no way of determining the number of aircraft that might need this action. ON-CONDITION COSTS Action Labor cost Parts cost Replacement .................................. 45 work-hours × $85 per hour = $3,825. Not Available ................................ According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all available costs in our cost estimate. ehiers on DSK5VPTVN1PROD with RULES 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 VerDate Sep<11>2014 13:37 Aug 03, 2016 Jkt 238001 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 PO 00000 Frm 00030 Fmt 4700 Sfmt 4700 Cost per product Not Available. 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; E:\FR\FM\04AUR1.SGM 04AUR1 Federal Register / Vol. 81, No. 150 / Thursday, August 4, 2016 / Rules and Regulations 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. 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): ■ 2016–16–01 Airbus: Amendment 39–18599; Docket No. FAA–2016–5460; Directorate Identifier 2015–NM–188–AD. (a) Effective Date This AD is effective September 8, 2016. (b) Affected ADs None. (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, manufacturer serial numbers 1175, 1180, 1287 through 1475 inclusive, 1478, 1480, 1483, and 1506. (1) Model A330–223F and –243F airplanes. (2) Model A330–201, –202, –203, –223, and –243 airplanes. (3) Model A330–301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes. ehiers on DSK5VPTVN1PROD with RULES (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by a report of a manufacturing defect (i.e. improperly heat treated materials) that affects the durability of affected parts in the cargo and cabin compartment. We are issuing this AD to prevent crack initiation and propagation, which could result in reduced structural integrity of the fuselage. (f) Compliance Comply with this AD within the compliance times specified, unless already done. VerDate Sep<11>2014 13:37 Aug 03, 2016 Jkt 238001 (g) Inspection of Affected Structure in the Cargo Compartment Within 72 months since first flight of the airplane, do an eddy current inspection (i.e., conductivity measurement) of affected structural parts in the cargo compartment to determine if proper heat treatment has been done as identified in, and in accordance with, the Accomplishment Instructions of Airbus Service Bulletin A330–53–3227, dated August 18, 2015. (h) Replacement of Non-Conforming Parts in the Cargo Compartment If, during the inspection required by paragraph (g) of this AD, an affected structural part in the cargo compartment is identified to have a measured value greater than 26 megasiemens per meter (MS/m), or greater than 44.8% International Annealed Copper Standard (IACS), before further flight, replace the affected structural part with a serviceable part, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330–53–3227, dated August 18, 2015. (i) Repair of Non-Conforming Parts in the Cargo Compartment If, during the inspection required by paragraph (g) of this AD, an affected structural part in the cargo compartment is identified to have a measured value other than those specified in Figure A–GFAAA, Sheet 01, ‘‘Inspection Flowchart,’’ of Airbus Service Bulletin A320–53–3227, dated August 18, 2015, before further flight, repair 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). (j) Inspection of Affected Structure in the Cabin Compartment Within 72 months since first flight of the airplane, do an eddy current inspection of affected structural parts in the cabin compartment to determine if proper heat treatment has been done as identified in, and in accordance with, the Accomplishment Instructions of Airbus Service Bulletin A330– 53–3228, dated August 18, 2015. (k) Replacement of Non-Conforming Parts in the Cabin Compartment If, during the inspection required by paragraph (j) of this AD, an affected structural part in the cabin compartment is identified to have a measured value greater than 26 MS/m or greater than 44.8% IACS, before further flight, replace the affected structural part with a serviceable part, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330– 53–3228, dated August 18, 2015. (l) Repair of Non-Conforming Parts in the Cabin Compartment If, during the inspection required by paragraph (j) of this AD, an affected structural part in the cabin compartment is identified to have a measured value other than those specified in Figure A–GFAAA, Sheet 01, ‘‘Inspection Flowchart,’’ of Airbus Service Bulletin A320–53–3228, dated PO 00000 Frm 00031 Fmt 4700 Sfmt 4700 51327 August 18, 2015, before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the EASA; or Airbus’s EASA DOA. (m) 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: 9ANM-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 EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or 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 operator’s 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 an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (n) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2015–0212, dated November 4, 2015, for related information. You may examine the MCAI on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016–5460. (o) 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\04AUR1.SGM 04AUR1 51328 Federal Register / Vol. 81, No. 150 / Thursday, August 4, 2016 / 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 Service Bulletin A330–53–3227, dated August 18, 2015. (ii) Airbus Service Bulletin A330–53–3228, dated August 18, 2015. (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 July 21, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–18168 Filed 8–3–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–8469; Directorate Identifier 2014–NM–105–AD; Amendment 39–18602; AD 2016–16–04] Airworthiness Directives; Fokker Services B.V. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F.28 Mark 1000, 2000, 3000, and 4000 airplanes. This AD was prompted by a design review that revealed insufficient measures were taken to ensure the correct locking of the attachments of the fuel quantity tank units (FQTUs) in each wing tank. When an FQTU becomes loose, this could lead to insufficient clearance between the FQTU and the adjacent tank structure or other metal parts, and under certain conditions, create an ignition source inside the wing fuel vapor space. This AD requires modifying the FQTUs by applying ehiers on DSK5VPTVN1PROD with RULES VerDate Sep<11>2014 13:37 Aug 03, 2016 Jkt 238001 This AD is effective September 8, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of September 8, 2016. DATES: For service information identified in this final rule, contact Fokker Services B.V., Technical Services Dept., P.O. Box 1357, 2130 EL Hoofddorp, the Netherlands; telephone +31 (0)88–6280–350; fax +31 (0)88– 6280–111; email technicalservices@ fokker.com; Internet https:// www.myfokkerfleet.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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 8469. ADDRESSES: Examining the AD Docket RIN 2120–AA64 SUMMARY: sealant to cover the nuts, washers, and stud ends at the FQTU attachments in each main wing tank. This AD also requires revising the maintenance or inspection program, as applicable, by incorporating a fuel airworthiness limitation item and a critical design configuration control limitation (CDCCL). We are issuing this AD to prevent an ignition source in the wing fuel tank vapor space, which could result in a wing fuel tank explosion and consequent loss of the airplane. You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 8469; 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 Office (telephone 800–647– 5527) is 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 20590. Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1137; fax 425–227–1149. FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: PO 00000 Frm 00032 Fmt 4700 Sfmt 4700 Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Fokker Services B.V. Model F.28 Mark 1000, 2000, 3000, and 4000 airplanes. The NPRM published in the Federal Register on January 20, 2016 (81 FR 3056) (‘‘the NPRM’’). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0106, dated May 7, 2014 (referred to after this the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Fokker Services B.V. Model F.28 Mark 1000, 2000, 3000, and 4000 airplanes. The MCAI states: Prompted by an accident * * *, the Federal Aviation Administration (FAA) published Special Federal Aviation Regulation (SFAR) 88 [(66 FR 23086, May 7, 2001)], and the Joint Aviation Authorities (JAA) published Interim Policy INT/POL/25/ 12. The review conducted by Fokker Services on the Fokker F28 design, in response to these regulations, revealed that insufficient measures were taken to ensure the correct locking of the attachments of the Fuel Quantity Tank Units (FQTUs). When a FQTU becomes loose, this could lead to insufficient clearance between the FQTU and the adjacent tank structure or other metal parts and, under certain conditions, create an ignition source inside the wing fuel tank vapour space. This condition, if not detected and corrected, could result in a wing fuel tank explosion and consequent loss of the aeroplane. To address this potential unsafe condition, Fokker Services developed a modification to ensure that each FQTU remains properly attached. For the reasons described above, this [EASA] AD requires the application of sealant covering the nuts, washers and stud ends at the FQTU attachment in each wing tank [and a revision to the maintenance or inspection program, as applicable, to incorporate a fuel airworthiness limitation item and a CDCCL]. More information on this subject can be found in Fokker Services All Operators Message AOF28.038#02. You may examine the MCAI in the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 8469. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. E:\FR\FM\04AUR1.SGM 04AUR1

Agencies

[Federal Register Volume 81, Number 150 (Thursday, August 4, 2016)]
[Rules and Regulations]
[Pages 51325-51328]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-18168]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-5460; Directorate Identifier 2015-NM-188-AD; 
Amendment 39-18599; AD 2016-16-01]
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 Freighter, -200, and -300 series airplanes. This 
AD was prompted by a report of a manufacturing defect that affects the 
durability of affected parts in the cargo and cabin compartment. This 
AD requires an inspection of affected structural parts in the cargo and 
cabin compartments to determine if proper heat treatment has been done, 
and replacement if necessary. We are issuing this AD to prevent crack 
initiation and propagation, which could result in reduced structural 
integrity of the fuselage.

DATES: This AD is effective September 8, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of September 8, 
2016.

ADDRESSES: For service information identified in this final rule, 
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. It is also available on the 
Internet at https://www.regulations.gov by searching for and locating 
Docket No. FAA-2016-5460.

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-2016-
5460; 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 Office (telephone 
800-647-5527) is 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 20590.

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 A330-200 
Freighter, -200, and -300 series airplanes. The NPRM published in the 
Federal Register on April 12, 2016 (81 FR 21486) (``the NPRM''). The 
NPRM was prompted by a report of a manufacturing defect that affects 
the durability of affected parts in the cargo and cabin compartment. 
The NPRM proposed to require an inspection of affected structural parts 
in the cargo and cabin compartments to determine if proper heat 
treatment has been done, and replacement if necessary. We are issuing 
this AD to prevent crack initiation and propagation, which could result 
in reduced structural integrity of the fuselage.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued European 
Airworthiness Directive 2015-0212, dated November 4, 2015, to correct 
an unsafe condition for all Airbus Model A330-200 Freighter, -200, and 
-300 series airplanes. The MCAI states:

    Airbus quality controls identified that several structural 
parts, intended for cargo or

[[Page 51326]]

cabin compartment installation, were manufactured from improperly 
heat-treated materials. Subsequent review identified that some of 
those parts were installed on airplanes manufactured between 
November 2011 and February 2013. From February 2013, Airbus 
implemented measures into manufacturing processes to ensure 
detection and to prevent installation of such non-conforming parts.
    A detailed safety assessment was accomplished to identify the 
possible impact of affected parts on the airplane structure. The 
result of this structural analysis demonstrated the capability of 
the affected structure to sustain static limit loads, but failed to 
confirm that the affected structures met the certified fatigue life.
    This condition, if not detected and corrected, could lead to 
crack initiation and propagation, possibly resulting in reduced 
structural integrity of the fuselage.
    To address this potentially unsafe condition, Airbus issued 
Service Bulletin (SB) SB A330-53-3227 and SB A330-53-3228 to provide 
inspection instructions for affected cargo and cabin structural 
parts respectively.
    For the reasons described above, this [EASA] AD requires a one-
time Special Detailed Inspection (SDI) [eddy current inspection] to 
measure the electrical conductivity of affected structural parts, to 
identify the presence or absence of heat treatment, and, depending 
on findings, corrective action [replacement].

    You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
5460.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM 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 for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information:
     Airbus Service Bulletin A330-53-3227, dated August 18, 
2015. The service information describes procedures to inspect affected 
structural parts in the cargo compartment to determine if proper heat 
treatment has been done, and replacement of parts; and
     Airbus Service Bulletin A330-53-3228, dated August 18, 
2015. The service information describes procedures to inspect affected 
structural parts in the cabin compartment to determine if proper heat 
treatment has been done, and replacement of parts.
    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.

Costs of Compliance

    We estimate that this AD affects 20 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
              Action                        Labor cost            Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Inspection........................  11 work-hours x $85 per                $0             $935          $18,700
                                     hour = $935.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that will be required based on the results of the required inspection. 
We have received no definitive data that will enable us to provide the 
cost of replacement parts for the on-condition actions specified in 
this AD, nor the cost of repairs. We have no way of determining the 
number of aircraft that might need this action.

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                Action                        Labor cost               Parts cost            Cost per product
----------------------------------------------------------------------------------------------------------------
Replacement..........................  45 work-hours x $85 per  Not Available..........  Not Available.
                                        hour = $3,825.
----------------------------------------------------------------------------------------------------------------

    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all available costs in our 
cost estimate.

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;

[[Page 51327]]

    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.

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):

2016-16-01 Airbus: Amendment 39-18599; Docket No. FAA-2016-5460; 
Directorate Identifier 2015-NM-188-AD.

(a) Effective Date

    This AD is effective September 8, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, 
manufacturer serial numbers 1175, 1180, 1287 through 1475 inclusive, 
1478, 1480, 1483, and 1506.
    (1) Model A330-223F and -243F airplanes.
    (2) Model A330-201, -202, -203, -223, and -243 airplanes.
    (3) Model A330-301, -302, -303, -321, -322, -323, -341, -342, 
and -343 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by a report of a manufacturing defect (i.e. 
improperly heat treated materials) that affects the durability of 
affected parts in the cargo and cabin compartment. We are issuing 
this AD to prevent crack initiation and propagation, which could 
result in reduced structural integrity of the fuselage.

(f) Compliance

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

(g) Inspection of Affected Structure in the Cargo Compartment

    Within 72 months since first flight of the airplane, do an eddy 
current inspection (i.e., conductivity measurement) of affected 
structural parts in the cargo compartment to determine if proper 
heat treatment has been done as identified in, and in accordance 
with, the Accomplishment Instructions of Airbus Service Bulletin 
A330-53-3227, dated August 18, 2015.

(h) Replacement of Non-Conforming Parts in the Cargo Compartment

    If, during the inspection required by paragraph (g) of this AD, 
an affected structural part in the cargo compartment is identified 
to have a measured value greater than 26 megasiemens per meter (MS/
m), or greater than 44.8% International Annealed Copper Standard 
(IACS), before further flight, replace the affected structural part 
with a serviceable part, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-53-3227, dated August 
18, 2015.

(i) Repair of Non-Conforming Parts in the Cargo Compartment

    If, during the inspection required by paragraph (g) of this AD, 
an affected structural part in the cargo compartment is identified 
to have a measured value other than those specified in Figure A-
GFAAA, Sheet 01, ``Inspection Flowchart,'' of Airbus Service 
Bulletin A320-53-3227, dated August 18, 2015, before further flight, 
repair 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).

(j) Inspection of Affected Structure in the Cabin Compartment

    Within 72 months since first flight of the airplane, do an eddy 
current inspection of affected structural parts in the cabin 
compartment to determine if proper heat treatment has been done as 
identified in, and in accordance with, the Accomplishment 
Instructions of Airbus Service Bulletin A330-53-3228, dated August 
18, 2015.

(k) Replacement of Non-Conforming Parts in the Cabin Compartment

    If, during the inspection required by paragraph (j) of this AD, 
an affected structural part in the cabin compartment is identified 
to have a measured value greater than 26 MS/m or greater than 44.8% 
IACS, before further flight, replace the affected structural part 
with a serviceable part, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A330-53-3228, dated August 
18, 2015.

(l) Repair of Non-Conforming Parts in the Cabin Compartment

    If, during the inspection required by paragraph (j) of this AD, 
an affected structural part in the cabin compartment is identified 
to have a measured value other than those specified in Figure A-
GFAAA, Sheet 01, ``Inspection Flowchart,'' of Airbus Service 
Bulletin A320-53-3228, dated August 18, 2015, before further flight, 
repair using a method approved by the Manager, International Branch, 
ANM-116, Transport Airplane Directorate, FAA; or the EASA; or 
Airbus's EASA DOA.

(m) 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 EASA; 
or Airbus's EASA DOA. If approved by the DOA, the approval must 
include the DOA-authorized signature.
    (3) Required for Compliance (RC): If any service information 
contains procedures or tests that are identified as RC, those 
procedures and tests must be done to comply with this AD; any 
procedures or 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 
operator's 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 an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(n) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
EASA AD 2015-0212, dated November 4, 2015, for related information. 
You may examine the MCAI on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-
2016-5460.

(o) 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 51328]]

    (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 A330-53-3227, dated August 18, 2015.
    (ii) Airbus Service Bulletin A330-53-3228, dated August 18, 
2015.
    (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 July 21, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-18168 Filed 8-3-16; 8:45 am]
 BILLING CODE 4910-13-P