80 FR 73960 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 228 (November 27, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 228 (November 27, 2015)
| Page Range | 73960-73963 | |
| FR Document | 2015-29851 |
[Federal Register Volume 80, Number 228 (Friday, November 27, 2015)] [Rules and Regulations] [Pages 73960-73963] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-29851] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2014-0928; Directorate Identifier 2014-NM-040-AD; Amendment 39-18333; AD 2015-24-01] 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 all Airbus Model A330-200 Freighter, A330-200, A330-300, A340-200, A340- 300, A340-500, and A340-600 series airplanes. This AD was prompted by a report of skin disbonding on a composite side panel of a rudder installed on an A310 airplane. This AD requires a review of the maintenance records of the rudder to determine if any composite side shell panel repair has been done; a thermography inspection limited to the repair areas or complete side shells, as applicable, to identify possible in-service rudder repairs, damages, or fluid ingress; and applicable related investigative and corrective actions. We are issuing this AD to detect and correct the rudder skin disbonding, which could affect the structural integrity of the rudder, and could result in reduced controllability of the airplane. DATES: This AD becomes effective January 4, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of January 4, 2016. ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0928 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 [email protected]; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014- 0928. 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, A330-200, A330-300, A340-200, A340-300, A340-500, and A340- 600 series airplanes. The NPRM published in the Federal Register on December 29, 2014 (79 FR 77972). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014-0033, dated February 4, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for all Airbus Model A330-200 Freighter, A330-200, A330-300, A340-200, A340-300, A340-500, and A340-600 series airplanes. The MCAI states: A case of skin disbonding was reported on a composite side panel of a rudder installed on an A310 aeroplane. The investigation results revealed that this disbonding started from a skin panel area previously repaired in-service in accordance with the Structural Repair Manual (SRM). The initial damage has been identified as a disbonding between the core and skin of the repaired area. This damage may not be visually detectable and likely propagates during normal operation due to the variation of pressure during ground-air-ground cycles. Composite rudder side shell panels are also installed on A330 and A340 aeroplanes, which may have been repaired in-service using a similar method. This condition, if not detected and corrected, could affect the structural integrity of the rudder, possibly resulting in reduced control of the aeroplane. For the reasons described above, this [EASA] AD requires a one- time thermography inspection of a repaired rudder or a rudder whose maintenance records are incomplete and, depending on findings, accomplishment of applicable corrective and follow-up actions [including repetitive inspections]. The related investigative actions in this AD include, as applicable, an ultrasonic inspection, an elasticity laminate checker inspection, a tap test inspection, detailed inspections, and thermography inspections, and ventilation of the core. The repetitive inspections include detailed inspections and thermography inspections. The corrective actions in this AD include repairs. The compliance time for the related investigative actions is before further flight after accomplishing the applicable inspection required by paragraph (g)(1) or (g)(2)(ii) of this AD. The intervals for the repetitive inspections are either 900 flight hours or 1,000 flight cycles, depending on the applicable conditions identified in the service information. The compliance times for the corrective actions range, depending on the applicable conditions identified in the service information, from before further flight to within 4,500 flight cycles but not to exceed 24 months after accomplishing the applicable inspection required by paragraph (g)(1) or (g)(2)(ii) of this AD. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0928-0002. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (79 FR 77972, December 29, 2014) and the FAA's response to each comment. Request To Use the Latest Service Information American Airlines (AAL) and Delta Airlines (DAL) requested that we revise the NPRM (79 FR 77972, December 29, 2014) to cite the latest service information. We agree with the commenters' request. Airbus has issued Airbus Service Bulletin A330-55-3043, Revision 1, dated August 20, 2014, Airbus Service Bulletin A340-55-4039, Revision 1, dated August 20, 2014, and Airbus Service Bulletin A340-55-5007, [[Page 73961]] Revision 1, dated August 20, 2014. The new service information requires no additional work, and there are no new actions required by this AD. We have updated the AD with the latest service information, and we have also added a credit paragraph for previous actions done before the effective date of this AD using the service information cited in the NPRM (79 FR 77972, December 29, 2014). Request To Clarify the Structural Repair Manual Repairs That Are Affected AAL requested that the NPRM (79 FR 77972, December 29, 2014) clarify the specific structural repair manual (SRM) repairs that are affected. AAL stated that paragraph (j) of the proposed AD states specific serial number ranges that are not affected by the AD provided that it is determined that no repair has been accomplished on the composite side shell panel of that rudder since first installation on the airplane. AAL believes this last sentence is too broad and not in line with the intent of the service information requirements. AAL commented that stating no repair has been accomplished limits acceptable repairs covered by an Airbus repair design approval sheet, designated engineering representative repairs, and other SRM repairs not affected by the improper practices that are the subject of the NPRM. AAL stated that paragraphs (g)(1) and paragraph (l) of the proposed AD list the affected SRM repairs in the service information figures. We agree with the commenter's request. We have revised paragraph (j) of this AD to clarify the specific repairs accomplished as described in the SRM procedures identified in Figure A-GBBAA (Sheet 01 and 02) or Figure A-GBCAA (Sheet 02) of the service information specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD, as applicable. Request To Add the Manufacturer Part Number DAL requested that the NPRM (79 FR 77972, December 29, 2014) include the manufacturer part numbers of the rudder serial numbers specified in paragraph (j), which provides only a list of rudder serial numbers not affected by the requirements of paragraphs (g) and (h) of the proposed AD. DAL commented that in the event of future aircraft acquisitions or rudder (component only) purchases, operators will need the manufacturer part numbers associated with the listed serial numbers to determine AD applicability. We disagree with the commenter's request to add part numbers to paragraph (j) of this AD. The rudder serial number, regardless of the part number, is the key to identifying whether the rudder is not affected. Only rudders that have certain serial numbers that meet the conditions specified in paragraph (j) of this AD are exempt from the actions required by paragraphs (g) and (h) of this AD. Airbus has informed us that rudders with the same manufacturer part number might or might not be affected; it is the serial number that determines whether it is an affected rudder. We have not changed the AD in this regard. Conclusion We reviewed the relevant data, considered the comments 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 (79 FR 77972, December 29, 2014) for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 77972, December 29, 2014). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information: Airbus Service Bulletin A330-55-3043, Revision 1, dated August 20, 2014. Airbus Service Bulletin A340-55-4039, Revision 1, dated August 20, 2014. Airbus Service Bulletin A340-55-5007, Revision 1, dated August 20, 2014. The service information describes procedures for a review of the maintenance records of the rudder to determine if any composite side shell panel repair has been done; a thermography inspection limited to the repair areas or complete side shells, as applicable, to identify possible in-service rudder repairs, damages, or fluid ingress; and applicable related investigative and corrective actions. 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. Costs of Compliance We estimate that this AD affects 55 airplanes of U.S. registry. We also estimate that it would take about 45 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts would cost about $0 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $210,375, or $3,825 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this AD. Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this AD is 2120- 0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information Collection Clearance Officer, AES-200. 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. [[Page 73962]] 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-2014-0928; 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): 2015-24-01 Airbus: Amendment 39-18333. Docket No. FAA-2014-0928; Directorate Identifier 2014-NM-040-AD. (a) Effective Date This AD becomes effective January 4, 2016. (b) Affected ADs None. (c) Applicability This AD applies to all airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category. (1) Airbus Model A330-201, -202, -203, -223, -223F,-243, -243F, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes, all manufacturer serial numbers. (2) Airbus Model A340-211, -212, -213, -311, -312, -313, -541, and -642 airplanes, all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 55, Stabilizers. (e) Reason This AD was prompted by a report of skin disbonding on a composite side panel of a rudder installed on an A310 airplane. We are issuing this AD to detect and correct the rudder skin disbonding, which could affect the structural integrity of the rudder, and could result in reduced controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Review the Maintenance Records Within 24 months after the effective date of this AD: Review the maintenance records of the rudder to determine if any composite side shell panel repair has been accomplished on the rudder since first installation on an airplane. (1) If, based on the maintenance record review, any repair identified in Figure A-GBBAA (Sheet 01 and 02) or Figure A-GBCAA (Sheet 02) of the service information specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD is found: Within 24 months after the effective date of this AD, do a thermography inspection for repair, damages, and fluid ingress, limited to the repaired areas, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD: (i) Airbus Service Bulletin A330-55-3043, Revision 1, dated August 20, 2014 (for Model A330-201, -202, -203, -223, -223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes). (ii) Airbus Service Bulletin A340-55-4039, Revision 1, dated August 20, 2014 (for Model A340-211, -212, -213, -311, -312, and - 313 airplanes). (iii) Airbus Service Bulletin A340-55-5007, Revision 1, dated August 20, 2014 (for Model A340-541 and -642 airplanes). (2) For a rudder for which maintenance records are unavailable or incomplete, do the actions specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD: (i) No later than 3 months before accomplishment of the thermography inspection, as required by paragraph (g)(2)(ii) of this AD, contact Airbus to request related rudder manufacturing data by submitting the serial number of the rudder to Airbus. (ii) Within 24 months after the effective date of this AD: Do a thermography inspection for any repair on complete side shells to identify and mark any repair, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD. (h) Related Investigative Actions, Corrective Actions, and Repetitive Inspections After the inspection as required by paragraph (g)(1) or (g)(2) of this AD: At the applicable compliance times specified in paragraph 1.E., ``Compliance,'' of Tables 3, 4A, 4B, 4C, 4D, and 5 of the applicable service information specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD, accomplish all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD; except as provided by paragraphs (i)(1) and (i)(2) of this AD. Options provided in the service information specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD for accomplishing the actions are acceptable for the corresponding requirements of this paragraph provided that the related investigative and corrective actions are done at the applicable times specified in paragraph 1.E., ``Compliance,'' of the applicable service information specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD, including applicable repetitive inspection intervals, except as required by paragraphs (i)(1) and (i)(2) of this AD. Thereafter repeat the inspections of the restored and repaired areas at the applicable compliance time specified in paragraph 1.E., ``Compliance,'' of Tables 3, 4A, 4B, 4C, 4D, and 5 of the applicable service information specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD. (i) Exceptions to the Service Information (1) Where the applicable service information specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD specifies a compliance time relative to the date of the service information, this AD requires compliance within the specified compliance time after the effective date of this AD. (2) If the service information in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD specifies to contact Airbus: At the applicable compliance times specified in paragraph 1.E., ``Compliance,'' of the applicable service information specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD, 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) Provisions for Certain Airplanes Airplanes fitted with a rudder having a serial number (S/N) that is not in the range of S/N TS-1001 through S/N TS-1043 inclusive, S/ N TS-2001 through S/N TS-2074 inclusive, S/N TS-3000 through S/N TS- 3525 inclusive, S/N TS-4001 through S/N TS-4170 inclusive, S/N TS- 6001 through S/N TS-6246 inclusive, or S/N TS-5001 through S/N TS- 5138 inclusive, are not [[Page 73963]] affected by the requirements of paragraphs (g) and (h) of this AD provided that it is determined that no repair has been accomplished as described in the procedures identified in Figure A-GBBAA (Sheet 01 and 02) or Figure A-GBCAA (Sheet 02) of the service information specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD, as applicable, on the composite side shell panel of that rudder since first installation on an airplane. (k) Parts Installation Limitations As of the effective date of this AD, no person may install, on any airplane, a rudder, unless the record review and thermography inspection specified in paragraph (g) of this AD has been done on that rudder and thereafter all applicable related investigative actions, repetitive inspections, and corrective actions are done as required by paragraph (h) of this AD, except as provided in paragraph (j) of this AD. (l) Repair Prohibition As of the effective date of this AD, no person may accomplish a side shell repair on any rudder using a structure repair manual procedure identified in Figure A-GBBAA (Sheet 01 and 02) or Figure A-GBCAA (Sheet 02) of the service information specified in paragraphs (g)(1)(i) through (g)(1)(iii) of this AD, as applicable, on any airplane. (m) Credit for Previous Actions This paragraph provides credit for the actions specified in this AD, if those actions were performed before the effective date of this AD using the service information in paragraphs (m)(1), (m)(2), and (m)(3) of this AD. (1) Airbus Service Bulletin A330-55-3043, dated February 7, 2013. (2) Airbus Service Bulletin A340-55-4039, dated February 7, 2013. (3) Airbus Service Bulletin A340-55-5007, dated February 7, 2013. (n) 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: [email protected]. 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. (o) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0033, dated February 4, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-0928. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (p)(3) and (p)(4) of this AD. (p) 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 A330-55-3043, Revision 1, dated August 20, 2014. (ii) Airbus Service Bulletin A340-55-4039, Revision 1, dated August 20, 2014. (iii) Airbus Service Bulletin A340-55-5007, Revision 1, dated August 20, 2014. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email [email protected]; Internet http://www.airbus.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on November 9, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-29851 Filed 11-25-15; 8:45 am] BILLING CODE 4910-13-P
![73960 Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Rules and Regulations
the availability of this material at NARA, call 30, West Building Ground Floor, Room This condition, if not detected and
202–741–6030, or go to: http:// W12–140, 1200 New Jersey Avenue SE., corrected, could affect the structural integrity
www.archives.gov/federal-register/cfr/ibr- Washington, DC. of the rudder, possibly resulting in reduced
locations.html. For service information identified in control of the aeroplane.
For the reasons described above, this
Issued in Kansas City, Missouri, on this AD, contact Airbus SAS, [EASA] AD requires a one-time
November 16, 2015. Airworthiness Office—EAL, 1 Rond thermography inspection of a repaired rudder
Melvin Johnson, Point Maurice Bellonte, 31707 Blagnac or a rudder whose maintenance records are
Acting Manager, Small Airplane Directorate, Cedex, France; telephone +33 5 61 93 36 incomplete and, depending on findings,
Aircraft Certification Service. 96; fax +33 5 61 93 45 80; email accomplishment of applicable corrective and
[FR Doc. 2015–29855 Filed 11–25–15; 8:45 am] airworthiness.A330-A340@airbus.com; follow-up actions [including repetitive
Internet http://www.airbus.com. You inspections].
BILLING CODE 4910–13–P
may view this referenced service The related investigative actions in
information at the FAA, Transport this AD include, as applicable, an
DEPARTMENT OF TRANSPORTATION Airplane Directorate, 1601 Lind Avenue ultrasonic inspection, an elasticity
SW., Renton, WA. For information on laminate checker inspection, a tap test
Federal Aviation Administration the availability of this material at the inspection, detailed inspections, and
FAA, call 425–227–1221. It is also thermography inspections, and
14 CFR Part 39 available on the Internet at http:// ventilation of the core. The repetitive
www.regulations.gov by searching for inspections include detailed inspections
[Docket No. FAA–2014–0928; Directorate
Identifier 2014–NM–040–AD; Amendment and locating Docket No. FAA–2014– and thermography inspections. The
39–18333; AD 2015–24–01] 0928. corrective actions in this AD include
FOR FURTHER INFORMATION CONTACT: repairs.
RIN 2120–AA64
Vladimir Ulyanov, Aerospace Engineer, The compliance time for the related
Airworthiness Directives; Airbus International Branch, ANM–116, investigative actions is before further
Airplanes Transport Airplane Directorate, FAA, flight after accomplishing the applicable
1601 Lind Avenue SW., Renton, WA inspection required by paragraph (g)(1)
AGENCY: Federal Aviation 98057–3356; telephone 425–227–1138; or (g)(2)(ii) of this AD.
Administration (FAA), Department of fax 425–227–1149. The intervals for the repetitive
Transportation (DOT). SUPPLEMENTARY INFORMATION: inspections are either 900 flight hours or
ACTION: Final rule. 1,000 flight cycles, depending on the
Discussion applicable conditions identified in the
SUMMARY: We are adopting a new We issued a notice of proposed service information.
airworthiness directive (AD) for all rulemaking (NPRM) to amend 14 CFR The compliance times for the
Airbus Model A330–200 Freighter, part 39 by adding an AD that would corrective actions range, depending on
A330–200, A330–300, A340–200, A340– apply to all Airbus Model A330–200 the applicable conditions identified in
300, A340–500, and A340–600 series Freighter, A330–200, A330–300, A340– the service information, from before
airplanes. This AD was prompted by a 200, A340–300, A340–500, and A340– further flight to within 4,500 flight
report of skin disbonding on a 600 series airplanes. The NPRM cycles but not to exceed 24 months after
composite side panel of a rudder published in the Federal Register on accomplishing the applicable inspection
installed on an A310 airplane. This AD December 29, 2014 (79 FR 77972). required by paragraph (g)(1) or (g)(2)(ii)
requires a review of the maintenance The European Aviation Safety Agency of this AD.
records of the rudder to determine if any (EASA), which is the Technical Agent You may examine the MCAI in the
composite side shell panel repair has for the Member States of the European AD docket on the Internet at http://
been done; a thermography inspection Union, has issued EASA Airworthiness www.regulations.gov/
limited to the repair areas or complete Directive 2014–0033, dated February 4, #!documentDetail;D=FAA-2014-0928-
side shells, as applicable, to identify 2014 (referred to after this as the 0002.
possible in-service rudder repairs, Mandatory Continuing Airworthiness Comments
damages, or fluid ingress; and Information, or ‘‘the MCAI’’), to correct
applicable related investigative and an unsafe condition for all Airbus We gave the public the opportunity to
corrective actions. We are issuing this Model A330–200 Freighter, A330–200, participate in developing this AD. The
AD to detect and correct the rudder skin A330–300, A340–200, A340–300, A340– following presents the comments
disbonding, which could affect the 500, and A340–600 series airplanes. The received on the NPRM (79 FR 77972,
structural integrity of the rudder, and MCAI states: December 29, 2014) and the FAA’s
could result in reduced controllability response to each comment.
A case of skin disbonding was reported on
of the airplane. a composite side panel of a rudder installed Request To Use the Latest Service
DATES: This AD becomes effective on an A310 aeroplane. Information
January 4, 2016. The investigation results revealed that this
disbonding started from a skin panel area American Airlines (AAL) and Delta
The Director of the Federal Register Airlines (DAL) requested that we revise
previously repaired in-service in accordance
approved the incorporation by reference with the Structural Repair Manual (SRM). the NPRM (79 FR 77972, December 29,
of certain publications listed in this AD The initial damage has been identified as 2014) to cite the latest service
as of January 4, 2016. a disbonding between the core and skin of information.
mstockstill on DSK4VPTVN1PROD with RULES
ADDRESSES: You may examine the AD the repaired area. This damage may not be We agree with the commenters’
docket on the Internet at http:// visually detectable and likely propagates request. Airbus has issued Airbus
www.regulations.gov/ during normal operation due to the variation Service Bulletin A330–55–3043,
of pressure during ground-air-ground cycles.
#!docketDetail;D=FAA-2014-0928 or in Composite rudder side shell panels are also Revision 1, dated August 20, 2014,
person at the Docket Management installed on A330 and A340 aeroplanes, Airbus Service Bulletin A340–55–4039,
Facility, U.S. Department of which may have been repaired in-service Revision 1, dated August 20, 2014, and
Transportation, Docket Operations, M– using a similar method. Airbus Service Bulletin A340–55–5007,
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![73962 Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Rules and Regulations
Regulatory Findings (b) Affected ADs (ii) Within 24 months after the effective
None. date of this AD: Do a thermography
We determined that this AD will not inspection for any repair on complete side
have federalism implications under (c) Applicability shells to identify and mark any repair, in
Executive Order 13132. This AD will This AD applies to all airplanes identified accordance with the Accomplishment
not have a substantial direct effect on in paragraphs (c)(1) and (c)(2) of this AD, Instructions of the applicable service
the States, on the relationship between certificated in any category. information specified in paragraphs (g)(1)(i)
the national government and the States, (1) Airbus Model A330–201, –202, –203, through (g)(1)(iii) of this AD.
or on the distribution of power and –223, –223F,–243, –243F, –301, –302, –303, (h) Related Investigative Actions, Corrective
responsibilities among the various –321, –322, –323, –341, –342, and –343 Actions, and Repetitive Inspections
airplanes, all manufacturer serial numbers.
levels of government. After the inspection as required by
(2) Airbus Model A340–211, –212, –213,
For the reasons discussed above, I –311, –312, –313, –541, and –642 airplanes, paragraph (g)(1) or (g)(2) of this AD: At the
certify that this AD: all manufacturer serial numbers. applicable compliance times specified in
1. Is not a ‘‘significant regulatory paragraph 1.E., ‘‘Compliance,’’ of Tables 3,
action’’ under Executive Order 12866; (d) Subject 4A, 4B, 4C, 4D, and 5 of the applicable
2. Is not a ‘‘significant rule’’ under the Air Transport Association (ATA) of service information specified in paragraphs
DOT Regulatory Policies and Procedures America Code 55, Stabilizers. (g)(1)(i) through (g)(1)(iii) of this AD,
accomplish all applicable related
(44 FR 11034, February 26, 1979); (e) Reason investigative and corrective actions, in
3. Will not affect intrastate aviation in This AD was prompted by a report of skin accordance with the Accomplishment
Alaska; and disbonding on a composite side panel of a Instructions of the applicable service
4. Will not have a significant rudder installed on an A310 airplane. We are information specified in paragraphs (g)(1)(i)
economic impact, positive or negative, issuing this AD to detect and correct the through (g)(1)(iii) of this AD; except as
on a substantial number of small entities rudder skin disbonding, which could affect provided by paragraphs (i)(1) and (i)(2) of
under the criteria of the Regulatory the structural integrity of the rudder, and this AD. Options provided in the service
Flexibility Act. could result in reduced controllability of the information specified in paragraphs (g)(1)(i)
airplane. through (g)(1)(iii) of this AD for
Examining the AD Docket accomplishing the actions are acceptable for
(f) Compliance the corresponding requirements of this
You may examine the AD docket on Comply with this AD within the paragraph provided that the related
the Internet at http:// compliance times specified, unless already investigative and corrective actions are done
www.regulations.gov/ done. at the applicable times specified in paragraph
#!docketDetail;D=FAA-2014-0928; or in 1.E., ‘‘Compliance,’’ of the applicable service
(g) Review the Maintenance Records
person at the Docket Management information specified in paragraphs (g)(1)(i)
Facility between 9 a.m. and 5 p.m., Within 24 months after the effective date through (g)(1)(iii) of this AD, including
Monday through Friday, except Federal of this AD: Review the maintenance records applicable repetitive inspection intervals,
of the rudder to determine if any composite except as required by paragraphs (i)(1) and
holidays. The AD docket contains this side shell panel repair has been (i)(2) of this AD. Thereafter repeat the
AD, the regulatory evaluation, any accomplished on the rudder since first inspections of the restored and repaired areas
comments received, and other installation on an airplane. at the applicable compliance time specified
information. The street address for the (1) If, based on the maintenance record in paragraph 1.E., ‘‘Compliance,’’ of Tables 3,
Docket Operations office (telephone review, any repair identified in Figure A– 4A, 4B, 4C, 4D, and 5 of the applicable
800–647–5527) is in the ADDRESSES GBBAA (Sheet 01 and 02) or Figure A– service information specified in paragraphs
section. GBCAA (Sheet 02) of the service information (g)(1)(i) through (g)(1)(iii) of this AD.
specified in paragraphs (g)(1)(i) through
List of Subjects in 14 CFR Part 39 (g)(1)(iii) of this AD is found: Within 24 (i) Exceptions to the Service Information
months after the effective date of this AD, do (1) Where the applicable service
Air transportation, Aircraft, Aviation
a thermography inspection for repair, information specified in paragraphs (g)(1)(i)
safety, Incorporation by reference, damages, and fluid ingress, limited to the through (g)(1)(iii) of this AD specifies a
Safety. repaired areas, in accordance with the compliance time relative to the date of the
Adoption of the Amendment Accomplishment Instructions of the service information, this AD requires
applicable service information specified in compliance within the specified compliance
Accordingly, under the authority paragraphs (g)(1)(i) through (g)(1)(iii) of this time after the effective date of this AD.
delegated to me by the Administrator, AD: (2) If the service information in paragraphs
the FAA amends 14 CFR part 39 as (i) Airbus Service Bulletin A330–55–3043, (g)(1)(i) through (g)(1)(iii) of this AD specifies
follows: Revision 1, dated August 20, 2014 (for Model to contact Airbus: At the applicable
A330–201, –202, –203, –223, –223F, –243, compliance times specified in paragraph 1.E.,
PART 39—AIRWORTHINESS –243F, –301, –302, –303, –321, –322, –323, ‘‘Compliance,’’ of the applicable service
–341, –342, and –343 airplanes). information specified in paragraphs (g)(1)(i)
DIRECTIVES
(ii) Airbus Service Bulletin A340–55–4039, through (g)(1)(iii) of this AD, repair using a
Revision 1, dated August 20, 2014 (for Model method approved by the Manager,
■ 1. The authority citation for part 39
A340–211, –212, –213, –311, –312, and –313 International Branch, ANM–116, Transport
continues to read as follows: airplanes). Airplane Directorate, FAA; or the European
Authority: 49 U.S.C. 106(g), 40113, 44701. (iii) Airbus Service Bulletin A340–55– Aviation Safety Agency (EASA); or Airbus’s
5007, Revision 1, dated August 20, 2014 (for EASA Design Organization Approval (DOA).
§ 39.13 [Amended] Model A340–541 and –642 airplanes).
(2) For a rudder for which maintenance (j) Provisions for Certain Airplanes
■ 2. The FAA amends § 39.13 by adding
records are unavailable or incomplete, do the Airplanes fitted with a rudder having a
the following new airworthiness
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actions specified in paragraphs (g)(2)(i) and serial number (S/N) that is not in the range
directive (AD): (g)(2)(ii) of this AD: of S/N TS–1001 through S/N TS–1043
2015–24–01 Airbus: Amendment 39–18333. (i) No later than 3 months before inclusive, S/N TS–2001 through S/N TS–
Docket No. FAA–2014–0928; Directorate accomplishment of the thermography 2074 inclusive, S/N TS–3000 through S/N
Identifier 2014–NM–040–AD. inspection, as required by paragraph (g)(2)(ii) TS–3525 inclusive, S/N TS–4001 through
of this AD, contact Airbus to request related S/N TS–4170 inclusive, S/N TS–6001
(a) Effective Date rudder manufacturing data by submitting the through S/N TS–6246 inclusive, or S/N TS–
This AD becomes effective January 4, 2016. serial number of the rudder to Airbus. 5001 through S/N TS–5138 inclusive, are not
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![Federal Register / Vol. 80, No. 228 / Friday, November 27, 2015 / Rules and Regulations 73963
affected by the requirements of paragraphs (g) actions from a manufacturer, the action must DEPARTMENT OF TRANSPORTATION
and (h) of this AD provided that it is be accomplished using a method approved
determined that no repair has been by the Manager, International Branch, ANM– Federal Aviation Administration
accomplished as described in the procedures 116, Transport Airplane Directorate, FAA; or
identified in Figure A–GBBAA (Sheet 01 and the EASA; or Airbus’s EASA DOA. If
02) or Figure A–GBCAA (Sheet 02) of the
14 CFR Part 39
approved by the DOA, the approval must
service information specified in paragraphs
(g)(1)(i) through (g)(1)(iii) of this AD, as include the DOA-authorized signature. [Docket No. FAA–2014–1048; Directorate
applicable, on the composite side shell panel Identifier 2014–NM–055–AD; Amendment
(o) Related Information 39–18332; AD 2015–23–14]
of that rudder since first installation on an
airplane. (1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA RIN 2120–AA64
(k) Parts Installation Limitations Airworthiness Directive 2014–0033, dated
As of the effective date of this AD, no February 4, 2014, for related information. Airworthiness Directives; Fokker
person may install, on any airplane, a rudder, This MCAI may be found in the AD docket Services B.V. Airplanes
unless the record review and thermography on the Internet at http://www.regulations.gov
inspection specified in paragraph (g) of this AGENCY: Federal Aviation
by searching for and locating Docket No.
AD has been done on that rudder and Administration (FAA), Department of
FAA–2014–0928.
thereafter all applicable related investigative Transportation (DOT).
actions, repetitive inspections, and corrective (2) Service information identified in this
AD that is not incorporated by reference is ACTION: Final rule.
actions are done as required by paragraph (h)
of this AD, except as provided in paragraph available at the addresses specified in
SUMMARY: We are adopting a new
(j) of this AD. paragraphs (p)(3) and (p)(4) of this AD.
airworthiness directive (AD) for all
(l) Repair Prohibition (p) Material Incorporated by Reference Fokker Services B.V. Model F.28 Mark
As of the effective date of this AD, no (1) The Director of the Federal Register 0070 and 0100 airplanes. This AD was
person may accomplish a side shell repair on approved the incorporation by reference prompted by reports that cracks can
any rudder using a structure repair manual (IBR) of the service information listed in this occur in a frame of the tail section on
procedure identified in Figure A–GBBAA paragraph under 5 U.S.C. 552(a) and 1 CFR certain airplanes. This AD requires a
(Sheet 01 and 02) or Figure A–GBCAA (Sheet one-time detailed inspection of the
part 51.
02) of the service information specified in oblique frame 67–2 for any cracking,
paragraphs (g)(1)(i) through (g)(1)(iii) of this (2) You must use this service information
AD, as applicable, on any airplane. as applicable to do the actions required by and repair if necessary. We are issuing
this AD, unless this AD specifies otherwise. this AD to detect and correct such
(m) Credit for Previous Actions (i) Airbus Service Bulletin A330–55–3043, cracking, which could lead to failure of
This paragraph provides credit for the Revision 1, dated August 20, 2014. the oblique frame 67–2, and consequent
actions specified in this AD, if those actions (ii) Airbus Service Bulletin A340–55–4039, loss of the structural integrity of the tail
were performed before the effective date of Revision 1, dated August 20, 2014. section.
this AD using the service information in (iii) Airbus Service Bulletin A340–55–
paragraphs (m)(1), (m)(2), and (m)(3) of this DATES: This AD becomes effective
5007, Revision 1, dated August 20, 2014. January 4, 2016.
AD.
(1) Airbus Service Bulletin A330–55–3043, (3) For service information identified in The Director of the Federal Register
dated February 7, 2013. this AD, contact Airbus SAS, Airworthiness approved the incorporation by reference
(2) Airbus Service Bulletin A340–55–4039, Office—EAL, 1 Rond Point Maurice Bellonte, of certain publications listed in this AD
dated February 7, 2013. 31707 Blagnac Cedex, France; telephone +33 as of January 4, 2016.
(3) Airbus Service Bulletin A340–55–5007, 5 61 93 36 96; fax +33 5 61 93 45 80; email
dated February 7, 2013. ADDRESSES: You may examine the AD
airworthiness.A330–A340@airbus.com;
docket on the Internet at http://
(n) Other FAA AD Provisions Internet http://www.airbus.com.
(4) You may view this service information
www.regulations.gov/
The following provisions also apply to this
at the FAA, Transport Airplane Directorate,
#!docketDetail;D=FAA-2014-1048 or in
AD: person at the Docket Management
(1) Alternative Methods of Compliance 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this Facility, U.S. Department of
(AMOCs): The Manager, International Transportation, Docket Operations, M–
Branch, ANM–116, Transport Airplane material at the FAA, call 425–227–1221.
Directorate, FAA, has the authority to (5) You may view this service information 30, West Building Ground Floor, Room
approve AMOCs for this AD, if requested that is incorporated by reference at the W12–140, 1200 New Jersey Avenue SE.,
using the procedures found in 14 CFR 39.19. National Archives and Records Washington, DC.
In accordance with 14 CFR 39.19, send your Administration (NARA). For information on For service information identified in
request to your principal inspector or local the availability of this material at NARA, call this AD, contact Fokker Services B.V.,
Flight Standards District Office, as Technical Services Dept., P.O. Box
202–741–6030, or go to: http://
appropriate. If sending information directly 1357, 2130 EL Hoofddorp, the
to the International Branch, send it to ATTN: www.archives.gov/federal-register/cfr/ibr-
locations.html. Netherlands; telephone +31 (0)88–6280–
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116, Transport 350; fax +31 (0)88–6280–111; email
Issued in Renton, Washington, on
Airplane Directorate, FAA, 1601 Lind technicalservices@fokker.com; Internet
November 9, 2015.
Avenue SW., Renton, WA 98057–3356; http://www.myfokkerfleet.com. You may
telephone 425–227–1138; fax 425–227–1149. Michael Kaszycki, view this referenced service information
Information may be emailed to: 9-ANM-116- Acting Manager, Transport Airplane at the FAA, Transport Airplane
AMOC-REQUESTS@faa.gov. Before using Directorate, Aircraft Certification Service. Directorate, 1601 Lind Avenue SW.,
mstockstill on DSK4VPTVN1PROD with RULES
any approved AMOC, notify your appropriate [FR Doc. 2015–29851 Filed 11–25–15; 8:45 am] Renton, WA. For information on the
principal inspector, or lacking a principal availability of this material at the FAA,
BILLING CODE 4910–13–P
inspector, the manager of the local flight
standards district office/certificate holding call 425–227–1221. It is also available
district office. The AMOC approval letter on the Internet at http://
must specifically reference this AD. www.regulations.gov by searching for
(2) Contacting the Manufacturer: For any and locating Docket No. FAA–2014–
requirement in this AD to obtain corrective 1048.
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Document Created: 2015-12-14 14:05:52
Document Modified: 2015-12-14 14:05:52
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD becomes effective January 4, 2016. | |
| 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. | |
| FR Citation | 80 FR 73960 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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