81 FR 12409 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 46 (March 9, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 46 (March 9, 2016)
| Page Range | 12409-12413 | |
| FR Document | 2016-04545 |
[Federal Register Volume 81, Number 46 (Wednesday, March 9, 2016)] [Rules and Regulations] [Pages 12409-12413] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-04545] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-0243; Directorate Identifier 2014-NM-114-AD; Amendment 39-18423; AD 2016-05-05] 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 A300 series airplanes; Model A300 B4-600, B4-600R, and F4- 600R series airplanes, and A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. This AD was prompted by reports of cracked aluminum support struts of the trimmable horizontal stabilizer (THS) caused by stress corrosion. This AD requires inspections to identify the part number of each support strut, repetitive inspections for cracking of the THS support strut ends, installation of reinforcing clamps on strut ends, and replacement of support struts, if necessary. We are issuing this AD to detect and correct cracked THS support struts, which could lead to the rupture of all four support struts making the remaining structure unable to carry limit loads, which could result in loss of the THS and reduced control of the airplane. DATES: This AD becomes effective April 13, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of April 13, 2016. ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-0243 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 final rule, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; 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-2015- 0243. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; 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 A300 series [[Page 12410]] airplanes; Model A300 B4-600, B4-600R, and F4-600R series airplanes, and A300 C4-605R Variant F airplanes (collectively called Model A300- 600 series airplanes); and Model A310 series airplanes. The NPRM published in the Federal Register on February 18, 2015 (80 FR 8571). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014-0164, dated July 11, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for all Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4-600R series airplanes, and A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes); and Model A310 series airplanes. The MCAI states: During scheduled maintenance, several Trimmable Horizontal Stabilizer (THS) support struts were found cracked at the strut ends. The THS is supported and articulated at frame (FR) 91 in the tail cone. Lateral movement is prevented by four diagonal support struts. Investigations revealed that the cracks were caused by stress corrosion and propagated from the inside to the outside of the strut. This condition, if not detected and corrected, could lead to the rupture of all four THS support struts at FR91, which would make the remaining structure unable to carry limit loads, potentially resulting in loss of the Horizontal Tail Plane. To address this unsafe condition, EASA issued AD 2014-0121 [http://ad.easa.europa.eu/ad/2014-0121] to require repetitive High Frequency Eddy Current (HFEC) inspections of the THS support strut ends, installation of reinforcing clamps on strut ends and, depending on findings, replacement of damaged support struts. Installation of reinforcing clamps on strut ends is considered a temporary solution pending introduction of a re-designed support strut. Since that [EASA] AD was issued, it was discovered that the [EASA] AD appeared to also require HFEC inspections of steel struts, which are not prone to cracking. The unsafe condition exists only on support struts made of aluminum, which were introduced through Airbus modification (mod) 06101, but may also have been installed in service as replacement parts on aeroplanes in pre-mod 06101 configuration. For the reason described above, this [EASA] AD retains the requirements of EASA AD 2014-0121, which is superseded, and clarifies the need for an initial identification of the support struts installed on aeroplanes in pre-mod 06101 configuration. The related Airbus Service Bulletins (SB) remain unchanged. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015-0243-0002. Comments We gave the public the opportunity to participate in developing this AD. We have considered the comments received. The following presents the comments received on the NPRM (80 FR 8571, February 18, 2015) (``the NPRM'') and the FAA's response to each comment. Request To Remove Repetitive Inspections From the NPRM FedEx stated that Airbus Service Bulletin A300-53-6172, dated February 14, 2014 and Airbus Service Bulletin A310-53-2136, dated February 14, 2014, require an application of sealant and installation of a clamp over the affected area. FedEx stated periodic re-inspections for cracking of the THS support strut ends would induce further damage since it requires removal of the reinforcing clamps and sealant before accomplishing the HFEC inspection. We infer from the commenter's statement that FedEx requests removal of the repetitive inspection requirement from the proposed AD. We disagree because if operators follow established procedures, removal of the sealant should not introduce damage to the support struts installed on the THS. We have not changed this final rule in this regard. Request To Remove Installation Requirement From the NPRM FedEx and United Parcel Service (UPS) stated they disagree with the requirement to install the clamping. Both commenters claimed that installing reinforcing clamps will not resolve any stress mitigation and crack progression. UPS stated that the NPRM proposed to require repair prior to further flight, if cracking is identified. FedEx and UPS stated that repetitive inspections provide a sufficient level of safety on the struts and that the installation of reinforcement clamps does not enhance the support strut installation, but adds an additional cost without a corresponding safety benefit. FedEx and UPS requested removal of the clamp installation requirement specified by paragraphs (i) and (j) of the proposed AD. We disagree to remove the requirement to install clamping from paragraphs (i) and (j) of this AD. The clamping reduces the circumferential stresses in the rod-ends and supports the circular shape of the rod ends. As a result, stress corrosion of the rod is stopped, or partially reduced, due to the lower circumferential stresses. We have not changed this final rule in this regard. Request To Remove Certain References From Paragraph (l) of the NPRM UPS requested that we remove reference to paragraphs (i)(1) through (i)(3) of the proposed AD from paragraph (l) of the proposed AD. UPS stated the service bulletins identified in paragraphs (i)(1) through (i)(3) of the proposed AD do not include an inspection form or inspection requirements within the accomplishment instructions of the service information and therefore these documents should not be referenced in paragraph (l) of the proposed AD, which specifies reporting inspection results. We agree with the request because paragraph (l) of this AD only requires the reporting of certain inspections results. Paragraph (i) of this AD requires an installation of reinforcing clamps. We have revised paragraph (l) of this AD to remove the reference to paragraphs (i)(1) through (i)(3) of this AD. We have also revised paragraph (l) of this AD by removing a reference to paragraph (h) of this AD in order to match the reporting requirement specified in the MCAI. Paragraph (l) of the proposed AD refers to inspections required by both paragraphs (g) and (h) of the proposed AD. However, reporting is only required for inspections required by paragraph (g) of this AD. Request To Revise Costs of Compliance FedEx requested that we revise the Costs of Compliance paragraph of the proposed AD to accurately reflect the cost of replacing cracked struts. FedEx stated it agrees that struts that are determined to be cracked should be replaced but finds that this adds an additional financial burden to the airlines. FedEx stated there are no warranty provisions stated in the manufacturer's service information to mitigate the additional expense of replacing struts, nor is it accounted for in the NPRM. We disagree because the conditional cost of replacing the struts was accounted for in the NPRM by using the standard part cost for non- avionics parts of $10,000 and an estimate that any necessary follow-on actions would take about 15 work-hours. Further, we do not control warranty coverage for affected individuals. We have not changed this final rule in this regard. Request To Include Installation of Steel Struts as Terminating Action FedEx requested that we revise the NPRM to state that the installation of steel struts constitutes a terminating [[Page 12411]] action for the repetitive inspections specified by paragraph (h) of the proposed AD. FedEx noted that Airbus may be developing a solution that would terminate the repetitive inspections, but as of yet, Airbus has not published any service information that would eliminate the need for the repetitive inspections specified by paragraph (h) of the proposed AD. We disagree to change this final rule because terminating action is not available at this time. When terminating action becomes available, the FAA may consider installation of the new design struts as an alternative method of compliance (AMOC) to this AD once the manufacturer's design solution is released. We have not changed this final rule in this regard. Request To Extend the Repetitive Inspection Interval UPS requested that we extend the repetitive inspection interval required by paragraph (h) of the proposed AD. UPS stated that a manufacturer's investigation identified the cracking to be the result of inter-granular stress corrosion and that for cracking to develop, three factors need to be present: a material flaw at the granular level, an environmental condition for corrosion to develop, and a tensile load to induce damage development/propagation at the material flaw. UPS added that the area is already protected with anti-corrosion materials. UPS stated that based on the low occurrence of cracking, the propagation properties of cracking due to stress corrosion, and the age of the fleet, fleet airworthiness can be maintained using all three operational parameters--flight hours, flight cycles, and calendar time. UPS requested that we revise the repetitive inspection interval from 24 months to 5,000 flight hours, 2,500 flight cycles, or 36 months, whichever occurs first. We do not agree with the request to extend the repetitive inspection required by paragraph (h) of this AD because the UPS proposal is not supported by analysis or data. In developing an appropriate compliance time for the actions specified in paragraph (h) of this AD, we considered the safety implications and normal maintenance schedules for the timely accomplishment of the specified actions. We have determined that the proposed interval will ensure an acceptable level of safety and allow the actions to be done during scheduled maintenance intervals for most affected operators. However, affected operators may request an AMOC to request an extension of the repetitive inspection interval under the provisions of paragraph (m)(1) of this AD by submitting data and analysis substantiating that the change would provide an acceptable level of safety. We have not changed this final rule in this regard. Request To Delay Rule Due to Pending Release of New Design of Support Strut and Service Information FedEx and UPS requested that the release date of the NPRM be suspended pending Airbus's release of a newly designed support strut that, if installed, would be terminating action for the repetitive inspections proposed by the NPRM. FedEx stated the manufacturer is working on service information that contains a terminating action for the repetitive inspections proposed in the NPRM, but as of yet, has not been published. UPS stated that suspending the release of the NPRM would prevent extra work for the FAA and operators. We disagree with delaying issuance of this final rule until new service information or a new design becomes available. We consider that to delay this AD action would be inappropriate, in light of the identified unsafe condition. When new service information or a new design becomes available, we may consider additional rulemaking. We may also consider new service information and/or installation of the new design struts as an AMOC to this AD. Operators may apply for an AMOC in accordance with the provisions of paragraph (m)(1) of this AD. We have not changed this final rule 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 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 A300-53-0394, dated February 14, 2014. This service information describes procedures for reinforcing the support struts of the THS at frame 91 in the fuselage tail section of Airbus Model A300 series airplanes. Airbus Service Bulletin A300-53-0395, dated February 14, 2014. This service information describes procedures for inspecting for cracking of the support struts of the THS at frame 91 in the fuselage tail section of Airbus Model A300 series airplanes. Airbus Service Bulletin A300-53-6172, dated February 14, 2014. This service information describes procedures for reinforcing the support struts of the THS at frame 91 in the fuselage tail section of Airbus Model A300-600 series airplanes. Airbus Service Bulletin A300-53-6174, dated February 14, 2014. This service information describes procedures for inspecting for cracking of the support struts of the THS at frame 91 in the fuselage tail section of Airbus Model A300-600 series airplanes. Airbus Service Bulletin A310-53-2136, dated February 14, 2014. This service information describes procedures for reinforcing the support struts of the THS at frame 91 in the fuselage tail section of Airbus Model A310 series airplanes. Airbus Service Bulletin A310-53-2137, dated February 14, 2014. This service information describes procedures for inspecting for cracking of the support struts of the THS at frame 91 in the fuselage tail section of Airbus Model A310 series airplanes. 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 174 airplanes of U.S. registry. We also estimate that it will take about 5 work-hours per product to comply with the basic requirements of this AD, and 1 work-hour per product for reporting. The average labor rate is $85 per work-hour. Required parts will cost about $2,100 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $454,140, or $2,610 per product. In addition, we estimate that any necessary follow-on actions will take about 15 work-hours and require parts costing $10,000, for a cost of $11,275 per product. We have no way of determining the number of aircraft that might need these actions. 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 [[Page 12412]] detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-0243; 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): 2016-05-05 Airbus: Amendment 39-18423. Docket No. FAA-2015-0243; Directorate Identifier 2014-NM-114-AD. (a) Effective Date This AD becomes effective April 13, 2016. (b) Affected ADs None. (c) Applicability This AD applies to the Airbus airplanes specified in paragraphs (c)(1) through (c)(6) of this AD, certificated in any category, all manufacturer serial numbers. (1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4- 103, and B4-203 airplanes. (2) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes. (3) Airbus Model A300 B4-605R and B4-622R airplanes. (4) Airbus Model A300 F4-605R and F4-622R airplanes. (5) Airbus Model A300 C4-605R Variant F airplanes. (6) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by reports of cracked aluminum support struts of the trimmable horizontal stabilizer (THS) caused by stress corrosion. We are issuing this AD to detect and correct cracked THS support struts, which could lead to the rupture of all four support struts making the remaining structure unable to carry limit loads, which could result in loss of the THS and reduced control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection for Part Number For airplanes in pre-modification 06101 configuration: Within 12 months after the effective date of this AD, do an inspection to identify the part number of each support strut installed on the THS at frame (FR) 91, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraphs (g)(1) through (g)(3) of this AD. A review of airplane maintenance records is acceptable in lieu of this inspection, provided those records can be relied upon for that purpose and the part number can be positively identified from that review. If no aluminum strut(s) having part number (P/N) R21449, R21449D, R21449G, or R21449H is found during any inspection required by this paragraph, no further action is required by this AD for that horizontal stabilizer, except for paragraph (l) of this AD. (1) For Airbus Model A300 series airplanes: Airbus Service Bulletin A300-53-0395, dated February 14, 2014. (2) For Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes): Airbus Service Bulletin A300-53- 6174, dated February 14, 2014. (3) For Airbus Model A310 series airplanes: Airbus Service Bulletin A310-53-2137, dated February 14, 2014. (h) Repetitive High Frequency Eddy Current (HFEC) Inspections For airplanes in post-modification 06101 configuration; and for airplanes in pre-modification 06101 configuration on which any aluminum support strut(s) having P/N R21449, P/N R21449D, P/N R21449G, or P/N R21449H is found: Within the applicable compliance times specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD, do an HFEC inspection for cracking of the aluminum THS support strut ends at FR 91, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraphs (g)(1) through (g)(3) of this AD. Reinforcing clamps already installed on strut ends must be removed before accomplishing the HFEC inspection and re-installed after the inspection, in accordance with the Accomplishment Instructions of the applicable service bulletin specified in paragraphs (g)(1) through (g)(3) of this AD. Repeat the inspection thereafter at intervals not to exceed 24 months. (1) For airplanes having manufacturer serial number (MSN) 0499 through MSN 0747 inclusive (post-mod 06101): Within 12 months after the effective date of this AD. (2) For airplanes having MSN 0748 through MSN 0878 inclusive (post-mod 06101): Within 18 months after the effective date of this AD. (3) For airplanes having MSN 0001 through MSN 0498 inclusive (pre-mod 06101) having one or more aluminum struts: Within 24 months after the effective date of this AD. (i) Installation of Reinforcing Clamps Concurrently with the initial HFEC inspection required by paragraph (h) of this AD, identify struts having P/N R21449, P/N R21449D, P/N R21449G, or P/N R21449H with no reinforcing clamps previously installed, and before next flight, install reinforcing clamps on each strut end, in accordance with the Accomplishment Instructions of the applicable service bulletin specified in paragraphs (i)(1) through (i)(3) of this AD. (1) For Airbus Model A300 series airplanes: Airbus Service Bulletin A300-53-0394, dated February 14, 2014. (2) For Airbus Model A300 B4-600, B4600R, and F4-600R series airplanes, and A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes): Airbus Service Bulletin A300-53- 6172, dated February 14, 2014. [[Page 12413]] (3) For Airbus Model A310 series airplanes: Airbus Service Bulletin A310-53-2136, dated February 14, 2014. (j) Corrective Actions If, during any inspection required by paragraph (h) of this AD, any cracking is found, before further flight, replace the affected THS support strut(s) with serviceable struts and install clamps on each strut end, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in paragraphs (g)(1) through (g)(3) of this AD. (k) Clarification Installation of reinforcing clamps as required by paragraph (i) of this AD, and the replacement of support struts and/or the installation of clamps as required by paragraph (j) of this AD, do not constitute terminating action for the repetitive inspections required by paragraph (h) of this AD. (l) Reporting At the applicable time specified in paragraphs (l)(1) and (l)(2) of this AD: After accomplishment of any inspection required by paragraph (g) of this AD, report all inspection results to Airbus, including no findings, in accordance with the Accomplishment Instructions of the applicable service bulletins specified in paragraphs (g)(1) through (g)(3) of this AD. (1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection. (2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. (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: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone 425-227-2125; 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 European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a 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 OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are 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. (n) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0164, dated July 11, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015- 0243-0002. (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. (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 A300-53-0394, dated February 14, 2014. (ii) Airbus Service Bulletin A300-53-0395, dated February 14, 2014. (iii) Airbus Service Bulletin A300-53-6172, dated February 14, 2014. (iv) Airbus Service Bulletin A300-53-6174, dated February 14, 2014. (v) Airbus Service Bulletin A310-53-2136, dated February 14, 2014. (vi) Airbus Service Bulletin A310-53-2137, dated February 14, 2014. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; 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 February 23, 2016. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-04545 Filed 3-8-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 46 / Wednesday, March 9, 2016 / Rules and Regulations 12409
the life limit established by the manufacturer paragraph under 5 U.S.C. 552(a) and 1 CFR called Model A300–600 series
for that generator. part 51. airplanes); and Model A310 series
(2) You must use this service information airplanes. This AD was prompted by
(k) Credit for Previous Actions as applicable to do the actions required by reports of cracked aluminum support
This paragraph provides credit for the this AD, unless this AD specifies otherwise.
applicable actions required by paragraphs (g), (i) Airbus Alert Operators Transmission
struts of the trimmable horizontal
(h), and (i) of this AD, if those actions were (AOT) A35L007–14, Revision 01, June 17, stabilizer (THS) caused by stress
performed before the effective date of this AD 2015; including Appendix A, Revision 01, corrosion. This AD requires inspections
using Airbus AOT A35L007–14, dated dated June 17, 2015. The revision date is not to identify the part number of each
December 18, 2014. shown on Appendix A. support strut, repetitive inspections for
(ii) B/E Aerospace Service Bulletin cracking of the THS support strut ends,
(l) Parts Installation Limitation
117042–35–001, dated December 10, 2014. installation of reinforcing clamps on
As of the effective date of this AD, no (3) For Airbus service information strut ends, and replacement of support
person may install a passenger chemical identified in this AD, contact Airbus SAS, struts, if necessary. We are issuing this
oxygen generator on any airplane, unless the Airworthiness Office—EAL, 1 Rond Point
passenger chemical oxygen generator is
AD to detect and correct cracked THS
Maurice Bellonte, 31707 Blagnac Cedex,
determined to be a serviceable unit, as France; telephone +33 5 61 93 36 96; fax +33
support struts, which could lead to the
defined in paragraph (j) of this AD. 5 61 93 45 80; email airworthiness.A330- rupture of all four support struts making
A340@airbus.com; Internet http:// the remaining structure unable to carry
(m) Other FAA AD Provisions limit loads, which could result in loss
www.airbus.com.
The following provisions also apply to this (4) For B/E Aerospace service information of the THS and reduced control of the
AD: identified in this AD, contact B/E Aerospace airplane.
(1) Alternative Methods of Compliance Inc., 10800 Pflumm Road, Lenexa, KS 66215; DATES: This AD becomes effective April
(AMOCs): The Manager, International telephone 913–338–9800; fax 913–469–8419;
Branch, ANM–116, Transport Airplane
13, 2016.
Internet http://beaerospace.com/home/global
Directorate, FAA, has the authority to The Director of the Federal Register
support.
approve AMOCs for this AD, if requested (5) You may view this service information approved the incorporation by reference
using the procedures found in 14 CFR 39.19. at the FAA, Transport Airplane Directorate, of certain publications listed in this AD
In accordance with 14 CFR 39.19, send your 1601 Lind Avenue SW., Renton, WA. For as of April 13, 2016.
request to your principal inspector or local information on the availability of this ADDRESSES: You may examine the AD
Flight Standards District Office, as material at the FAA, call 425–227–1221. docket on the Internet at http://
appropriate. If sending information directly (6) You may view this service information www.regulations.gov/#!docket
to the International Branch, send it to ATTN: that is incorporated by reference at the Detail;D=FAA-2015-0243 or in person at
Vladimir Ulyanov, Aerospace Engineer, National Archives and Records
International Branch, ANM–116, Transport Administration (NARA). For information on
the Docket Management Facility, U.S.
Airplane Directorate, FAA, 1601 Lind the availability of this material at NARA, call Department of Transportation, Docket
Avenue SW., Renton, WA 98057–3356; 202–741–6030, or go to: http:// Operations, M–30, West Building
telephone 425–227–1138; fax 425–227–1149. www.archives.gov/federal-register/cfr/ibr- Ground Floor, Room W12–140, 1200
Information may be emailed to: 9-ANM-116- locations.html. New Jersey Avenue SE., Washington,
AMOC-REQUESTS@faa.gov. Before using
Issued in Renton, Washington, on February DC.
any approved AMOC, notify your appropriate
19, 2016. For service information identified in
principal inspector, or lacking a principal this final rule, contact Airbus SAS,
inspector, the manager of the local flight Dorr M. Anderson,
Airworthiness Office—EAW, 1 Rond
standards district office/certificate holding Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
Point Maurice Bellonte, 31707 Blagnac
district office. The AMOC approval letter
must specifically reference this AD.
Cedex, France; telephone +33 5 61 93 36
[FR Doc. 2016–04538 Filed 3–8–16; 8:45 am]
(2) Contacting the Manufacturer: For any 96; fax +33 5 61 93 44 51; email
BILLING CODE 4910–13–P
requirement in this AD to obtain corrective account.airworth-eas@airbus.com;
actions from a manufacturer, the action must Internet http://www.airbus.com. You
be accomplished using a method approved may view this referenced service
DEPARTMENT OF TRANSPORTATION
by the Manager, International Branch, ANM– information at the FAA, Transport
116, Transport Airplane Directorate, FAA; or Airplane Directorate, 1601 Lind Avenue
Federal Aviation Administration
the European Aviation Safety Agency SW., Renton, WA. For information on
(EASA); or Airbus’s EASA Design the availability of this material at the
Organization Approval (DOA). If approved by 14 CFR Part 39
the DOA, the approval must include the
FAA, call 425–227–1221. It is also
[Docket No. FAA–2015–0243; Directorate available on the Internet at http://
DOA-authorized signature. Identifier 2014–NM–114–AD; Amendment www.regulations.gov by searching for
(n) Related Information 39–18423; AD 2016–05–05]
and locating Docket No. FAA–2015–
(1) Refer to Mandatory Continuing RIN 2120–AA64 0243.
Airworthiness Information (MCAI) EASA
FOR FURTHER INFORMATION CONTACT: Dan
Airworthiness Directive 2015–0119, dated Airworthiness Directives; Airbus
June 24, 2015, correction January 12, 2016, Airplanes Rodina, Aerospace Engineer,
for related information. This MCAI may be International Branch, ANM–116,
found in the AD docket on the Internet at AGENCY: Federal Aviation Transport Airplane Directorate, FAA,
http://www.regulations.gov by searching for Administration (FAA), Department of 1601 Lind Avenue SW., Renton, WA
and locating Docket No. FAA–2015–3149. Transportation (DOT). 98057–3356; telephone 425–227–2125;
(2) Service information identified in this ACTION: Final rule. fax 425–227–1149.
AD that is not incorporated by reference is
SUPPLEMENTARY INFORMATION:
Lhorne on DSK5TPTVN1PROD with RULES
available at the addresses specified in SUMMARY: We are adopting a new
paragraphs (o)(3) and (o)(5) of this AD. Discussion
airworthiness directive (AD) for all
(o) Material Incorporated by Reference Airbus Model A300 series airplanes; We issued a notice of proposed
(1) The Director of the Federal Register Model A300 B4–600, B4–600R, and F4– rulemaking (NPRM) to amend 14 CFR
approved the incorporation by reference 600R series airplanes, and A300 C4– part 39 by adding an AD that would
(IBR) of the service information listed in this 605R Variant F airplanes (collectively apply to all Airbus Model A300 series
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![12410 Federal Register / Vol. 81, No. 46 / Wednesday, March 9, 2016 / Rules and Regulations
airplanes; Model A300 B4–600, B4– www.regulations.gov/#!document not changed this final rule in this
600R, and F4–600R series airplanes, and Detail;D=FAA-2015-0243-0002. regard.
A300 C4–605R Variant F airplanes
Comments Request To Remove Certain References
(collectively called Model A300–600
From Paragraph (l) of the NPRM
series airplanes); and Model A310 series We gave the public the opportunity to
airplanes. The NPRM published in the participate in developing this AD. We UPS requested that we remove
Federal Register on February 18, 2015 have considered the comments received. reference to paragraphs (i)(1) through
(80 FR 8571). The following presents the comments (i)(3) of the proposed AD from
The European Aviation Safety Agency received on the NPRM (80 FR 8571, paragraph (l) of the proposed AD. UPS
(EASA), which is the Technical Agent February 18, 2015) (‘‘the NPRM’’) and stated the service bulletins identified in
for the Member States of the European the FAA’s response to each comment. paragraphs (i)(1) through (i)(3) of the
Union, has issued EASA Airworthiness proposed AD do not include an
Request To Remove Repetitive inspection form or inspection
Directive 2014–0164, dated July 11, Inspections From the NPRM
2014 (referred to after this as the requirements within the
Mandatory Continuing Airworthiness FedEx stated that Airbus Service accomplishment instructions of the
Information, or ‘‘the MCAI’’), to correct Bulletin A300–53–6172, dated February service information and therefore these
an unsafe condition for all Airbus 14, 2014 and Airbus Service Bulletin documents should not be referenced in
Model A300 series airplanes; Model A310–53–2136, dated February 14, paragraph (l) of the proposed AD, which
A300 B4–600, B4–600R, and F4–600R 2014, require an application of sealant specifies reporting inspection results.
series airplanes, and A300 C4–605R and installation of a clamp over the We agree with the request because
Variant F airplanes (collectively called affected area. FedEx stated periodic re- paragraph (l) of this AD only requires
Model A300–600 series airplanes); and inspections for cracking of the THS the reporting of certain inspections
Model A310 series airplanes. The MCAI support strut ends would induce further results. Paragraph (i) of this AD requires
states: damage since it requires removal of the an installation of reinforcing clamps.
reinforcing clamps and sealant before We have revised paragraph (l) of this AD
During scheduled maintenance, several
Trimmable Horizontal Stabilizer (THS) accomplishing the HFEC inspection. to remove the reference to paragraphs
support struts were found cracked at the strut We infer from the commenter’s (i)(1) through (i)(3) of this AD.
ends. The THS is supported and articulated We have also revised paragraph (l) of
statement that FedEx requests removal
at frame (FR) 91 in the tail cone. Lateral this AD by removing a reference to
of the repetitive inspection requirement
movement is prevented by four diagonal paragraph (h) of this AD in order to
from the proposed AD. We disagree
support struts. match the reporting requirement
Investigations revealed that the cracks were
because if operators follow established
specified in the MCAI. Paragraph (l) of
caused by stress corrosion and propagated procedures, removal of the sealant
the proposed AD refers to inspections
from the inside to the outside of the strut. should not introduce damage to the
required by both paragraphs (g) and (h)
This condition, if not detected and support struts installed on the THS. We
of the proposed AD. However, reporting
corrected, could lead to the rupture of all have not changed this final rule in this
four THS support struts at FR91, which is only required for inspections required
regard.
would make the remaining structure unable by paragraph (g) of this AD.
to carry limit loads, potentially resulting in Request To Remove Installation
Request To Revise Costs of Compliance
loss of the Horizontal Tail Plane. Requirement From the NPRM
To address this unsafe condition, EASA FedEx requested that we revise the
issued AD 2014–0121 [http://
FedEx and United Parcel Service Costs of Compliance paragraph of the
ad.easa.europa.eu/ad/2014-0121] to require (UPS) stated they disagree with the proposed AD to accurately reflect the
repetitive High Frequency Eddy Current requirement to install the clamping. cost of replacing cracked struts. FedEx
(HFEC) inspections of the THS support strut Both commenters claimed that installing stated it agrees that struts that are
ends, installation of reinforcing clamps on reinforcing clamps will not resolve any determined to be cracked should be
strut ends and, depending on findings, stress mitigation and crack progression.
replacement of damaged support struts.
replaced but finds that this adds an
UPS stated that the NPRM proposed to additional financial burden to the
Installation of reinforcing clamps on strut require repair prior to further flight, if
ends is considered a temporary solution airlines. FedEx stated there are no
cracking is identified. FedEx and UPS warranty provisions stated in the
pending introduction of a re-designed
support strut.
stated that repetitive inspections manufacturer’s service information to
Since that [EASA] AD was issued, it was provide a sufficient level of safety on mitigate the additional expense of
discovered that the [EASA] AD appeared to the struts and that the installation of replacing struts, nor is it accounted for
also require HFEC inspections of steel struts, reinforcement clamps does not enhance in the NPRM.
which are not prone to cracking. The unsafe the support strut installation, but adds We disagree because the conditional
condition exists only on support struts made an additional cost without a cost of replacing the struts was
of aluminum, which were introduced corresponding safety benefit. FedEx and
through Airbus modification (mod) 06101,
accounted for in the NPRM by using the
UPS requested removal of the clamp standard part cost for non-avionics parts
but may also have been installed in service installation requirement specified by
as replacement parts on aeroplanes in pre- of $10,000 and an estimate that any
mod 06101 configuration.
paragraphs (i) and (j) of the proposed necessary follow-on actions would take
For the reason described above, this AD. about 15 work-hours. Further, we do not
[EASA] AD retains the requirements of EASA We disagree to remove the control warranty coverage for affected
AD 2014–0121, which is superseded, and requirement to install clamping from individuals. We have not changed this
clarifies the need for an initial identification paragraphs (i) and (j) of this AD. The final rule in this regard.
Lhorne on DSK5TPTVN1PROD with RULES
of the support struts installed on aeroplanes clamping reduces the circumferential
in pre-mod 06101 configuration. The related stresses in the rod-ends and supports Request To Include Installation of Steel
Airbus Service Bulletins (SB) remain the circular shape of the rod ends. As a Struts as Terminating Action
unchanged.
result, stress corrosion of the rod is FedEx requested that we revise the
You may examine the MCAI in the stopped, or partially reduced, due to the NPRM to state that the installation of
AD docket on the Internet at http:// lower circumferential stresses. We have steel struts constitutes a terminating
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![12412 Federal Register / Vol. 81, No. 46 / Wednesday, March 9, 2016 / Rules and Regulations
detail the scope of the Agency’s PART 39—AIRWORTHINESS review. If no aluminum strut(s) having part
authority. DIRECTIVES number (P/N) R21449, R21449D, R21449G, or
R21449H is found during any inspection
We are issuing this rulemaking under
■ 1. The authority citation for part 39 required by this paragraph, no further action
the authority described in ‘‘Subtitle VII, is required by this AD for that horizontal
Part A, Subpart III, Section 44701: continues to read as follows:
stabilizer, except for paragraph (l) of this AD.
General requirements.’’ Under that Authority: 49 U.S.C. 106(g), 40113, 44701. (1) For Airbus Model A300 series
section, Congress charges the FAA with airplanes: Airbus Service Bulletin A300–53–
promoting safe flight of civil aircraft in § 39.13 [Amended] 0395, dated February 14, 2014.
air commerce by prescribing regulations ■ 2. The FAA amends § 39.13 by adding (2) For Airbus Model A300 B4–600, B4–
for practices, methods, and procedures the following new airworthiness 600R, and F4–600R series airplanes, and
A300 C4–605R Variant F airplanes
the Administrator finds necessary for directive (AD): (collectively called Model A300–600 series
safety in air commerce. This regulation 2016–05–05 Airbus: Amendment 39–18423. airplanes): Airbus Service Bulletin A300–53–
is within the scope of that authority Docket No. FAA–2015–0243; Directorate 6174, dated February 14, 2014.
because it addresses an unsafe condition Identifier 2014–NM–114–AD. (3) For Airbus Model A310 series
that is likely to exist or develop on airplanes: Airbus Service Bulletin A310–53–
(a) Effective Date 2137, dated February 14, 2014.
products identified in this rulemaking
action. This AD becomes effective April 13, 2016.
(h) Repetitive High Frequency Eddy Current
(b) Affected ADs (HFEC) Inspections
Regulatory Findings
None. For airplanes in post-modification 06101
We determined that this AD will not configuration; and for airplanes in pre-
have federalism implications under (c) Applicability
modification 06101 configuration on which
Executive Order 13132. This AD will This AD applies to the Airbus airplanes any aluminum support strut(s) having P/N
not have a substantial direct effect on specified in paragraphs (c)(1) through (c)(6) R21449, P/N R21449D, P/N R21449G, or P/
of this AD, certificated in any category, all N R21449H is found: Within the applicable
the States, on the relationship between
manufacturer serial numbers. compliance times specified in paragraph
the national government and the States, (1) Airbus Model A300 B2–1A, B2–1C, (h)(1), (h)(2), or (h)(3) of this AD, do an HFEC
or on the distribution of power and B2K–3C, B2–203, B4–2C, B4–103, and B4– inspection for cracking of the aluminum THS
responsibilities among the various 203 airplanes. support strut ends at FR 91, in accordance
levels of government. (2) Airbus Model A300 B4–601, B4–603, with the Accomplishment Instructions of the
For the reasons discussed above, I B4–620, and B4–622 airplanes. applicable service bulletin identified in
certify that this AD: (3) Airbus Model A300 B4–605R and B4– paragraphs (g)(1) through (g)(3) of this AD.
1. Is not a ‘‘significant regulatory 622R airplanes. Reinforcing clamps already installed on strut
(4) Airbus Model A300 F4–605R and F4– ends must be removed before accomplishing
action’’ under Executive Order 12866;
622R airplanes. the HFEC inspection and re-installed after
2. Is not a ‘‘significant rule’’ under the (5) Airbus Model A300 C4–605R Variant F the inspection, in accordance with the
DOT Regulatory Policies and Procedures airplanes. Accomplishment Instructions of the
(44 FR 11034, February 26, 1979); (6) Airbus Model A310–203, –204, –221, applicable service bulletin specified in
3. Will not affect intrastate aviation in –222, –304, –322, –324, and –325 airplanes. paragraphs (g)(1) through (g)(3) of this AD.
Alaska; and Repeat the inspection thereafter at intervals
(d) Subject
4. Will not have a significant not to exceed 24 months.
Air Transport Association (ATA) of (1) For airplanes having manufacturer
economic impact, positive or negative, America Code 53, Fuselage. serial number (MSN) 0499 through MSN
on a substantial number of small entities 0747 inclusive (post-mod 06101): Within 12
under the criteria of the Regulatory (e) Reason
months after the effective date of this AD.
Flexibility Act. This AD was prompted by reports of (2) For airplanes having MSN 0748 through
cracked aluminum support struts of the MSN 0878 inclusive (post-mod 06101):
Examining the AD Docket trimmable horizontal stabilizer (THS) caused Within 18 months after the effective date of
You may examine the AD docket on by stress corrosion. We are issuing this AD this AD.
the Internet at http:// to detect and correct cracked THS support (3) For airplanes having MSN 0001 through
struts, which could lead to the rupture of all MSN 0498 inclusive (pre-mod 06101) having
www.regulations.gov/#!docket four support struts making the remaining one or more aluminum struts: Within 24
Detail;D=FAA-2015-0243; or in person structure unable to carry limit loads, which months after the effective date of this AD.
at the Docket Management Facility could result in loss of the THS and reduced
between 9 a.m. and 5 p.m., Monday control of the airplane. (i) Installation of Reinforcing Clamps
through Friday, except Federal holidays. Concurrently with the initial HFEC
(f) Compliance inspection required by paragraph (h) of this
The AD docket contains this AD, the
regulatory evaluation, any comments Comply with this AD within the AD, identify struts having P/N R21449, P/N
received, and other information. The compliance times specified, unless already R21449D, P/N R21449G, or P/N R21449H
done. with no reinforcing clamps previously
street address for the Docket Operations installed, and before next flight, install
office (telephone 800–647–5527) is in (g) Inspection for Part Number
reinforcing clamps on each strut end, in
the ADDRESSES section. For airplanes in pre-modification 06101 accordance with the Accomplishment
configuration: Within 12 months after the Instructions of the applicable service bulletin
List of Subjects in 14 CFR Part 39 effective date of this AD, do an inspection to specified in paragraphs (i)(1) through (i)(3) of
Air transportation, Aircraft, Aviation identify the part number of each support this AD.
safety, Incorporation by reference, strut installed on the THS at frame (FR) 91, (1) For Airbus Model A300 series
Safety. in accordance with the Accomplishment airplanes: Airbus Service Bulletin A300–53–
Lhorne on DSK5TPTVN1PROD with RULES
Instructions of the applicable service bulletin 0394, dated February 14, 2014.
Adoption of the Amendment identified in paragraphs (g)(1) through (g)(3) (2) For Airbus Model A300 B4–600,
of this AD. A review of airplane maintenance B4600R, and F4–600R series airplanes, and
Accordingly, under the authority records is acceptable in lieu of this A300 C4–605R Variant F airplanes
delegated to me by the Administrator, inspection, provided those records can be (collectively called Model A300–600 series
the FAA amends 14 CFR part 39 as relied upon for that purpose and the part airplanes): Airbus Service Bulletin A300–53–
follows: number can be positively identified from that 6172, dated February 14, 2014.
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![Federal Register / Vol. 81, No. 46 / Wednesday, March 9, 2016 / Rules and Regulations 12413
(3) For Airbus Model A310 series (EASA); or Airbus’s EASA Design www.archives.gov/federal-register/cfr/ibr-
airplanes: Airbus Service Bulletin A310–53– Organization Approval (DOA). If approved by locations.html.
2136, dated February 14, 2014. the DOA, the approval must include the
Issued in Renton, Washington, on February
DOA-authorized signature.
(j) Corrective Actions 23, 2016.
(3) Reporting Requirements: A federal
If, during any inspection required by agency may not conduct or sponsor, and a Dionne Palermo,
paragraph (h) of this AD, any cracking is person is not required to respond to, nor Acting Manager, Transport Airplane
found, before further flight, replace the shall a person be subject to a penalty for Directorate, Aircraft Certification Service.
affected THS support strut(s) with failure to comply with a collection of [FR Doc. 2016–04545 Filed 3–8–16; 8:45 am]
serviceable struts and install clamps on each information subject to the requirements of BILLING CODE 4910–13–P
strut end, in accordance with the the Paperwork Reduction Act unless that
Accomplishment Instructions of the collection of information displays a current
applicable service bulletin identified in valid OMB Control Number. The OMB
paragraphs (g)(1) through (g)(3) of this AD. Control Number for this information
DEPARTMENT OF TRANSPORTATION
(k) Clarification collection is 2120–0056. Public reporting for
this collection of information is estimated to
Federal Aviation Administration
Installation of reinforcing clamps as be approximately 5 minutes per response,
required by paragraph (i) of this AD, and the including the time for reviewing instructions, 14 CFR Part 39
replacement of support struts and/or the completing and reviewing the collection of
installation of clamps as required by [Docket No. FAA–2014–0529; Directorate
information. All responses to this collection
paragraph (j) of this AD, do not constitute Identifier 2013–NM–260–AD; Amendment
of information are mandatory. Comments
terminating action for the repetitive 39–18420; AD 2016–05–02]
concerning the accuracy of this burden and
inspections required by paragraph (h) of this suggestions for reducing the burden should
AD. RIN 2120–AA64
be directed to the FAA at 800 Independence
(l) Reporting Ave. SW., Washington, DC 20591, Attn: Airworthiness Directives; Airbus
At the applicable time specified in Information Collection Clearance Officer, Airplanes
paragraphs (l)(1) and (l)(2) of this AD: After AES–200.
accomplishment of any inspection required (n) Related Information
AGENCY: Federal Aviation
by paragraph (g) of this AD, report all Administration (FAA), Department of
Refer to Mandatory Continuing Transportation (DOT).
inspection results to Airbus, including no
Airworthiness Information (MCAI) EASA
findings, in accordance with the ACTION: Final rule.
Airworthiness Directive 2014–0164, dated
Accomplishment Instructions of the
July 11, 2014, for related information. This
applicable service bulletins specified in SUMMARY: We are superseding
MCAI may be found in the AD docket on the
paragraphs (g)(1) through (g)(3) of this AD. Airworthiness Directive (AD) 2011–13–
(1) If the inspection was done on or after Internet at http://www.regulations.gov/
#!documentDetail;D=FAA-2015-0243-0002. 11 and AD 2013–16–09 for all Airbus
the effective date of this AD: Submit the
report within 30 days after the inspection. Model A318, A319, A320, and A321
(o) Material Incorporated by Reference
(2) If the inspection was done before the series airplanes. AD 2011–13–11
(1) The Director of the Federal Register required an amendment of the airplane
effective date of this AD: Submit the report
approved the incorporation by reference
within 30 days after the effective date of this flight manual (AFM), repetitive checks
(IBR) of the service information listed in this
AD. of specific centralized fault display
paragraph under 5 U.S.C. 552(a) and 1 CFR
(m) Other FAA AD Provisions part 51. system (CFDS) messages, an inspection
(2) You must use this service information of the opening sequence of the main
The following provisions also apply to this
AD: as applicable to do the actions required by landing gear (MLG) door for
(1) Alternative Methods of Compliance this AD, unless this AD specifies otherwise. discrepancies if certain messages are
(AMOCs): The Manager, International (i) Airbus Service Bulletin A300–53–0394, found, and corrective actions if
Branch, ANM–116, Transport Airplane dated February 14, 2014. necessary. AD 2013–16–09 required an
Directorate, FAA, has the authority to (ii) Airbus Service Bulletin A300–53–0395, inspection to determine airplane
approve AMOCs for this AD, if requested dated February 14, 2014.
configuration and part numbers of the
using the procedures found in 14 CFR 39.19. (iii) Airbus Service Bulletin A300–53–
6172, dated February 14, 2014. landing gear control interface unit and
In accordance with 14 CFR 39.19, send your MLG door actuators; and, for affected
request to your principal inspector or local (iv) Airbus Service Bulletin A300–53–
Flight Standards District Office, as 6174, dated February 14, 2014. airplanes, repetitive inspections of the
appropriate. If sending information directly (v) Airbus Service Bulletin A310–53–2136, opening sequence of the MLG door, and
to the International Branch, send it to ATTN: dated February 14, 2014. replacement of the MLG door actuator if
Dan Rodina, Aerospace Engineer, (vi) Airbus Service Bulletin A310–53– necessary. AD 2013–16–09 also
International Branch, ANM–116, Transport 2137, dated February 14, 2014. provided optional terminating action for
Airplane Directorate, FAA, 1601 Lind (3) For service information identified in the repetitive inspections. This new AD
Avenue SW., Renton, WA 98057–3356; this AD, contact Airbus SAS, Airworthiness
reduces the interval of the MLG door
telephone 425–227–2125; fax 425–227–1149. Office—EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; opening sequence inspection, requires
Information may be emailed to: 9-ANM-116-
AMOC-REQUESTS@faa.gov. Before using telephone +33 5 61 93 36 96; fax +33 5 61 replacing or modifying certain MLG
any approved AMOC, notify your appropriate 93 44 51; email account.airworth-eas@ door actuators, and also requires a
principal inspector, or lacking a principal airbus.com; Internet http://www.airbus.com. flushing procedure to be performed
inspector, the manager of the local flight (4) You may view this service information when installing a new MLG door
standards district office/certificate holding at the FAA, Transport Airplane Directorate, actuator. This AD was prompted by a
district office. The AMOC approval letter 1601 Lind Avenue SW., Renton, WA. For determination that the interval of the
must specifically reference this AD. information on the availability of this MLG door opening sequence inspection
Lhorne on DSK5TPTVN1PROD with RULES
(2) Contacting the Manufacturer: For any material at the FAA, call 425–227–1221.
must be reduced. We are issuing this AD
requirement in this AD to obtain corrective (5) You may view this service information
actions from a manufacturer, the action must that is incorporated by reference at the to detect and correct deterioration of the
be accomplished using a method approved National Archives and Records damping ring and associated retaining
by the Manager, International Branch, ANM– Administration (NARA). For information on ring of the MLG door actuator, which
116, Transport Airplane Directorate, FAA; or the availability of this material at NARA, call can sufficiently increase the friction
the European Aviation Safety Agency 202–741–6030, or go to: http:// inside the actuator to restrict opening of
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Document Created: 2016-03-09 00:13:42
Document Modified: 2016-03-09 00:13:42
| 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 April 13, 2016. | |
| Contact | Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. | |
| FR Citation | 81 FR 12409 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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