83 FR 5689 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 28 (February 9, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 28 (February 9, 2018)
| Page Range | 5689-5700 | |
| FR Document | 2018-01803 |
[Federal Register Volume 83, Number 28 (Friday, February 9, 2018)] [Rules and Regulations] [Pages 5689-5700] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-01803] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0713; Product Identifier 2016-NM-199-AD; Amendment 39-19170; AD 2018-02-17] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2012-12-12 and AD 2013-16-26, which applied to all Airbus Model A330-200, A330-200 Freighter, A330-300, A340-200, and A340-300 series airplanes. AD 2012- 12-12 required repetitive inspections of the outer skin rivets of the cargo doors, repair if necessary, and other repetitive inspections. AD 2013-16-26 required repetitive inspections of certain cargo doors, and repair if necessary. This new AD continues to require repetitive inspections, and repair if necessary. This new AD revises the applicability; adds a one-time inspection and adjustment of certain hook gaps; reinforcement of the door frame structure; related investigative and corrective actions if necessary; and a modification, which allows deferring reinforcement of the cargo door structure. This AD was prompted by a determination that a new inspection procedure is necessary to address the unsafe condition. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective March 16, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of March 16, 2018. ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 45 80; email: airworthiness.A330-A340@airbus.com; internet: http://www.airbus.com. You may view this referenced service information at the FAA, Transport Standards Branch, 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-2017-0713. Examining the AD Docket You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017- 0713; 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 address for the Docket Office (telephone 800- 647-5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227- 1149. SUPPLEMENTARY INFORMATION: [[Page 5690]] Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2012-12-12, Amendment 39-17092 (77 FR 37797, June 25, 2012) (``AD 2012-12-12''); and AD 2013-16-26, Amendment 39- 17564 (78 FR 53640, August 30, 2013) (``AD 2013-16-26''). AD 2012-12-12 and AD 2013-16-26 applied to all Airbus Model A330-200 series airplanes, Model A330-200 Freighter series airplanes, Model A330-300 series airplanes, Model A340-200 series airplanes, and Model A340-300 series airplanes. The NPRM published in the Federal Register on August 10, 2017 (82 FR 37360). The NPRM was prompted by a determination that a new inspection procedure is necessary to address the unsafe condition. The NPRM proposed to continue to require repetitive inspections, and repair if necessary. The NPRM also proposed to add a one-time inspection and adjustment of certain hook gaps; reinforcement of the door frame structure; related investigative and corrective actions if necessary; and a modification, which would allow deferring reinforcement of the cargo door structure. We are issuing this AD to detect and correct cracked or ruptured cargo door frames, which could result in reduced structural integrity of the forward or aft cargo door. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2016-0188, dated September 21, 2016; corrected September 22, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''); to correct an unsafe condition for certain Airbus Model A330-200 and -300 series airplanes; Model A330-200 Freighter series airplanes; and Model A340-200, -300, -500, and -600 series airplanes. The MCAI states: Several cases of cracked forward (FWD) and aft (AFT) cargo door frames, as well as loose, lost, or sheared rivets, have been reported by operators. Investigation showed that these findings are due to the low margins with respect to fatigue requirements for the AFT/FWD cargo door internal structure. Further analysis determined that the cargo door hook adjustment is a contributing factor to this issue. In case of a cracked or ruptured (FWD or AFT) cargo door frame, the loads will be transferred to the remaining structural elements. However, the secondary load path is able to sustain those loads only for a limited number of flight cycles (FC). This condition, if not detected and corrected, could lead to rupture of adjacent vertical frames and consequent reduced structural integrity of the FWD or AFT cargo door, possibly resulting in a cargo door failure, decompression of the aeroplane and injury to occupants. To initially address this potential unsafe condition, Airbus issued Service Bulletin (SB) A330-52-3043 and SB A340-52-4053 and, consequently, DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] France issued AD 2001-124(B) and AD 2001-126(B), requiring a special detailed inspection of A330 and A340 AFT cargo doors. Since those [DGAC] ADs were issued, prompted by new occurrences, Airbus issued Alert Operators Transmission (AOT) A330-52A3085, AOT A340- 52A4092, AOT A330-52A3084, AOT A340-52A4091, AOT A330-A52L003-12, AOT 340-A52L004-12, AOT A330-A52L001-12 and AOT A340-A52L002-12, providing instructions to inspect the affected areas of both FWD and AFT cargo doors. Consequently, EASA issued AD 2011-0007 (later revised) [which corresponds to FAA AD 2012-12-12], and AD 2012-0274 [which corresponds to FAA AD 2013-16-26], to require repetitive detailed visual inspections of AFT and FWD cargo doors at specific frames and outer skin at all frame fork ends. Since these EASA ADs were issued, Airbus published SB A330-52-3087, SB A330-52-3095, SB A340-52-4095, SB A340-52-4101, SB A340-52-5020 and SB A340-52-5023, which took over the instructions of the above mentioned AOTs, and introduced revised thresholds and intervals. In addition, the inspection program was expanded to A340-500/-600 aeroplanes. Taking into account experience from inspections accomplished in accordance with the applicable Airbus SBs at original issue (listed above), Airbus issued Revision 01 of these SBs. Consequently, EASA issued AD 2015-0192, which superseded EASA AD 2011-0007R1 and EASA AD 2012-0274, to require for each FWD and AFT cargo door, a one-time inspection/adjustment of the hook gaps ``U'' and ``V'', repetitive detailed inspections (DET) of all frame fork areas, frame head areas and outer skin areas to detect cracks or loose/sheared/missing fasteners, and, depending on findings, accomplishment of applicable corrective action(s). In addition, EASA AD 2015-0192 expanded the Applicability to Airbus A340-500/-600 aeroplanes. Since EASA AD 2015-0192 was issued, Airbus published Revision 02 of the inspection SBs, introducing high-frequency eddy-current inspection method for the frame forks structure. Airbus also determined that the interval for these repetitive inspections could be increased. In addition, Airbus released some modifications (mod) introducing reinforcements to the cargo door structure improving the fatigue characteristics. These modifications and associated SBs constitute terminating action for the required repetitive inspections. Furthermore, Airbus also published other SBs, introducing cold working after oversizing of the fastener holes as a means for structural reinforcement. Accomplishment of these SBs allows postponement of the required Point of Embodiment (Structural Modification Point) for the structural reinforcement modification SBs which terminate the repetitive inspection requirement. For the reasons described above, this [EASA] AD partially retains the requirements of EASA AD 2015-0192, which is superseded, and requires for each FWD and AFT cargo door initial and repetitive special detailed inspections (SDI) of all frame fork areas and detailed inspections (DET) of frame head areas and outer skin areas, and a one-time inspection/adjustment of the hook gaps ``U'' and ``V'' and, depending on findings, the accomplishment of applicable corrective action(s). Additionally, this [EASA] AD requires reinforcement of the cargo door frame structure, while accomplishment of a cold working modification allows to defer the reinforcement of the cargo door structure. It should be noted that additional inspections exist for the cargo doors, as specified in Airbus A330 ALS [Airworthiness Limitation Section] Part 2 task 523211-02-01 and task 523211-02-02, and in Airbus A340 ALS Part 2 Task 523211-02-01. This [EASA] AD is re-published to correct typographical errors when referencing Airbus SB A340-52-4118. Related investigative actions include detailed inspections and high frequency non-destructive test inspections. Corrective actions include reaming holes, bushing holes, replacing affected parts, and repairing cracks. Additional work includes a one-time inspection of the ``U'' and ``V'' hook gaps, and, if necessary, an adjustment of the hook gaps. You may examine the MCAI in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017- 0713. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Request To Allow Alternative Fastener American Airlines (AAL) asked that we allow use of an alternative fastener when doing repairs of the cargo doors. AAL stated that paragraph (l) of the proposed AD allows credit for aft cargo doors inspected in accordance with Airbus Service Bulletin A330-52-3095, Revision 01, dated July 28, 2014. AAL noted that this service information could not be accomplished due to the non-availability of fasteners having part number ``ANSA2657'' that are necessary to repair findings in the door beam 1 and 4 areas of the aft cargo door. AAL added that, as a result of this parts issue, Airbus provided Technical Advisory (TA) Reference 80016786/003/2014, Issue 03, for all affected A330 operators, which allows using an alternative HST11 series fastener; Airbus also issued Operators Information Transmission SBIT- 15-0085, dated [[Page 5691]] October 9, 2015, to identify this substitution and AALs compliance paperwork was written with this deviation added. AAL asked that this deviation to Airbus Service Bulletin A330-52-3095, Revision 01, dated July 28, 2014, be acceptable for compliance with the proposed AD. We agree with the commenter's request for the reasons provided. However, AAL transposed the part number in their comment, the correct part number is ASNA2657. We have added paragraph (s)(5) to this AD to include this exception. Request To Revise Terminating Action Requirements Delta Airlines (DAL) asked that the terminating actions specified in paragraphs (j), (n), and (o) of the proposed AD be revised. DAL stated that the actions in those paragraphs specify that doing the modification constitutes terminating action for the repetitive inspections. DAL noted that this implies that an operator must do the initial inspection prior to or concurrently with the initial requirements; and if the modification is done prior to the repetitive requirements that action would not comply with the requirements. DAL added that the terminating action should be for both the initial and repetitive inspections. We agree with the commenter's request because the intent of the terminating modification is to terminate all inspections. Although the EASA AD also specifies that the terminating action is for repetitive inspections, EASA confirmed that it applies to all inspections. Therefore, we have revised paragraphs (j), (n), and (o) of this AD to include the initial inspection as terminated actions. Request To Include a No-Reporting Provision DAL asked that a paragraph that specifically addresses that there are no reporting requirements for the inspections be included in the proposed AD. DAL stated that there are reporting instructions within the ``RC'' (Required for Compliance) Accomplishment Instructions in Airbus Service Bulletin A330-52-3087, Revision 02, including Appendix 01, dated February 18, 2016; and Airbus Service Bulletin A330-52-3095, Revision 02, including Appendices 01 and 02, dated February 19, 2016. DAL noted that operators must request an alternative method of compliance if they deviate from an RC task, so a no-reporting paragraph in the proposed AD would clarify that reporting would not be required by the proposed AD. We agree with the commenter's request because the terminating action will eliminate the unsafe condition, so reporting areas of difficulty during accomplishment of the required inspections is not necessary. We have added paragraph (r) to this AD to include a no- reporting requirement, and re-redesignated subsequent paragraphs accordingly. Request To Revise Heading Delta requested that we revise the heading for paragraph (m) of the proposed AD by removing ``For Pre-modified airplanes.'' Delta stated that paragraph (m) specifies it pertains to the modification of pre- modified airplanes. Paragraph (n) of the proposed AD specifies that accomplishing (m)(1) or (m)(3) serves as terminating action for pre- modified airplanes. However, for post-modified airplanes, paragraph (o) of the proposed AD states that paragraphs (m)(1)(i) thru (m)(1)(vi) of the proposed AD serve as terminating action--therefore, paragraph (m) serves as terminating for both pre- and modified airplanes. Delta therefore requested that we revise the heading to remove ``for pre- modified airplanes'' We agree to clarify the heading to paragraph (m) of this AD. We acknowledge that the actions for the modification accomplished by the service information in paragraph (m)(l)(i) through (m)(1)(iv) of this AD are terminating actions to the inspections required by paragraph (l)(1) and (l)(2) of this AD when accomplished on a pre- or post- modified airplane. However, the actions for the modification accomplished by the service information in paragraph (m)(1)(i) through (m)(1)(iv) of this AD are optional for post-modified airplanes, whereas, these actions are required for pre-modified airplanes. Furthermore, the requirements of paragraph (m)(2) and (m)(3) of this AD are not applicable to post-modified airplanes. For these reasons, the heading of paragraph (m) of this AD is stated as ``Modification for Pre-Modification Airplanes.'' We have not changed this AD in this regard. Request To Specify Modification Locations DAL asked that the word ``aft'' be included in the header for paragraph (k) of the proposed AD. DAL stated that this would clarify that the actions in that paragraph apply only to the aft cargo door modification. DAL added that it would also align with the headers for paragraphs (k) and (l) of the proposed AD. DAL also asked that the word ``aft'' be added to the first sentence in paragraph (n) of the proposed AD. DAL stated that this would clarify that the actions in that paragraph apply only to pre-modified aft cargo doors. In addition, DAL asked that the header for paragraph (n) of the proposed AD be revised from ``Aft Cargo Door Terminating Action'' to include ``pre-modified airplanes'' in the header. DAL stated that this would clarify that the requirements in that paragraph apply only to pre-modified aft cargo doors. We agree with the commenter's requests to include the word ``aft'' in the header for paragraph (k) and the first sentence of paragraph (n) of this AD for the reasons provided. We have included the word ``aft'' in the subject language for clarification. We agree to change the header for paragraph (n) of this AD. That header for that paragraph merely gives information about the content of the paragraph. We have changed the header for paragraph (n) of this AD accordingly. Request To Provide Credit for Certain Actions AAL asked that paragraphs (h)(2) and (l)(2) of the proposed AD be revised to provide credit for previously accomplishing the check of the forward and aft cargo door hook gaps, in accordance with Airbus Service Bulletin A330-52-3087, Revision 01, dated July 9, 2014; or Airbus Service Bulletin A330-52-3095, Revision 01, dated July 28, 2014. AAL stated that it accomplished the check in accordance with the referenced service information. We agree with the commenter's request. However, paragraphs (s)(2) and (s)(4) of this AD already provide the requested credit. Therefore, we have not changed this AD in this regard. Conclusion We reviewed the available data, including 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 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. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. [[Page 5692]] Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. The following service information describes procedures for inspecting and repairing the frame fork area at beam 4 and frame head area at beam 1 from frame 20B to frame 25 of the forward cargo door, and adjusting the hook gaps ``U'' and ``V.'' This service information is distinct since it applies to different airplane models. Service Bulletin A330-52-3087, Revision 02, including Appendix 01, dated February 18, 2016. Service Bulletin A340-52-4095, Revision 02, including Appendix 01, dated November 29, 2015. Service Bulletin A340-52-5020, Revision 02, including Appendices 01 and 02, dated November 27, 2015. The following service information describes procedures for modifying the frame fork area at beam 4 and frame head area at beam 1 from frame 20B to frame 25 of the forward cargo door frame. This service information is distinct since it applies to different airplane models and configurations. Service Bulletin A330-52-3105, dated February 24, 2016. Service Bulletin A330-52-3110, dated February 15, 2016. Service Bulletin A330-52-3111, dated February 15, 2016. Service Bulletin A340-52-4108, dated February 15, 2016. Service Bulletin A340-52-4113, dated February 15, 2016. Service Bulletin A340-52-4114, dated February 15, 2016. The following service information describes procedures for modifying the fastener holes in the forward cargo door frame structure by cold working and changing the fastener type and size. This service information is distinct since it applies to different airplane models and configurations. Service Bulletin A330-52-3116, dated April 20, 2016. Service Bulletin A330-52-3117, dated April 20, 2016. Service Bulletin A330-52-3118, dated April 20, 2016. Service Bulletin A340-52-4119, dated April 20, 2016. Service Bulletin A340-52-4120, dated April 20, 2016. Service Bulletin A340-52-4121, dated April 20, 2016. The following service information describes procedures for inspecting the frame fork area at beam 4 and frame head area at beam 1 of the aft cargo door from frame 60 to frame 64A, adjusting the hook gaps ``U'' and ``V,'' and doing corrective actions. This service information is distinct since it applies to different airplane models and configurations. Service Bulletin A330-52-3095, Revision 02, including Appendices 01 and 02, dated February 19, 2016. Service Bulletin A340-52-4101, Revision 02, including Appendices 01 and 02, dated November 27, 2015. Service Bulletin A340-52-5023, Revision 02, including Appendices 01 and 02, dated November 27, 2015. The following service information describes procedures for modifying the frame fork and head of the aft cargo door frame from frame 59A to frame 65. This service information is distinct since it applies to different airplane models and configurations. Service Bulletin A330-52-3106, dated February 24, 2016. Service Bulletin A330-52-3112, dated February 24, 2016. Service Bulletin A330-52-3113, dated February 15, 2016. Service Bulletin A330-52-3114, dated February 15, 2016. Service Bulletin A340-52-4109, dated February 25, 2016. Service Bulletin A340-52-4115, dated February 19, 2016. The following service information describes procedures for modifying the fastener holes in the aft cargo door frame structure by cold working and changing the fastener type and size. This service information is distinct since it applies to different airplane models. Service Bulletin A330-52-3115, dated April 20, 2016. Service Bulletin A340-52-4118, dated April 20, 2016. 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 73 airplanes of U.S. registry. We estimate that it takes up to 888 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts will cost up to $126,420 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be up to $14,738,700, or up to $201,900 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. 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. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. 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. 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, [[Page 5693]] 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: 0 a. Removing Airworthiness Directive (AD) 2012-12-12, Amendment 39-17092 (77 FR 37797, June 25, 2012); and AD 2013-16-26, Amendment 39-17564 (78 FR 53640, August 30, 2013); and 0 b. Adding the following new AD: 2018-02-17 Airbus: Amendment 39-19170; Docket No. FAA-2017-0713; Product Identifier 2016-NM-199-AD. (a) Effective Date This AD is effective March 16, 2018. (b) Affected ADs This AD replaces AD 2012-12-12, Amendment 39-17092 (77 FR 37797, June 25, 2012); and AD 2013-16-26, Amendment 39-17564 (78 FR 53640, August 30, 2013). (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certified in any category, all manufacturer serial numbers, except those on which Airbus Modification 202702 and Modification 202790 have been embodied in production; and the Airbus airplanes identified in paragraphs (c)(3) through (c)(5) of this AD, certified in any category, all manufacturer serial numbers. (1) Model A330-201, -202, -203, -223, -223F, -243, and -243F airplanes. (2) Model A330-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes. (3) Model A340-211, -212, and -213 airplanes. (4) Model A340-311, -312, and -313 airplanes. (5) Model A340-541 and -642 airplanes. (d) Subject Air Transport Association (ATA) of America Code 52, Doors. (e) Reason This AD was prompted by reports of cracked forward and aft cargo door frames, and loose, missing, or sheared rivets. We are issuing this AD to detect and correct cracked or ruptured cargo door frames, which could result in reduced structural integrity of the forward or aft cargo door. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Affected Cargo Doors For the purpose of this AD, the affected cargo doors are pre- modification 202702 (forward cargo door) and pre-modification 202790 (aft cargo door), and are listed by part number (P/N) in the applicable service information identified in paragraph (h)(1) or (l)(1) of this AD. For post-modification doors, which are not affected by this AD, the P/Ns are identified as F52370900XXX (forward cargo door) and F52372315XXX (aft cargo door), where ``XXX'' can be a combination of any three numerical digits. (h) Forward Cargo Door Repetitive Inspections (1) Before exceeding 5,300 total flight cycles since first installation of the forward cargo door on an airplane, or within the applicable compliance time specified in table 1 to paragraph (h)(1) of this AD, whichever occurs later, except as specified in paragraph (q) of this AD: Do all applicable detailed and high frequency eddy current (HFEC) inspections of all frame fork areas, frame head areas, and outer skin areas of each affected forward cargo door, as applicable; in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (h)(1)(i), (h)(1)(ii), or (h)(1)(iii) of this AD. Do all applicable related investigative actions and corrective actions before further flight in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (h)(1)(i), (h)(1)(ii), or (h)(1)(iii) of this AD, except as required by paragraph (p) of this AD. Repeat the applicable inspections of the frame fork areas, frame head areas, and outer skin areas of each affected forward cargo door thereafter at intervals not to exceed 1,400 flight cycles. BILLING CODE 4910-13-P [[Page 5694]] [GRAPHIC] [TIFF OMITTED] TR09FE18.000 [[Page 5695]] [GRAPHIC] [TIFF OMITTED] TR09FE18.001 BILLING CODE 4910-13-C (i) Airbus Service Bulletin A330-52-3087, Revision 02, including Appendix 01, dated February 18, 2016 (``SB A330-52-3087, R02''). (ii) Airbus Service Bulletin A340-52-4095, Revision 02, including Appendix 01, dated November 29, 2015 (``SB A340-52-4095, R02''). (iii) Airbus Service Bulletin A340-52-5020, Revision 02, including Appendices 01 and 02, dated November 27, 2015 (``SB A340- 52-5020, R02''). (2) Concurrently with the first inspection required by paragraph (h)(1) of this AD: Do a one-time detailed inspection of the hook gaps ``U'' and ``V'' of each affected forward cargo door for proper adjustment, and, depending on findings, adjust the hook(s), in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (h)(2)(i), (h)(2)(ii), or (h)(2)(iii) of this AD. Do all the required hook gap adjustments before further flight. (i) SB A330-52-3087, R02. (ii) SB A340-52-4095, R02. (iii) SB A340-52-5020, R02. (i) Forward Cargo Door Modification (1) Except as specified in paragraph (i)(2) of this AD, before exceeding 18,500 total flight cycles since first installation of the forward cargo door on an airplane, or within 12 months after the effective date of this AD, whichever occurs later: Do reinforcement modifications on the frame structure of each affected forward cargo door, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (i)(1)(i) through (i)(1)(vi) of this AD, except as required by paragraph (p) of this AD. (i) Airbus Service Bulletin A330-52-3105, dated February 24, 2016 (for certain Model A330-202, -223, and -243 airplanes; and Model A330-301, -321, -322, -341, and -342 airplanes). (ii) Airbus Service Bulletin A330-52-3110, dated February 15, 2016 (for certain Model A330-202, -203, -223, and -243 airplanes; and Model A330-303, -323, and -343 airplanes). (iii) Airbus Service Bulletin A330-52-3111, dated February 15, 2016 (for certain Model A330-202, -203, -223, -223F, -243, and -243F airplanes; and Model A330-302, -303, -323, -342, and -343 airplanes). (iv) Airbus Service Bulletin A340-52-4108, dated February 15, 2016 (for certain Model A340-211, -212, and -213 airplanes; and Model A340-311, -312, and -313 airplanes). (v) Airbus Service Bulletin A340-52-4113, dated February 15, 2016 (for certain Model A340-312 and -313 airplanes). (vi) Airbus Service Bulletin A340-52-4114, dated February 15, 2016 (for certain Model A340-313 airplanes). (2) Accomplishment of the reinforcement modifications required by paragraph (i)(1) of this AD may be deferred, provided that, before exceeding 18,500 total flight cycles since first installation of the forward cargo door on an airplane, or within 12 months after the effective date of this AD, whichever occurs later, but not earlier than 14,500 total flight cycles for Model A330 airplanes, or 12,500 total flight cycles for Model A340 airplanes, cold working is accomplished on the frame structure of each affected forward cargo door, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (i)(2)(i) through (i)(2)(vi) of this AD, except as required by paragraph (p) of this AD. Modification of an airplane by accomplishment of the cold working specified in this paragraph does not constitute terminating action for the repetitive inspections required by paragraph (h)(1) of this AD. (i) Airbus Service Bulletin A330-52-3116, dated April 20, 2016 (for certain Model A330-202, -223, and -243 airplanes; and Model A330-301, -321, -322, -341, and -342 airplanes). (ii) Airbus Service Bulletin A330-52-3117, dated April 20, 2016 (for certain Model A330-202, -203, -223, and -243 airplanes; and Model A330-303, -323, and -343 airplanes). (iii) Airbus Service Bulletin A330-52-3118, dated April 20, 2016 (for certain Model A330-202, -203, -223, -223F, -243, and -243F airplanes; and Model A330-302, -303, -323, -342, and -343 airplanes). (iv) Airbus Service Bulletin A340-52-4119, dated April 20, 2016 (for certain Model A340-211, -212, and -213 airplanes; and Model A340-311, -312, and -313 airplanes). (v) Airbus Service Bulletin A340-52-4120, dated April 20, 2016 (for certain Model A340-312 and -313 airplanes). (vi) Airbus Service Bulletin A340-52-4121, dated April 20, 2016 (for certain Model A340-313 airplanes). (3) Within 18,500 flight cycles after cold working is accomplished on the frame structure of each affected forward cargo door as specified in paragraph (i)(2) of this AD: Do the reinforcement modifications on the frame structure of each affected forward cargo door, using a method approved by the Manager, International Section, Transport Standards Branch, 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. (j) Forward Cargo Door Terminating Action Modification of an airplane by reinforcement of the forward cargo door frame structure required by paragraph (i)(1) or (i)(3) of this AD constitutes terminating action for the inspections required by paragraph (h)(1) and (h)(2) of this AD for that airplane. (k) Definitions of Pre-Modified and Post-Modified Airplanes of Aft Cargo Door (1) For the purpose of this AD, pre-modified Model A330-200 series airplanes, Model A330-200 Freighter series airplanes, Model A330-300 series airplanes, Model A340-200 series airplanes, and Model A340-300 series airplanes are defined as those not having Airbus Modification 44852, or Modification 44854 applied in production, or being in pre-Airbus Service Bulletin A330-52-3044 or pre-Airbus Service Bulletin A340-52-4054 configuration, as applicable. (2) For the purpose of this AD, post-modification Model A330-200 series airplanes, Model A330-200 Freighter series airplanes, Model A330-300 series airplanes, Model A340-200 series airplanes, and Model A340-300 series airplanes are defined as those having Airbus Modification 44852 or Modification 44854 applied in production, or modified in service as specified in Airbus Service Bulletin A330-52- 3044 or Airbus [[Page 5696]] Service Bulletin A340-52-4054, as applicable. (l) Aft Cargo Door Repetitive Inspections (1) Before exceeding 4,000 total flight cycles for pre-modified airplanes, or 12,000 total flight cycles for post-modified airplanes, since first installation of the aft cargo door on an airplane, as applicable, or within the compliance time specified in table 2 to paragraph (l)(1) of this AD or table 3 to paragraph (l)(1) of this AD, as applicable, whichever occurs later, except as specified in paragraph (q) of this AD: Do all applicable inspections of all frame fork areas, frame head areas, and outer skin area of each affected aft cargo door, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (l)(1)(i), (l)(1)(ii), or (l)(1)(iii) of this AD. Do all applicable related investigative actions and corrective actions before further flight in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (l)(1)(i), (l)(1)(ii), or (l)(1)(iii) of this AD, except as required by paragraph (p) of this AD. Repeat the applicable inspections thereafter at intervals not to exceed 1,400 flight cycles. BILLING CODE 4910-13-P [[Page 5697]] [GRAPHIC] [TIFF OMITTED] TR09FE18.002 [[Page 5698]] [GRAPHIC] [TIFF OMITTED] TR09FE18.003 BILLING CODE 4910-13-C (i) Airbus Service Bulletin A330-52-3095, Revision 02, including Appendices 01 and 02, dated February 19, 2016 (``SB A330-52-3095, R02''). (ii) Airbus Service Bulletin A340-52-4101, Revision 02, including Appendices 01 and 02, dated November 27, 2015 (``SB A340- 52-4101, R02''). (iii) Airbus Service Bulletin A340-52-5023, Revision 02, including Appendices 01 and 02, dated November 27, 2015 (``SB A340- 52-5023, R02''). [[Page 5699]] (2) Concurrently with the first inspection required by paragraph (l)(1) of this AD: Do a one-time detailed inspection of the hook gaps ``U'' and ``V'' of each affected aft cargo door for proper adjustment and, depending on findings, adjust the hook(s) in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (l)(2)(i), (l)(2)(ii), or (l)(2)(iii) of this AD. Do all the required hook gap adjustments before further flight. (i) SB A330-52-3095, R02. (ii) SB A340-52-4101, R02. (iii) SB A340-52-5023, R02. (m) Modification for Pre-Modified Airplanes (1) For pre-modified airplanes, except as specified in paragraph (m)(2) of this AD: Before exceeding 18,500 total flight cycles since first installation of the aft cargo door on an airplane, or within 12 months after the effective date of this AD, whichever occurs later, do reinforcement modifications, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (m)(1)(i) through (m)(1)(vi) of this AD, except as required by paragraph (p) of this AD. (i) Airbus Service Bulletin A330-52-3106, dated February 24, 2016 (for certain Model A330-301, -321, -322, -341, and -342 airplanes). (ii) Airbus Service Bulletin A330-52-3112, dated February 24, 2016 (for certain Model A330-202 and -223 airplanes; and Model A330- 301, -322, -341, and -342 airplanes). (iii) Airbus Service Bulletin A330-52-3113, dated February 15, 2016 (for certain Model A330-223 and -243 airplanes; and Model A330- 322 and -342 airplanes). (iv) Airbus Service Bulletin A330-52-3114, dated February 15, 2016 (for certain Model A330-202, -203, -223, -223F, -243, and -243F airplanes; and Model A330-302, -303, -323, -342, and -343 airplanes). (v) Airbus Service Bulletin A340-52-4109, dated February 25, 2016 (for certain Model A340-211, -212, and -213 airplanes; and Model A340-311, -312, and -313 airplanes). (vi) Airbus Service Bulletin A340-52-4115, dated February 19, 2016 (for certain Model A340-212, -213, and -313 airplanes). (2) Accomplishment of the reinforcement modifications required by paragraph (m)(1) of this AD may be deferred provided that before exceeding 18,500 total flight cycles since first installation of the aft cargo door on an airplane, or within 12 months after the effective date of this AD, whichever occurs later, but not earlier than 14,500 total flight cycles, cold working is accomplished on the frame structure of each affected aft cargo door, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-52- 3115, dated April 20, 2016; or Airbus Service Bulletin A340-52-4118, dated April 20, 2016; as applicable. Modification of an airplane by accomplishment of the cold working specified in this paragraph does not constitute terminating action for the repetitive inspections required by paragraph (l)(1) of this AD. (3) For an airplane on which the cold working on the cargo door frame structure is accomplished, as specified in paragraph (m)(2) of this AD: Within 18,500 flight cycles after the application of cold working, do reinforcement modifications, in accordance with the Accomplishment Instructions of the service information specified in paragraphs (m)(1)(i) through (m)(1)(vi) of this AD, as applicable, or using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (n) Terminating Action Aft Cargo Doors for Pre-Modified Airplanes Modification of an airplane by reinforcement of the aft cargo door frame structure required by paragraph (m)(1) or (m)(3) of this AD constitutes terminating action for the inspections required by paragraph (l)(1) and (l)(2) of this AD for that airplane. (o) Optional Terminating Action Modification for Post-Modified Airplanes For post-modified airplanes, modification of an airplane by reinforcement of the aft cargo door frame structure, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraphs (m)(1)(i) through (m)(1)(vi) of this AD, or using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA, constitutes terminating action for the inspections required by paragraph (l)(1) and (l)(2) of this AD for that airplane. If approved by the DOA, the approval must include the DOA-authorized signature. (p) Exceptions to Service Information Where the service information specified in paragraphs (h)(1), (i)(1), (i)(2), (l)(1), and (m) of this AD specifies to contact Airbus for instructions or repair, before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (t)(2) of this AD. (q) Exception to Initial Inspection Compliance Time For the purposes of table 1 to paragraph (h)(1) of this AD, table 2 to paragraph (l)(1) of this AD, and table 3 to paragraph (l)(1) of this AD: As soon as a cargo door is inspected using any applicable service information specified in this AD, the previous inspections accomplished in accordance with any alert operator transmission can be disregarded for the determination of the compliance time for the initial inspection required by this AD. (r) Exception to Reporting in the Service Information Although the Airbus service bulletins specified in paragraphs (r)(1) through (r)(6) of this AD specify to submit certain information to the manufacturer, and specify that action as ``RC'' (Required for Compliance), this AD does not include that requirement. (1) SB A330-52-3087, R02. (2) SB A330-52-3095, R02. (3) SB A340-52-4095, R02. (4) SB A340-52-4101, R02. (5) SB A340-52-5020, R02. (6) SB A340-52-5023, R02. (s) Credit for Previous Actions (1) This paragraph provides credit for the initial inspection required by paragraph (h) of this AD, if that inspection was performed before the effective date of this AD using Airbus Service Bulletin A330-52-3087, dated August 29, 2013; Airbus Service Bulletin A340-52-4095, dated August 29, 2013; or Airbus Service Bulletin A340-52-5020, dated August 29, 2013; as applicable; provided that the actions identified as ``additional work'' in the Accomplishment Instructions of Airbus Service Bulletin A330-52-3087, Revision 01, dated July 9, 2014; Airbus Service Bulletin A340-52- 4095, Revision 01, dated July 28, 2014; or Airbus Service Bulletin A340-52-5020, Revision 01, dated July 9, 2014; as applicable; are accomplished within 1,100 flight cycles after that inspection; and provided the next inspection of all frame fork areas, frame head areas, and outer skin area of each affected forward cargo door is accomplished within 1,100 flight cycles after that inspection, in accordance with the Accomplishment Instructions of SB A330-52-3087, R02; SB A340-52-4095, R02; or SB A340-52-5020, R02, as applicable. (2) This paragraph provides credit for the initial inspection required by paragraph (h) of this AD, if that inspection was performed before the effective date of this AD using Airbus Service Bulletin A330-52-3087, Revision 01, dated July 9, 2014; Airbus Service Bulletin A340-52-4095, Revision 01, dated July 28, 2014; or Airbus Service Bulletin A340-52-5020, Revision 01, dated July 9, 2014; as applicable; provided that the next inspection of all frame fork areas, frame head areas, and outer skin area of each affected forward cargo door, is accomplished within 1,100 flight cycles after that inspection in accordance with the Accomplishment Instructions of SB A330-52-3087, R02; SB A340-52-4095, R02; or SB A340-52-5020, R02, as applicable. (3) This paragraph provides credit for the initial inspection required by paragraph (l) of this AD, if that inspection was performed before the effective date of this AD using Airbus Service Bulletin A330-52-3095, dated August 29, 2013; Airbus Service Bulletin A340-52-4101, dated August 29, 2013; or Airbus Service Bulletin A340-52-5023, dated August 29, 2013; provided that the actions identified as ``additional work'' in the Accomplishment Instructions of Airbus Service Bulletin A330-52-3095, Revision 01, dated July 28, 2014; Airbus Service Bulletin A340-52-4101, Revision 01, dated July 28, 2014; or Airbus Service Bulletin A340-52-5023, Revision 01, dated July 28, 2014; as applicable; are accomplished within 550 flight cycles after that inspection, and provided the next inspection of all frame fork areas, frame head areas, and outer skin area of each affected aft cargo door is accomplished within 550 flight cycles after that inspection in accordance with the Accomplishment Instructions of SB A330-52-3095, R02; SB A340-52- 4101, R02; or SB A340-52-5023, R02, as applicable. (4) This paragraph provides credit for the initial inspection required by paragraph (l) of this AD, if that inspection was performed before the effective date of this AD using [[Page 5700]] Airbus Service Bulletin A330-52-3095, Revision 01, dated July 28, 2014; Airbus Service Bulletin A340-52-4101, Revision 01, dated July 28, 2014; or Airbus Service Bulletin A340-52-5023, Revision 01, dated July 28, 2014; as applicable; provided that the next inspection of all frame fork areas, frame head areas, and outer skin area of each affected aft cargo door is accomplished within 550 flight cycles after that inspection in accordance with the Accomplishment Instructions of SB A330-52-3095, R02; SB A340-52- 4101, R02; or SB A340-52-5023, R02, as applicable. (5) Where Airbus Service Bulletins A330-52-3095, Revision 01, dated July 28, 2014; A340-52-4101, Revision 01, dated July 28, 2014; A340-52-5020, Revision 01, dated July 9, 2014; and A340-52-5023, Revision 01, dated July 28, 2014; refers to using fasteners having P/N ASNA2657, this AD also allows the use of alternative HST11 series fasteners. (t) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, 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 manager of the certification office, send it to the attention of the person identified in paragraph (u)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: As of the effective date of this AD, 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 Section, Transport Standards Branch, FAA; or the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as required by paragraph (p) of this AD: If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (u) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016-0188, dated September 21, 2016; corrected September 22, 2016, 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-2017-0713. (2) For more information about this AD, contact Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (v)(4) and (v)(5) of this AD. (v) 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 A330-52-3087, Revision 02, including Appendix 01, dated February 18, 2016. (ii) Airbus Service Bulletin A330-52-3095, Revision 02, including Appendices 01 and 02, dated February 19, 2016. (iii) Airbus Service Bulletin A330-52-3105, dated February 15, 2016. (iv) Airbus Service Bulletin A330-52-3106, dated February 24, 2016. (v) Airbus Service Bulletin A330-52-3110, dated February 15, 2016. (vi) Airbus Service Bulletin A330-52-3111, dated February 15, 2016. (vii) Airbus Service Bulletin A330-52-3112, dated February 24, 2016. (viii) Airbus Service Bulletin A330-52-3113, dated February 15, 2016. (ix) Airbus Service Bulletin A330-52-3114, dated February 15, 2016. (x) Airbus Service Bulletin A330-52-3115, dated April 20, 2016. (xi) Airbus Service Bulletin A330-52-3116, dated April 20, 2016. (xii) Airbus Service Bulletin A330-52-3117, dated April 20, 2016. (xiii) Airbus Service Bulletin A330-52-3118, dated April 20, 2016. (xiv) Airbus Service Bulletin A340-52-4095, Revision 02, including Appendix 01, dated November 27, 2015. (xv) Airbus Service Bulletin A340-52-4101, Revision 02, including Appendices 01 and 02, dated November 27, 2015. (xvi) Airbus Service Bulletin A340-52-4108, dated February 15, 2016. (xvii) Airbus Service Bulletin A340-52-4109, dated February 25, 2016. (xviii) Airbus Service Bulletin A340-52-4113, dated February 15, 2016. (xix) Airbus Service Bulletin A340-52-4114, dated February 15, 2016. (xx) Airbus Service Bulletin A340-52-4115, dated February 19, 2016. (xxi) Airbus Service Bulletin A340-52-4118, dated April 20, 2016. (xxii) Airbus Service Bulletin A340-52-4119, dated April 20, 2016. (xxiii) Airbus Service Bulletin A340-52-4120, dated April 20, 2016. (xxiv) Airbus Service Bulletin A340-52-4121, dated April 20, 2016. (xxv) Airbus Service Bulletin A340-52-5020, Revision 02, including Appendices 01 and 02, dated November 27, 2015. (xxvi) Airbus Service Bulletin A340-52-5023, Revision 02, including Appendices 01 and 02, dated November 27, 2015. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 45 80; email: airworthiness.A330-A340@airbus.com; internet: http://www.airbus.com. (4) You may view this service information at the FAA, Transport Standards Branch, 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 January 11, 2018. John P. Piccola, Jr., Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-01803 Filed 2-8-18; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 83, No. 28 / Friday, February 9, 2018 / Rules and Regulations 5689
(i) Optional Terminating Action for (IBR) of the service information listed in this the applicability; adds a one-time
Repetitive Inspections paragraph under 5 U.S.C. 552(a) and 1 CFR inspection and adjustment of certain
Accomplishment of ‘‘PART 5: CLEANING part 51. hook gaps; reinforcement of the door
AND NEUTRALIZATION,’’ as specified in (2) You must use this service information
as applicable to do the actions required by
frame structure; related investigative
the Accomplishment Instructions of Boeing and corrective actions if necessary; and
Alert Service Bulletin 777–53A0083, dated this AD, unless the AD specifies otherwise.
(i) Boeing Alert Service Bulletin 777– a modification, which allows deferring
April 20, 2017, terminates the repetitive
inspections required by paragraph (g) of this 53A0083, dated April 20, 2017. reinforcement of the cargo door
AD. (ii) Reserved. structure. This AD was prompted by a
(3) For service information identified in determination that a new inspection
(j) Alternative Methods of Compliance this AD, contact Boeing Commercial
(AMOCs)
procedure is necessary to address the
Airplanes, Attention: Contractual & Data
unsafe condition. We are issuing this
(1) The Manager, Seattle ACO Branch, Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600; AD to address the unsafe condition on
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures telephone: 562–797–1717; internet: https:// these products.
found in 14 CFR 39.19. In accordance with www.myboeingfleet.com. DATES: This AD is effective March 16,
14 CFR 39.19, send your request to your (4) You may view this service information
at the FAA, Transport Standards Branch,
2018. The Director of the Federal
principal inspector or local Flight Standards
District Office, as appropriate. If sending 1601 Lind Avenue SW, Renton, WA. For Register approved the incorporation by
information directly to the manager of the information on the availability of this reference of certain publications listed
certification office, send it to the attention of material at the FAA, call 425–227–1221. in this AD as of March 16, 2018.
the person identified in paragraph (k) of this (5) You may view this service information
AD. Information may be emailed to: 9-ANM- that is incorporated by reference at the ADDRESSES: For service information
Seattle-ACO-AMOC-Requests@faa.gov. National Archives and Records identified in this final rule, contact
(2) Before using any approved AMOC, Administration (NARA). For information on Airbus SAS, Airworthiness Office—
notify your appropriate principal inspector, the availability of this material at NARA, call EAL, 1 Rond Point Maurice Bellonte,
or lacking a principal inspector, the manager 202–741–6030, or go to: http:// 31707 Blagnac Cedex, France;
of the local flight standards district office/ www.archives.gov/federal-register/cfr/ibr- telephone: +33 5 61 93 36 96; fax: +33
certificate holding district office. locations.html. 5 61 93 45 80; email:
(3) An AMOC that provides an acceptable
Issued in Renton, Washington, on January airworthiness.A330-A340@airbus.com;
level of safety may be used for any repair,
19, 2018. internet: http://www.airbus.com. You
modification, or alteration required by this
AD if it is approved by the Boeing Michael Kaszycki, may view this referenced service
Commercial Airplanes Organization Acting Director, System Oversight Division, information at the FAA, Transport
Designation Authorization (ODA) that has Aircraft Certification Service. Standards Branch, 1601 Lind Avenue
been authorized by the Manager, Seattle ACO [FR Doc. 2018–01807 Filed 2–8–18; 8:45 am] SW, Renton, WA. For information on
Branch, to make those findings. To be BILLING CODE 4910–13–P the availability of this material at the
approved, the repair method, modification FAA, call 425–227–1221. It is also
deviation, or alteration deviation must meet
the certification basis of the airplane, and the available on the internet at http://
DEPARTMENT OF TRANSPORTATION www.regulations.gov by searching for
approval must specifically refer to this AD.
(4) Except as required by paragraphs (h)(2) and locating Docket No. FAA–2017–
Federal Aviation Administration 0713.
and (h)(3) of this AD: For service information
that contains steps that are labeled as
Required for Compliance (RC), the provisions 14 CFR Part 39 Examining the AD Docket
of paragraphs (j)(4)(i) and (j)(4)(ii) of this AD [Docket No. FAA–2017–0713; Product
apply. You may examine the AD docket on
Identifier 2016–NM–199–AD; Amendment the internet at http://
(i) The steps labeled as RC, including 39–19170; AD 2018–02–17]
substeps under an RC step and any figures www.regulations.gov by searching for
identified in an RC step, must be done to RIN 2120–AA64 and locating Docket No. FAA–2017–
comply with the AD. If a step or substep is 0713; or in person at the Docket
labeled ‘‘RC Exempt,’’ then the RC Airworthiness Directives; Airbus Management Facility between 9 a.m.
requirement is removed from that step or Airplanes and 5 p.m., Monday through Friday,
substep. An AMOC is required for any
AGENCY: Federal Aviation except Federal holidays. The AD docket
deviations to RC steps, including substeps
and identified figures. Administration (FAA), Department of contains this AD, the regulatory
(ii) Steps not labeled as RC may be Transportation (DOT). evaluation, any comments received, and
deviated from using accepted methods in other information. The address for the
ACTION: Final rule.
accordance with the operator’s maintenance Docket Office (telephone 800–647–5527)
or inspection program without obtaining SUMMARY: We are superseding is Docket Management Facility, U.S.
approval of an AMOC, provided the RC steps, Airworthiness Directive (AD) 2012–12– Department of Transportation, Docket
including substeps and identified figures, can Operations, M–30, West Building
12 and AD 2013–16–26, which applied
still be done as specified, and the airplane Ground Floor, Room W12–140, 1200
can be put back in an airworthy condition. to all Airbus Model A330–200, A330–
200 Freighter, A330–300, A340–200, New Jersey Avenue SE, Washington, DC
(k) Related Information and A340–300 series airplanes. AD 20590.
For more information about this AD, 2012–12–12 required repetitive FOR FURTHER INFORMATION CONTACT:
contact Eric Lin, Aerospace Engineer, inspections of the outer skin rivets of Vladimir Ulyanov, Aerospace Engineer,
sradovich on DSK3GMQ082PROD with RULES
Airframe Section, FAA, Seattle ACO Branch, the cargo doors, repair if necessary, and
1601 Lind Avenue SW, Renton, WA 98057– International Section, Transport
other repetitive inspections. AD 2013–
3356; phone: 425–917–6412; fax: 425–917– Standards Branch, FAA, 1601 Lind
16–26 required repetitive inspections of
6590; email: eric.lin@faa.gov. Avenue SW, Renton, WA 98057–3356;
certain cargo doors, and repair if
(l) Material Incorporated by Reference
telephone 425–227–1138; fax 425–227–
necessary. This new AD continues to
1149.
(1) The Director of the Federal Register require repetitive inspections, and
approved the incorporation by reference repair if necessary. This new AD revises SUPPLEMENTARY INFORMATION:
VerDate Sep<11>2014 15:59 Feb 08, 2018 Jkt 244001 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 E:\FR\FM\09FER1.SGM 09FER1](https://thefederalregister.org/doc/83_FR_5717/page/1.svg)
![5690 Federal Register / Vol. 83, No. 28 / Friday, February 9, 2018 / Rules and Regulations
Discussion failure, decompression of the aeroplane and For the reasons described above, this
injury to occupants. [EASA] AD partially retains the requirements
We issued a notice of proposed To initially address this potential unsafe of EASA AD 2015–0192, which is
rulemaking (NPRM) to amend 14 CFR condition, Airbus issued Service Bulletin superseded, and requires for each FWD and
part 39 to supersede AD 2012–12–12, (SB) A330–52–3043 and SB A340–52–4053 AFT cargo door initial and repetitive special
Amendment 39–17092 (77 FR 37797, and, consequently, DGAC [Direction detailed inspections (SDI) of all frame fork
June 25, 2012) (‘‘AD 2012–12–12’’); and Générale de l’Aviation Civile] France issued areas and detailed inspections (DET) of frame
AD 2013–16–26, Amendment 39–17564 AD 2001–124(B) and AD 2001–126(B), head areas and outer skin areas, and a one-
(78 FR 53640, August 30, 2013) (‘‘AD requiring a special detailed inspection of time inspection/adjustment of the hook gaps
2013–16–26’’). AD 2012–12–12 and AD A330 and A340 AFT cargo doors. Since those ‘‘U’’ and ‘‘V’’ and, depending on findings, the
[DGAC] ADs were issued, prompted by new accomplishment of applicable corrective
2013–16–26 applied to all Airbus Model occurrences, Airbus issued Alert Operators action(s). Additionally, this [EASA] AD
A330–200 series airplanes, Model Transmission (AOT) A330–52A3085, AOT requires reinforcement of the cargo door
A330–200 Freighter series airplanes, A340–52A4092, AOT A330–52A3084, AOT frame structure, while accomplishment of a
Model A330–300 series airplanes, A340–52A4091, AOT A330–A52L003–12, cold working modification allows to defer the
Model A340–200 series airplanes, and AOT 340–A52L004–12, AOT A330– reinforcement of the cargo door structure.
Model A340–300 series airplanes. The A52L001–12 and AOT A340–A52L002–12, It should be noted that additional
NPRM published in the Federal providing instructions to inspect the affected inspections exist for the cargo doors, as
Register on August 10, 2017 (82 FR areas of both FWD and AFT cargo doors. specified in Airbus A330 ALS [Airworthiness
Consequently, EASA issued AD 2011–0007 Limitation Section] Part 2 task 523211–02–01
37360). The NPRM was prompted by a (later revised) [which corresponds to FAA and task 523211–02–02, and in Airbus A340
determination that a new inspection AD 2012–12–12], and AD 2012–0274 [which ALS Part 2 Task 523211–02–01.
procedure is necessary to address the corresponds to FAA AD 2013–16–26], to This [EASA] AD is re-published to correct
unsafe condition. The NPRM proposed require repetitive detailed visual inspections typographical errors when referencing Airbus
to continue to require repetitive of AFT and FWD cargo doors at specific SB A340–52–4118.
inspections, and repair if necessary. The frames and outer skin at all frame fork ends.
Related investigative actions include
NPRM also proposed to add a one-time Since these EASA ADs were issued, Airbus
published SB A330–52–3087, SB A330–52– detailed inspections and high frequency
inspection and adjustment of certain non-destructive test inspections.
hook gaps; reinforcement of the door 3095, SB A340–52–4095, SB A340–52–4101,
SB A340–52–5020 and SB A340–52–5023, Corrective actions include reaming
frame structure; related investigative which took over the instructions of the above holes, bushing holes, replacing affected
and corrective actions if necessary; and mentioned AOTs, and introduced revised parts, and repairing cracks. Additional
a modification, which would allow thresholds and intervals. In addition, the work includes a one-time inspection of
deferring reinforcement of the cargo inspection program was expanded to A340– the ‘‘U’’ and ‘‘V’’ hook gaps, and, if
door structure. We are issuing this AD 500/–600 aeroplanes. Taking into account necessary, an adjustment of the hook
to detect and correct cracked or experience from inspections accomplished in
gaps.
ruptured cargo door frames, which accordance with the applicable Airbus SBs at
original issue (listed above), Airbus issued
You may examine the MCAI in the
could result in reduced structural AD docket on the internet at http://
integrity of the forward or aft cargo Revision 01 of these SBs.
Consequently, EASA issued AD 2015– www.regulations.gov by searching for
door. 0192, which superseded EASA AD 2011– and locating Docket No. FAA–2017–
The European Aviation Safety Agency 0007R1 and EASA AD 2012–0274, to require 0713.
(EASA), which is the Technical Agent for each FWD and AFT cargo door, a one-
for the Member States of the European time inspection/adjustment of the hook gaps Comments
Union, has issued EASA AD 2016–0188, ‘‘U’’ and ‘‘V’’, repetitive detailed inspections We gave the public the opportunity to
dated September 21, 2016; corrected (DET) of all frame fork areas, frame head participate in developing this AD. The
September 22, 2016 (referred to after areas and outer skin areas to detect cracks or following presents the comments
this as the Mandatory Continuing loose/sheared/missing fasteners, and, received on the NPRM and the FAA’s
Airworthiness Information, or ‘‘the depending on findings, accomplishment of
applicable corrective action(s). In addition,
response to each comment.
MCAI’’); to correct an unsafe condition
EASA AD 2015–0192 expanded the Request To Allow Alternative Fastener
for certain Airbus Model A330–200 and Applicability to Airbus A340–500/–600
–300 series airplanes; Model A330–200 aeroplanes. American Airlines (AAL) asked that
Freighter series airplanes; and Model Since EASA AD 2015–0192 was issued, we allow use of an alternative fastener
A340–200, –300, –500, and –600 series Airbus published Revision 02 of the when doing repairs of the cargo doors.
airplanes. The MCAI states: inspection SBs, introducing high-frequency AAL stated that paragraph (l) of the
Several cases of cracked forward (FWD) eddy-current inspection method for the frame proposed AD allows credit for aft cargo
and aft (AFT) cargo door frames, as well as forks structure. Airbus also determined that doors inspected in accordance with
loose, lost, or sheared rivets, have been the interval for these repetitive inspections Airbus Service Bulletin A330–52–3095,
reported by operators. Investigation showed could be increased. In addition, Airbus
Revision 01, dated July 28, 2014. AAL
that these findings are due to the low margins released some modifications (mod)
introducing reinforcements to the cargo door noted that this service information
with respect to fatigue requirements for the could not be accomplished due to the
AFT/FWD cargo door internal structure. structure improving the fatigue
Further analysis determined that the cargo characteristics. These modifications and non-availability of fasteners having part
door hook adjustment is a contributing factor associated SBs constitute terminating action number ‘‘ANSA2657’’ that are necessary
to this issue. In case of a cracked or ruptured for the required repetitive inspections. to repair findings in the door beam 1
(FWD or AFT) cargo door frame, the loads Furthermore, Airbus also published other and 4 areas of the aft cargo door. AAL
will be transferred to the remaining structural SBs, introducing cold working after added that, as a result of this parts issue,
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elements. However, the secondary load path oversizing of the fastener holes as a means for Airbus provided Technical Advisory
is able to sustain those loads only for a structural reinforcement. Accomplishment of
(TA) Reference 80016786/003/2014,
limited number of flight cycles (FC). these SBs allows postponement of the
required Point of Embodiment (Structural Issue 03, for all affected A330 operators,
This condition, if not detected and
corrected, could lead to rupture of adjacent Modification Point) for the structural which allows using an alternative
vertical frames and consequent reduced reinforcement modification SBs which HST11 series fastener; Airbus also
structural integrity of the FWD or AFT cargo terminate the repetitive inspection issued Operators Information
door, possibly resulting in a cargo door requirement. Transmission SBIT–15–0085, dated
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![Federal Register / Vol. 83, No. 28 / Friday, February 9, 2018 / Rules and Regulations 5693
the FAA amends 14 CFR part 39 as Modification 202790 have been embodied in information identified in paragraph (h)(1) or
follows: production; and the Airbus airplanes (l)(1) of this AD. For post-modification doors,
identified in paragraphs (c)(3) through (c)(5) which are not affected by this AD, the P/Ns
PART 39—AIRWORTHINESS of this AD, certified in any category, all are identified as F52370900XXX (forward
DIRECTIVES manufacturer serial numbers. cargo door) and F52372315XXX (aft cargo
(1) Model A330–201, –202, –203, –223, door), where ‘‘XXX’’ can be a combination of
■ 1. The authority citation for part 39 –223F, –243, and –243F airplanes. any three numerical digits.
continues to read as follows: (2) Model A330–301, –302, –303, –321,
–322, –323, –341, –342, and –343 airplanes. (h) Forward Cargo Door Repetitive
Authority: 49 U.S.C. 106(g), 40113, 44701. (3) Model A340–211, –212, and –213 Inspections
airplanes. (1) Before exceeding 5,300 total flight
§ 39.13 [Amended] (4) Model A340–311, –312, and –313 cycles since first installation of the forward
■ 2. The FAA amends § 39.13 by: airplanes. cargo door on an airplane, or within the
■ a. Removing Airworthiness Directive (5) Model A340–541 and –642 airplanes.
applicable compliance time specified in table
(AD) 2012–12–12, Amendment 39– (d) Subject 1 to paragraph (h)(1) of this AD, whichever
17092 (77 FR 37797, June 25, 2012); and Air Transport Association (ATA) of occurs later, except as specified in paragraph
AD 2013–16–26, Amendment 39–17564 America Code 52, Doors. (q) of this AD: Do all applicable detailed and
(78 FR 53640, August 30, 2013); and high frequency eddy current (HFEC)
■ b. Adding the following new AD: (e) Reason inspections of all frame fork areas, frame
2018–02–17 Airbus: Amendment 39–19170; This AD was prompted by reports of head areas, and outer skin areas of each
Docket No. FAA–2017–0713; Product cracked forward and aft cargo door frames, affected forward cargo door, as applicable; in
Identifier 2016–NM–199–AD. and loose, missing, or sheared rivets. We are accordance with the Accomplishment
issuing this AD to detect and correct cracked Instructions of the applicable service
(a) Effective Date or ruptured cargo door frames, which could information specified in paragraph (h)(1)(i),
This AD is effective March 16, 2018. result in reduced structural integrity of the (h)(1)(ii), or (h)(1)(iii) of this AD. Do all
forward or aft cargo door. applicable related investigative actions and
(b) Affected ADs
(f) Compliance corrective actions before further flight in
This AD replaces AD 2012–12–12, accordance with the Accomplishment
Amendment 39–17092 (77 FR 37797, June Comply with this AD within the
Instructions of the applicable service
25, 2012); and AD 2013–16–26, Amendment compliance times specified, unless already
information specified in paragraph (h)(1)(i),
39–17564 (78 FR 53640, August 30, 2013). done.
(h)(1)(ii), or (h)(1)(iii) of this AD, except as
(c) Applicability (g) Affected Cargo Doors required by paragraph (p) of this AD. Repeat
This AD applies to the Airbus airplanes For the purpose of this AD, the affected the applicable inspections of the frame fork
identified in paragraphs (c)(1) and (c)(2) of cargo doors are pre-modification 202702 areas, frame head areas, and outer skin areas
this AD, certified in any category, all (forward cargo door) and pre-modification of each affected forward cargo door thereafter
manufacturer serial numbers, except those on 202790 (aft cargo door), and are listed by part at intervals not to exceed 1,400 flight cycles.
which Airbus Modification 202702 and number (P/N) in the applicable service BILLING CODE 4910–13–P
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![5700 Federal Register / Vol. 83, No. 28 / Friday, February 9, 2018 / Rules and Regulations
Airbus Service Bulletin A330–52–3095, 2016–0188, dated September 21, 2016; (xxiv) Airbus Service Bulletin A340–52–
Revision 01, dated July 28, 2014; Airbus corrected September 22, 2016, for related 4121, dated April 20, 2016.
Service Bulletin A340–52–4101, Revision 01, information. This MCAI may be found in the (xxv) Airbus Service Bulletin A340–52–
dated July 28, 2014; or Airbus Service AD docket on the internet at http:// 5020, Revision 02, including Appendices 01
Bulletin A340–52–5023, Revision 01, dated www.regulations.gov by searching for and and 02, dated November 27, 2015.
July 28, 2014; as applicable; provided that locating Docket No. FAA–2017–0713. (xxvi) Airbus Service Bulletin A340–52–
the next inspection of all frame fork areas, (2) For more information about this AD, 5023, Revision 02, including Appendices 01
frame head areas, and outer skin area of each contact Vladimir Ulyanov, Aerospace and 02, dated November 27, 2015.
affected aft cargo door is accomplished Engineer, International Section, Transport (3) For service information identified in
within 550 flight cycles after that inspection Standards Branch, FAA, 1601 Lind Avenue this AD, contact Airbus SAS, Airworthiness
in accordance with the Accomplishment SW, Renton, WA 98057–3356; telephone Office—EAL, 1 Rond Point Maurice Bellonte,
Instructions of SB A330–52–3095, R02; SB 425–227–1138; fax 425–227–1149. 31707 Blagnac Cedex, France; telephone: +33
A340–52–4101, R02; or SB A340–52–5023, (3) Service information identified in this 5 61 93 36 96; fax: +33 5 61 93 45 80; email:
R02, as applicable. AD that is not incorporated by reference is airworthiness.A330-A340@airbus.com;
(5) Where Airbus Service Bulletins A330– available at the addresses specified in internet: http://www.airbus.com.
52–3095, Revision 01, dated July 28, 2014; paragraphs (v)(4) and (v)(5) of this AD. (4) You may view this service information
A340–52–4101, Revision 01, dated July 28, at the FAA, Transport Standards Branch,
(v) Material Incorporated by Reference
2014; A340–52–5020, Revision 01, dated July 1601 Lind Avenue SW, Renton, WA. For
9, 2014; and A340–52–5023, Revision 01, (1) The Director of the Federal Register information on the availability of this
dated July 28, 2014; refers to using fasteners approved the incorporation by reference material at the FAA, call 425–227–1221.
having P/N ASNA2657, this AD also allows (IBR) of the service information listed in this (5) You may view this service information
the use of alternative HST11 series fasteners. paragraph under 5 U.S.C. 552(a) and 1 CFR that is incorporated by reference at the
part 51. National Archives and Records
(t) Other FAA AD Provisions (2) You must use this service information Administration (NARA). For information on
The following provisions also apply to this as applicable to do the actions required by the availability of this material at NARA, call
AD: this AD, unless this AD specifies otherwise. 202–741–6030, or go to: http://
(1) Alternative Methods of Compliance (i) Airbus Service Bulletin A330–52–3087, www.archives.gov/federal-register/cfr/ibr-
(AMOCs): The Manager, International Revision 02, including Appendix 01, dated locations.html.
Section, Transport Standards Branch, FAA, February 18, 2016.
(ii) Airbus Service Bulletin A330–52–3095, Issued in Renton, Washington, on January
has the authority to approve AMOCs for this
Revision 02, including Appendices 01 and 11, 2018.
AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR 02, dated February 19, 2016. John P. Piccola, Jr.,
39.19, send your request to your principal (iii) Airbus Service Bulletin A330–52– Acting Director, System Oversight Division,
inspector or local Flight Standards District 3105, dated February 15, 2016. Aircraft Certification Service.
Office, as appropriate. If sending information (iv) Airbus Service Bulletin A330–52– [FR Doc. 2018–01803 Filed 2–8–18; 8:45 am]
directly to the manager of the certification 3106, dated February 24, 2016.
BILLING CODE 4910–13–P
office, send it to the attention of the person (v) Airbus Service Bulletin A330–52–3110,
identified in paragraph (u)(2) of this AD. dated February 15, 2016.
Information may be emailed to: 9-ANM-116- (vi) Airbus Service Bulletin A330–52–
AMOC-REQUESTS@faa.gov. Before using 3111, dated February 15, 2016. DEPARTMENT OF TRANSPORTATION
any approved AMOC, notify your appropriate (vii) Airbus Service Bulletin A330–52–
principal inspector, or lacking a principal 3112, dated February 24, 2016. Federal Aviation Administration
inspector, the manager of the local flight (viii) Airbus Service Bulletin A330–52–
standards district office/certificate holding 3113, dated February 15, 2016. 14 CFR Part 39
district office. (ix) Airbus Service Bulletin A330–52–
[Docket No. FAA–2016–6616; Product
(2) Contacting the Manufacturer: As of the 3114, dated February 15, 2016.
Identifier 2016–CE–004–AD; Amendment
effective date of this AD, for any requirement (x) Airbus Service Bulletin A330–52–3115,
39–19177; AD 2018–03–04]
in this AD to obtain corrective actions from dated April 20, 2016.
a manufacturer, the action must be (xi) Airbus Service Bulletin A330–52– RIN 2120–AA64
accomplished using a method approved by 3116, dated April 20, 2016.
the Manager, International Section, Transport (xii) Airbus Service Bulletin A330–52– Airworthiness Directives; Rosemount
Standards Branch, FAA; or the EASA; or 3117, dated April 20, 2016. Aerospace, Inc. Pitot Probes
Airbus’s EASA DOA. If approved by the (xiii) Airbus Service Bulletin A330–52–
DOA, the approval must include the DOA- 3118, dated April 20, 2016. AGENCY: Federal Aviation
authorized signature. (xiv) Airbus Service Bulletin A340–52– Administration (FAA), DOT.
(3) Required for Compliance (RC): Except 4095, Revision 02, including Appendix 01, ACTION: Final rule.
as required by paragraph (p) of this AD: If dated November 27, 2015.
any service information contains procedures (xv) Airbus Service Bulletin A340–52– SUMMARY: We are adopting a new
or tests that are identified as RC, those 4101, Revision 02, including Appendices 01 airworthiness directive (AD) for
procedures and tests must be done to comply and 02, dated November 27, 2015. Rosemount Aerospace Model 851AK
with this AD; any procedures or tests that are (xvi) Airbus Service Bulletin A340–52– pitot probes that were repaired by CSI
not identified as RC are recommended. Those 4108, dated February 15, 2016.
(xvii) Airbus Service Bulletin A340–52–
Aerospace, Inc. between January 2013
procedures and tests that are not identified
as RC may be deviated from using accepted 4109, dated February 25, 2016. and July 2014 that are installed on
methods in accordance with the operator’s (xviii) Airbus Service Bulletin A340–52– airplanes. This AD was prompted by a
maintenance or inspection program without 4113, dated February 15, 2016. report that certain pitot probes are
obtaining approval of an AMOC, provided (xix) Airbus Service Bulletin A340–52– indicating the wrong airspeed during
the procedures and tests identified as RC can 4114, dated February 15, 2016. flight. This AD requires inspecting the
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be done and the airplane can be put back in (xx) Airbus Service Bulletin A340–52– airplane to determine the number of
an airworthy condition. Any substitutions or 4115, dated February 19, 2016. affected pitot probes installed and
changes to procedures or tests identified as (xxi) Airbus Service Bulletin A340–52– replacing the affected pitot probes. We
RC require approval of an AMOC. 4118, dated April 20, 2016.
(xxii) Airbus Service Bulletin A340–52–
are issuing this AD to address the unsafe
(u) Related Information 4119, dated April 20, 2016. condition on these products.
(1) Refer to Mandatory Continuing (xxiii) Airbus Service Bulletin A340–52– DATES: This AD is effective March 16,
Airworthiness Information (MCAI) EASA AD 4120, dated April 20, 2016. 2018.
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Document Created: 2018-02-09 00:12:05
Document Modified: 2018-02-09 00:12:05
| 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 is effective March 16, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of March 16, 2018. | |
| Contact | Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227- 1149. | |
| FR Citation | 83 FR 5689 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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