82 FR 37360 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 153 (August 10, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 153 (August 10, 2017)
| Page Range | 37360-37366 | |
| FR Document | 2017-16051 |
[Federal Register Volume 82, Number 153 (Thursday, August 10, 2017)] [Proposed Rules] [Pages 37360-37366] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-16051] ======================================================================== Proposed Rules Federal Register ________________________________________________________________________ This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. ======================================================================== Federal Register / Vol. 82, No. 153 / Thursday, August 10, 2017 / Proposed Rules [[Page 37360]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0713; Directorate Identifier 2016-NM-199-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 2012-12- 12, for all Airbus Model A330-200, A330-200 Freighter, A330-300, A340- 200, and A340-300 series airplanes; and AD 2013-16-26 for all Airbus Model A330-200 Freighter, A330-200 and -300, and A340-200 and -300 series airplanes. AD 2012-12-12 requires repetitive inspections of the outer skin rivets of the cargo doors; repair if necessary; and other repetitive inspections. AD 2013-16-26 requires repetitive inspections of certain cargo doors, and repair if necessary. Since we issued AD 2012-12-12 and AD 2013-16-26, we have determined that a new inspection procedure is necessary to address the unsafe condition. This proposed AD would continue to require repetitive inspections and repair if necessary. This proposed AD would 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 proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by September 25, 2017. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 45 80; email: [email protected]; Internet: http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. 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 proposed 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. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1138; fax: 425-227-1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2017-0713; Directorate Identifier 2016-NM-199-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On June 7, 2012, we issued AD 2012-12-12, Amendment 39-17092 (77 FR 37797, June 25, 2012) (``AD 2012-12-12''), for 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. AD 2012-12-12 was prompted by reports of sheared fasteners located on the outside skin of the forward cargo door and cracks on the frame fork ends, as well as cracks of the aft cargo door frame 64A. AD 2012-12-12 requires a detailed inspection of the outer skin rivets at the frame fork ends of the forward and aft cargo doors for sheared, loose, and missing rivets; repair of the outer skin rivets if necessary; and other repetitive inspections. We issued AD 2012-12-12 to detect and correct sheared, loose, or missing fasteners on the forward and aft cargo door frame, which could result in the loss of structural integrity of the forward and aft cargo door. On August 9, 2013, we issued AD 2013-16-26, Amendment 39-17564 (78 FR 53640, August 30, 2013) (``2013-16-26''), for all Airbus Model A330- 200 Freighter series airplanes, Model A330-200 and -300 series airplanes, and Model A340-200 and -300 series airplanes. AD 2013-16-26 was prompted by reports of cracked adjacent frame forks of a forward cargo door. AD 2013-16-26 requires repetitive detailed inspections for cracks and sheared, loose, or missing rivets of the forward cargo door and, for certain airplanes, of the aft cargo door, and repair if necessary. We issued AD 2013-16-26 to detect and correct cracked or ruptured cargo door frames, which could result in [[Page 37361]] reduced structural integrity of the forward or aft cargo door. Since we issued AD 2012-12-12 and AD 2013-16-26, we have determined that a new inspection procedure is necessary to address the unsafe condition. In addition, the manufacturer has released some terminating action modifications for the cargo door structure, and provided procedures that allow postponing the structural reinforcement modification, which terminate the repetitive inspections. 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. 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. [[Page 37362]] 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. FAA's Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type designs. Costs of Compliance We estimate that this proposed AD affects 73 airplanes of U.S. registry. We estimate that it would take up to 888 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost up to $126,420 per product. Based on these figures, we estimate the cost of this proposed 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 proposed 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. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation: 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. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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: Airbus: Docket No. FAA-2017-0713; Directorate Identifier 2016-NM- 199-AD. (a) Comments Due Date We must receive comments by September 25, 2017. (b) Affected ADs This AD replaces 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''). (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. [[Page 37363]] (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) 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. Table 1 to Paragraph (h)(1) of This AD--Forward Cargo Door Inspection Compliance Time ------------------------------------------------------------------------ Airplane condition (on the effective date of this AD) Compliance time ------------------------------------------------------------------------ Inspected only as specified in Airbus Within 1,100 flight cycles Alert Operator Transmission (AOT) A330- after the last inspection, but 52A3085 or AOT A340-52A4092, as without exceeding 10,600 applicable. flight cycles since first installation of the forward cargo door on an airplane. Inspected as specified in Airbus AOT Within 1,100 flight cycles A330-52A3085 and as specified in AOT after the last inspection as A330-A52L003-12, and the last specified in AOT A330-52A3085. inspection was accomplished as specified in AOT A330-A52L003-12. Inspected as specified in Airbus AOT Within 1,100 flight cycles A330-52A3085 and as specified in AOT after the last inspection as A330-A52L003-12, and the last specified in AOT A330-A52L003- inspection was accomplished as 12. specified in AOT A330-52A3085. Inspected as specified in Airbus AOT Within 1,100 flight cycles A340-52A4092 and as specified in AOT after the last inspection as A340-A52L004-12, and the last specified in AOT A340-52A4092. inspection was accomplished as specified in AOT A340-A52L004-12. Inspected as specified in Airbus AOT Within 1,100 flight cycles A340-52A4092 and as specified in AOT after the last inspection as A340-A52L004-12, and the last specified in AOT A340-A52L004- inspection was accomplished as 12. specified in AOT A340-52A4092. Inspected as specified in the original There is no compliance time for issue of Airbus Service Bulletin (SB) the initial inspection in A330-52-3087, or SB A340-52-4095, or paragraph (h)(1) of this AD SB A340-52-5020, as applicable. for these airplanes, provided these airplanes comply with the actions specified paragraph (r)(1) of this AD. Inspected as specified in Revision 01 There is no compliance time for of Airbus SB A330-52-3087, or SB A340- the initial inspection in 52-4095, or SB A340-52-5020, as paragraph (h)(1) of this AD applicable. for these airplanes, provided these airplanes comply with the actions specified in paragraph (r)(2) of this AD. Inspected as specified in Revision 02 Within 1,400 flight cycles of Airbus SB A330-52-3087, or SB A340- after the last inspection, but 52-4095, or SB A340-52-5020, as without exceeding 5,300 total applicable. flight cycles since first installation of the forward cargo door on an airplane. Never inspected........................ Within 1,100 flight cycles after the effective date of this AD, but without exceeding 6,400 flight cycles since first installation of the forward cargo door on an airplane. ------------------------------------------------------------------------ (i) Airbus Service Bulletin A330-52-3087, Revision 02, dated February 18, 2016 (``A330-52-3087, R2''). (ii) Airbus Service Bulletin A340-52-4095, Revision 02, dated November 29, 2015 (``A340-52-4095, R2''). (iii) Airbus Service Bulletin A340-52-5020, Revision 02, dated November 27, 2015 (``A340-52-5020, R2''). (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 required hook gap adjustments before further flight. (i) A330-52-3087, R2. (ii) A340-52-4095, R2. (iii) A340-52-5020, R2. (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 [[Page 37364]] 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 Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). (j) Forward Cargo Door Terminating Action Modification of an airplane by reinforcement of the cargo door frame structure required by paragraph (i)(1) or (i)(3) of this AD constitutes terminating action for the repetitive inspections required by paragraph (h)(1) of this AD for that airplane. (k) Definitions of Pre-Modified and Post-Modified Airplanes (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 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. Table 2 to Paragraph (l)(1) of This AD--Aft Cargo Door Inspection Compliance Times for Pre-Modified Airplanes ------------------------------------------------------------------------ Airplane condition (on the effective date of this AD) Compliance time ------------------------------------------------------------------------ Inspected only as specified in Airbus Within 550 flight cycles after AOT A330-52A3084, or AOT A340-52A4091, the last inspection, but as applicable. without exceeding 15,800 flight cycles since first installation of the aft cargo door on an airplane. Inspected as specified in Airbus AOT Within 550 flight cycles after A330-52A3084 and as specified in AOT the last inspection as A330-A52L001-12, and the last specified in AOT A330-52A3084. inspection was accomplished as specified in AOT A330-A52L001-12. Inspected as specified in Airbus AOT Within 550 flight cycles after A330-52A3084 and as specified in AOT the last inspection as A330-A52L001-12, and the last specified in AOT A330-A52L001- inspection was accomplished as 12. specified in AOT A330-52A3084. Inspected as specified in Airbus AOT Within 550 flight cycles after A340-52A4091 and as specified in AOT the last inspection as A340-A52L002-12, and the last specified in AOT A340-52A4091. inspection was accomplished as specified in AOT A340-A52L002-12. Inspected as specified in Airbus AOT Within 550 flight cycles after A340-52A4091 and as specified in AOT the last inspection as A340-A52L002-12, and the last specified in AOT A340-A52L002- inspection was accomplished as 12. specified in AOT A340-52A4091. Inspected as specified in the original There is no compliance time for issue of Airbus SB A330-52-3095, or SB the initial inspection in A340-52-4101, as applicable. paragraph (l)(1) of this AD for these airplanes, provided these airplanes comply with the actions specified in paragraph (r)(3) of this AD. Inspected as specified in Revision 01 There is no compliance time for of Airbus SB A330-52-3095, or SB A340- the initial inspection in 52-4101, as applicable. paragraph (l)(1) of this AD for these airplanes, provided these airplanes comply with the actions specified in paragraph (r)(4) of this AD. Inspected as specified in Revision 02 Within 1,400 flight cycles of Airbus SB A330-52-3095, or SB A340- after the last inspection as 52-4101, as applicable. specified in Revision 02 of Airbus SB A330-52-3095, or SB A340-52-4101, as applicable but without exceeding 4,000 flight cycles since first installation of the aft cargo door on an airplane, as applicable. [[Page 37365]] Never inspected........................ Within 550 flight cycles after the effective date of this AD, but without exceeding 4,550 flight cycles since first installation of the aft cargo door on an airplane. ------------------------------------------------------------------------ Table 3 to Paragraph (l)(1) of This AD--Aft Cargo Door Inspection Compliance Times for Post-Modified Airplanes and Model A340-500 and -600 Airplanes ------------------------------------------------------------------------ Airplane condition (on the effective date of this AD) Compliance time ------------------------------------------------------------------------ Never inspected........................ Within 550 flight cycles after the effective date of this AD, but without exceeding 12,550 flight cycles since first installation of the aft cargo door on an airplane. Inspected as specified in the original There is no compliance time for issue of Airbus SB A330-52-3095 or SB paragraph (l)(1) of this AD A340-52-4101, or SB A340-5023, as for these airplanes, provided applicable. these airplanes comply with the actions specified in paragraph (r)(3) of this AD. Inspected as specified in Revision 01 There is no compliance time for of Airbus SB A330-52-3095, or SB A340- paragraph (l)(1) of this AD 52-4101, or SB A340-5023, as for these airplanes, provided applicable. these airplanes comply with the actions specified in paragraph (r)(4) of this AD. Inspected as specified in Revision 02 Within 1,400 flight cycles of Airbus SB A330-52-3095, or SB A340- after the last inspection as 52-4101, or SB A340-5023, as specified in Revision 02 of applicable. Airbus SB A330-52-3095, or SB A340-52-4101, or SB A340-5023, as applicable, but without exceeding 12,000 flight cycles since first installation of the aft cargo door on an airplane. ------------------------------------------------------------------------ (i) Airbus Service Bulletin A330-52-3095, Revision 02, dated February 19, 2016 (``A330-52-3095, R2''). (ii) Airbus Service Bulletin A340-52-4101, Revision 02, dated November 27, 2015 (``A340-52-4101, R2''). (iii) Airbus Service Bulletin A340-52-5023, Revision 02, dated November 27, 2015 (``A340-52-5023, R2''). (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 required hook gap adjustments before further flight. (i) A330-52-3095, R2. (ii) A340-52-4101, R2. (iii) A340-52-5023, R2. (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 Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. (n) Aft Cargo Door Terminating Action Modification of an airplane by reinforcement of the cargo door frame structure required by paragraph (m)(1) or (m)(3) of this AD constitutes terminating action for the repetitive inspections required by paragraph (l)(1) 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 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 Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA, constitutes terminating action for the repetitive inspections required by paragraph (l)(1) of this AD. (p) Exception 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 (s)(2) of this AD. [[Page 37366]] (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) 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 A330-52-3087, R2; A330-52-3095, R2; or A340-52-5020, R2, 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 A330-52-3087, R2; A330-52-3095, R2; or A340-52-5020, R2, 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 A330-52-3095, R2; A340-52-4101, R2; or A340-52-5023, R2, 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 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 A330-52-3095, R2; A340-52-4101, R2; or A340-52-5023, R2, as applicable. (s) 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 manager of the International Branch, send it to the attention of the person identified in paragraph (t)(2) of this AD. 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. (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 Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): 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. (t) 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 Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1138; fax: 425-227-1149. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 45 80; email: [email protected]; Internet: http://www.airbus.com. 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. Issued in Renton, Washington, on July 19, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-16051 Filed 8-9-17; 8:45 am] BILLING CODE 4910-13-P
![37360
Proposed Rules Federal Register
Vol. 82, No. 153
Thursday, August 10, 2017
This section of the FEDERAL REGISTER 11.43 and 11.45, by any of the following 2017–0713; Directorate Identifier 2016–
contains notices to the public of the proposed methods: NM–199–AD’’ at the beginning of your
issuance of rules and regulations. The • Federal eRulemaking Portal: Go to comments. We specifically invite
purpose of these notices is to give interested http://www.regulations.gov. Follow the comments on the overall regulatory,
persons an opportunity to participate in the instructions for submitting comments. economic, environmental, and energy
rule making prior to the adoption of the final
• Fax: 202–493–2251. aspects of this proposed AD. We will
rules.
• Mail: U.S. Department of consider all comments received by the
Transportation, Docket Operations, M– closing date and may amend this
DEPARTMENT OF TRANSPORTATION 30, West Building Ground Floor, Room proposed AD based on those comments.
W12–140, 1200 New Jersey Avenue SE., We will post all comments we
Federal Aviation Administration Washington, DC 20590. receive, without change, to http://
• Hand Delivery: Deliver to Mail www.regulations.gov, including any
14 CFR Part 39 address above between 9 a.m. and 5 personal information you provide. We
p.m., Monday through Friday, except will also post a report summarizing each
[Docket No. FAA–2017–0713; Directorate Federal holidays.
Identifier 2016–NM–199–AD]
substantive verbal contact we receive
For service information identified in about this proposed AD.
RIN 2120–AA64 this NPRM, contact Airbus SAS,
Airworthiness Office—EAL, 1 Rond Discussion
Airworthiness Directives; Airbus Point Maurice Bellonte, 31707 Blagnac On June 7, 2012, we issued AD 2012–
Airplanes Cedex, France; telephone: +33 5 61 93 12–12, Amendment 39–17092 (77 FR
36 96; fax: +33 5 61 93 45 80; email: 37797, June 25, 2012) (‘‘AD 2012–12–
AGENCY: Federal Aviation airworthiness.A330-A340@airbus.com; 12’’), for all Airbus Model A330–200
Administration (FAA), DOT. Internet: http://www.airbus.com. You series airplanes, Model A330–200
ACTION: Notice of proposed rulemaking may view this referenced service Freighter series airplanes, Model A330–
(NPRM). information at the FAA, Transport 300 series airplanes, Model A340–200
Airplane Directorate, 1601 Lind Avenue series airplanes, and Model A340–300
SUMMARY: We propose to supersede
SW., Renton, WA. For information on series airplanes. AD 2012–12–12 was
Airworthiness Directive (AD) 2012–12–
the availability of this material at the prompted by reports of sheared
12, for all Airbus Model A330–200,
FAA, call 425–227–1221. fasteners located on the outside skin of
A330–200 Freighter, A330–300, A340–
200, and A340–300 series airplanes; and Examining the AD Docket the forward cargo door and cracks on
AD 2013–16–26 for all Airbus Model the frame fork ends, as well as cracks of
You may examine the AD docket on the aft cargo door frame 64A. AD 2012–
A330–200 Freighter, A330–200 and the Internet at http://
–300, and A340–200 and –300 series 12–12 requires a detailed inspection of
www.regulations.gov by searching for the outer skin rivets at the frame fork
airplanes. AD 2012–12–12 requires and locating Docket No. FAA–2017–
repetitive inspections of the outer skin ends of the forward and aft cargo doors
0713; or in person at the Docket for sheared, loose, and missing rivets;
rivets of the cargo doors; repair if Management Facility between 9 a.m.
necessary; and other repetitive repair of the outer skin rivets if
and 5 p.m., Monday through Friday, necessary; and other repetitive
inspections. AD 2013–16–26 requires except Federal holidays. The AD docket
repetitive inspections of certain cargo inspections. We issued AD 2012–12–12
contains this proposed AD, the to detect and correct sheared, loose, or
doors, and repair if necessary. Since we regulatory evaluation, any comments
issued AD 2012–12–12 and AD 2013– missing fasteners on the forward and aft
received, and other information. The cargo door frame, which could result in
16–26, we have determined that a new street address for the Docket Operations
inspection procedure is necessary to the loss of structural integrity of the
office (telephone: 800–647–5527) is in forward and aft cargo door.
address the unsafe condition. This the ADDRESSES section. Comments will
proposed AD would continue to require On August 9, 2013, we issued AD
be available in the AD docket shortly 2013–16–26, Amendment 39–17564 (78
repetitive inspections and repair if after receipt.
necessary. This proposed AD would add FR 53640, August 30, 2013) (‘‘2013–16–
FOR FURTHER INFORMATION CONTACT: 26’’), for all Airbus Model A330–200
a one-time inspection and adjustment of
Vladimir Ulyanov, Aerospace Engineer, Freighter series airplanes, Model A330–
certain hook gaps; reinforcement of the
International Branch, ANM–116, 200 and –300 series airplanes, and
door frame structure; related
Transport Airplane Directorate, FAA, Model A340–200 and –300 series
investigative and corrective actions if
1601 Lind Avenue SW., Renton, WA airplanes. AD 2013–16–26 was
necessary; and a modification, which
98057–3356; telephone: 425–227–1138; prompted by reports of cracked adjacent
would allow deferring reinforcement of
fax: 425–227–1149. frame forks of a forward cargo door. AD
mstockstill on DSK30JT082PROD with PROPOSALS
the cargo door structure. We are
proposing this AD to address the unsafe SUPPLEMENTARY INFORMATION: 2013–16–26 requires repetitive detailed
condition on these products. inspections for cracks and sheared,
Comments Invited loose, or missing rivets of the forward
DATES: We must receive comments on
We invite you to send any written cargo door and, for certain airplanes, of
this proposed AD by September 25, relevant data, views, or arguments about the aft cargo door, and repair if
2017. this proposal. Send your comments to necessary. We issued AD 2013–16–26 to
ADDRESSES: You may send comments, an address listed under the ADDRESSES detect and correct cracked or ruptured
using the procedures found in 14 CFR section. Include ‘‘Docket No. FAA– cargo door frames, which could result in
VerDate Sep<11>2014 16:24 Aug 09, 2017 Jkt 241001 PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 E:\FR\FM\10AUP1.SGM 10AUP1](https://thefederalregister.org/doc/82_FR_37513/page/1.svg)
![Federal Register / Vol. 82, No. 153 / Thursday, August 10, 2017 / Proposed Rules 37361
reduced structural integrity of the Since these EASA ADs were issued, Airbus Related investigative actions include
forward or aft cargo door. published SB A330–52–3087, SB A330–52– detailed inspections and high frequency
Since we issued AD 2012–12–12 and 3095, SB A340–52–4095, SB A340–52–4101, non-destructive test inspections.
AD 2013–16–26, we have determined SB A340–52–5020 and SB A340–52–5023, Corrective actions include reaming
that a new inspection procedure is which took over the instructions of the above
holes, bushing holes, replacing affected
mentioned AOTs, and introduced revised
necessary to address the unsafe thresholds and intervals. In addition, the parts, and repairing cracks. Additional
condition. In addition, the manufacturer inspection program was expanded to A340– work includes a one-time inspection of
has released some terminating action 500/–600 aeroplanes. Taking into account the ‘‘U’’ and ‘‘V’’ hook gaps, and if
modifications for the cargo door experience from inspections accomplished in necessary, an adjustment of the hook
structure, and provided procedures that accordance with the applicable Airbus SBs at gaps.
allow postponing the structural original issue (listed above), Airbus issued You may examine the MCAI in the
reinforcement modification, which Revision 01 of these SBs. AD docket on the Internet at http://
terminate the repetitive inspections. Consequently, EASA issued AD 2015– www.regulations.gov by searching for
The European Aviation Safety Agency 0192, which superseded EASA AD 2011– and locating Docket No. FAA–2017–
(EASA), which is the Technical Agent 0007R1 and EASA AD 2012–0274, to require 0713.
for each FWD and AFT cargo door, a one-
for the Member States of the European Related Service Information Under 1
time inspection/adjustment of the hook gaps
Union, has issued EASA AD 2016–0188, ‘‘U’’ and ‘‘V’’, repetitive detailed inspections CFR Part 51
dated September 21, 2016; corrected (DET) of all frame fork areas, frame head
September 22, 2016 (referred to after Airbus has issued the following
areas and outer skin areas to detect cracks or
this as the Mandatory Continuing loose/sheared/missing fasteners, and,
service information.
Airworthiness Information, or ‘‘the depending on findings, accomplishment of
The following service information
MCAI’’); to correct an unsafe condition applicable corrective action(s). In addition, describes procedures for inspecting and
for certain Airbus Model A330–200 and EASA AD 2015–0192 expanded the repairing the frame fork area at beam 4
–300 series airplanes; Model A330–200 Applicability to Airbus A340–500/–600 and frame head area at beam 1 from
Freighter series airplanes; and Model aeroplanes. frame 20B to frame 25 of the forward
A340–200, –300, –500, and –600 series Since EASA AD 2015–0192 was issued, cargo door, and adjusting the hook gaps
Airbus published Revision 02 of the ‘‘U’’ and ‘‘V.’’ This service information
airplanes. The MCAI states: inspection SBs, introducing high-frequency is distinct since it applies to different
Several cases of cracked forward (FWD) eddy-current inspection method for the frame airplane models.
and aft (AFT) cargo door frames, as well as forks structure. Airbus also determined that • Service Bulletin A330–52–3087,
loose, lost, or sheared rivets, have been the interval for these repetitive inspections Revision 02, including Appendix 01,
reported by operators. Investigation showed could be increased. In addition, Airbus
that these findings are due to the low margins dated February 18, 2016.
released some modifications (mod)
with respect to fatigue requirements for the • Service Bulletin A340–52–4095,
introducing reinforcements to the cargo door
AFT/FWD cargo door internal structure. structure improving the fatigue
Revision 02, including Appendix 01,
Further analysis determined that the cargo characteristics. These modifications and dated November 29, 2015.
door hook adjustment is a contributing factor associated SBs constitute terminating action • Service Bulletin A340–52–5020,
to this issue. In case of a cracked or ruptured for the required repetitive inspections. Revision 02, including Appendices 01
(FWD or AFT) cargo door frame, the loads Furthermore, Airbus also published other and 02, dated November 27, 2015.
will be transferred to the remaining structural SBs, introducing cold working after The following service information
elements. However, the secondary load path oversizing of the fastener holes as a means for describes procedures for modifying the
is able to sustain those loads only for a structural reinforcement. Accomplishment of frame fork area at beam 4 and frame
limited number of flight cycles (FC). these SBs allows postponement of the head area at beam 1 from frame 20B to
This condition, if not detected and required Point of Embodiment (Structural
corrected, could lead to rupture of adjacent frame 25 of the forward cargo door
Modification Point) for the structural frame. This service information is
vertical frames and consequent reduced reinforcement modification SBs which
structural integrity of the FWD or AFT cargo distinct since it applies to different
terminate the repetitive inspection
door, possibly resulting in a cargo door airplane models and configurations.
requirement.
failure, decompression of the aeroplane and • Service Bulletin A330–52–3105,
For the reasons described above, this
injury to occupants.
[EASA] AD partially retains the requirements
dated February 24, 2016.
To initially address this potential unsafe
of EASA AD 2015–0192, which is • Service Bulletin A330–52–3110,
condition, Airbus issued Service Bulletin dated February 15, 2016.
superseded, and requires for each FWD and
(SB) A330–52–3043 and SB A340–52–4053
AFT cargo door initial and repetitive special • Service Bulletin A330–52–3111,
and, consequently, DGAC [Direction dated February 15, 2016.
Générale de l’Aviation Civile] France issued detailed inspections (SDI) of all frame fork
areas and detailed inspections (DET) of frame • Service Bulletin A340–52–4108,
AD 2001–124(B) and AD 2001–126(B),
requiring a special detailed inspection of head areas and outer skin areas, and a one- dated February 15, 2016.
A330 and A340 AFT cargo doors. Since those time inspection/adjustment of the hook gaps • Service Bulletin A340–52–4113,
[DGAC] ADs were issued, prompted by new ‘‘U’’ and ‘‘V’’ and, depending on findings, the dated February 15, 2016.
occurrences, Airbus issued Alert Operators accomplishment of applicable corrective • Service Bulletin A340–52–4114,
Transmission (AOT) A330–52A3085, AOT action(s). Additionally, this [EASA] AD dated February 15, 2016.
A340–52A4092, AOT A330–52A3084, AOT requires reinforcement of the cargo door The following service information
A340–52A4091, AOT A330–A52L003–12, frame structure, while accomplishment of a describes procedures for modifying the
AOT 340–A52L004–12, AOT A330– cold working modification allows to defer the fastener holes in the forward cargo door
A52L001–12 and AOT A340–A52L002–12, reinforcement of the cargo door structure. frame structure by cold working and
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providing instructions to inspect the affected It should be noted that additional
changing the fastener type and size.
areas of both FWD and AFT cargo doors. inspections exist for the cargo doors, as
specified in Airbus A330 ALS [Airworthiness This service information is distinct
Consequently, EASA issued AD 2011–0007
(later revised) [which corresponds to FAA Limitation Section] Part 2 task 523211–02–01 since it applies to different airplane
AD 2012–12–12], and AD 2012–0274 [which and task 523211–02–02, and in Airbus A340 models and configurations.
corresponds to FAA AD 2013–16–26], to ALS Part 2 Task 523211–02–01. • Service Bulletin A330–52–3116,
require repetitive detailed visual inspections This [EASA] AD is re-published to correct dated April 20, 2016.
of AFT and FWD cargo doors at specific typographical errors when referencing Airbus • Service Bulletin A330–52–3117,
frames and outer skin at all frame fork ends. SB A340–52–4118. dated April 20, 2016.
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• Service Bulletin A330–52–3118, in the United States. Pursuant to our 1. Is not a ‘‘significant regulatory
dated April 20, 2016. bilateral agreement with the State of action’’ under Executive Order 12866;
• Service Bulletin A340–52–4119, Design Authority, we have been notified 2. Is not a ‘‘significant rule’’ under the
dated April 20, 2016. of the unsafe condition described in the DOT Regulatory Policies and Procedures
• Service Bulletin A340–52–4120, MCAI and service information (44 FR 11034, February 26, 1979);
dated April 20, 2016. referenced above. We are proposing this 3. Will not affect intrastate aviation in
• Service Bulletin A340–52–4121, AD because we evaluated all pertinent Alaska; and
dated April 20, 2016. information and determined an unsafe 4. Will not have a significant
The following service information condition exists and is likely to exist or economic impact, positive or negative,
describes procedures for inspecting the develop on other products of the same on a substantial number of small entities
frame fork area at beam 4 and frame type designs. under the criteria of the Regulatory
head area at beam 1 of the aft cargo door Flexibility Act.
from frame 60 to frame 64A, adjusting Costs of Compliance
the hook gaps ‘‘U’’ and ‘‘V,’’ and doing List of Subjects in 14 CFR Part 39
We estimate that this proposed AD
corrective actions. This service affects 73 airplanes of U.S. registry. Air transportation, Aircraft, Aviation
information is distinct since it applies to We estimate that it would take up to safety, Incorporation by reference,
different airplane models and 888 work-hours per product to comply Safety.
configurations. with the basic requirements of this The Proposed Amendment
• Service Bulletin A330–52–3095, proposed AD. The average labor rate is
Revision 02, including Appendices 01 $85 per work-hour. Required parts Accordingly, under the authority
and 02, dated February 19, 2016. would cost up to $126,420 per product. delegated to me by the Administrator,
• Service Bulletin A340–52–4101, Based on these figures, we estimate the the FAA proposes to amend 14 CFR part
Revision 02, including Appendices 01 cost of this proposed AD on U.S. 39 as follows:
and 02, dated November 27, 2015. operators to be up to $14,738,700, or up
• Service Bulletin A340–52–5023, to $201,900 per product.
PART 39—AIRWORTHINESS
Revision 02, including Appendices 01 DIRECTIVES
We have received no definitive data
and 02, dated November 27, 2015. that would enable us to provide cost
The following service information ■ 1. The authority citation for part 39
estimates for the on-condition actions continues to read as follows:
describes procedures for modifying the specified in this proposed AD.
frame fork and head of the aft cargo door Authority: 49 U.S.C. 106(g), 40113, 44701.
frame from frame 59A to frame 65. This Authority for This Rulemaking
§ 39.13 [Amended]
service information is distinct since it Title 49 of the United States Code
applies to different airplane models and ■ 2. The FAA amends § 39.13 by:
specifies the FAA’s authority to issue ■ a. Removing Airworthiness Directive
configurations. rules on aviation safety. Subtitle I,
• Service Bulletin A330–52–3106, section 106, describes the authority of
(AD) 2012–12–12, Amendment 39–
dated February 24, 2016. 17092 (77 FR 37797, June 25, 2012); and
the FAA Administrator. ‘‘Subtitle VII:
• Service Bulletin A330–52–3112, AD 2013–16–26, Amendment 39–17564
Aviation Programs,’’ describes in more (78 FR 53640, August 30, 2013); and
dated February 24, 2016.
detail the scope of the Agency’s
• Service Bulletin A330–52–3113, ■ b. Adding the following new AD:
authority.
dated February 15, 2016. AIRBUS: Docket No. FAA–2017–0713;
• Service Bulletin A330–52–3114, We are issuing this rulemaking under Directorate Identifier 2016–NM–199–AD.
dated February 15, 2016. the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701: (a) Comments Due Date
• Service Bulletin A340–52–4109,
dated February 25, 2016. General requirements.’’ Under that We must receive comments by September
• Service Bulletin A340–52–4115, section, Congress charges the FAA with 25, 2017.
dated February 19, 2016. promoting safe flight of civil aircraft in (b) Affected ADs
The following service information air commerce by prescribing regulations
This AD replaces AD 2012–12–12,
describes procedures for modifying the for practices, methods, and procedures Amendment 39–17092 (77 FR 37797, June
fastener holes in the aft cargo door the Administrator finds necessary for 25, 2012) (‘‘AD 2012–12–12’’); and AD 2013–
frame structure by cold working and safety in air commerce. This regulation 16–26, Amendment 39–17564 (78 FR 53640,
changing the fastener type and size. is within the scope of that authority August 30, 2013) (‘‘AD 2013–16–26’’).
This service information is distinct because it addresses an unsafe condition
(c) Applicability
since it applies to different airplane that is likely to exist or develop on
products identified in this rulemaking This AD applies to the Airbus airplanes
models. identified in paragraphs (c)(1) and (c)(2) of
• Service Bulletin A330–52–3115, action.
this AD, certified in any category, all
dated April 20, 2016. Regulatory Findings manufacturer serial numbers, except those on
• Service Bulletin A340–52–4118, which Airbus Modification 202702 and
dated April 20, 2016. We determined that this proposed AD Modification 202790 have been embodied in
This service information is reasonably would not have federalism implications production; and the Airbus airplanes
available because the interested parties under Executive Order 13132. This identified in paragraphs (c)(3) through (c)(5)
have access to it through their normal proposed AD would not have a of this AD, certified in any category, all
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course of business or by the means substantial direct effect on the States, on manufacturer serial numbers.
the relationship between the national (1) Model A330–201, –202, –203, –223,
identified in the ADDRESSES section.
Government and the States, or on the –223F, –243, and –243F airplanes.
FAA’s Determination and Requirements (2) Model A330–301, –302, –303, –321,
distribution of power and
of This Proposed AD –322, –323, –341, –342, and –343 airplanes.
responsibilities among the various (3) Model A340–211, –212, and –213
This product has been approved by levels of government. airplanes.
the aviation authority of another For the reasons discussed above, I (4) Model A340–311, –312, and –313
country, and is approved for operation certify this proposed regulation: airplanes.
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(q) Exception to Initial Inspection flight cycles after that inspection, and changes to procedures or tests identified as
Compliance Time provided the next inspection of all frame fork RC require approval of an AMOC.
For the purposes of table 1 to paragraph areas, frame head areas, and outer skin area
(t) Related Information
(h)(1) of this AD, table 2 to paragraph (l)(1) of each affected aft cargo door is
accomplished within 550 flight cycles after (1) Refer to Mandatory Continuing
of this AD, and table 3 to paragraph (l)(1) of
that inspection in accordance with the Airworthiness Information (MCAI) EASA AD
this AD: As soon as a cargo door is inspected
Accomplishment Instructions of A330–52– 2016–0188, dated September 21, 2016;
using any applicable service information
3095, R2; A340–52–4101, R2; or A340–52– corrected September 22, 2016, for related
specified in this AD, the previous inspections
5023, R2, as applicable. information. This MCAI may be found in the
accomplished in accordance with any alert AD docket on the Internet at http://
operator transmission can be disregarded for (4) This paragraph provides credit for the
initial inspection required by paragraph (l) of www.regulations.gov by searching for and
the determination of the compliance time for locating Docket No. FAA–2017–0713.
the initial inspection required by this AD. this AD, if that inspection was performed
before the effective date of this AD using (2) For more information about this AD,
(r) Credit for Previous Actions Airbus Service Bulletin A330–52–3095, contact, Vladimir Ulyanov, Aerospace
Revision 01, dated July 28, 2014; Airbus Engineer, International Branch, ANM–116,
(1) This paragraph provides credit for the
Service Bulletin A340–52–4101, Revision 01, Transport Airplane Directorate, FAA, 1601
initial inspection required by paragraph (h)
dated July 28, 2014; or Airbus Service Lind Avenue SW., Renton, WA 98057–3356;
of this AD, if that inspection was performed
Bulletin A340–52–5023, Revision 01, dated telephone: 425–227–1138; fax: 425–227–
before the effective date of this AD using 1149.
Airbus Service Bulletin A330–52–3087, July 28, 2014; as applicable; provided that
the next inspection of all frame fork areas, (3) For service information identified in
dated August 29, 2013; Airbus Service this AD, contact Airbus SAS, Airworthiness
Bulletin A340–52–4095, dated August 29, frame head areas, and outer skin area of each
affected aft cargo door is accomplished Office—EAL, 1 Rond Point Maurice Bellonte,
2013; or Airbus Service Bulletin A340–52– 31707 Blagnac Cedex, France; telephone: +33
5020, dated August 29, 2013; as applicable; within 550 flight cycles after that inspection
5 61 93 36 96; fax: +33 5 61 93 45 80; email:
provided that the actions identified as in accordance with the Accomplishment
airworthiness.A330-A340@airbus.com;
‘‘additional work’’ in the Accomplishment Instructions of A330–52–3095, R2; A340–52–
Internet: http://www.airbus.com. You may
Instructions of Airbus Service Bulletin A330– 4101, R2; or A340–52–5023, R2, as
view this service information at the FAA,
52–3087, Revision 01, dated July 9, 2014; applicable.
Transport Airplane Directorate, 1601 Lind
Airbus Service Bulletin A340–52–4095, Avenue SW., Renton, WA. For information
(s) Other FAA AD Provisions
Revision 01, dated July 28, 2014; or Airbus on the availability of this material at the
Service Bulletin A340–52–5020, Revision 01, The following provisions also apply to this
AD: FAA, call 425–227–1221.
dated July 9, 2014; as applicable; are
accomplished within 1,100 flight cycles after (1) Alternative Methods of Compliance Issued in Renton, Washington, on July 19,
that inspection; and provided the next (AMOCs): The Manager, International 2017.
inspection of all frame fork areas, frame head Branch, ANM–116, Transport Airplane Michael Kaszycki,
areas, and outer skin area of each affected Directorate, FAA, has the authority to Acting Manager, Transport Airplane
forward cargo door is accomplished within approve AMOCs for this AD, if requested Directorate, Aircraft Certification Service.
1,100 flight cycles after that inspection, in using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your [FR Doc. 2017–16051 Filed 8–9–17; 8:45 am]
accordance with the Accomplishment
Instructions of A330–52–3087, R2; A330–52– request to your principal inspector or local BILLING CODE 4910–13–P
3095, R2; or A340–52–5020, R2, as Flight Standards District Office, as
applicable. appropriate. If sending information directly
(2) This paragraph provides credit for the to the manager of the International Branch, DEPARTMENT OF TRANSPORTATION
initial inspection required by paragraph (h) send it to the attention of the person
of this AD, if that inspection was performed identified in paragraph (t)(2) of this AD. Federal Aviation Administration
before the effective date of this AD using Information may be emailed to: 9-ANM-116-
Airbus Service Bulletin A330–52–3087, AMOC-REQUESTS@faa.gov. Before using 14 CFR Part 39
Revision 01, dated July 9, 2014; Airbus any approved AMOC, notify your appropriate
Service Bulletin A340–52–4095, Revision 01, principal inspector, or lacking a principal [Docket No. FAA–2017–0715; Product
dated July 28, 2014; or Airbus Service inspector, the manager of the local flight Identifier 2017–NM–073–AD]
Bulletin A340–52–5020, Revision 01, dated standards district office/certificate holding RIN 2120–AA64
July 9, 2014; as applicable; provided that the district office.
next inspection of all frame fork areas, frame (2) Contacting the Manufacturer: As of the Airworthiness Directives; The Boeing
head areas, and outer skin area of each effective date of this AD, for any requirement
Company Airplanes
affected forward cargo door, is accomplished in this AD to obtain corrective actions from
within 1,100 flight cycles after that a manufacturer, the action must be AGENCY: Federal Aviation
inspection in accordance with the accomplished using a method approved by Administration (FAA), DOT.
Accomplishment Instructions of A330–52– the Manager, International Branch, ANM–
ACTION: Notice of proposed rulemaking
3087, R2; A330–52–3095, R2; or A340–52– 116, Transport Airplane Directorate, FAA; or
5020, R2, as applicable. the EASA; or Airbus’s EASA DOA. If (NPRM).
(3) This paragraph provides credit for the approved by the DOA, the approval must
SUMMARY: We propose to adopt a new
initial inspection required by paragraph (l) of include the DOA-authorized signature.
this AD, if that inspection was performed (3) Required for Compliance (RC): Except airworthiness directive (AD) for certain
before the effective date of this AD using as required by paragraph (p) of this AD: If The Boeing Company Model 737–200,
Airbus Service Bulletin A330–52–3095, any service information contains procedures –200C, –300, –400, and –500 series
dated August 29, 2013; Airbus Service or tests that are identified as RC, those airplanes. This AD was prompted by an
Bulletin A340–52–4101, dated August 29, procedures and tests must be done to comply evaluation by the design approval
2013; or Airbus Service Bulletin A340–52– with this AD; any procedures or tests that are holder (DAH) indicating that the
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5023, dated August 29, 2013; provided that not identified as RC are recommended. Those fuselage crown skin panels are subject
the actions identified as ‘‘additional work’’ in procedures and tests that are not identified to widespread fatigue damage (WFD).
the Accomplishment Instructions of Airbus as RC may be deviated from using accepted
This proposed AD would require
Service Bulletin A330–52–3095, Revision 01, methods in accordance with the operator’s
dated July 28, 2014; Airbus Service Bulletin maintenance or inspection program without repetitive inspections, replacement, and
A340–52–4101, Revision 01, dated July 28, obtaining approval of an AMOC, provided applicable on-condition actions for
2014; or Airbus Service Bulletin A340–52– the procedures and tests identified as RC can certain fuselage crown skin panels. We
5023, Revision 01, dated July 28, 2014; as be done and the airplane can be put back in are proposing this AD to address the
applicable; are accomplished within 550 an airworthy condition. Any substitutions or unsafe condition on these products.
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Document Created: 2017-08-10 01:01:49
Document Modified: 2017-08-10 01:01:49
| 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 | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by September 25, 2017. | |
| Contact | Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1138; fax: 425-227-1149. | |
| FR Citation | 82 FR 37360 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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