Airworthiness Directives; Airbus Airplanes, 16787-16792 [2018-07626]

Download as PDF 16787 Proposed Rules Federal Register Vol. 83, No. 74 Tuesday, April 17, 2018 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. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0277; Product Identifier 2017–NM–124–AD] RIN 2120–AA64 Examining the AD Docket Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2017–15– 17, which applies to certain Airbus Model A300 B4–600R series airplanes, Model A300 C4–605R Variant F airplanes, and Model A300 F4–600R series airplanes. AD 2017–15–17 requires an inspection of the lower area of a certain frame radius for cracking, and corrective action if necessary. Since we issued AD 2017–15–17, we have determined that repetitive inspections and applicable corrective actions are necessary. This proposed AD would add new repetitive inspections of the lower area of a certain frame radius for cracking, and corrective actions if necessary. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by June 1, 2018. 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 amozie on DSK30RV082PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 17:36 Apr 16, 2018 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. Jkt 244001 You may examine the AD docket on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0277; 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: Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3225. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2018–0277; Product Identifier 2017–NM–124–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 PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 substantive verbal contact we receive about this proposed AD. Discussion We issued AD 2017–15–17, Amendment 39–18977 (82 FR 35644, August 1, 2017) (‘‘AD 2017–15–17’’), for certain Airbus Model A300 B4–600R series airplanes, Model A300 C4–605R Variant F airplanes, and Model A300 F4–600R series airplanes. AD 2017–15– 17 was prompted by the detection of cracking that originated from the fastener holes in the forward fitting lower radius of frame (FR) 40. AD 2017– 15–17 requires an inspection of the lower area of a certain frame radius for cracking, and corrective action if necessary. We issued AD 2017–15–17 to detect and correct cracking in the forward fitting lower radius of FR 40. Such cracking could reduce the structural integrity of the fuselage. Since we issued AD 2017–15–17, we have determined that new repetitive inspections of the lower area of a certain frame radius for cracking, and corrective actions are necessary. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2017–0158, dated August 25, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A300 B4–600R series airplanes, Model A300 C4–605R Variant F airplanes, and Model A300 F4–600R series airplanes. The MCAI states: Following a full stress analysis of the Frame (FR) 40 lower area, supported by a Finite Element Model (FEM), of the post-mod [modification] 10221 configuration, it was demonstrated that, for the FR40 forward fitting lower radius, a crack could occur after a certain number of flight cycles (FC). This condition, if not detected and corrected, could reduce the structural integrity of the fuselage. To address this potential unsafe condition, Airbus established that crack detection could be achieved through a special detailed inspection (SDI) using a high frequency eddy current (HFEC) method, and issued Alert Operators Transmission (AOT) A57W009–16 to provide those inspection instructions. Consequently, EASA issued AD 2016–0085 to require a one-time SDI of the FR40 lower area and, depending on findings, accomplishment of applicable corrective action(s). After that [EASA] AD was issued, further cracks were detected, originating from E:\FR\FM\17APP1.SGM 17APP1 16788 Federal Register / Vol. 83, No. 74 / Tuesday, April 17, 2018 / Proposed Rules the fastener hole, and, based on these findings, it was determined that the inspection area must be enlarged, and Airbus issued AOT A57W009–16 Revision (Rev.) 01 accordingly. Consequently, EASA issued AD 2016–0179 [which corresponds to FAA AD 2017–15–17], retaining the requirements of EASA AD 2016–0085, which was superseded, to extend the area of inspection, and to require an additional inspection for aeroplanes that were previously inspected. The one-time SDI for high cycle A300–600 aeroplanes was intended to mitigate the highest risks within the fleet, pending development of instructions for repetitive inspections. Since EASA AD 2016–0179 was issued, Airbus published SB A300–57–6120 * * * [for] the inspection programme for A300–600 * * * post-mod 10221 * * * [airplanes]. The AOT one-time inspection is superseded by these repetitive inspection SBs. These SBs include alternative inspection methods and repair solutions in case of findings together with the associated inspection programme. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2016–0179, which is superseded, * * * and defines new inspections methods with new compliance times, including repetitive inspections, depending on the aeroplane inspection status. 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–2018– 0277. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A300–57–6120, including Appendices 1 through 7, dated April 28, 2017. This service information describes procedures for repetitive inspections of the forward fitting lower radius of FR 40 for cracking, and corrective action. 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. amozie on DSK30RV082PROD with PROPOSALS 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 design. VerDate Sep<11>2014 17:36 Apr 16, 2018 Jkt 244001 Costs of Compliance We estimate that this proposed AD affects 94 airplanes of U.S. registry. The actions required by AD 2017–15– 17, and retained in this proposed AD, take about 4 work-hours per product, at an average labor rate of $85 per workhour. Based on these figures, the estimated cost of the actions that are required by AD 2017–15–17 is $340 per product. We also estimate that it would take about 4 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $31,960, or $340 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. Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this AD is 2120–0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW, Washington, DC 20591, ATTN: Information Collection Clearance Officer, AES–200. 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 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. Authority for This Rulemaking The Proposed Amendment 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 Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2017–15–17, Amendment 39–18977 (82 ■ E:\FR\FM\17APP1.SGM 17APP1 Federal Register / Vol. 83, No. 74 / Tuesday, April 17, 2018 / Proposed Rules Airbus: Docket No. FAA–2018–0277; Product Identifier 2017–NM–124–AD. (a) Comments Due Date We must receive comments by June 1, 2018. (f) Compliance (b) Affected ADs This AD replaces AD 2017–15–17, Amendment 39–18977 (82 FR 35644, August 1, 2017) (‘‘AD 2017–15–17’’). (c) Applicability This AD applies to Airbus airplanes, certificated in any category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, on which Airbus Modification 10221 was embodied in production. (1) Airbus Model A300 B4–605R and B4– 622R airplanes. (2) Airbus Model A300 C4–605R Variant F airplanes. (3) Airbus Model A300 F4–605R and F4– 622R airplanes. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason amozie on DSK30RV082PROD with PROPOSALS This AD was prompted by the detection of cracking that originated from the fastener VerDate Sep<11>2014 17:36 Apr 16, 2018 Jkt 244001 holes in the forward fitting lower radius of frame (FR) 40. We are issuing this AD to detect and correct cracking in the forward fitting lower radius of FR 40. Such cracking could reduce the structural integrity of the fuselage. Comply with this AD within the compliance times specified, unless already done. (g) Definitions (1) For the purpose of this AD, the average flight time (AFT) can be established by dividing the flight hours (FHs) by the flight cycles (FCs) counted: (i) From first flight, for selecting the inspection threshold of the non-repaired area, (ii) From repair, for selecting the inspection threshold of the repaired area, (iii) From the last inspection, for selecting the inspection interval. (2) For the purpose of this AD, Group 1 airplanes are those airplanes already inspected in accordance with paragraph 4.2.2 in Alert Operators Transmission (AOT) A57W009–16, Revision 01, dated July 13, 2016, before the effective date of this AD. Group 2 airplanes are those airplanes not inspected in accordance with paragraph 4.2.2 in AOT A57W009–16, Revision 01, dated PO 00000 Frm 00003 Fmt 4702 Sfmt 4725 July 13, 2016, as of the effective date of this AD. (3) For the purpose of this AD, inspection method A is a high frequency (HFEC) inspection of the radius and fastener area. Inspection method B is a HFEC inspection of the radius and fastener area and a rototest of the fastener hole. Both are defined as a special detailed inspection (SDI) in this AD. (h) Repetitive Inspections for Non-Repaired Areas Within the compliance time specified in table 1 to paragraph (h) of this AD (Group 1 airplanes) or table 2 to paragraph (h) of this AD (Group 2 airplanes), as applicable, and, thereafter, at intervals not exceeding the values specified in table 3 to paragraph (h) of this AD, do a SDI for cracking of any nonrepaired radius, fastener areas, and fastener holes, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–57–6120, including Appendices 1 through 7, dated April 28, 2017; except where Airbus Service Bulletin A300–57–6120, including Appendices 1 through 7, dated April 28, 2017, specifies contacting Airbus for appropriate action, before further flight, obtain instructions using the procedures specified in paragraph (l) of this AD and accomplish those instructions. BILLING CODE 4910–13–P E:\FR\FM\17APP1.SGM 17APP1 EP17AP18.008</GPH> FR 35644, August 1, 2017), and adding the following new AD: 16789 16790 Federal Register / Vol. 83, No. 74 / Tuesday, April 17, 2018 / Proposed Rules Table 2 to Paragraph (h) of this AD- Group 2 Inspection Thresholds- Non-repaired Areas AFT Compliance Time (whichever occurs later, A orB) A: Before exceeding 14,700 FC or 31,900 FH since first flight of the airplane, whichever occurs first. B: Within 12 months after the effective Greater than 1. 5 date of this AD, without exceeding (whichever occurs later): - 19,000 FC or 41,000 FH, whichever occurs first since airplane first flight. - 300 FC or 630 FH, whichever occurs first after September 5, 2017 (the effective date of AD 2017-15-17). A: Before exceeding 15,900 FC or 23,900 FH since first flight of the airplane, whichever occurs first. 1.5 or less B: Within 12 months after the effective date of this AD, without exceeding (whichever occurs later): - 19,000 FC or 41,000 FH, whichever occurs first since airplane first flight. VerDate Sep<11>2014 17:36 Apr 16, 2018 Jkt 244001 PO 00000 Frm 00004 Fmt 4702 Sfmt 4725 E:\FR\FM\17APP1.SGM 17APP1 EP17AP18.009</GPH> amozie on DSK30RV082PROD with PROPOSALS - 300 FC or 630 FH, whichever occurs first after September 5, 2017 (the effective date of AD 2017-15-17). Federal Register / Vol. 83, No. 74 / Tuesday, April 17, 2018 / Proposed Rules (j) Corrective Action If any crack is found during any inspection required by paragraph (h) or (i) of this AD: Before further flight, repair in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–57–6120, including Appendices 1 through 7, dated April 28, 2017. amozie on DSK30RV082PROD with PROPOSALS (k) Reporting Submit a report of the findings (both positive and negative) of each inspection required by paragraph (h) and (i) of this AD to Airbus, in accordance with the instructions of Airbus Service Bulletin A300– 57–6120, including Appendices 1 through 7, dated April 28, 2017, at the applicable time specified in paragraph (k)(1) or (k)(2) of this AD. (1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection. (2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. VerDate Sep<11>2014 17:36 Apr 16, 2018 Jkt 244001 cracking of the repaired radius, fastener areas, and fastener holes, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–57–6120, including Appendices 1 through 7, dated April 28, 2017; except where Airbus Service Bulletin A300–57–6120, including Appendices 1 through 7, dated April 28, 2017, specifies contacting Airbus for appropriate action, before further flight, obtain instructions using the procedures specified in paragraph (l) of this AD and accomplish those instructions. (l) Other FAA AD Provisions (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 International Section, send it to the attention of the person identified in paragraph (m)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@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 European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as required by paragraphs (g) and (h) 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. PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2017–0158, dated August 25, 2017, for related information. This MCAI may be found in the AD docket E:\FR\FM\17APP1.SGM 17APP1 EP17AP18.011</GPH> (i) Repetitive Inspections for Repaired Areas Within the compliance time values as specified in table 4 to paragraph (i) of this AD, and, thereafter, at intervals not exceeding those same values, do a SDI for EP17AP18.010</GPH> BILLING CODE 4910–13–C 16791 16792 Federal Register / Vol. 83, No. 74 / Tuesday, April 17, 2018 / Proposed Rules on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2018–0277. (2) For more information about this AD, contact Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206– 231–3225. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; internet http://www.airbus.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. Issued in Des Moines, Washington, on March 30, 2018. Chris Spangenberg, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–07626 Filed 4–16–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0271; Product Identifier 2017–NM–111–AD] RIN 2120–AA64 Examining the AD Docket Airworthiness Directives; Saab AB, Saab Aeronautics (Formerly Known as Saab AB, Saab Aerosystems) Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2016–13– 06, which applies to certain Saab AB, Saab Aeronautics Model 340A (SAAB/ SF340A) and SAAB 340B airplanes. AD 2016–13–06 requires a revision of the applicable airplane flight manual (AFM), repetitive inspections of the horizontal stabilizer de-icing boots, and applicable corrective actions. Since we issued AD 2016–13–06, the manufacturer has developed an improved de-icing boot. This proposed AD would continue to require a revision of the applicable AFM, repetitive inspections of the horizontal stabilizer de-icing boots, and applicable corrective actions. This proposed AD would also require replacement of single stitched de-icing boots with improved double stitched boots, and re-identification of amozie on DSK30RV082PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 17:36 Apr 16, 2018 the modified horizontal stabilizer leading edge. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by June 1, 2018. 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 Saab AB, Saab ¨ Aeronautics, SE–581 88, Linkoping, Sweden; telephone: +46 13 18 5591; fax: +46 13 18 4874; email: saab340techsupport@saabgroup.com; internet: http://www.saabgroup.com. You may view this referenced service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. Jkt 244001 You may examine the AD docket on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0271; 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: Shahram Daneshmandi, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax: 206–231–3220. 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– PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 2018–0271; Product Identifier 2017– NM–111–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 We issued AD 2016–13–06, Amendment 39–18570 (81 FR 41432, June 27, 2016) (‘‘AD 2016–13–06’’), for certain Saab AB, Saab Aeronautics Model 340A (SAAB/SF340A) and SAAB 340B airplanes. AD 2016–13–06 was prompted by reports of ruptured horizontal stabilizer de-icing boots. AD 2016–13–06 requires a revision of the applicable AFM, repetitive inspections of the horizontal stabilizer de-icing boots, and applicable corrective actions. We issued AD 2016–13–06 to detect and correct damage of the de-icing boot; such damage could lead to a ruptured boot, severe vibrations, and possible reduced control of the airplane. Since we issued AD 2016–13–06, the manufacturer has developed an improved de-icing boot, reinforced through double stitch lines. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2017–0144, dated August 9, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Saab AB, Saab Aeronautics Model 340A (SAAB/SF340A) and SAAB 340B airplanes. The MCAI states: Several occurrences were reported of rupture of the horizontal stabilizer de-icing boot in flight. In some of the reported events, the de-icing boot had formed a large open scoop. This condition, if not detected and corrected, could lead to complete loss of the de-icing function within its associated zone and severe vibrations, possibly resulting in reduced control of the aeroplane. To address this potential unsafe condition, Saab AB, Aeronautics (hereafter referred to as ‘‘Saab’’ in this [EASA] AD) issued Alert Operations Bulletin (AOB) No. 12 and AOB No. 23 as temporary measures, recommending to select Flaps 0 for landing in the event of a suspected rupture of the deicing boot on the horizontal stabilizer. In addition, Saab issued SB [Service Bulletin] 340–30–094 providing instructions for inspection of de-icing boots. E:\FR\FM\17APP1.SGM 17APP1

Agencies

[Federal Register Volume 83, Number 74 (Tuesday, April 17, 2018)]
[Proposed Rules]
[Pages 16787-16792]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-07626]


========================================================================
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. 83, No. 74 / Tuesday, April 17, 2018 / 
Proposed Rules

[[Page 16787]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0277; Product Identifier 2017-NM-124-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) 2017-15-
17, which applies to certain Airbus Model A300 B4-600R series 
airplanes, Model A300 C4-605R Variant F airplanes, and Model A300 F4-
600R series airplanes. AD 2017-15-17 requires an inspection of the 
lower area of a certain frame radius for cracking, and corrective 
action if necessary. Since we issued AD 2017-15-17, we have determined 
that repetitive inspections and applicable corrective actions are 
necessary. This proposed AD would add new repetitive inspections of the 
lower area of a certain frame radius for cracking, and corrective 
actions if necessary. We are proposing this AD to address the unsafe 
condition on these products.

DATES: We must receive comments on this proposed AD by June 1, 2018.

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--EAW, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 
51; email [email protected]; internet http://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. 
For information on the availability of this material at the FAA, call 
206-231-3195.

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-2018-
0277; 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: Dan Rodina, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3225.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2018-0277; 
Product Identifier 2017-NM-124-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

    We issued AD 2017-15-17, Amendment 39-18977 (82 FR 35644, August 1, 
2017) (``AD 2017-15-17''), for certain Airbus Model A300 B4-600R series 
airplanes, Model A300 C4-605R Variant F airplanes, and Model A300 F4-
600R series airplanes. AD 2017-15-17 was prompted by the detection of 
cracking that originated from the fastener holes in the forward fitting 
lower radius of frame (FR) 40. AD 2017-15-17 requires an inspection of 
the lower area of a certain frame radius for cracking, and corrective 
action if necessary. We issued AD 2017-15-17 to detect and correct 
cracking in the forward fitting lower radius of FR 40. Such cracking 
could reduce the structural integrity of the fuselage.
    Since we issued AD 2017-15-17, we have determined that new 
repetitive inspections of the lower area of a certain frame radius for 
cracking, and corrective actions are necessary.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2017-0158, dated August 25, 2017 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for certain Airbus Model A300 B4-600R 
series airplanes, Model A300 C4-605R Variant F airplanes, and Model 
A300 F4-600R series airplanes. The MCAI states:

    Following a full stress analysis of the Frame (FR) 40 lower 
area, supported by a Finite Element Model (FEM), of the post-mod 
[modification] 10221 configuration, it was demonstrated that, for 
the FR40 forward fitting lower radius, a crack could occur after a 
certain number of flight cycles (FC).
    This condition, if not detected and corrected, could reduce the 
structural integrity of the fuselage.
    To address this potential unsafe condition, Airbus established 
that crack detection could be achieved through a special detailed 
inspection (SDI) using a high frequency eddy current (HFEC) method, 
and issued Alert Operators Transmission (AOT) A57W009-16 to provide 
those inspection instructions.
    Consequently, EASA issued AD 2016-0085 to require a one-time SDI 
of the FR40 lower area and, depending on findings, accomplishment of 
applicable corrective action(s). After that [EASA] AD was issued, 
further cracks were detected, originating from

[[Page 16788]]

the fastener hole, and, based on these findings, it was determined 
that the inspection area must be enlarged, and Airbus issued AOT 
A57W009-16 Revision (Rev.) 01 accordingly. Consequently, EASA issued 
AD 2016-0179 [which corresponds to FAA AD 2017-15-17], retaining the 
requirements of EASA AD 2016-0085, which was superseded, to extend 
the area of inspection, and to require an additional inspection for 
aeroplanes that were previously inspected.
    The one-time SDI for high cycle A300-600 aeroplanes was intended 
to mitigate the highest risks within the fleet, pending development 
of instructions for repetitive inspections.
    Since EASA AD 2016-0179 was issued, Airbus published SB A300-57-
6120 * * * [for] the inspection programme for A300-600 * * * post-
mod 10221 * * * [airplanes]. The AOT one-time inspection is 
superseded by these repetitive inspection SBs. These SBs include 
alternative inspection methods and repair solutions in case of 
findings together with the associated inspection programme.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2016-0179, which is superseded, * * * and 
defines new inspections methods with new compliance times, including 
repetitive inspections, depending on the aeroplane inspection 
status.

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-2018-
0277.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A300-57-6120, including 
Appendices 1 through 7, dated April 28, 2017. This service information 
describes procedures for repetitive inspections of the forward fitting 
lower radius of FR 40 for cracking, and corrective action. 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 design.

Costs of Compliance

    We estimate that this proposed AD affects 94 airplanes of U.S. 
registry.
    The actions required by AD 2017-15-17, and retained in this 
proposed AD, take about 4 work-hours per product, at an average labor 
rate of $85 per work-hour. Based on these figures, the estimated cost 
of the actions that are required by AD 2017-15-17 is $340 per product.
    We also estimate that it would take about 4 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $31,960, or $340 
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.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the FAA 
at 800 Independence Ave. SW, Washington, DC 20591, ATTN: Information 
Collection Clearance Officer, AES-200.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.
    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 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 removing Airworthiness Directive (AD) 
2017-15-17, Amendment 39-18977 (82

[[Page 16789]]

FR 35644, August 1, 2017), and adding the following new AD:

Airbus: Docket No. FAA-2018-0277; Product Identifier 2017-NM-124-AD.

(a) Comments Due Date

    We must receive comments by June 1, 2018.

(b) Affected ADs

    This AD replaces AD 2017-15-17, Amendment 39-18977 (82 FR 35644, 
August 1, 2017) (``AD 2017-15-17'').

(c) Applicability

    This AD applies to Airbus airplanes, certificated in any 
category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of 
this AD, on which Airbus Modification 10221 was embodied in 
production.
    (1) Airbus Model A300 B4-605R and B4-622R airplanes.
    (2) Airbus Model A300 C4-605R Variant F airplanes.
    (3) Airbus Model A300 F4-605R and F4-622R airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by the detection of cracking that 
originated from the fastener holes in the forward fitting lower 
radius of frame (FR) 40. We are issuing this AD to detect and 
correct cracking in the forward fitting lower radius of FR 40. Such 
cracking could reduce the structural integrity of the fuselage.

(f) Compliance

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

(g) Definitions

    (1) For the purpose of this AD, the average flight time (AFT) 
can be established by dividing the flight hours (FHs) by the flight 
cycles (FCs) counted:
    (i) From first flight, for selecting the inspection threshold of 
the non-repaired area,
    (ii) From repair, for selecting the inspection threshold of the 
repaired area,
    (iii) From the last inspection, for selecting the inspection 
interval.
    (2) For the purpose of this AD, Group 1 airplanes are those 
airplanes already inspected in accordance with paragraph 4.2.2 in 
Alert Operators Transmission (AOT) A57W009-16, Revision 01, dated 
July 13, 2016, before the effective date of this AD. Group 2 
airplanes are those airplanes not inspected in accordance with 
paragraph 4.2.2 in AOT A57W009-16, Revision 01, dated July 13, 2016, 
as of the effective date of this AD.
    (3) For the purpose of this AD, inspection method A is a high 
frequency (HFEC) inspection of the radius and fastener area. 
Inspection method B is a HFEC inspection of the radius and fastener 
area and a rototest of the fastener hole. Both are defined as a 
special detailed inspection (SDI) in this AD.

(h) Repetitive Inspections for Non-Repaired Areas

    Within the compliance time specified in table 1 to paragraph (h) 
of this AD (Group 1 airplanes) or table 2 to paragraph (h) of this 
AD (Group 2 airplanes), as applicable, and, thereafter, at intervals 
not exceeding the values specified in table 3 to paragraph (h) of 
this AD, do a SDI for cracking of any non-repaired radius, fastener 
areas, and fastener holes, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-57-6120, including 
Appendices 1 through 7, dated April 28, 2017; except where Airbus 
Service Bulletin A300-57-6120, including Appendices 1 through 7, 
dated April 28, 2017, specifies contacting Airbus for appropriate 
action, before further flight, obtain instructions using the 
procedures specified in paragraph (l) of this AD and accomplish 
those instructions.
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(i) Repetitive Inspections for Repaired Areas

    Within the compliance time values as specified in table 4 to 
paragraph (i) of this AD, and, thereafter, at intervals not 
exceeding those same values, do a SDI for cracking of the repaired 
radius, fastener areas, and fastener holes, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-57-6120, 
including Appendices 1 through 7, dated April 28, 2017; except where 
Airbus Service Bulletin A300-57-6120, including Appendices 1 through 
7, dated April 28, 2017, specifies contacting Airbus for appropriate 
action, before further flight, obtain instructions using the 
procedures specified in paragraph (l) of this AD and accomplish 
those instructions.
[GRAPHIC] [TIFF OMITTED] TP17AP18.011

(j) Corrective Action

    If any crack is found during any inspection required by 
paragraph (h) or (i) of this AD: Before further flight, repair in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-57-6120, including Appendices 1 through 7, dated April 
28, 2017.

(k) Reporting

    Submit a report of the findings (both positive and negative) of 
each inspection required by paragraph (h) and (i) of this AD to 
Airbus, in accordance with the instructions of Airbus Service 
Bulletin A300-57-6120, including Appendices 1 through 7, dated April 
28, 2017, at the applicable time specified in paragraph (k)(1) or 
(k)(2) of this AD.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 30 days after the effective date of 
this AD.

(l) Other FAA AD Provisions

    (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 International Section, send it to the attention of 
the person identified in paragraph (m)(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 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.
    (3) Required for Compliance (RC): Except as required by 
paragraphs (g) and (h) 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.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2017-0158, dated August 25, 
2017, for related information. This MCAI may be found in the AD 
docket

[[Page 16792]]

on the internet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2018-0277.
    (2) For more information about this AD, contact Dan Rodina, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 
and fax 206-231-3225.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; email [email protected]; 
internet http://www.airbus.com. You may view this service 
information at the FAA, Transport Standards Branch, 2200 South 216th 
St., Des Moines, WA. For information on the availability of this 
material at the FAA, call 206-231-3195.

    Issued in Des Moines, Washington, on March 30, 2018.
Chris Spangenberg,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-07626 Filed 4-16-18; 8:45 am]
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