Airworthiness Directives; Airbus SAS Airplanes, 26781-26785 [2019-11896]

Download as PDF khammond on DSKBBV9HB2PROD with PROPOSALS Federal Register / Vol. 84, No. 111 / Monday, June 10, 2019 / Proposed Rules Boeing Service Bulletin 737–28A1216, or within 12 months after the most recent inspection was performed as specified in AWL No. 28–AWL–20, whichever is later. (iv) For AWL No. 28–AWL–21, ‘‘Auxiliary Tank Fuel Boost Pump Automatic Shutoff System’’: Within 12 months after accomplishment of the actions specified in Boeing Service Bulletin 737–28A1216, or within 12 months after the most recent inspection was performed as specified in AWL No. 28–AWL–21, whichever is later. (v) For AWL No. 28–AWL–22, ‘‘OverCurrent and Arcing Protection Electrical Design Features Operation—Boost Pump Ground Fault Interrupter (GFI)’’: Within 12 months after accomplishment of the actions specified in Boeing Service Bulletin 737– 28A1212, or within 12 months after the most recent inspection was performed as specified in AWL No. 28–AWL–22, whichever is later. (vi) For AWL No. 28–AWL–23, ‘‘Center Tank Fuel Boost Pump Power Failed On Protection System’’: Within 12 months after accomplishment of the actions specified in Boeing Service Bulletin 737–28A1227, or within 12 months after the most recent inspection was performed as specified in AWL No. 28–AWL–23, whichever is later. (vii) For AWL No. 28–AWL–24, ‘‘Auxiliary Fuel Tank Boost Pump Power Failed On Protection System’’: Within 12 months after accomplishment of the actions specified in Boeing Service Bulletin 737–28A1227, or within 12 months after the most recent inspection was performed as specified in AWL No. 28–AWL–24, whichever is later. (viii) For AWL No. 28–AWL–27, ‘‘AC Fuel Boost Pump Installation’’: Within 72 months after the most recent inspection was performed as specified in AWL No. 28– AWL–27, or within 12 months after the effective date of this AD if no inspection has been performed in the last 72 months. (ix) For AWL No. 28–AWL–31, ‘‘Cushion Clamps and Teflon Sleeving Installed on Outof-Tank Wire Bundles Installed on Brackets that are Mounted Directly on the Fuel Tanks’’: Within 144 months after accomplishment of the actions specified in Boeing Service Bulletin 737–28A1228. (x) For AWL No. 47–AWL–04, ‘‘Nitrogen Generation System (NGS)—Thermal Switch’’: Within 22,500 flight hours after accomplishment of the actions specified in Boeing Service Bulletin 737–47–1005; within 22,500 flight hours after accomplishment of the actions specified in Boeing Service Bulletin 737–47–1008; or within 22,500 flight hours after the most recent inspection was performed as specified in AWL No. 47– AWL–04; whichever is latest. (xi) For AWL No. 47–AWL–05, ‘‘Nitrogen Generation System (NGS)—Nitrogen Enriched Air (NEA) Distribution Ducting Integrity’’: Within 14,500 flight hours after accomplishment of the actions specified in Boeing Service Bulletin 737–47–1005; within 14,500 flight hours after accomplishment of the actions specified in Boeing Service Bulletin 737–47–1008; or within 14,500 flight hours after the most recent inspection was performed as specified in AWL No. 47– AWL–05; whichever is latest. VerDate Sep<11>2014 16:18 Jun 07, 2019 Jkt 247001 (h) Additional Acceptable Wire Types and Sleeving As an option, when accomplishing the actions required by paragraph (g) of this AD, the changes specified in paragraphs (h)(1) and (h)(2) of this AD are acceptable. (1) Where AWL No. 28–AWL–05 identifies wire types BMS 13–48, BMS 13–58, and BMS 13–60, the following wire types are acceptable: MIL–W–22759/16, SAE AS22759/16 (M22759/16), MIL–W–22759/32, SAE AS22759/32 (M22759/32), MIL–W– 22759/34, SAE AS22759/34 (M22759/34), MIL–W–22759/41, SAE AS22759/41 (M22759/41), MIL–W–22759/86, SAE AS22759/86 (M22759/86), MIL–W–22759/87, SAE AS22759/87 (M22759/87), MIL–W– 22759/92, and SAE AS22759/92 (M22759/ 92); and MIL–C–27500 and NEMA WC 27500 cables constructed from these military or SAE specification wire types, as applicable. (2) Where AWL No. 28–AWL–05 identifies TFE–2X Standard wall for wire sleeving, the following sleeving materials are acceptable: Roundit 2000NX and Varglas Type HO, HP, or HM. (i) No Alternative Actions, Intervals, or Critical Design Configuration Control Limitations (CDCCLs) After the existing maintenance or inspection program has been revised as required by paragraph (g) of this AD, no alternative actions (e.g., inspections), intervals, or CDCCLs may be used unless the actions, intervals, and CDCCLs are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (k) of this AD. (j) Terminating Actions for Certain AD Requirements Accomplishment of the revision required by paragraph (g) of this AD terminates the requirements specified in paragraphs (j)(1) through (j)(6) of this AD for that airplane: (1) All requirements of AD 2008–10–09 R1. (2) The revision required by paragraph (l) of AD 2011–12–09. (3) The revision required by paragraph (h) of AD 2013–13–15. (4) The revision required by paragraph (j) of AD 2013–25–05. (5) The revisions required by paragraphs (l) and (n) of AD 2016–18–16. (6) The revision required by paragraph (h) of AD 2017–17–09. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles ACO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (l)(2) of this AD. Information may be emailed to: 9ANM-LAACO-AMOC-Requests@faa.gov. (2) 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. PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 26781 (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO Branch, FAA, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (l) Related Information (1) For more information about this AD, contact Jeffrey Rothman, Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206–231–3558; email: jeffrey.rothman@faa.gov. (2) For information about AMOCs, contact Serj Harutunian, Aerospace Engineer, Propulsion Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627– 5254; fax: 562–627–5210; email: serj.harutunian@faa.gov. (3) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; phone: 562–797–1717; internet: https:// www.myboeingfleet.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 May 20, 2019. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2019–11925 Filed 6–7–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0402; Product Identifier 2019–NM–008–AD] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2005–17– 14, which applies to all Airbus SAS Model A300 series airplanes; Model A300 B4–600, B4–600R, and F4–600R series airplanes, and Model A300 C4– SUMMARY: E:\FR\FM\10JNP1.SGM 10JNP1 khammond on DSKBBV9HB2PROD with PROPOSALS 26782 Federal Register / Vol. 84, No. 111 / Monday, June 10, 2019 / Proposed Rules 605R Variant F airplanes (collectively called Model A300–600 series airplanes); and Model A310 series airplanes. AD 2005–17–14 requires repetitive tests to detect desynchronization of the rudder servo actuators, and adjustment or replacement of the spring rods of the rudder servo actuators, if necessary. AD 2005–17–14 also requires repetitive tests/inspections/analyses of the rudder servo actuators, and related investigative/corrective actions if necessary. Since we issued AD 2005– 17–14, analyses of the inspection results indicated that the assumptions made to establish the survey campaign were not adequate, and a new investigation determined the existing inspection procedures and compliance times do not adequately address the unsafe condition. This proposed AD would retain some requirements of AD 2005– 17–14 and revise the inspection procedures and compliance times, as specified in an European Aviation Safety Agency (EASA) AD, which will be incorporated by reference. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by July 25, 2019. 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 https://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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For the incorporation by reference (IBR) material described in the ‘‘Related IBR material under 1 CFR part 51’’ section in SUPPLEMENTARY INFORMATION, contact the EASA, Konrad-AdenauerUfer 3, 50668 Cologne, Germany; telephone +49 221 89990 1000; email ADs@easa.europa.eu; internet www.easa.europa.eu. You may find this IBR material on the EASA website at https://ad.easa.europa.eu. You may view this IBR material 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. VerDate Sep<11>2014 16:18 Jun 07, 2019 Jkt 247001 It is also available in the AD docket on the internet at https:// www.regulations.gov. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2019– 0402; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations (telephone 800–647–5527) is listed above. 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 proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2019–0402; Product Identifier 2019– NM–008–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this NPRM. Discussion We issued AD 2005–17–14, Amendment 39–14235 (70 FR 50157, August 26, 2005) (‘‘AD 2005–17–14’’), for all Airbus SAS Model A300 series airplanes, Model A300–600 series airplanes, and Model A310 series airplanes. AD 2005–17–14 requires repetitive tests to detect desynchronization of the rudder servo actuators, and adjustment or replacement of the spring rods of the rudder servo actuators, if necessary; and repetitive tests, inspections, and analyses of the rudder servo actuators, and related investigative and corrective actions if necessary. AD 2005–17–14 resulted from new reports of desynchronization of the rudder servo PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 actuators. We issued AD 2005–17–14 to address desynchronization of one of the three rudder servo actuators, which, if combined with an engine failure, could result in the loss of the related hydraulic system and could cause the loss of one of the two synchronized actuators. This condition could create additional fatigue loading and possible cracking of the attachment fittings and could result in the inability of the remaining synchronized actuator to maintain the commanded rudder deflection, leading to reduced controllability of the airplane. Actions Since AD 2005–17–14 Was Issued Since we issued AD 2005–17–14, EASA reported that analyses of the inspection results indicate that the assumptions made in 2004 to establish the survey campaign were not adequate. This determination led to investigation and revision of the service information with revised inspection instructions and compliance times, depending on airplane configuration. The EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2019–0017, dated January 29, 2019 (‘‘EASA AD 2019–0017’’) (also referred to as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus SAS Model A300 series airplanes, Model A300–600 series airplanes, and Model A310 series airplanes. The MCAI states: Numerous occurrences were reported of rudder servo control de-synchronization, some of which had caused structural damages to the fin or side fittings of the rudder actuator attachments. Analyses revealed that a de-synchronization of the rudder servo control induced by misalignment of the three servo controls, or by thermal expansion, can provoke opposing loads. This condition, if not detected and corrected, could induce failure of rudderassociated systems, possibly resulting in reduced control of the aeroplane. Previously, DGAC [Direction Ge´ne´rale de l’Aviation Civile] France issued AD F–2004– 063 for A300–600ST aeroplanes, and AD F– 2004–092 (EASA approval 2004–6368) [which corresponds to FAA AD 2005–17–14] for A300, A310 and A300–600 aeroplanes, to require repetitive inspections of rudder servo controls, fin box and rudder structures, and, depending on findings, accomplishment of applicable corrective action(s). Since those ADs were issued, analyses of the inspection results indicate that the assumptions made in 2004 to establish the survey campaign were not adequate. This determination induced new investigation and ATA 55 SBs [service bulletins] revision with new inspection instructions and new E:\FR\FM\10JNP1.SGM 10JNP1 26783 Federal Register / Vol. 84, No. 111 / Monday, June 10, 2019 / Proposed Rules compliance times, depending on aeroplane configuration. For the reason described above, this [EASA] AD retains partially the requirements of DGAC France AD F–2004–063 and AD F– 2004–092 (EASA approval 2004–6368), which are superseded, and requires the new inspections (latest SB revision) at new intervals. The new repetitive intervals for the inspections specified in paragraph (2) of EASA AD 2019–0017 range from 300 flight cycles to 6,000 flight cycles, depending on inspection type. Explanation of Retained Requirements Although this proposed AD does not explicitly restate the requirements of AD 2005–17–14, this proposed AD would retain certain requirements of AD 2005– 17–14. Those requirements are referenced in EASA AD 2019–0017, which, in turn, is referenced in paragraph (g) of this proposed AD. Related IBR Material Under 1 CFR Part 51 EASA AD 2019–0017 describes procedures for repetitive inspections of the rudder servo actuators and related investigative/corrective actions. Related investigative actions include repetitive inspections of fin box and rudder servo controls. Corrective actions include repair. This material 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 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. Proposed Requirements of This NPRM This proposed AD would require accomplishing the actions specified in EASA AD 2019–0017 described previously, as incorporated by reference, except for any differences identified as exceptions in the regulatory text of this AD and except as discussed under ‘‘Differences Between this Proposed AD and the MCAI.’’ Explanation of Required Compliance Information In the FAA’s ongoing efforts to improve the efficiency of the AD process, the FAA worked with Airbus and EASA to develop a process to use certain EASA ADs as the primary source of information for compliance with requirements for corresponding FAA ADs. As a result, EASA AD 2019–0017 will be incorporated by reference in the FAA final rule. This proposed AD would, therefore, require compliance with the provisions specified in EASA AD 2019–0017, except for any differences identified as exceptions in the regulatory text of this proposed AD. Service information specified in EASA AD 2019–0017 that is required for compliance with EASA AD 2019–0017 will be available on the internet https:// www.regulations.gov by searching for and locating Docket No. FAA–2019– 0402 after the FAA final rule is published. Differences Between This Proposed AD and the MCAI Where paragraph (4) of EASA AD 2019–0017 refers to ‘‘during any inspection as required by paragraph (2) of this AD,’’ this proposed AD would require using ‘‘during any inspection as required by paragraph (2) or (3) of this AD.’’ EASA AD 2019–0017 did not specify a corrective action for the inspections required by paragraph (3) of EASA AD 2019–0017. Costs of Compliance We estimate that this proposed AD affects 133 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS FOR REQUIRED ACTIONS * Action Labor cost Retained actions from AD 2005–17–14 ......... New proposed actions .................................... 1 work-hour × $85 per hour = $85 ................. 2 work-hours × $85 per hour = $85 ............... Cost per product Parts cost $0 0 $85 170 Cost on U.S. operators $11,305 22,610 * Table does not include estimated costs for reporting. We estimate that it would take about 1 work-hour per product to comply with the proposed reporting requirement in this proposed AD. The average labor rate is $85 per hour. Based on these figures, we estimate the cost of reporting the inspection results on U.S. operators to be $11,305, or $85 per product. We estimate the following costs to do any necessary on-condition inspections that would be required based on the results of any required actions. We have no way of determining the number of aircraft that might need these oncondition actions: khammond on DSKBBV9HB2PROD with PROPOSALS ESTIMATED COSTS OF ON-CONDITION ACTIONS Labor cost Parts cost Cost per product 34 work-hours × $85 per hour = $2,890 ................................................................................................................. $0 $2,890 We have received no definitive data that would enable us to provide cost estimates for the on-condition repair specified in this proposed AD. VerDate Sep<11>2014 16:18 Jun 07, 2019 Jkt 247001 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 PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 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 NPRM is 2120–0056. The paperwork cost associated with this NPRM has been detailed in the Costs of E:\FR\FM\10JNP1.SGM 10JNP1 26784 Federal Register / Vol. 84, No. 111 / Monday, June 10, 2019 / Proposed Rules 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 NPRM 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 proposed 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 and associated appliances to the Director of the System Oversight Division. khammond on DSKBBV9HB2PROD with PROPOSALS 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; VerDate Sep<11>2014 16:18 Jun 07, 2019 Jkt 247001 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 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) 2005–17–14, Amendment 39–14235 (70 FR 50157, August 26, 2005), and adding the following new AD: ■ Airbus SAS: Docket No. FAA–2019–0402; Product Identifier 2019–NM–008–AD. (a) Comments Due Date We must receive comments by July 25, 2019. (b) Affected ADs This AD replaces AD 2005–17–14, Amendment 39–14235 (70 FR 50157, August 26, 2005) (‘‘AD 2005–17–14’’). (c) Applicability This AD applies to the Airbus SAS airplanes, certificated in any category, specified in paragraphs (c)(1) through (c)(3) of this AD, as identified in European Aviation Safety Agency (EASA) AD 2019– 0017, dated January 29, 2019 (‘‘EASA AD 2019–0017’’). (1) Model A300 B2–1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 airplanes. (2) Model A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R, F4–605R and F4–622R airplanes, and Model A300 C4– 605R Variant F airplanes. (3) Model A310–203, –204, –221, –222, –304, –322, –324, and –325 airplanes. (d) Subject Air Transport Association (ATA) of America Code 27, Flight controls; 55, Stabilizers. (e) Reason This AD was prompted by reports of desynchronization of the rudder servo PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 actuators. We are issuing this AD to address desynchronization of one of the three rudder servo actuators, which, if combined with an engine failure, could result in the loss of the related hydraulic system and could cause the loss of one of the two synchronized actuators. This condition could create additional fatigue loading and possible cracking of the attachment fittings and could result in the inability of the remaining synchronized actuator to maintain the commanded rudder deflection, leading to reduced controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Requirements Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2019–0017. (h) Exceptions to EASA AD 2019–0017 (1) For purposes of determining compliance with the requirements of this AD: Where EASA AD 2019–0017 refers to its effective date, this AD requires using the effective date of this AD. (2) For purposes of determining compliance with the requirements of this AD: Where paragraph (1) of EASA AD 2019–0017 specifies ‘‘after the last inspection as previously required by DGAC France AD F– 2004–092,’’ this AD requires using ‘‘after the most recent inspection done as specified in Airbus Service Bulletin A300–27–0188, Revision 2, dated October 1, 1997; A300–27– 6036, Revision 2, dated October 1, 1997; A300–55–0044, dated October 22, 1996; A300–55–6023, dated October 22, 1996; A310–27–2082, Revision 2, dated October 1, 1997; or A310–55–2026, dated October 22, 1996.’’ (3) For purposes of determining compliance with the requirements of this AD: Where paragraph (1) of EASA AD 2019–0017 refers to ‘‘the 03 July 2004,’’ this AD requires using ‘‘September 30, 2005’’ (the effective date of AD 2005–17–14). (4) For purposes of determining compliance with the requirements of this AD: Where paragraph (4) of EASA AD 2019–0017 refers to ‘‘during any inspection as required by paragraph (2) of this AD,’’ this AD requires using ‘‘during any inspection as required by paragraph (2) or (3) of this AD.’’ (5) Where any service information referenced in EASA AD 2019–0017 specifies reporting, this AD requires reporting all inspection results at the applicable time specified in paragraph (h)(5)(i) or (h)(5)(ii) of this AD. If operators have reported findings as part of obtaining any corrective actions approved by Airbus SAS’s EASA Design Organization Approval (DOA), operators are not required to report those findings as specified in this paragraph. (i) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection. (ii) 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. E:\FR\FM\10JNP1.SGM 10JNP1 Federal Register / Vol. 84, No. 111 / Monday, June 10, 2019 / Proposed Rules khammond on DSKBBV9HB2PROD with PROPOSALS (6) The ‘‘Remarks’’ section of EASA AD 2019–0017 does not apply to this AD. (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Section, send it to the attention of the person identified in paragraph (j)(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: For any requirement in this AD to obtain instructions from a manufacturer, the instructions must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOAauthorized signature. (3) Required for Compliance (RC): For any service information referenced in EASA AD 2019–0017 that contains RC procedures and tests: Except as required by paragraph (i)(2) of this AD, RC 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. (4) Paperwork Reduction Act Burden Statement: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 1 hour per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW, Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. VerDate Sep<11>2014 16:18 Jun 07, 2019 Jkt 247001 (j) Related Information (1) For information about EASA AD 2019– 0017, contact the EASA, Konrad-AdenauerUfer 3, 50668 Cologne, Germany; telephone +49 221 89990 6017; email ADs@ easa.europa.eu; Internet www.easa.europa.eu. You may find this EASA AD on the EASA website at https:// ad.easa.europa.eu. You may view this EASA AD 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. EASA AD 2019–0017 may be found in the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2019–0402. (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. Issued in Des Moines, Washington, on May 28, 2019. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2019–11896 Filed 6–7–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF THE INTERIOR Bureau of Indian Affairs 25 CFR Part 30 [190D0102DR/DS5A300000/ DR.5A311.IA000119] RIN 1076–AF13 Standards, Assessments, and Accountability System AGENCY: Bureau of Indian Affairs, Interior. Proposed rule and Tribal consultation. ACTION: The Bureau of Indian Education (BIE) is proposing a rule developed using a negotiated rulemaking process, as required by the 2015 Every Student Succeeds Act (ESSA), for implementation of the Secretary of the Interior’s obligation to define the standards, assessments, and accountability system consistent with ESSA for BIE-funded schools. DATES: Please submit comments by August 9, 2019. Please see ‘‘V. Consultation Schedule’’ of this preamble for dates of consultation sessions on this proposed rule. ADDRESSES: You may submit comments by any of the following methods: Federal rulemaking portal: https:// www.regulations.gov. The rule is listed under the agency name ‘‘Bureau of SUMMARY: PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 26785 Indian Affairs’’ under Docket BIA– 2016–0005. Email: comments@bia.gov. Include the number 1076–AF13 in the subject line of the message. Mail: Elizabeth Appel, Office of Regulatory Affairs & Collaborative Action, U.S. Department of the Interior, 1849 C Street NW, Mail Stop 4660, Washington, DC 20240. Include the number 1076–AF13 in the subject line of the message. Hand delivery: Elizabeth Appel, Office of Regulatory Affairs & Collaborative Action, U.S. Department of the Interior, 1849 C Street NW, Mail Stop 4660, Washington, DC 20240. Include the number 1076–AF13 in the subject line of the message. Docket: For access to the docket to read background documents or comments received, go to https:// www.regulations.gov and search for Docket Number BIA–2016–0005. We cannot ensure that comments received after the close of the comment period (see DATES) will be included in the docket for this rulemaking and considered. Comments on the information collections contained in this proposed regulation (see ‘‘Paperwork Reduction Act’’ section, below) are separate from those on the substance of the rule. Send comments on the information collection burden to OMB by facsimile to (202) 395–5806 or email to the OMB Desk Officer for the Department of the Interior at OIRA_DOCKET@ omb.eop.gov. Please send a copy of your comments to the person listed in the FOR FURTHER INFORMATION CONTACT section of this notice. Please see ‘‘V. Consultation Schedule’’ of this preamble for addresses of consultation sessions on this proposed rule. FOR FURTHER INFORMATION CONTACT: Elizabeth Appel, Director, Office of Regulatory Affairs & Collaborative Action, (202) 273–4680; elizabeth.appel@bia.gov. SUPPLEMENTARY INFORMATION: I. Background II. General Description of the Proposed Rule III. Section-by-Section Analysis IV. Other Proposed Changes Under Consideration V. Consultation Schedule VI. Procedural Requirements A. Regulatory Planning and Review (E.O. 12866 and 13563) B. Reducing Regulation and Controlling Regulatory Costs (E.O. 13771) C. Regulatory Flexibility Act D. Small Business Regulatory Enforcement Fairness Act E. Unfunded Mandates Reform Act F. Takings (E.O. 12630) E:\FR\FM\10JNP1.SGM 10JNP1

Agencies

[Federal Register Volume 84, Number 111 (Monday, June 10, 2019)]
[Proposed Rules]
[Pages 26781-26785]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-11896]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0402; Product Identifier 2019-NM-008-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2005-17-
14, which applies to all Airbus SAS Model A300 series airplanes; Model 
A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-

[[Page 26782]]

605R Variant F airplanes (collectively called Model A300-600 series 
airplanes); and Model A310 series airplanes. AD 2005-17-14 requires 
repetitive tests to detect desynchronization of the rudder servo 
actuators, and adjustment or replacement of the spring rods of the 
rudder servo actuators, if necessary. AD 2005-17-14 also requires 
repetitive tests/inspections/analyses of the rudder servo actuators, 
and related investigative/corrective actions if necessary. Since we 
issued AD 2005-17-14, analyses of the inspection results indicated that 
the assumptions made to establish the survey campaign were not 
adequate, and a new investigation determined the existing inspection 
procedures and compliance times do not adequately address the unsafe 
condition. This proposed AD would retain some requirements of AD 2005-
17-14 and revise the inspection procedures and compliance times, as 
specified in an European Aviation Safety Agency (EASA) AD, which will 
be incorporated by reference. We are proposing this AD to address the 
unsafe condition on these products.

DATES: We must receive comments on this proposed AD by July 25, 2019.

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 https://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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For the incorporation by reference (IBR) material described in the 
``Related IBR material under 1 CFR part 51'' section in SUPPLEMENTARY 
INFORMATION, contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, 
Germany; telephone +49 221 89990 1000; email [email protected]; 
internet www.easa.europa.eu. You may find this IBR material on the EASA 
website at https://ad.easa.europa.eu. You may view this IBR material 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. It is also available in the AD docket on the 
internet at https://www.regulations.gov.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0402; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this NPRM, the regulatory evaluation, any comments received, and other 
information. The street address for Docket Operations (telephone 800-
647-5527) is listed above. 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 proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2019-0402; 
Product Identifier 2019-NM-008-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this NPRM. We will consider all 
comments received by the closing date and may amend this NPRM based on 
those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this NPRM.

Discussion

    We issued AD 2005-17-14, Amendment 39-14235 (70 FR 50157, August 
26, 2005) (``AD 2005-17-14''), for all Airbus SAS Model A300 series 
airplanes, Model A300-600 series airplanes, and Model A310 series 
airplanes. AD 2005-17-14 requires repetitive tests to detect 
desynchronization of the rudder servo actuators, and adjustment or 
replacement of the spring rods of the rudder servo actuators, if 
necessary; and repetitive tests, inspections, and analyses of the 
rudder servo actuators, and related investigative and corrective 
actions if necessary. AD 2005-17-14 resulted from new reports of 
desynchronization of the rudder servo actuators. We issued AD 2005-17-
14 to address desynchronization of one of the three rudder servo 
actuators, which, if combined with an engine failure, could result in 
the loss of the related hydraulic system and could cause the loss of 
one of the two synchronized actuators. This condition could create 
additional fatigue loading and possible cracking of the attachment 
fittings and could result in the inability of the remaining 
synchronized actuator to maintain the commanded rudder deflection, 
leading to reduced controllability of the airplane.

Actions Since AD 2005-17-14 Was Issued

    Since we issued AD 2005-17-14, EASA reported that analyses of the 
inspection results indicate that the assumptions made in 2004 to 
establish the survey campaign were not adequate. This determination led 
to investigation and revision of the service information with revised 
inspection instructions and compliance times, depending on airplane 
configuration.
    The EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2019-0017, dated January 29, 2019 
(``EASA AD 2019-0017'') (also referred to as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition for all Airbus SAS Model A300 series airplanes, Model A300-
600 series airplanes, and Model A310 series airplanes. The MCAI states:

    Numerous occurrences were reported of rudder servo control de-
synchronization, some of which had caused structural damages to the 
fin or side fittings of the rudder actuator attachments. Analyses 
revealed that a de-synchronization of the rudder servo control 
induced by misalignment of the three servo controls, or by thermal 
expansion, can provoke opposing loads.
    This condition, if not detected and corrected, could induce 
failure of rudder-associated systems, possibly resulting in reduced 
control of the aeroplane.
    Previously, DGAC [Direction G[eacute]n[eacute]rale de l'Aviation 
Civile] France issued AD F-2004-063 for A300-600ST aeroplanes, and 
AD F-2004-092 (EASA approval 2004-6368) [which corresponds to FAA AD 
2005-17-14] for A300, A310 and A300-600 aeroplanes, to require 
repetitive inspections of rudder servo controls, fin box and rudder 
structures, and, depending on findings, accomplishment of applicable 
corrective action(s).
    Since those ADs were issued, analyses of the inspection results 
indicate that the assumptions made in 2004 to establish the survey 
campaign were not adequate. This determination induced new 
investigation and ATA 55 SBs [service bulletins] revision with new 
inspection instructions and new

[[Page 26783]]

compliance times, depending on aeroplane configuration.
    For the reason described above, this [EASA] AD retains partially 
the requirements of DGAC France AD F-2004-063 and AD F-2004-092 
(EASA approval 2004-6368), which are superseded, and requires the 
new inspections (latest SB revision) at new intervals.

    The new repetitive intervals for the inspections specified in 
paragraph (2) of EASA AD 2019-0017 range from 300 flight cycles to 
6,000 flight cycles, depending on inspection type.

Explanation of Retained Requirements

    Although this proposed AD does not explicitly restate the 
requirements of AD 2005-17-14, this proposed AD would retain certain 
requirements of AD 2005-17-14. Those requirements are referenced in 
EASA AD 2019-0017, which, in turn, is referenced in paragraph (g) of 
this proposed AD.

Related IBR Material Under 1 CFR Part 51

    EASA AD 2019-0017 describes procedures for repetitive inspections 
of the rudder servo actuators and related investigative/corrective 
actions. Related investigative actions include repetitive inspections 
of fin box and rudder servo controls. Corrective actions include 
repair. This material 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 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.

Proposed Requirements of This NPRM

    This proposed AD would require accomplishing the actions specified 
in EASA AD 2019-0017 described previously, as incorporated by 
reference, except for any differences identified as exceptions in the 
regulatory text of this AD and except as discussed under ``Differences 
Between this Proposed AD and the MCAI.''

Explanation of Required Compliance Information

    In the FAA's ongoing efforts to improve the efficiency of the AD 
process, the FAA worked with Airbus and EASA to develop a process to 
use certain EASA ADs as the primary source of information for 
compliance with requirements for corresponding FAA ADs. As a result, 
EASA AD 2019-0017 will be incorporated by reference in the FAA final 
rule. This proposed AD would, therefore, require compliance with the 
provisions specified in EASA AD 2019-0017, except for any differences 
identified as exceptions in the regulatory text of this proposed AD. 
Service information specified in EASA AD 2019-0017 that is required for 
compliance with EASA AD 2019-0017 will be available on the internet 
https://www.regulations.gov by searching for and locating Docket No. 
FAA-2019-0402 after the FAA final rule is published.

Differences Between This Proposed AD and the MCAI

    Where paragraph (4) of EASA AD 2019-0017 refers to ``during any 
inspection as required by paragraph (2) of this AD,'' this proposed AD 
would require using ``during any inspection as required by paragraph 
(2) or (3) of this AD.'' EASA AD 2019-0017 did not specify a corrective 
action for the inspections required by paragraph (3) of EASA AD 2019-
0017.

Costs of Compliance

    We estimate that this proposed AD affects 133 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                     Estimated Costs for Required Actions *
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2005-17-14...  1 work-hour x $85 per                 $0             $85         $11,305
                                         hour = $85.
New proposed actions..................  2 work-hours x $85 per                 0             170          22,610
                                         hour = $85.
----------------------------------------------------------------------------------------------------------------
* Table does not include estimated costs for reporting.

    We estimate that it would take about 1 work-hour per product to 
comply with the proposed reporting requirement in this proposed AD. The 
average labor rate is $85 per hour. Based on these figures, we estimate 
the cost of reporting the inspection results on U.S. operators to be 
$11,305, or $85 per product.
    We estimate the following costs to do any necessary on-condition 
inspections that would be required based on the results of any required 
actions. We have no way of determining the number of aircraft that 
might need these on-condition actions:

                 Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
                                                             Cost per
              Labor cost                   Parts cost        product
------------------------------------------------------------------------
34 work-hours x $85 per hour = $2,890.              $0           $2,890
------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition repair 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 NPRM is 2120-
0056. The paperwork cost associated with this NPRM has been detailed in 
the Costs of

[[Page 26784]]

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 NPRM 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 proposed 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 and associated appliances 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) 
2005-17-14, Amendment 39-14235 (70 FR 50157, August 26, 2005), and 
adding the following new AD:

Airbus SAS: Docket No. FAA-2019-0402; Product Identifier 2019-NM-
008-AD.

(a) Comments Due Date

    We must receive comments by July 25, 2019.

(b) Affected ADs

    This AD replaces AD 2005-17-14, Amendment 39-14235 (70 FR 50157, 
August 26, 2005) (``AD 2005-17-14'').

(c) Applicability

    This AD applies to the Airbus SAS airplanes, certificated in any 
category, specified in paragraphs (c)(1) through (c)(3) of this AD, 
as identified in European Aviation Safety Agency (EASA) AD 2019-
0017, dated January 29, 2019 (``EASA AD 2019-0017'').
    (1) Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and 
B4-203 airplanes.
    (2) Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, 
F4-605R and F4-622R airplanes, and Model A300 C4-605R Variant F 
airplanes.
    (3) Model A310-203, -204, -221, -222, -304, -322, -324, and -325 
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 27, Flight 
controls; 55, Stabilizers.

(e) Reason

    This AD was prompted by reports of desynchronization of the 
rudder servo actuators. We are issuing this AD to address 
desynchronization of one of the three rudder servo actuators, which, 
if combined with an engine failure, could result in the loss of the 
related hydraulic system and could cause the loss of one of the two 
synchronized actuators. This condition could create additional 
fatigue loading and possible cracking of the attachment fittings and 
could result in the inability of the remaining synchronized actuator 
to maintain the commanded rudder deflection, leading to reduced 
controllability of the airplane.

(f) Compliance

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

(g) Requirements

    Except as specified in paragraph (h) of this AD: Comply with all 
required actions and compliance times specified in, and in 
accordance with, EASA AD 2019-0017.

(h) Exceptions to EASA AD 2019-0017

    (1) For purposes of determining compliance with the requirements 
of this AD: Where EASA AD 2019-0017 refers to its effective date, 
this AD requires using the effective date of this AD.
    (2) For purposes of determining compliance with the requirements 
of this AD: Where paragraph (1) of EASA AD 2019-0017 specifies 
``after the last inspection as previously required by DGAC France AD 
F-2004-092,'' this AD requires using ``after the most recent 
inspection done as specified in Airbus Service Bulletin A300-27-
0188, Revision 2, dated October 1, 1997; A300-27-6036, Revision 2, 
dated October 1, 1997; A300-55-0044, dated October 22, 1996; A300-
55-6023, dated October 22, 1996; A310-27-2082, Revision 2, dated 
October 1, 1997; or A310-55-2026, dated October 22, 1996.''
    (3) For purposes of determining compliance with the requirements 
of this AD: Where paragraph (1) of EASA AD 2019-0017 refers to ``the 
03 July 2004,'' this AD requires using ``September 30, 2005'' (the 
effective date of AD 2005-17-14).
    (4) For purposes of determining compliance with the requirements 
of this AD: Where paragraph (4) of EASA AD 2019-0017 refers to 
``during any inspection as required by paragraph (2) of this AD,'' 
this AD requires using ``during any inspection as required by 
paragraph (2) or (3) of this AD.''
    (5) Where any service information referenced in EASA AD 2019-
0017 specifies reporting, this AD requires reporting all inspection 
results at the applicable time specified in paragraph (h)(5)(i) or 
(h)(5)(ii) of this AD. If operators have reported findings as part 
of obtaining any corrective actions approved by Airbus SAS's EASA 
Design Organization Approval (DOA), operators are not required to 
report those findings as specified in this paragraph.
    (i) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (ii) 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.

[[Page 26785]]

    (6) The ``Remarks'' section of EASA AD 2019-0017 does not apply 
to this AD.

(i) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Section, send it to the attention of 
the person identified in paragraph (j)(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: For any requirement in this AD 
to obtain instructions from a manufacturer, the instructions must be 
accomplished using a method approved by the Manager, International 
Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's 
EASA Design Organization Approval (DOA). If approved by the DOA, the 
approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): For any service information 
referenced in EASA AD 2019-0017 that contains RC procedures and 
tests: Except as required by paragraph (i)(2) of this AD, RC 
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.
    (4) Paperwork Reduction Act Burden Statement: A federal agency 
may not conduct or sponsor, and a person is not required to respond 
to, nor shall a person be subject to a penalty for failure to comply 
with a collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 1 
hour per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW, Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

(j) Related Information

    (1) For information about EASA AD 2019-0017, contact the EASA, 
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 
89990 6017; email [email protected]; Internet www.easa.europa.eu. 
You may find this EASA AD on the EASA website at https://ad.easa.europa.eu. You may view this EASA AD 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. EASA AD 2019-0017 may be found in the AD docket on the 
internet at https://www.regulations.gov by searching for and locating 
Docket No. FAA-2019-0402.
    (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.

    Issued in Des Moines, Washington, on May 28, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-11896 Filed 6-7-19; 8:45 am]
 BILLING CODE 4910-13-P