Airworthiness Directives; Airbus SAS Airplanes, 30579-30588 [2019-13545]

Download as PDF Federal Register / Vol. 84, No. 124 / Thursday, June 27, 2019 / Rules and Regulations under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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 adding the following new airworthiness directive (AD): ■ 2019–12–13 The Boeing Company: Amendment 39–19668; Docket No. FAA–2019–0445; Product Identifier 2019–NM–083–AD. (a) Effective Date This AD is effective July 12, 2019. (b) Affected ADs None. (c) Applicability This AD applies to all The Boeing Company Model 757–200, –200PF, –200CB, and –300 series airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 27, Flight controls. (e) Unsafe Condition This AD was prompted by a report of the failure of the aileron trim actuator attachment lug. The FAA is issuing this AD to address failure of the aileron trim actuator attachment lug and subsequent loss of feel force, wheel centering, and lateral trim. This condition, if not corrected, could cause over-control of the airplane and subsequent lateral pilot induced oscillations (PIO), which could adversely affect continued safe flight and landing. jspears on DSK30JT082PROD with RULES (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions Except as specified by paragraph (h) of this AD: At the applicable times specified in the ‘‘Compliance’’ paragraph of Boeing Alert Requirements Bulletin 757–27A0159 RB, dated March 29, 2019, do all applicable actions identified in, and in accordance with, the Accomplishment Instructions of Boeing Alert Requirements Bulletin 757–27A0159 RB, dated March 29, 2019. VerDate Sep<11>2014 17:21 Jun 26, 2019 Jkt 247001 Note 1 to paragraph (g): Guidance for accomplishing the actions required by this AD can be found in Boeing Alert Service Bulletin 757–27A0159, dated March 29, 2019, which is referred to in Boeing Alert Requirements Bulletin 757–27A0159 RB, dated March 29, 2019. (h) Exceptions to Service Information Specifications (1) For purposes of determining compliance with the requirements of this AD: Where Boeing Alert Requirements Bulletin 757–27A0159 RB, dated March 29, 2019, uses the phrase ‘‘the original issue date of the Requirements Bulletin 757–27A0159 RB,’’ this AD requires using ‘‘the effective date of this AD.’’ (2) Where Boeing Alert Requirements Bulletin 757–27A0159 RB, dated March 29, 2019, specifies contacting Boeing for repair instructions: This AD requires doing the repair using a method approved in accordance with the procedures specified in paragraph (i) of this AD. (i) 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 (j) of this AD. Information may be emailed to: 9-ANMLAACO-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. (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 Company 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. (j) Related Information For more information about this AD, contact Katherine Venegas, Aerospace Engineer, Cabin Safety and Environmental Systems Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627– 5353; fax: 562–627–5210; email: katherine.venegas@faa.gov. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 30579 (i) Boeing Alert Requirements Bulletin 757–27A0159 RB, dated March 29, 2019. (ii) [Reserved] (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; telephone 562–797–1717; internet https:// www.myboeingfleet.com. (4) 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Des Moines, Washington, on June 18, 2019. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2019–13514 Filed 6–26–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0017; Product Identifier 2018–NM–112–AD; Amendment 39–19662; AD 2019–12–07] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: The FAA is superseding Airworthiness Directive (AD) 2007–11– 11 and AD 2017–01–11, which applied to all Airbus SAS Model A318 and Model A319 series airplanes; Model A320–211, –212, –214, –231, –232, and –233 airplanes; and Model A321 series airplanes. AD 2007–11–11 required an inspection to determine the serial number of both main landing gear (MLG) sliding tubes, repetitive inspections for cracking of the affected MLG sliding tubes and corrective actions if necessary, and eventual replacement of both MLG shock absorbers. AD 2017–01–11 required identification of the part number and serial number of the MLG sliding tubes; inspection of affected chromium plates and sliding tube axles for damage; and replacement of the sliding tube if SUMMARY: E:\FR\FM\27JNR1.SGM 27JNR1 30580 Federal Register / Vol. 84, No. 124 / Thursday, June 27, 2019 / Rules and Regulations necessary. This AD retains certain requirements of AD 2007–11–11 and AD 2017–01–11. This AD also requires repetitive inspections of affected MLG sliding tubes for cracking, replacement of cracked MLG sliding tubes, and eventual replacement of each affected MLG sliding tube. This AD was prompted by cracks found in the MLG sliding tubes due to certain manufacturing defects that might not be identified using the current on-wing scheduled inspections. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective August 1, 2019. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of August 1, 2019. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of February 22, 2017 (82 FR 5362, January 18, 2017). The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of June 29, 2007 (72 FR 29241, May 25, 2007). ADDRESSES: For Airbus service information identified in this final rule, contact Airbus SAS, Airworthiness Office—EIAS, Rond-Point Emile Dewoitine No: 2, 31700 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. For Safran and Messier-Dowty service information identified in this final rule, contact Safran Landing Systems, One Carbon Way, Walton, KY 41094; telephone (859) 525–8583; fax (859) 485–8827; internet https://www.safranlanding-systems.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. It is also available on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2019– 0017. jspears on DSK30JT082PROD with RULES 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–2019– 0017; 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 final rule, the regulatory evaluation, any VerDate Sep<11>2014 17:21 Jun 26, 2019 Jkt 247001 comments received, and other information. The address for Docket Operations is U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3223. SUPPLEMENTARY INFORMATION: Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2007–11–11, Amendment 39–15068 (72 FR 29241, May 25, 2007) (‘‘AD 2007–11–11’’), and AD 2017–01–11, Amendment 39–18778 (82 FR 5362, January 18, 2017) (‘‘AD 2017–01–11’’). AD 2007–11–11 applied to all Airbus SAS Model A318 and Model A319 series airplanes; Model A320–211, –212, –214, –231, –232, and –233 airplanes; and Model A321 series airplanes. AD 2017–01–11 applied to all Airbus SAS Model A318 and Model A319 series airplanes; Model A320–211, –212, –214, –231, –232, and –233 airplanes; and Model A321 series airplanes. The NPRM published in the Federal Register on February 25, 2019 (84 FR 5960). The NPRM was prompted by a determination that cracks were found in the MLG sliding tubes due to certain manufacturing defects that might not be identified using the current on-wing scheduled inspections. The NPRM proposed to retain certain requirements of AD 2007–11–11 and AD 2017–01–11. The NPRM also proposed to require repetitive inspections of affected MLG sliding tubes for cracking, replacement of cracked MLG sliding tubes, and eventual replacement of each affected MLG sliding tube. The FAA is issuing this AD to address cracking in an MLG sliding tube, which could lead to failure of an MLG sliding tube resulting in MLG collapse, damage to the airplane, and injury to passengers. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2018–0135, dated June 26, 2018 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus SAS Model A318 and A319 series airplanes; Model A320–211, –212, –214, –216, –231, –232, and –233 airplanes; and Model A321–111, –112, PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 –131, –211, –212, –213, –231, and –232 airplanes. The MCAI states: Cracks were reported on [main landing gear] MLG sliding tubes and the investigations determined metallic inclusion during production and abnormal grinding operation during overhaul as cause of these cracks. Prompted by these reports, respectively, [Direction Generale de l’Aviation Civile] DGAC France issued [French] AD F–2005–115 (EASA approval 2005–6032) [which corresponds to FAA AD 2007–11–11] and EASA issued AD 2014– 0058 [which corresponds to FAA AD 2017– 01–11], both requiring inspections and replacement of certain MLG sliding tubes. More recently, during overhaul, cracks were found in the lower slave link bracket lug holes on two MLG sliding tubes. Subsequent investigations determined that these cracks may have developed due to burrs, which could have been present since manufacture. Based on the fact that the sliding tube is certified as a safe life part, this is considered to be a non-compliance with the requirements of [Joint Aviation Requirements] JAR 25.571(c). Cracks in the affected sliding tubes may not be found during the existing on-wing scheduled inspections. This condition, if not detected and corrected, could lead to sliding tube failure, possibly resulting in MLG collapse, damage to the aeroplane and injury to occupants. Prompted by these findings, Safran Landing Systems, the MLG manufacturer (formerly Messier-Dowty, Messier-BugattiDowty, and hereafter referred to as ‘‘Safran’’ in this AD), introduced additional quality steps to eliminate burrs in the manufacturing process. To address this potential unsafe condition on delivered MLG sliding tubes, Airbus issued SB [service bulletin] A320–32– 1441, providing instructions for on-wing repetitive inspections, and Safran issued SB 200–32–321 and SB 201–32–68, as applicable to MLG configuration, providing instructions for inspection in shop. For the reason described above, this [EASA] AD partially retains the requirements of DGAC France AD F–2005–115 (EASA approval 2005–6032) and EASA AD 2014– 0058, which are superseded, requires repetitive inspections of the affected MLG sliding tubes [for cracking] and, depending on findings, accomplishment of applicable corrective action(s) [replacement of a cracked MLG sliding tube with a serviceable MLG sliding tube]. This [EASA] AD also defines criteria for installation on an aeroplane of an affected MLG sliding tube. 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–2019– 0017. Comments The FAA gave the public the opportunity to participate in developing this final rule. The following presents the comments received on the NPRM and the FAA’s response to each comment. E:\FR\FM\27JNR1.SGM 27JNR1 Federal Register / Vol. 84, No. 124 / Thursday, June 27, 2019 / Rules and Regulations Support for the NPRM Air Line Pilots Association, International (ALPA) supported the intent of the NPRM. Request To Remove Functional Testing From ‘‘Required for Compliance (RC)’’ Requirements Delta Air Lines (DAL) requested that the functional testing requirement be removed from the required for compliance ‘‘RC’’ procedures identified in the Accomplishment Instructions of Airbus Service Bulletin A320–32–1441, Revision 01, dated December 14, 2017. The commenter explained that paragraph 3.D. of the Accomplishment Instructions of Airbus Service Bulletin A320–32–1441, Revision 01, dated December 14, 2017, describes postmodification testing, which results in functional testing of the brake and wheel installation functionality. The commenter noted that these tests do not require any special equipment for testing or require the operation of equipment. The commenter stated that it would prefer to use the airplane maintenance manual (AMM) procedures instead of a functional test. The FAA disagrees with the commenter’s request. Functional testing is required by EASA, the state of design authority for the Model A318 and Model A319 series airplanes; Model A320–211, –212, –214, –231, –232, and –233 airplanes; and Model A321 series airplanes; to restore the airplane to its type design requirements. In addition, the functional test procedure described in the above mentioned Airbus service information refers to the procedures in AMM task 32–41–11–400–006, ‘‘Installation of the MLG Wheels,’’ to perform the functional test, which is what the commenter requested. The functional test is required for compliance to ensure that risk has been mitigated and the airplane can be returned to service per the type design requirements. The FAA has not changed this AD in regard to this issue. jspears on DSK30JT082PROD with RULES Request for Clarification of Definition DAL observed that paragraph (n)(1) of the proposed AD defined affected MLG shock absorbers as those having a part number and serial number identified in Messier-Dowty Service Bulletin 200– 32–286, Revision 3, dated October 3, 2008, for Model A318, A319, and A320 series airplanes; and Messier-Dowty Service Bulletin 201–32–43, Revision 3, dated October 3, 2008, for Model A321 series airplanes. DAL noted that, upon review of this service information, it determined that there are no specific part number and serial number VerDate Sep<11>2014 17:21 Jun 26, 2019 Jkt 247001 combinations for the MLG shock absorbers listed, and that the service information identified serial numbers for only the MLG sliding tubes. From these statements, the FAA infers that DAL was requesting clarification of the definition of an affected MLG shock absorber. The FAA agrees to clarify this definition. An affected MLG shock absorber assembly contains an affected MLG sliding tube subassembly. The intent of paragraph (n) of this AD is to assist operators in identification of the discrepant MLG sliding tube part numbers. Furthermore, this definition matches what was provided in the corresponding MCAI AD issued by EASA. The FAA has not revised this AD in regard to this issue. Request for Clarification of Parts Installation Prohibition DAL requested that paragraph (r)(1) of the proposed AD be revised to state that, as of the effective date of the AD, no person may install an affected MLG sliding tube on any airplane. The commenter noted that paragraph (r)(1) of the proposed AD stated that, as of the effective date of this AD, no person may install on any airplane an affected MLG shock absorber. The commenter stated that its request is supported by the fact that the proposed AD only described inspections and actions based on the MLG sliding tubes, not the remainder of the MLG shock absorber. The commenter further explained that it is feasible that non-sliding tube components of the MLG shock absorber assemblies may be perfectly fit for operation beyond the AD replacement times. The commenter observed that this change would allow operators to use any existing stock of MLG shock absorber related components (other than the affected MLG sliding tubes). The commenter stated that its position is further supported by the statements in the ‘‘Proposed Requirements of this NPRM’’ paragraph, because no mention of an MLG shock absorber replacement is discussed. The commenter also explained that it would be difficult to comply with the proposed requirement specified in paragraph (r)(1) of the proposed AD, since paragraph (n)(2) of the proposed AD does not list specific MLG shock absorber part number and serial number combinations. The FAA agrees with the intent of the commenter’s request. The affected MLG shock absorber assembly contains an MLG sliding tube subassembly. The intent of paragraph (r)(1) of this AD is to prohibit the installation of an MLG shock absorber assembly containing a discrepant MLG sliding tube subassembly part number. The FAA has PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 30581 revised paragraph (r)(1) of this AD to prohibit, as of the effective date of this AD, the installation of an MLG shock absorber assembly containing a discrepant MLG sliding tube part number. Request To Allow the Use of Future Revisions of Service Information DAL requested that the proposed AD be revised to allow the use of future revisions of the service information. The commenter noted that the EASA AD allows the use of future revisions of service information. The FAA disagrees with the commenter’s request. The FAA may not refer to any document that does not yet exist. In general terms, the FAA is required by Office of the Federal Register (OFR) regulations for approval of materials incorporated by reference, as specified in 1 CFR 51.1(f), to either publish the service document contents as part of the actual AD language; or submit the service document to the OFR for approval as referenced material, in which case the FAA may only refer to such material in the text of an AD. The AD may refer to the service document only if the OFR approved it for incorporation by reference. See 1 CFR part 51. To allow operators to use later revisions of the referenced document (issued after publication of the AD), either the FAA must revise the AD to reference specific later revisions, or operators must request approval to use later revisions as an alternative method of compliance with this AD under the provisions of paragraph (w)(1) of this AD. The FAA has not revised this AD regarding this issue. Conclusion The FAA reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this final rule with the changes described previously and minor editorial changes. The FAA has determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. The FAA also determined that these changes will not increase the economic burden on any operator or increase the scope of this final rule. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. E:\FR\FM\27JNR1.SGM 27JNR1 30582 Federal Register / Vol. 84, No. 124 / Thursday, June 27, 2019 / Rules and Regulations • Service Bulletin A320–32–1441, Revision 01, dated December 14, 2017. This service information describes procedures for inspections of the MLG sliding tubes for cracking and corrective actions (which includes replacing the MLG sliding tubes). • Service Bulletin A320–32A1273, Revision 02, dated May 26, 2005. This service information specifies the serial numbers of the MLG sliding tubes that must be replaced. Safran Landing Systems has issued the following service information. These documents are distinct since they apply to different airplane models. • Safran Service Bulletin 200–32– 321, Revision 2, dated October 3, 2017; and Service Bulletin 201–32–68, Revision 2, dated October 3, 2017. These documents specify the part numbers and serial numbers of the affected MLG sliding tubes. • Messier-Dowty Service Bulletin 200–32–286, Revision 3, dated October 3, 2008; and Service Bulletin 201–32– 43, Revision 3, dated October 3, 2008. These documents specify the part numbers and serial numbers of the affected MLG shock absorbers. This AD also requires Airbus Service Bulletin A320–32–1416, including Appendix 01, dated March 10, 2014, which the Director of the Federal Register approved for incorporation by reference as of February 22, 2017 (82 FR 5362, January 18, 2017). This AD also requires Airbus Service Bulletin A320–32A1273, Revision 02, including Appendix 01, dated May 26, 2005, which the Director of the Federal Register approved for incorporation by reference as of June 29, 2007 (72 FR 29241, May 25, 2007). This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance The FAA estimates that this AD affects 1,186 airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: ESTIMATED COSTS FOR REQUIRED ACTIONS Action Labor cost Parts cost Cost per product Cost on U.S. operators Retained actions from AD 2007–11–11 (297 airplanes) *. Retained actions from AD 2017–01–11 .. New actions ............................................. 8 work-hours × $85 per hour = $680 ...... Up to $45,310 .. Up to $46,670 .. Up to $13,659,030.* 18 work-hours × $85 per hour = $1,530 13 work-hours × $85 per hour = $1,105 $0 ..................... (**) ................... $1,530 .............. $1,105 ** .......... $1,814,580. $1,310,530.** * Operators should note that, although all U.S.-registered airplanes are subject to the requirements of AD 2007–11–11, there are only 297 possible affected MLG sliding tubes in the worldwide fleet. The FAA has no way of knowing how many affected MLG sliding tubes, if any, are installed in U.S.-registered airplanes. ** The FAA has received no definitive data for the parts costs for the replacements. The FAA estimates the following costs to do any necessary on-condition action that would be required based on the results of any required actions. The FAA has no way of determining the number of aircraft that might need this on-condition action: ESTIMATED COSTS OF ON-CONDITION ACTION Labor cost Parts cost Cost per product 6 work-hours × $85 per hour = $510 ...................................................................................................................... (*) * $510 * The FAA has received no definitive data for the parts costs for the on-condition actions. jspears on DSK30JT082PROD with RULES 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. The FAA is 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 VerDate Sep<11>2014 17:21 Jun 26, 2019 Jkt 247001 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 and associated appliances to the Director of the System Oversight Division. Regulatory Findings The FAA determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Will not affect intrastate aviation in Alaska; and 3. 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. E:\FR\FM\27JNR1.SGM 27JNR1 Federal Register / Vol. 84, No. 124 / Thursday, June 27, 2019 / Rules and Regulations (3) Model A320–211, –212, –214, –216, –231, –232, and –233 airplanes. (4) Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: (d) Subject Air Transport Association (ATA) of America Code 32, Landing gear. 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: a. Removing Airworthiness Directive (AD) 2007–11–11, Amendment 39– 15068 (72 FR 29241, May 25, 2007); and AD 2017–01–11, Amendment 39–18778 (82 FR 5362, January 18, 2017); ■ b. Adding the following new AD: ■ ■ 2019–12–07 Airbus SAS: Amendment 39– 19662; Docket No. FAA–2019–0017; Product Identifier 2018–NM–112–AD. (a) Effective Date This AD is effective August 1, 2019. (b) Affected ADs This AD replaces the following ADs. (1) AD 2007–11–11, Amendment 39–15068 (72 FR 29241, May 25, 2007) (‘‘AD 2007–11– 11’’). (2) AD 2017–01–11, Amendment 39–18778 (82 FR 5362, January 18, 2017) (‘‘AD 2017– 01–11’’). jspears on DSK30JT082PROD with RULES (c) Applicability This AD applies to the Airbus SAS airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, all manufacturer serial numbers (MSNs). (1) Model A318–111, –112, –121, and –122 airplanes. (2) Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. VerDate Sep<11>2014 17:21 Jun 26, 2019 Jkt 247001 (e) Reason This AD was prompted by a determination that cracks were found in the main landing gear (MLG) sliding tubes due to certain manufacturing defects that might not be identified using the current on-wing scheduled inspections. The FAA is issuing this AD to address cracking in an MLG sliding tube, which could lead to failure of an MLG sliding tube resulting in MLG collapse, damage to the airplane, and injury to passengers. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Replacement of AD 2007–11–11, With Updated References to Service Information and Specific Delegation Approval Language This paragraph restates the requirements of paragraph (i) of AD 2007–11–11, with updated references to service information and specific delegation approval language. Within 41 months after June 29, 2007 (the effective date of AD 2007–11–11), replace all MLG shock absorbers equipped with MLG sliding tubes having serial numbers listed in Airbus All Operators Telex (AOT) A320– 32A1273, Revision 01, dated May 6, 2004; or the Accomplishment Instructions of Airbus Service Bulletin A320–32A1273, Revision 02, including Appendix 01, dated May 26, 2005; with new or serviceable MLG shock absorbers equipped with MLG sliding tubes having serial numbers not listed in Airbus AOT A320–32A1273, Revision 01, dated May 6, 2004; or the Accomplishment Instructions of Airbus Service Bulletin A320–32A1273, Revision 02, including Appendix 01, dated PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 30583 May 26, 2005; using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus SAS’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. As of June 29, 2007, only Airbus Service Bulletin A320–32A1273, Revision 02, including Appendix 01, dated May 26, 2005, may be used to determine the affected MLG sliding tubes. Note 1 to paragraph (g): Guidance on the replacement specified in paragraph (g) of this AD can be found in Airbus A318/A319/ A320/A321 Aircraft Maintenance Manual Chapter 32–11–13, page block 401. (h) Retained MLG Sliding Tube Part Number and Serial Number Identification of AD 2017–01–11, With No Changes This paragraph restates the requirements of paragraph (g) of AD 2017–01–11, with no changes. Within three months after February 22, 2017 (the effective date of AD 2017–01– 11): Do an inspection to identify the part number and serial number of the MLG sliding tubes installed on the airplane. A review of airplane maintenance records is acceptable in lieu of this inspection if the part number and serial number of the MLG sliding tubes can be conclusively determined from that review. (i) Retained Identification of Airplanes of AD 2017–01–11, With No Changes This paragraph restates the identification specified in paragraph (h) of AD 2017–01–11, with no changes. An airplane with a MSN not listed in figure 1 to paragraph (i) of this AD is not affected by the requirements of paragraph (j) of this AD, provided it can be determined that no MLG sliding tube having a part number and serial number listed in table 1 to paragraphs (i), (j), (l)(1), (l)(2), (m)(1), and (m)(2) of this AD has been installed on that airplane since first flight of the airplane. BILLING CODE 4910–13–P E:\FR\FM\27JNR1.SGM 27JNR1 30584 Federal Register / Vol. 84, No. 124 / Thursday, June 27, 2019 / Rules and Regulations Figure 1 to Paragraph (i) -Affected Airplanes Listed by MSN Affected Airplanes Listed by MSN 0179 0214 0296 0412 0558 0604 0607 0668 0704 0720 0726 0731 0754 0771 0799 0828 0841 0855 0909 0914 0925 0939 0986 1028 1030 1041 1070 1083 1093 1098 1108 1148 1294 1356 2713 2831 Serial Number 201160302 788 201160302 1016811 201160302 11448 201371302 84493 201371302 84513 201371302 SS4359 201371302 84530 201371302 84517 201371302 84568 201371302 84498 201371302 44908 201371302 8202-4598 201371302 8165-4623 201371302 8244-4766 201371302 8267-4794 201371302 8272-4813 201160302 11088 ER27JN19.001</GPH> Part Number VerDate Sep<11>2014 17:21 Jun 26, 2019 Jkt 247001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4725 E:\FR\FM\27JNR1.SGM 27JNR1 ER27JN19.000</GPH> jspears on DSK30JT082PROD with RULES Table 1 to Paragraphs (i), (j), (1)(1), (1)(2), (m)(1), and (m)(2)- Affected MLG Sliding Tubes VerDate Sep<11>2014 17:21 Jun 26, 2019 Jkt 247001 Part Number Serial Number 201371304 B041-4871 201371304 B045-4869 201371304 B001-4781 201371304 B051-4892 201371304 B110-1952 201371304 B054-4891 201371304 B063-4921 201371304 B071-4911 201371304 B071-4917 201371304 B080-1933 201371304 B117-5010 201371304 B120-4989 201371304 B132-2023 201371304 B114-1956 201371304 B208-2009 201371304 B133-1947 201371304 B154-5037 201371304 B89 4952 201371304 B129-1964 201371304 B227-2010 201371304 B170-5031 201371304 B182-5047 201371304 B239-2053 201371304 201371304 B1401-2856 B1813-3142 201371304 B116-5004 201522353 B011-149 201522350 B014-25 201522350 B019-56 PO 00000 Frm 00009 Fmt 4700 Sfmt 4725 E:\FR\FM\27JNR1.SGM 27JNR1 30585 ER27JN19.002</GPH> jspears on DSK30JT082PROD with RULES Federal Register / Vol. 84, No. 124 / Thursday, June 27, 2019 / Rules and Regulations Federal Register / Vol. 84, No. 124 / Thursday, June 27, 2019 / Rules and Regulations BILLING CODE 4910–13–C jspears on DSK30JT082PROD with RULES (j) Retained Inspections of AD 2017–01–11, With No Changes This paragraph restates the requirements of paragraph (i) of AD 2017–01–11, with no changes. For each MLG sliding tube identified as required by paragraph (h) of this AD, having a part number and serial number listed in table 1 to paragraphs (i), (j), (l)(1), (l)(2), (m)(1), and (m)(2) of this AD: Within 3 months after February 22, 2017 (the effective date of AD 2017–01–11) inspect affected MLG axles and brake flanges by doing a detailed visual inspection of the chromium plates for damage, and a Barkhausen noise inspection of the MLG sliding tube axles for damage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–32–1416, including Appendix 01, dated March 10, 2014. For Model A318 series airplanes, use the procedures specified for Model A319 series airplanes in Airbus Service Bulletin A320–32–1416, including Appendix 01, dated March 10, 2014. (k) Retained Corrective Action of AD 2017– 01–11, With No Changes This paragraph restates the requirements of paragraph (j) of AD 2017–01–11, with no changes. If, during any inspection required by paragraph (j) of this AD, any damage is detected: Before further flight, replace the MLG sliding tube with a serviceable MLG sliding tube, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–32–1416, including Appendix 01, dated March 10, 2014. For Model A318 series airplanes, use the VerDate Sep<11>2014 17:21 Jun 26, 2019 Jkt 247001 procedures specified for Model A319 series airplanes in Airbus Service Bulletin A320– 32–1416, including Appendix 01, dated March 10, 2014. (l) Retained Definition of Serviceable MLG Sliding Tube of AD 2017–01–11, With No Changes This paragraph restates the definition specified in paragraph (k) of AD 2017–01–11, with no changes. For the purpose of paragraph (k) of this AD, a serviceable MLG sliding tube is defined as an MLG sliding tube that meets the criterion in either paragraph (l)(1) or (l)(2) of this AD. (1) An MLG sliding tube having a part number and serial number not listed in table 1 to paragraphs (i), (j), (l)(1), (l)(2), (m)(1), and (m)(2) of this AD. (2) An MLG sliding tube having a part number and serial number listed in table 1 to paragraphs (i), (j), (l)(1), (l)(2), (m)(1), and (m)(2) of this AD that has passed the inspections required by paragraph (j) of this AD. (m) Retained Parts Installation Prohibition of AD 2017–01–11, With No Changes This paragraph restates the requirements of paragraph (l) of AD 2017–01–11, with no changes. (1) For airplanes that have an MLG sliding tube installed that has a part number and serial number listed in table 1 to paragraphs (i), (j), (l)(1), (l)(2), (m)(1), and (m)(2) of this AD: After an airplane is returned to service following accomplishment of the actions required by paragraphs (h), (i), and (j) of this AD, no person may install on any airplane an MLG sliding tube having a part number and PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 serial number listed in table 1 to paragraphs (i), (j), (l)(1), (l)(2), (m)(1), and (m)(2) of this AD, unless that MLG sliding tube has passed the inspection required by paragraph (j) of this AD. (2) For airplanes that, as of February 22, 2017 (the effective date of AD 2017–01–11), do not have an MLG sliding tube installed that has a part number and serial number listed in table 1 to paragraphs (i), (j), (l)(1), (l)(2), (m)(1), and (m)(2) of this AD: No person may install, on any airplane, an MLG sliding tube having a part number and serial number listed in table 1 to paragraphs (i), (j), (l)(1), (l)(2), (m)(1), and (m)(2) of this AD unless that MLG sliding tube has passed the inspection required by paragraph (j) of this AD. (n) New Definitions For the purpose of paragraphs (o), (p), (q), (r), and (s) of this AD the following definitions apply. (1) Affected MLG shock absorber: An MLG shock absorber having a part number and serial number as identified in Messier-Dowty Service Bulletin 200–32–286, Revision 3, dated October 3, 2008, for Model A318, A319, and A320 series airplanes; and Messier-Dowty Service Bulletin 201–32–43, Revision 3, dated October 3, 2008, for Model A321 series airplanes. (2) Affected MLG sliding tube: An MLG sliding tube having a part number and serial number as identified in Appendix B of Safran Service Bulletin 200–32–321, Revision 2, dated October 3, 2017, for Model A318, A319, and A320 series airplanes; or Safran Service Bulletin 201–32–68, Revision 2, dated October 3, 2017, for Model A321 series E:\FR\FM\27JNR1.SGM 27JNR1 ER27JN19.003</GPH> 30586 Federal Register / Vol. 84, No. 124 / Thursday, June 27, 2019 / Rules and Regulations airplanes, except those parts that passed an inspection as specified in Safran Service Bulletin 200–32–321; or Safran Service Bulletin 201–32–68; as applicable; and those parts that, after that inspection, have been repaired, using instructions approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS’s EASA DOA. If approved by the DOA, the approval must include the DOAauthorized signature. (3) Serviceable MLG sliding tube: An MLG sliding tube that is not affected, or an affected MLG sliding tube, that has not exceeded 10,000 flight cycle since first installation on an airplane, or an affected MLG sliding tube that, within the last 5,000 flight cycles before installation on an airplane, passed an inspection specified in Airbus Service Bulletin A320–32–1441. (o) New Requirement of This AD: Repetitive Inspections Note 2 to paragraph (o): If no reliable data regarding the number of flight cycles accumulated by the MLG sliding tube are available, operators may refer to the guidance specified in Chapter 5.2, ‘‘Traceability’’, of Section 1, of Part 1 of the Airbus A318/A319/ A320/A321 Airworthiness Limitations Section. (2) Do not install an affected MLG sliding tube on any airplane as specified in paragraph (r)(2)(i) or (r)(2)(ii) of this AD, as applicable. (i) For an airplane with an affected MLG sliding tube installed as of the effective date of this AD: After replacement of each affected MLG sliding tube as required by paragraph (q) of this AD. (ii) For an airplane that does not have an affected MLG sliding tube installed as of the effective date of this AD: As of the effective date of this AD. (v) No Reporting Requirement Although Airbus Service Bulletin A320– 32–1441, Revision 01, dated December 14, 2017, specifies to submit certain information to the manufacturer, and specifies that action as ‘‘RC,’’ (required for compliance) this AD does not include that requirement. (s) Identification of Airplanes Not Affected by Certain Requirements of This AD An airplane on which Airbus Modification 161202 or Modification 161346 has been installed in production is not affected by the requirements of paragraphs (g), (h), (j), (o), and (q), of this AD, provided it has been verified that no affected MLG sliding tube is installed on that airplane. (q) New Requirement of This AD: Part Replacement (1) Within 10 years after the effective date of this AD: Replace each affected MLG sliding tube with an MLG sliding tube that is not affected. Installation of an MLG sliding tube that is not affected on an airplane constitutes terminating action for the repetitive inspections required by paragraph (o) of this AD for that airplane. (2) Replacement of an MLG on an airplane with an MLG that does not have an affected MLG sliding tube installed is an acceptable method to comply with the requirement of paragraph (q)(1) of this AD for that airplane. (t) Credit for Previous Actions (1) This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before June 29, 2007, using Airbus AOT A320–32A1273, Revision 01, dated May 6, 2004. This document was incorporated by reference in AD 2004–11–13, Amendment 39–13659 (69 FR 31867, June 8, 2004). (2) This paragraph provides credit for the initial inspection and applicable corrective actions required by paragraphs (o) and (p) of this AD if those actions were performed before the effective date of this AD, using the Accomplishment Instructions in Airbus Service Bulletin A320–32–1441, dated December 28, 2016. (r) New Requirement of This AD: Parts Installation Limitation (1) As of the effective date of this AD no person may install on any airplane an affected MLG shock absorber assembly containing a discrepant MLG sliding tube part number. (u) Service Information Exceptions The service information specified in paragraph (g) of this AD has instructions to send any cracked part to Messier-Dowty. This AD does not include such a requirement, in accordance with the procedures specified in paragraph (w)(2) of this AD. VerDate Sep<11>2014 17:21 Jun 26, 2019 Jkt 247001 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 At the compliance time specified in figure 2 to paragraph (o) of this AD, and thereafter at intervals not to exceed 5,000 flight cycles: Do a detailed inspection of each affected MLG sliding tube, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–32–1441, Revision 01, dated December 14, 2017. (w) 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 (x)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. (i) 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. (ii) AMOCs approved previously for AD 2007–11–11 are approved as AMOCs for the corresponding provisions of paragraph (g) of this AD. (iii) AMOCs approved previously for AD 2017–01–11 are approved as AMOCs for the corresponding provisions of paragraphs (h), (i), (j), (k), (l), and (m) of this AD. (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 EASA; or Airbus SAS’s EASA DOA. If approved by the DOA, the approval must include the DOAauthorized signature. (3) Required for Compliance (RC): Except as required by paragraphs (u) and (v) of this AD: If any service information contains E:\FR\FM\27JNR1.SGM 27JNR1 ER27JN19.004</GPH> (p) New Requirement of This AD: Corrective Actions (1) If, during any inspection required by paragraph (o) of this AD, any crack is detected on an MLG sliding tube: Before further flight, replace that MLG sliding tube with a serviceable MLG sliding tube, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 32–1441, Revision 01, dated December 14, 2017. (2) Replacement of an MLG on an airplane with an MLG having a serviceable MLG sliding tube installed is an acceptable method to comply with the requirements of paragraph (p)(1) of this AD for that airplane. jspears on DSK30JT082PROD with RULES 30587 30588 Federal Register / Vol. 84, No. 124 / Thursday, June 27, 2019 / Rules and Regulations 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. jspears on DSK30JT082PROD with RULES (x) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2018–0135, dated June 26, 2018, for related information. This MCAI may be found in the AD docket on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2019–0017. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206– 231–3223. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (y)(6), (y)(7), and (y)(8) of this AD. (y) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following service information was approved for IBR on August 1, 2019. (i) Airbus Service Bulletin A320–32–1441, Revision 01, dated December 14, 2017. (ii) Messier-Dowty Service Bulletin 200– 32–286, Revision 3, dated October 3, 2008. (iii) Messier-Dowty Service Bulletin 201– 32–43, Revision 3, dated October 3, 2008. (iv) Safran Service Bulletin 200–32–321, Revision 2, dated October 3, 2017. (v) Safran Service Bulletin 201–32–68, Revision 2, dated October 3, 2017. (4) The following service information was approved for IBR on February 22, 2017 (82 FR 5362, January 18, 2017). (i) Airbus Service Bulletin A320–32–1416, including Appendix 01, dated March 10, 2014. (ii) [Reserved] (5) The following service information was approved for IBR on June 29, 2007 (72 FR 29241, May 25, 2007). (i) Airbus Service Bulletin A320–32A1273, Revision 02, including Appendix 01, dated May 26, 2005. (ii) [Reserved] (6) For Airbus service information identified in this AD, contact Airbus SAS, Airworthiness Office—EIAS, Rond-Point Emile Dewoitine No: 2, 31700 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. VerDate Sep<11>2014 17:21 Jun 26, 2019 Jkt 247001 (7) For Safran and Messier-Dowty service information identified in this AD, contact Safran Landing Systems, One Carbon Way, Walton, KY 41094; telephone (859) 525– 8583; fax (859) 485–8827; internet https:// www.safran-landing-systems.com. (8) 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. (9) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Des Moines, Washington, on June 19, 2019. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2019–13545 Filed 6–26–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–1071; Product Identifier 2018–NM–119–AD; Amendment 39–19665; AD 2019–12–10] RIN 2120–AA64 Airworthiness Directives; Fokker Services B.V. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective August 1, 2019. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 1, 2019. ADDRESSES: For service information identified in this final rule, contact Fokker Services B.V., Technical Services Dept., P.O. Box 1357, 2130 EL Hoofddorp, the Netherlands; telephone SUMMARY: PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 +31 (0)88–6280–350; fax +31 (0)88– 6280–111; email technicalservices@ fokker.com; internet http:// www.myfokkerfleet.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. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2018– 1071. 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– 1071; 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 final rule, the regulatory evaluation, any comments received, and other information. The address for Docket Operations is U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3226. SUPPLEMENTARY INFORMATION: Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. The NPRM published in the Federal Register on February 8, 2019 (84 FR 2796). The NPRM was prompted by a determination that new or more restrictive airworthiness limitations are necessary. The NPRM proposed to require revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. The agency is issuing this AD to address reduced structural integrity of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2018–0159, dated July 25, 2018 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. The MCAI states: E:\FR\FM\27JNR1.SGM 27JNR1

Agencies

[Federal Register Volume 84, Number 124 (Thursday, June 27, 2019)]
[Rules and Regulations]
[Pages 30579-30588]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-13545]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0017; Product Identifier 2018-NM-112-AD; Amendment 
39-19662; AD 2019-12-07]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2007-11-11 
and AD 2017-01-11, which applied to all Airbus SAS Model A318 and Model 
A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233 
airplanes; and Model A321 series airplanes. AD 2007-11-11 required an 
inspection to determine the serial number of both main landing gear 
(MLG) sliding tubes, repetitive inspections for cracking of the 
affected MLG sliding tubes and corrective actions if necessary, and 
eventual replacement of both MLG shock absorbers. AD 2017-01-11 
required identification of the part number and serial number of the MLG 
sliding tubes; inspection of affected chromium plates and sliding tube 
axles for damage; and replacement of the sliding tube if

[[Page 30580]]

necessary. This AD retains certain requirements of AD 2007-11-11 and AD 
2017-01-11. This AD also requires repetitive inspections of affected 
MLG sliding tubes for cracking, replacement of cracked MLG sliding 
tubes, and eventual replacement of each affected MLG sliding tube. This 
AD was prompted by cracks found in the MLG sliding tubes due to certain 
manufacturing defects that might not be identified using the current 
on-wing scheduled inspections. The FAA is issuing this AD to address 
the unsafe condition on these products.

DATES: This AD is effective August 1, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of August 1, 
2019.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
February 22, 2017 (82 FR 5362, January 18, 2017).
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of June 
29, 2007 (72 FR 29241, May 25, 2007).

ADDRESSES: For Airbus service information identified in this final 
rule, contact Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile 
Dewoitine No: 2, 31700 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.
    For Safran and Messier-Dowty service information identified in this 
final rule, contact Safran Landing Systems, One Carbon Way, Walton, KY 
41094; telephone (859) 525-8583; fax (859) 485-8827; internet https://www.safran-landing-systems.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. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0017.

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-2019-
0017; 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 final rule, the regulatory evaluation, any comments received, and 
other information. The address for Docket Operations is U.S. Department 
of Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3223.

SUPPLEMENTARY INFORMATION: 

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2007-11-11, Amendment 39-15068 (72 FR 
29241, May 25, 2007) (``AD 2007-11-11''), and AD 2017-01-11, Amendment 
39-18778 (82 FR 5362, January 18, 2017) (``AD 2017-01-11''). AD 2007-
11-11 applied to all Airbus SAS Model A318 and Model A319 series 
airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; 
and Model A321 series airplanes. AD 2017-01-11 applied to all Airbus 
SAS Model A318 and Model A319 series airplanes; Model A320-211, -212, -
214, -231, -232, and -233 airplanes; and Model A321 series airplanes.
    The NPRM published in the Federal Register on February 25, 2019 (84 
FR 5960). The NPRM was prompted by a determination that cracks were 
found in the MLG sliding tubes due to certain manufacturing defects 
that might not be identified using the current on-wing scheduled 
inspections. The NPRM proposed to retain certain requirements of AD 
2007-11-11 and AD 2017-01-11. The NPRM also proposed to require 
repetitive inspections of affected MLG sliding tubes for cracking, 
replacement of cracked MLG sliding tubes, and eventual replacement of 
each affected MLG sliding tube. The FAA is issuing this AD to address 
cracking in an MLG sliding tube, which could lead to failure of an MLG 
sliding tube resulting in MLG collapse, damage to the airplane, and 
injury to passengers.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2018-0135, dated June 26, 2018 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for all Airbus SAS Model A318 and A319 series 
airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 
airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and 
-232 airplanes. The MCAI states:

    Cracks were reported on [main landing gear] MLG sliding tubes 
and the investigations determined metallic inclusion during 
production and abnormal grinding operation during overhaul as cause 
of these cracks. Prompted by these reports, respectively, [Direction 
Generale de l'Aviation Civile] DGAC France issued [French] AD F-
2005-115 (EASA approval 2005-6032) [which corresponds to FAA AD 
2007-11-11] and EASA issued AD 2014-0058 [which corresponds to FAA 
AD 2017-01-11], both requiring inspections and replacement of 
certain MLG sliding tubes.
    More recently, during overhaul, cracks were found in the lower 
slave link bracket lug holes on two MLG sliding tubes. Subsequent 
investigations determined that these cracks may have developed due 
to burrs, which could have been present since manufacture. Based on 
the fact that the sliding tube is certified as a safe life part, 
this is considered to be a non-compliance with the requirements of 
[Joint Aviation Requirements] JAR 25.571(c). Cracks in the affected 
sliding tubes may not be found during the existing on-wing scheduled 
inspections.
    This condition, if not detected and corrected, could lead to 
sliding tube failure, possibly resulting in MLG collapse, damage to 
the aeroplane and injury to occupants.
    Prompted by these findings, Safran Landing Systems, the MLG 
manufacturer (formerly Messier-Dowty, Messier-Bugatti-Dowty, and 
hereafter referred to as ``Safran'' in this AD), introduced 
additional quality steps to eliminate burrs in the manufacturing 
process. To address this potential unsafe condition on delivered MLG 
sliding tubes, Airbus issued SB [service bulletin] A320-32-1441, 
providing instructions for on-wing repetitive inspections, and 
Safran issued SB 200-32-321 and SB 201-32-68, as applicable to MLG 
configuration, providing instructions for inspection in shop.
    For the reason described above, this [EASA] AD partially retains 
the requirements of DGAC France AD F-2005-115 (EASA approval 2005-
6032) and EASA AD 2014-0058, which are superseded, requires 
repetitive inspections of the affected MLG sliding tubes [for 
cracking] and, depending on findings, accomplishment of applicable 
corrective action(s) [replacement of a cracked MLG sliding tube with 
a serviceable MLG sliding tube]. This [EASA] AD also defines 
criteria for installation on an aeroplane of an affected MLG sliding 
tube.

    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-2019-
0017.

Comments

    The FAA gave the public the opportunity to participate in 
developing this final rule. The following presents the comments 
received on the NPRM and the FAA's response to each comment.

[[Page 30581]]

Support for the NPRM

    Air Line Pilots Association, International (ALPA) supported the 
intent of the NPRM.

Request To Remove Functional Testing From ``Required for Compliance 
(RC)'' Requirements

    Delta Air Lines (DAL) requested that the functional testing 
requirement be removed from the required for compliance ``RC'' 
procedures identified in the Accomplishment Instructions of Airbus 
Service Bulletin A320-32-1441, Revision 01, dated December 14, 2017. 
The commenter explained that paragraph 3.D. of the Accomplishment 
Instructions of Airbus Service Bulletin A320-32-1441, Revision 01, 
dated December 14, 2017, describes post-modification testing, which 
results in functional testing of the brake and wheel installation 
functionality. The commenter noted that these tests do not require any 
special equipment for testing or require the operation of equipment. 
The commenter stated that it would prefer to use the airplane 
maintenance manual (AMM) procedures instead of a functional test.
    The FAA disagrees with the commenter's request. Functional testing 
is required by EASA, the state of design authority for the Model A318 
and Model A319 series airplanes; Model A320-211, -212, -214, -231, -
232, and -233 airplanes; and Model A321 series airplanes; to restore 
the airplane to its type design requirements. In addition, the 
functional test procedure described in the above mentioned Airbus 
service information refers to the procedures in AMM task 32-41-11-400-
006, ``Installation of the MLG Wheels,'' to perform the functional 
test, which is what the commenter requested. The functional test is 
required for compliance to ensure that risk has been mitigated and the 
airplane can be returned to service per the type design requirements. 
The FAA has not changed this AD in regard to this issue.

Request for Clarification of Definition

    DAL observed that paragraph (n)(1) of the proposed AD defined 
affected MLG shock absorbers as those having a part number and serial 
number identified in Messier-Dowty Service Bulletin 200-32-286, 
Revision 3, dated October 3, 2008, for Model A318, A319, and A320 
series airplanes; and Messier-Dowty Service Bulletin 201-32-43, 
Revision 3, dated October 3, 2008, for Model A321 series airplanes. DAL 
noted that, upon review of this service information, it determined that 
there are no specific part number and serial number combinations for 
the MLG shock absorbers listed, and that the service information 
identified serial numbers for only the MLG sliding tubes.
    From these statements, the FAA infers that DAL was requesting 
clarification of the definition of an affected MLG shock absorber. The 
FAA agrees to clarify this definition. An affected MLG shock absorber 
assembly contains an affected MLG sliding tube subassembly. The intent 
of paragraph (n) of this AD is to assist operators in identification of 
the discrepant MLG sliding tube part numbers. Furthermore, this 
definition matches what was provided in the corresponding MCAI AD 
issued by EASA. The FAA has not revised this AD in regard to this 
issue.

Request for Clarification of Parts Installation Prohibition

    DAL requested that paragraph (r)(1) of the proposed AD be revised 
to state that, as of the effective date of the AD, no person may 
install an affected MLG sliding tube on any airplane. The commenter 
noted that paragraph (r)(1) of the proposed AD stated that, as of the 
effective date of this AD, no person may install on any airplane an 
affected MLG shock absorber. The commenter stated that its request is 
supported by the fact that the proposed AD only described inspections 
and actions based on the MLG sliding tubes, not the remainder of the 
MLG shock absorber. The commenter further explained that it is feasible 
that non-sliding tube components of the MLG shock absorber assemblies 
may be perfectly fit for operation beyond the AD replacement times. The 
commenter observed that this change would allow operators to use any 
existing stock of MLG shock absorber related components (other than the 
affected MLG sliding tubes). The commenter stated that its position is 
further supported by the statements in the ``Proposed Requirements of 
this NPRM'' paragraph, because no mention of an MLG shock absorber 
replacement is discussed. The commenter also explained that it would be 
difficult to comply with the proposed requirement specified in 
paragraph (r)(1) of the proposed AD, since paragraph (n)(2) of the 
proposed AD does not list specific MLG shock absorber part number and 
serial number combinations.
    The FAA agrees with the intent of the commenter's request. The 
affected MLG shock absorber assembly contains an MLG sliding tube 
subassembly. The intent of paragraph (r)(1) of this AD is to prohibit 
the installation of an MLG shock absorber assembly containing a 
discrepant MLG sliding tube subassembly part number. The FAA has 
revised paragraph (r)(1) of this AD to prohibit, as of the effective 
date of this AD, the installation of an MLG shock absorber assembly 
containing a discrepant MLG sliding tube part number.

Request To Allow the Use of Future Revisions of Service Information

    DAL requested that the proposed AD be revised to allow the use of 
future revisions of the service information. The commenter noted that 
the EASA AD allows the use of future revisions of service information.
    The FAA disagrees with the commenter's request. The FAA may not 
refer to any document that does not yet exist. In general terms, the 
FAA is required by Office of the Federal Register (OFR) regulations for 
approval of materials incorporated by reference, as specified in 1 CFR 
51.1(f), to either publish the service document contents as part of the 
actual AD language; or submit the service document to the OFR for 
approval as referenced material, in which case the FAA may only refer 
to such material in the text of an AD. The AD may refer to the service 
document only if the OFR approved it for incorporation by reference. 
See 1 CFR part 51. To allow operators to use later revisions of the 
referenced document (issued after publication of the AD), either the 
FAA must revise the AD to reference specific later revisions, or 
operators must request approval to use later revisions as an 
alternative method of compliance with this AD under the provisions of 
paragraph (w)(1) of this AD. The FAA has not revised this AD regarding 
this issue.

Conclusion

    The FAA reviewed the relevant data, considered the comments 
received, and determined that air safety and the public interest 
require adopting this final rule with the changes described previously 
and minor editorial changes. The FAA has determined that these minor 
changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    The FAA also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this final 
rule.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information.

[[Page 30582]]

     Service Bulletin A320-32-1441, Revision 01, dated December 
14, 2017. This service information describes procedures for inspections 
of the MLG sliding tubes for cracking and corrective actions (which 
includes replacing the MLG sliding tubes).
     Service Bulletin A320-32A1273, Revision 02, dated May 26, 
2005. This service information specifies the serial numbers of the MLG 
sliding tubes that must be replaced.
    Safran Landing Systems has issued the following service 
information. These documents are distinct since they apply to different 
airplane models.
     Safran Service Bulletin 200-32-321, Revision 2, dated 
October 3, 2017; and Service Bulletin 201-32-68, Revision 2, dated 
October 3, 2017. These documents specify the part numbers and serial 
numbers of the affected MLG sliding tubes.
     Messier-Dowty Service Bulletin 200-32-286, Revision 3, 
dated October 3, 2008; and Service Bulletin 201-32-43, Revision 3, 
dated October 3, 2008. These documents specify the part numbers and 
serial numbers of the affected MLG shock absorbers.
    This AD also requires Airbus Service Bulletin A320-32-1416, 
including Appendix 01, dated March 10, 2014, which the Director of the 
Federal Register approved for incorporation by reference as of February 
22, 2017 (82 FR 5362, January 18, 2017).
    This AD also requires Airbus Service Bulletin A320-32A1273, 
Revision 02, including Appendix 01, dated May 26, 2005, which the 
Director of the Federal Register approved for incorporation by 
reference as of June 29, 2007 (72 FR 29241, May 25, 2007).
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Costs of Compliance

    The FAA estimates that this AD affects 1,186 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                                          Estimated Costs for Required Actions
--------------------------------------------------------------------------------------------------------------------------------------------------------
               Action                        Labor cost                 Parts cost               Cost per product            Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Retained actions from AD 2007-11-11   8 work-hours x $85 per   Up to $45,310..............  Up to $46,670.............  Up to $13,659,030.*
 (297 airplanes) *.                    hour = $680.
Retained actions from AD 2017-01-11.  18 work-hours x $85 per  $0.........................  $1,530....................  $1,814,580.
                                       hour = $1,530.
New actions.........................  13 work-hours x $85 per  (**).......................  $1,105 **.................  $1,310,530.**
                                       hour = $1,105.
--------------------------------------------------------------------------------------------------------------------------------------------------------
* Operators should note that, although all U.S.-registered airplanes are subject to the requirements of AD 2007-11-11, there are only 297 possible
  affected MLG sliding tubes in the worldwide fleet. The FAA has no way of knowing how many affected MLG sliding tubes, if any, are installed in U.S.-
  registered airplanes.
** The FAA has received no definitive data for the parts costs for the replacements.

    The FAA estimates the following costs to do any necessary on-
condition action that would be required based on the results of any 
required actions. The FAA has no way of determining the number of 
aircraft that might need this on-condition action:

                 Estimated Costs of On-Condition Action
------------------------------------------------------------------------
                                                             Cost per
              Labor cost                   Parts cost        product
------------------------------------------------------------------------
6 work-hours x $85 per hour = $510....             (*)           * $510
------------------------------------------------------------------------
* The FAA has received no definitive data for the parts costs for the on-
  condition actions.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    The FAA is 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 and 
associated appliances to the Director of the System Oversight Division.

Regulatory Findings

    The FAA determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Will not affect intrastate aviation in Alaska; and
    3. 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.

[[Page 30583]]

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by:
0
a. Removing Airworthiness Directive (AD) 2007-11-11, Amendment 39-15068 
(72 FR 29241, May 25, 2007); and AD 2017-01-11, Amendment 39-18778 (82 
FR 5362, January 18, 2017);
0
b. Adding the following new AD:

2019-12-07 Airbus SAS: Amendment 39-19662; Docket No. FAA-2019-0017; 
Product Identifier 2018-NM-112-AD.

(a) Effective Date

    This AD is effective August 1, 2019.

(b) Affected ADs

    This AD replaces the following ADs.
    (1) AD 2007-11-11, Amendment 39-15068 (72 FR 29241, May 25, 
2007) (``AD 2007-11-11'').
    (2) AD 2017-01-11, Amendment 39-18778 (82 FR 5362, January 18, 
2017) (``AD 2017-01-11'').

(c) Applicability

    This AD applies to the Airbus SAS airplanes identified in 
paragraphs (c)(1) through (c)(4) of this AD, certificated in any 
category, all manufacturer serial numbers (MSNs).
    (1) Model A318-111, -112, -121, and -122 airplanes.
    (2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 
airplanes.
    (3) Model A320-211, -212, -214, -216, -231, -232, and -233 
airplanes.
    (4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing 
gear.

(e) Reason

    This AD was prompted by a determination that cracks were found 
in the main landing gear (MLG) sliding tubes due to certain 
manufacturing defects that might not be identified using the current 
on-wing scheduled inspections. The FAA is issuing this AD to address 
cracking in an MLG sliding tube, which could lead to failure of an 
MLG sliding tube resulting in MLG collapse, damage to the airplane, 
and injury to passengers.

(f) Compliance

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

(g) Retained Replacement of AD 2007-11-11, With Updated References to 
Service Information and Specific Delegation Approval Language

    This paragraph restates the requirements of paragraph (i) of AD 
2007-11-11, with updated references to service information and 
specific delegation approval language. Within 41 months after June 
29, 2007 (the effective date of AD 2007-11-11), replace all MLG 
shock absorbers equipped with MLG sliding tubes having serial 
numbers listed in Airbus All Operators Telex (AOT) A320-32A1273, 
Revision 01, dated May 6, 2004; or the Accomplishment Instructions 
of Airbus Service Bulletin A320-32A1273, Revision 02, including 
Appendix 01, dated May 26, 2005; with new or serviceable MLG shock 
absorbers equipped with MLG sliding tubes having serial numbers not 
listed in Airbus AOT A320-32A1273, Revision 01, dated May 6, 2004; 
or the Accomplishment Instructions of Airbus Service Bulletin A320-
32A1273, Revision 02, including Appendix 01, dated May 26, 2005; 
using a method approved by the Manager, International Section, 
Transport Standards Branch, FAA; or the European Aviation Safety 
Agency (EASA); or Airbus SAS's EASA Design Organization Approval 
(DOA). If approved by the DOA, the approval must include the DOA-
authorized signature. As of June 29, 2007, only Airbus Service 
Bulletin A320-32A1273, Revision 02, including Appendix 01, dated May 
26, 2005, may be used to determine the affected MLG sliding tubes.

    Note 1 to paragraph (g):  Guidance on the replacement specified 
in paragraph (g) of this AD can be found in Airbus A318/A319/A320/
A321 Aircraft Maintenance Manual Chapter 32-11-13, page block 401.

(h) Retained MLG Sliding Tube Part Number and Serial Number 
Identification of AD 2017-01-11, With No Changes

    This paragraph restates the requirements of paragraph (g) of AD 
2017-01-11, with no changes. Within three months after February 22, 
2017 (the effective date of AD 2017-01-11): Do an inspection to 
identify the part number and serial number of the MLG sliding tubes 
installed on the airplane. A review of airplane maintenance records 
is acceptable in lieu of this inspection if the part number and 
serial number of the MLG sliding tubes can be conclusively 
determined from that review.

(i) Retained Identification of Airplanes of AD 2017-01-11, With No 
Changes

    This paragraph restates the identification specified in 
paragraph (h) of AD 2017-01-11, with no changes. An airplane with a 
MSN not listed in figure 1 to paragraph (i) of this AD is not 
affected by the requirements of paragraph (j) of this AD, provided 
it can be determined that no MLG sliding tube having a part number 
and serial number listed in table 1 to paragraphs (i), (j), (l)(1), 
(l)(2), (m)(1), and (m)(2) of this AD has been installed on that 
airplane since first flight of the airplane.
BILLING CODE 4910-13-P

[[Page 30584]]

[GRAPHIC] [TIFF OMITTED] TR27JN19.000

[GRAPHIC] [TIFF OMITTED] TR27JN19.001


[[Page 30585]]


[GRAPHIC] [TIFF OMITTED] TR27JN19.002


[[Page 30586]]


[GRAPHIC] [TIFF OMITTED] TR27JN19.003

BILLING CODE 4910-13-C

(j) Retained Inspections of AD 2017-01-11, With No Changes

    This paragraph restates the requirements of paragraph (i) of AD 
2017-01-11, with no changes. For each MLG sliding tube identified as 
required by paragraph (h) of this AD, having a part number and 
serial number listed in table 1 to paragraphs (i), (j), (l)(1), 
(l)(2), (m)(1), and (m)(2) of this AD: Within 3 months after 
February 22, 2017 (the effective date of AD 2017-01-11) inspect 
affected MLG axles and brake flanges by doing a detailed visual 
inspection of the chromium plates for damage, and a Barkhausen noise 
inspection of the MLG sliding tube axles for damage, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A320-32-1416, including Appendix 01, dated March 10, 2014. For Model 
A318 series airplanes, use the procedures specified for Model A319 
series airplanes in Airbus Service Bulletin A320-32-1416, including 
Appendix 01, dated March 10, 2014.

(k) Retained Corrective Action of AD 2017-01-11, With No Changes

    This paragraph restates the requirements of paragraph (j) of AD 
2017-01-11, with no changes. If, during any inspection required by 
paragraph (j) of this AD, any damage is detected: Before further 
flight, replace the MLG sliding tube with a serviceable MLG sliding 
tube, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-32-1416, including Appendix 01, dated March 
10, 2014. For Model A318 series airplanes, use the procedures 
specified for Model A319 series airplanes in Airbus Service Bulletin 
A320-32-1416, including Appendix 01, dated March 10, 2014.

(l) Retained Definition of Serviceable MLG Sliding Tube of AD 2017-01-
11, With No Changes

    This paragraph restates the definition specified in paragraph 
(k) of AD 2017-01-11, with no changes. For the purpose of paragraph 
(k) of this AD, a serviceable MLG sliding tube is defined as an MLG 
sliding tube that meets the criterion in either paragraph (l)(1) or 
(l)(2) of this AD.
    (1) An MLG sliding tube having a part number and serial number 
not listed in table 1 to paragraphs (i), (j), (l)(1), (l)(2), 
(m)(1), and (m)(2) of this AD.
    (2) An MLG sliding tube having a part number and serial number 
listed in table 1 to paragraphs (i), (j), (l)(1), (l)(2), (m)(1), 
and (m)(2) of this AD that has passed the inspections required by 
paragraph (j) of this AD.

(m) Retained Parts Installation Prohibition of AD 2017-01-11, With No 
Changes

    This paragraph restates the requirements of paragraph (l) of AD 
2017-01-11, with no changes.
    (1) For airplanes that have an MLG sliding tube installed that 
has a part number and serial number listed in table 1 to paragraphs 
(i), (j), (l)(1), (l)(2), (m)(1), and (m)(2) of this AD: After an 
airplane is returned to service following accomplishment of the 
actions required by paragraphs (h), (i), and (j) of this AD, no 
person may install on any airplane an MLG sliding tube having a part 
number and serial number listed in table 1 to paragraphs (i), (j), 
(l)(1), (l)(2), (m)(1), and (m)(2) of this AD, unless that MLG 
sliding tube has passed the inspection required by paragraph (j) of 
this AD.
    (2) For airplanes that, as of February 22, 2017 (the effective 
date of AD 2017-01-11), do not have an MLG sliding tube installed 
that has a part number and serial number listed in table 1 to 
paragraphs (i), (j), (l)(1), (l)(2), (m)(1), and (m)(2) of this AD: 
No person may install, on any airplane, an MLG sliding tube having a 
part number and serial number listed in table 1 to paragraphs (i), 
(j), (l)(1), (l)(2), (m)(1), and (m)(2) of this AD unless that MLG 
sliding tube has passed the inspection required by paragraph (j) of 
this AD.

(n) New Definitions

    For the purpose of paragraphs (o), (p), (q), (r), and (s) of 
this AD the following definitions apply.
    (1) Affected MLG shock absorber: An MLG shock absorber having a 
part number and serial number as identified in Messier-Dowty Service 
Bulletin 200-32-286, Revision 3, dated October 3, 2008, for Model 
A318, A319, and A320 series airplanes; and Messier-Dowty Service 
Bulletin 201-32-43, Revision 3, dated October 3, 2008, for Model 
A321 series airplanes.
    (2) Affected MLG sliding tube: An MLG sliding tube having a part 
number and serial number as identified in Appendix B of Safran 
Service Bulletin 200-32-321, Revision 2, dated October 3, 2017, for 
Model A318, A319, and A320 series airplanes; or Safran Service 
Bulletin 201-32-68, Revision 2, dated October 3, 2017, for Model 
A321 series

[[Page 30587]]

airplanes, except those parts that passed an inspection as specified 
in Safran Service Bulletin 200-32-321; or Safran Service Bulletin 
201-32-68; as applicable; and those parts that, after that 
inspection, have been repaired, using instructions approved by the 
Manager, International Section, Transport Standards Branch, FAA; or 
EASA; or Airbus SAS's EASA DOA. If approved by the DOA, the approval 
must include the DOA-authorized signature.
    (3) Serviceable MLG sliding tube: An MLG sliding tube that is 
not affected, or an affected MLG sliding tube, that has not exceeded 
10,000 flight cycle since first installation on an airplane, or an 
affected MLG sliding tube that, within the last 5,000 flight cycles 
before installation on an airplane, passed an inspection specified 
in Airbus Service Bulletin A320-32-1441.

(o) New Requirement of This AD: Repetitive Inspections

    At the compliance time specified in figure 2 to paragraph (o) of 
this AD, and thereafter at intervals not to exceed 5,000 flight 
cycles: Do a detailed inspection of each affected MLG sliding tube, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-32-1441, Revision 01, dated December 14, 2017.
[GRAPHIC] [TIFF OMITTED] TR27JN19.004


    Note 2 to paragraph (o):  If no reliable data regarding the 
number of flight cycles accumulated by the MLG sliding tube are 
available, operators may refer to the guidance specified in Chapter 
5.2, ``Traceability'', of Section 1, of Part 1 of the Airbus A318/
A319/A320/A321 Airworthiness Limitations Section.

(p) New Requirement of This AD: Corrective Actions

    (1) If, during any inspection required by paragraph (o) of this 
AD, any crack is detected on an MLG sliding tube: Before further 
flight, replace that MLG sliding tube with a serviceable MLG sliding 
tube, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-32-1441, Revision 01, dated December 14, 2017.
    (2) Replacement of an MLG on an airplane with an MLG having a 
serviceable MLG sliding tube installed is an acceptable method to 
comply with the requirements of paragraph (p)(1) of this AD for that 
airplane.

(q) New Requirement of This AD: Part Replacement

    (1) Within 10 years after the effective date of this AD: Replace 
each affected MLG sliding tube with an MLG sliding tube that is not 
affected. Installation of an MLG sliding tube that is not affected 
on an airplane constitutes terminating action for the repetitive 
inspections required by paragraph (o) of this AD for that airplane.
    (2) Replacement of an MLG on an airplane with an MLG that does 
not have an affected MLG sliding tube installed is an acceptable 
method to comply with the requirement of paragraph (q)(1) of this AD 
for that airplane.

(r) New Requirement of This AD: Parts Installation Limitation

    (1) As of the effective date of this AD no person may install on 
any airplane an affected MLG shock absorber assembly containing a 
discrepant MLG sliding tube part number.
    (2) Do not install an affected MLG sliding tube on any airplane 
as specified in paragraph (r)(2)(i) or (r)(2)(ii) of this AD, as 
applicable.
    (i) For an airplane with an affected MLG sliding tube installed 
as of the effective date of this AD: After replacement of each 
affected MLG sliding tube as required by paragraph (q) of this AD.
    (ii) For an airplane that does not have an affected MLG sliding 
tube installed as of the effective date of this AD: As of the 
effective date of this AD.

(s) Identification of Airplanes Not Affected by Certain Requirements of 
This AD

    An airplane on which Airbus Modification 161202 or Modification 
161346 has been installed in production is not affected by the 
requirements of paragraphs (g), (h), (j), (o), and (q), of this AD, 
provided it has been verified that no affected MLG sliding tube is 
installed on that airplane.

(t) Credit for Previous Actions

    (1) This paragraph provides credit for the actions required by 
paragraph (g) of this AD, if those actions were performed before 
June 29, 2007, using Airbus AOT A320-32A1273, Revision 01, dated May 
6, 2004. This document was incorporated by reference in AD 2004-11-
13, Amendment 39-13659 (69 FR 31867, June 8, 2004).
    (2) This paragraph provides credit for the initial inspection 
and applicable corrective actions required by paragraphs (o) and (p) 
of this AD if those actions were performed before the effective date 
of this AD, using the Accomplishment Instructions in Airbus Service 
Bulletin A320-32-1441, dated December 28, 2016.

(u) Service Information Exceptions

    The service information specified in paragraph (g) of this AD 
has instructions to send any cracked part to Messier-Dowty. This AD 
does not include such a requirement, in accordance with the 
procedures specified in paragraph (w)(2) of this AD.

(v) No Reporting Requirement

    Although Airbus Service Bulletin A320-32-1441, Revision 01, 
dated December 14, 2017, specifies to submit certain information to 
the manufacturer, and specifies that action as ``RC,'' (required for 
compliance) this AD does not include that requirement.

(w) 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 (x)(2) of this AD. Information 
may be emailed to: [email protected].
    (i) 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.
    (ii) AMOCs approved previously for AD 2007-11-11 are approved as 
AMOCs for the corresponding provisions of paragraph (g) of this AD.
    (iii) AMOCs approved previously for AD 2017-01-11 are approved 
as AMOCs for the corresponding provisions of paragraphs (h), (i), 
(j), (k), (l), and (m) of this AD.
    (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 EASA; or Airbus SAS's EASA DOA. If approved by the 
DOA, the approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraphs (u) and (v) of this AD: If any service information 
contains

[[Page 30588]]

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.

(x) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2018-0135, dated June 26, 2018, for related 
information. This MCAI may be found in the AD docket on the internet 
at http://www.regulations.gov by searching for and locating Docket 
No. FAA-2019-0017.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 
and fax 206-231-3223.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (y)(6), (y)(7), and (y)(8) of this AD.

(y) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
August 1, 2019.
    (i) Airbus Service Bulletin A320-32-1441, Revision 01, dated 
December 14, 2017.
    (ii) Messier-Dowty Service Bulletin 200-32-286, Revision 3, 
dated October 3, 2008.
    (iii) Messier-Dowty Service Bulletin 201-32-43, Revision 3, 
dated October 3, 2008.
    (iv) Safran Service Bulletin 200-32-321, Revision 2, dated 
October 3, 2017.
    (v) Safran Service Bulletin 201-32-68, Revision 2, dated October 
3, 2017.
    (4) The following service information was approved for IBR on 
February 22, 2017 (82 FR 5362, January 18, 2017).
    (i) Airbus Service Bulletin A320-32-1416, including Appendix 01, 
dated March 10, 2014.
    (ii) [Reserved]
    (5) The following service information was approved for IBR on 
June 29, 2007 (72 FR 29241, May 25, 2007).
    (i) Airbus Service Bulletin A320-32A1273, Revision 02, including 
Appendix 01, dated May 26, 2005.
    (ii) [Reserved]
    (6) For Airbus service information identified in this AD, 
contact Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile 
Dewoitine No: 2, 31700 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.
    (7) For Safran and Messier-Dowty service information identified 
in this AD, contact Safran Landing Systems, One Carbon Way, Walton, 
KY 41094; telephone (859) 525-8583; fax (859) 485-8827; internet 
https://www.safran-landing-systems.com.
    (8) 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.
    (9) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on June 19, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-13545 Filed 6-26-19; 8:45 am]
 BILLING CODE 4910-13-P