Airworthiness Directives; Airbus Airplanes, 21955-21961 [2018-09847]

Download as PDF Federal Register / Vol. 83, No. 92 / Friday, May 11, 2018 / Proposed Rules 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Dassault Aviation: Docket No. FAA–2018– 0394; Product Identifier 2018–NM–036– AD. (a) Comments Due Date We must receive comments by June 25, 2018. (b) Affected ADs This AD affects AD 2010–26–05, Amendment 39–16544 (75 FR 79952, December 21, 2010) (‘‘AD 2010–26–05’’); AD 2012–02–18, Amendment 39–16941 (77 FR 12175, February 29, 2012) (‘‘AD 2012–02– 18’’); and AD 2017–09–03 Amendment 39– 18865 (82 FR 21467, May 9, 2017) (‘‘AD 2017–09–03’’). (c) Applicability This AD applies to Dassault Aviation Model MYSTERE–FALCON 50 airplanes, certificated in any category, all manufacturer serial numbers. sradovich on DSK3GMQ082PROD with PROPOSALS (d) Subject Air Transport Association (ATA) of America Code 05, Time limits/maintenance checks. (e) Reason This AD was prompted by a determination that more restrictive maintenance requirements and airworthiness limitations are necessary. We are issuing this AD to prevent reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. VerDate Sep<11>2014 17:56 May 10, 2018 Jkt 244001 (g) Revision of Maintenance or Inspection Program Within 90 days after the effective date of this AD, revise the maintenance or inspection program, as applicable, to incorporate the information specified in Chapter 5–40, Airworthiness Limitations, of the Dassault Falcon 50/50EX Maintenance Manual, Revision 24, dated July 2017. The initial compliance times for doing the tasks are at the time specified in Chapter 5–40, Airworthiness Limitations, of the Dassault Falcon 50/50EX Maintenance Manual, Revision 24, dated July 2017, or within 90 days after the effective date of this AD, whichever occurs later. (h) No Alternative Actions or Intervals After the maintenance or inspection program has been revised as required by paragraph (g) of this AD, no alternative actions (e.g., inspections), or intervals, may be used unless the actions, or intervals, are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (j)(1) of this AD. (i) Terminating Actions for Other ADs (1) Accomplishing the actions required by paragraph (g) of this AD terminates all requirements of AD 2017–09–03. (2) Accomplishing the actions required by paragraph (g) of this AD terminates all requirements of AD 2010–26–05 and AD 2012–02–18 for the Dassault Aviation Model MYSTERE–FALCON 50 airplanes specified in those ADs. (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Section, send it to the attention of the person identified in paragraph (k)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Dassault Aviation’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 21955 Airworthiness Directive 2018–0026, dated January 30, 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–2018–0394. (2) For more information about this AD, contact Tom Rodriguez, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th Street, Des Moines, WA 98198; telephone and fax 206– 231–3226. (3) For service information identified in this AD, contact Dassault Falcon Jet Corporation, Teterboro Airport, P.O. Box 2000, South Hackensack, NJ 07606; telephone 201–440–6700; internet http:// www.dassaultfalcon.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th Street, Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. Issued in Des Moines, Washington, on April 27, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–09979 Filed 5–10–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0390; Product Identifier 2017–NM–130–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all Airbus Model A300 series airplanes. This proposed AD was prompted by a revision of an airworthiness limitation items (ALI) document. This proposed AD would require revising the maintenance or inspection program, as applicable, to incorporate the specified maintenance requirements and airworthiness limitations. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by June 25, 2018. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. SUMMARY: E:\FR\FM\11MYP1.SGM 11MYP1 21956 Federal Register / Vol. 83, No. 92 / Friday, May 11, 2018 / Proposed Rules • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; internet http://www.airbus.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th Street, Des Moines, WA. For information on the availability of this material at the FAA, call 206–231– 3195. Examining the AD Docket You may examine the AD docket on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0390; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th Street, Des Moines, WA 98198; telephone and fax 206–231–3225. SUPPLEMENTARY INFORMATION: sradovich on DSK3GMQ082PROD with PROPOSALS Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2018–0390; Product Identifier 2017– NM–130–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM based on those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We VerDate Sep<11>2014 17:56 May 10, 2018 Jkt 244001 will also post a report summarizing each substantive verbal contact we receive about this NPRM. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2017–0145, dated August 31, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A300 series airplanes. The MCAI states: Some airworthiness limitations previously defined in A300 ALS Part 1 have been removed from that document and should normally be included in an ALS Part 4. Airbus does not plan to issue an ALS Part 4 for A300 aeroplanes. Nevertheless, failure to comply with these airworthiness limitations could result in an unsafe condition. For the reason described above, it has been decided to require the application of these airworthiness limitations through a separate AD. Previously, EASA issued AD 2013–0210 [which corresponds to FAA AD 2014–16–13, Amendment 39–17937 (79 FR 51083, August 27, 2014) (‘‘AD 2014–16–13’’)] to require implementation of airworthiness limitations applicable to main landing gear (MLG) barrel assembly, retraction actuator assembly, linkage assembly and flanged duct, which were previously defined in Revision 00 of A300 ALS Part 1 but removed from Revision 01 of A300 ALS Part 1, adding those limits as an Appendix to the AD. Since EASA AD 2013–0210 was issued, improvement of safe life component selection resulted, among others, in removal of 15 nose landing gear (NLG) parts from Revision 02 of A300 ALS Part 1. Consequently, this [EASA] AD retains the requirements of EASA AD 2013–0210, which is superseded, and requires, in addition to the implementation of airworthiness limitations already contained in EASA AD 2013–0210, the implementation of airworthiness limitations applicable to NLG barrel assembly and shock absorber assembly, previously contained in Revision 01 of A300 ALS Part 1, as specified in Appendix 1 of this AD. You may examine the MCAI in the AD docket on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0390. Relationship of Proposed AD to AD 2014–16–13 This NPRM would not supersede AD 2014–16–13. Rather, we have determined that a stand-alone AD would be more appropriate to address the changes in the MCAI. This NPRM would require revising the maintenance or inspection program to incorporate the PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 new maintenance requirements and airworthiness limitations. Accomplishment of the proposed actions would then terminate all requirements of AD 2014–16–13. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type designs. This proposed AD requires revisions to certain operator maintenance documents to include new actions (e.g., inspections). Compliance with these actions is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by this proposed AD, the operator may not be able to accomplish the actions described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (j)(1) of this proposed AD. The request should include a description of changes to the required inspections that will ensure the continued operational safety of the airplane. Differences Between This Proposed AD and the MCAI or Service Information The MCAI specifies that if there are findings from the airworthiness limitations section (ALS) inspection tasks, corrective actions must be accomplished in accordance with Airbus maintenance documentation. However, this proposed AD does not include that requirement. Operators of U.S.-registered airplanes are required by general airworthiness and operational regulations to perform maintenance using methods that are acceptable to the FAA. We consider those methods to be adequate to address any corrective actions necessitated by the findings of ALS inspections required by this proposed AD. Costs of Compliance We estimate that this proposed AD affects 5 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: E:\FR\FM\11MYP1.SGM 11MYP1 Federal Register / Vol. 83, No. 92 / Friday, May 11, 2018 / Proposed Rules We have determined that revising the maintenance or inspection program takes an average of 90 work-hours per operator, although we recognize that this number may vary from operator to operator. In the past, we have estimated that this action takes 1 work-hour per airplane. Since operators incorporate maintenance or inspection program changes for their affected fleet(s), we have determined that a per-operator estimate is more accurate than a perairplane estimate. Therefore, we estimate the total cost per operator to be $7,650 (90 work-hours × $85 per workhour). sradovich on DSK3GMQ082PROD with PROPOSALS Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. This proposed AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to VerDate Sep<11>2014 17:56 May 10, 2018 Jkt 244001 21957 issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. Airbus: Docket No. FAA–2018–0390; Product Identifier 2017–NM–130–AD. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We must receive comments by June 25, 2018. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. (f) Compliance The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: (g) Revision of Maintenance or Inspection Program 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): ■ PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 (a) Comments Due Date (b) Affected ADs This AD affects AD 2014–16–13, Amendment 39–17937 (79 FR 51083, August 27, 2014) (‘‘AD 2014–16–13’’). (c) Applicability This AD applies to Airbus Model A300 B2– 1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 05, Time Limits/Maintenance Checks. (e) Reason This AD was prompted by a revision of an airworthiness limitation items (ALI) document. We are issuing this AD to prevent reduced structural integrity of the airplane and possible loss of controllability of the airplane. Comply with this AD within the compliance times specified, unless already done. Within 90 days after the effective date of this AD, revise the maintenance or inspection program, as applicable, to incorporate the safe life limits included in figure 1 to paragraph (g) of this AD. The initial compliance time for the replacements is prior to the applicable life limits specified in figure 1 to paragraph (g) of this AD, or within 90 days after the effective date of this AD, whichever occurs later. The term ‘‘FH’’ in figure 1 to paragraph (g) of this AD means total flight hours. The term ‘‘LDG’’ in figure 1 to paragraph (g) of this AD means total airplane landings. BILLING CODE 4910–13–P E:\FR\FM\11MYP1.SGM 11MYP1 21958 Federal Register / Vol. 83, No. 92 / Friday, May 11, 2018 / Proposed Rules Figure 1 to paragraph (g) of this AD- New Life Limits for the Main Landing Gear (MLG) Barrel Assembly, Retraction Actuator Assembly, Linkage Assembly; Pneumatic Flange Duct; Nose Landing Gear (NLG) Barrel Assembly and Shock Absorber Assembly SAFE LIFE LIMITS(*) Part Name Part Number FH LOG Cal 66600 B2-1A B2-1C B2K-3C B2-20x N/A Affected Model(s) B4-2C 82-320 B4-2xx B4-1xx C4-203 F4-203 ATA 32-10-00 MAIN LANDING GEAR BARREL ASSEMBLY C66277-10 N/A X X X X X X X X X X X X X X X X X X X X X X X X X C66277-12 N/A 76600 N/A C66277-14 N/A 76600 N/A 058303-1 N/A 76600 N/A C66457 N/A 76600 N/A 048939 N/A 76600 N/A 048939-1 N/A 76600 N/A 058314-1 N/A 76600 N/A C66279 N/A 76600 N/A C66279-2 N/A 76600 N/A X X X X X X C66279-6 N/A 76600 N/A X X X X X X 058313-1 N/A 76600 N/A X X X X C61637-10 N/A 76600 N/A C61637-11 N/A 76600 N/A C61637-12 Stirrup N/A 76600 N/A X X X X X X X X X X X X X X Stirrup pin Universal joint Plate (Upper end) X X X C61638-10 N/A 53300 N/A X C61638-11 N/A 53300 N/A C61638-20 Plate (Rear head end) N/A 76600 N/A C68523-3 N/A 76600 X X X Tie rod X X X X X X X X X X X X X RETRACTION ACTUATOR ASSEMBLY (1) When SB AJ00-32..{)123 embodied before SB A300-32-0113. ! (2) When SB AJ00-32..{)123 embodied after SB AJ00-32-0113. C69028-1 N/A C69029-1 ( 1 ) N/A 34000 X ~000~ X 32000 C69029-2 N/A 32000 C69029-3 N/A 32000 N/A C69029-4 (2) N/A 22000 N/A Piston sradovich on DSK3GMQ082PROD with PROPOSALS End fitting VerDate Sep<11>2014 X X 17:56 May 10, 2018 X C67078 N/A 33000 N/A X X X X C67078-1 N/A 33000 N/A X X X X X X X X C61342-4 N/A 36700 N/A C66510-4 N/A 32000 Jkt 244001 PO 00000 Frm 00018 X N/A Fmt 4702 Sfmt 4725 X E:\FR\FM\11MYP1.SGM 11MYP1 EP11MY18.004</GPH> Sliding rod N/A C69028-4 21959 Federal Register / Vol. 83, No. 92 / Friday, May 11, 2018 / Proposed Rules LINKAGE ASSEMBLY Upper C61505 N/A 76600 N/A X X multiple link C61505-1 N/A 76600 N/A X X pin (Multiple link/Upper N/A C61505-20 X X N/A 76600 link) ATA36-11-05 PNEUMATIC (1) "xx" at the end of the P/N stands for anv number between 00 and 99. A21274063000 Duct flanged ( 1) N/A X X I X XX ATA32-20-00 NOSE LANDING GEAR BARREL ASSEMBLY (FIG.07) (1) Limitation applicable to WV01 & WV03 only. (2) Part must be replaced by a new one every time it is removed from the barrel. (3) The nut must be replaced by a new one every time it is removed from the pin. When the nut is temporarily removed and reinstalled for the purpose of performing maintenance outside a workshop, no replacement is required provided the nut's removal and reinstallation are performed on the same pin and neither the pin nor the nut accumulates time in service during the period between the removal and reinstallation. 068062 N/A (2) N/A X X X X X X End fitting pin nut MS17825-6 N/A (2) N/A X X X X X X ,- AN6-17 N/A (2) N/A X X X X X X 061183 N/A (2) X N/A N/A (2) X X X X 068063 NAS1306-220 N/A N/A N/A X X X X X X X X X X X X X X X X End fitting pin (2) C62032 65700 N/A X N/A 65700 N/A X X X X X X X X C62032-2 N/A 65700 N/A X X X X X X C62032-10 061184 N/A N/A 65700 65700 N/A N/A X X X X X X X X X X X X X 061184-1 X X X X X N/A X X X X X X N/A N/A 65700 65700 N/A N/A X X X X (1) X X X X N/A 65700 N/A X X X X X X C61453-15 N/A 65700 N/A X X X X X X C61453-20 N/A 65700 N/A X X X X X X C61453-40 N/A 65700 N/A X X X X X C61453-41 N/A 65700 N/A X X X X X X X C61453-205 sradovich on DSK3GMQ082PROD with PROPOSALS N/A 65700 C61453-1 VerDate Sep<11>2014 65700 N/A 068695 C61453 Rack N/A 068076 N/A 65700 N/A X X X X X X 17:56 May 10, 2018 Jkt 244001 PO 00000 Frm 00019 Fmt 4702 Sfmt 4725 E:\FR\FM\11MYP1.SGM 11MYP1 EP11MY18.005</GPH> End fitting N/A C62032-1 21960 Federal Register / Vol. 83, No. 92 / Friday, May 11, 2018 / Proposed Rules SAFE LIFE LIMITS(*) Part Name Part Number Affected Model(s) FH LOG Cal B2-1A B2-1C B2K-3C B2-20x 82-320 B4-2C B4-1xx B4-2xx C4-203 F4-203 C59050-30 N/A 24000 N/A X X X X X X C59050-40 N/A 24000 N/A X X X X X X X X X X X X X X X X X X C59050-50 N/A X N/A 65700 N/A X X C59050 N/A 24000 N/A X X (1) C59050-2 N/A 24000 N/A X X (1) C59050-3 N/A 24000 N/A X X (1) C59050-4 N/A 24000 N/A X X X X X X C59050-20 N/A 24000 N/A X X X X X X C59050-28 N/A 24000 N/A X X (1) X X X X C62223-1 N/A 65700 N/A X X X X X X C62223-15 N/A 65700 N/A X X X X X X C62223-20 N/A 65700 N/A X X X X X X C59562-2 Torque link pin (Upper & Lower) 65700 C59050-60 Turning tube N/A X N/A 65700 N/A X X X X X X C59562-3 N/A 65700 N/A X X X X C59562-4 N/A 65700 N/A X X X X X X C59562-20 Torque Links (Upper & Lower) N/A 65700 N/A X X X X X X C62041-1 N/A 65700 N/A X X X X X X C62041-15 N/A 65700 N/A X X X X X X ~ C62041-20 N/A 65700 N/A X X X X X X C62041-200 N/A 65700 N/A X X X X X X 053431 Torque link medium pin N/A 65700 N/A X X X X X X 053431-20 N/A 65700 N/A X X X X X X A X SL40110P X SHOCK ABSORBER ASSEMBLY Limitation applicable to WV01 & WV03 only. Limitation applicable to WV 00 only. Limitation applicable to WV 06 only. Part must be replaced by a new one every time it is removed from the sliding rod. Part must be replaced by a new one every time it is removed from the upper rod. Upper cam dowel sradovich on DSK3GMQ082PROD with PROPOSALS (4) N/A X X X X X X N/A 65700 N/A X X X X X X C62034-10 N/A 65700 N/A X X X X X X C68534 VerDate Sep<11>2014 N/A C62034-1 Upper cam C62270 N/A 65700 N/A X X X X X X Frm 00020 Fmt 4702 Sfmt 4725 17:56 May 10, 2018 Jkt 244001 PO 00000 E:\FR\FM\11MYP1.SGM 11MYP1 EP11MY18.006</GPH> (1) (2) (3) (4) (6) Federal Register / Vol. 83, No. 92 / Friday, May 11, 2018 / Proposed Rules (h) No Alternative Actions or Intervals After the maintenance or inspection program has been revised as required by paragraph (g) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (j)(1) of this AD. sradovich on DSK3GMQ082PROD with PROPOSALS (i) Terminating Action for AD 2014–16–13 Accomplishing the actions required by this AD terminates all requirements of AD 2014– 16–13. (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information VerDate Sep<11>2014 17:56 May 10, 2018 Jkt 244001 directly to the International Section, send it to the attention of the person identified in paragraph (k)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOAauthorized signature. (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2017–0145, dated August 31, 2017, for related information. This MCAI may be found in the AD docket on the internet at http://www.regulations.gov PO 00000 Frm 00021 Fmt 4702 Sfmt 9990 by searching for and locating Docket No. FAA–2018–0390. (2) For more information about this AD, contact Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th Street, Des Moines, WA 98198; telephone and fax 206– 231–3225. (3) For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; internet http://www.airbus.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th Street, Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. Issued in Des Moines, Washington, on April 27, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–09847 Filed 5–10–18; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\11MYP1.SGM 11MYP1 EP11MY18.007</GPH> BILLING CODE 4910–13–C 21961

Agencies

[Federal Register Volume 83, Number 92 (Friday, May 11, 2018)]
[Proposed Rules]
[Pages 21955-21961]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-09847]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0390; Product Identifier 2017-NM-130-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Airbus Model A300 series airplanes. This proposed AD was prompted by a 
revision of an airworthiness limitation items (ALI) document. This 
proposed AD would require revising the maintenance or inspection 
program, as applicable, to incorporate the specified maintenance 
requirements and airworthiness limitations. We are proposing this AD to 
address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by June 25, 2018.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.

[[Page 21956]]

     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Airbus, 
Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 
51; email [email protected]; internet http://www.airbus.com. You may view this service information at the FAA, 
Transport Standards Branch, 2200 South 216th Street, Des Moines, WA. 
For information on the availability of this material at the FAA, call 
206-231-3195.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0390; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this NPRM, the regulatory evaluation, any comments received, 
and other information. The street address for the Docket Operations 
office (telephone 800-647-5527) is in the ADDRESSES section. Comments 
will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th Street, Des Moines, WA 98198; telephone and fax 206-231-3225.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2018-0390; 
Product Identifier 2017-NM-130-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this NPRM. We will consider all 
comments received by the closing date and may amend this NPRM based on 
those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this NPRM.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2017-0145, dated August 31, 2017 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model A300 
series airplanes. The MCAI states:

    Some airworthiness limitations previously defined in A300 ALS 
Part 1 have been removed from that document and should normally be 
included in an ALS Part 4. Airbus does not plan to issue an ALS Part 
4 for A300 aeroplanes.
    Nevertheless, failure to comply with these airworthiness 
limitations could result in an unsafe condition.
    For the reason described above, it has been decided to require 
the application of these airworthiness limitations through a 
separate AD.
    Previously, EASA issued AD 2013-0210 [which corresponds to FAA 
AD 2014-16-13, Amendment 39-17937 (79 FR 51083, August 27, 2014) 
(``AD 2014-16-13'')] to require implementation of airworthiness 
limitations applicable to main landing gear (MLG) barrel assembly, 
retraction actuator assembly, linkage assembly and flanged duct, 
which were previously defined in Revision 00 of A300 ALS Part 1 but 
removed from Revision 01 of A300 ALS Part 1, adding those limits as 
an Appendix to the AD.
    Since EASA AD 2013-0210 was issued, improvement of safe life 
component selection resulted, among others, in removal of 15 nose 
landing gear (NLG) parts from Revision 02 of A300 ALS Part 1.
    Consequently, this [EASA] AD retains the requirements of EASA AD 
2013-0210, which is superseded, and requires, in addition to the 
implementation of airworthiness limitations already contained in 
EASA AD 2013-0210, the implementation of airworthiness limitations 
applicable to NLG barrel assembly and shock absorber assembly, 
previously contained in Revision 01 of A300 ALS Part 1, as specified 
in Appendix 1 of this AD.

    You may examine the MCAI in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0390.

Relationship of Proposed AD to AD 2014-16-13

    This NPRM would not supersede AD 2014-16-13. Rather, we have 
determined that a stand-alone AD would be more appropriate to address 
the changes in the MCAI. This NPRM would require revising the 
maintenance or inspection program to incorporate the new maintenance 
requirements and airworthiness limitations. Accomplishment of the 
proposed actions would then terminate all requirements of AD 2014-16-
13.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type designs.
    This proposed AD requires revisions to certain operator maintenance 
documents to include new actions (e.g., inspections). Compliance with 
these actions is required by 14 CFR 91.403(c). For airplanes that have 
been previously modified, altered, or repaired in the areas addressed 
by this proposed AD, the operator may not be able to accomplish the 
actions described in the revisions. In this situation, to comply with 
14 CFR 91.403(c), the operator must request approval for an alternative 
method of compliance according to paragraph (j)(1) of this proposed AD. 
The request should include a description of changes to the required 
inspections that will ensure the continued operational safety of the 
airplane.

Differences Between This Proposed AD and the MCAI or Service 
Information

    The MCAI specifies that if there are findings from the 
airworthiness limitations section (ALS) inspection tasks, corrective 
actions must be accomplished in accordance with Airbus maintenance 
documentation. However, this proposed AD does not include that 
requirement. Operators of U.S.-registered airplanes are required by 
general airworthiness and operational regulations to perform 
maintenance using methods that are acceptable to the FAA. We consider 
those methods to be adequate to address any corrective actions 
necessitated by the findings of ALS inspections required by this 
proposed AD.

Costs of Compliance

    We estimate that this proposed AD affects 5 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

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    We have determined that revising the maintenance or inspection 
program takes an average of 90 work-hours per operator, although we 
recognize that this number may vary from operator to operator. In the 
past, we have estimated that this action takes 1 work-hour per 
airplane. Since operators incorporate maintenance or inspection program 
changes for their affected fleet(s), we have determined that a per-
operator estimate is more accurate than a per-airplane estimate. 
Therefore, we estimate the total cost per operator to be $7,650 (90 
work-hours x $85 per work-hour).

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.
    This proposed AD is issued in accordance with authority delegated 
by the Executive Director, Aircraft Certification Service, as 
authorized by FAA Order 8000.51C. In accordance with that order, 
issuance of ADs is normally a function of the Compliance and 
Airworthiness Division, but during this transition period, the 
Executive Director has delegated the authority to issue ADs applicable 
to transport category airplanes to the Director of the System Oversight 
Division.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2018-0390; Product Identifier 2017-NM-130-AD.

(a) Comments Due Date

    We must receive comments by June 25, 2018.

(b) Affected ADs

    This AD affects AD 2014-16-13, Amendment 39-17937 (79 FR 51083, 
August 27, 2014) (``AD 2014-16-13'').

(c) Applicability

    This AD applies to Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-
203, B4-2C, B4-103, and B4-203 airplanes, certificated in any 
category.

(d) Subject

    Air Transport Association (ATA) of America Code 05, Time Limits/
Maintenance Checks.

(e) Reason

    This AD was prompted by a revision of an airworthiness 
limitation items (ALI) document. We are issuing this AD to prevent 
reduced structural integrity of the airplane and possible loss of 
controllability of the airplane.

(f) Compliance

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

(g) Revision of Maintenance or Inspection Program

    Within 90 days after the effective date of this AD, revise the 
maintenance or inspection program, as applicable, to incorporate the 
safe life limits included in figure 1 to paragraph (g) of this AD. 
The initial compliance time for the replacements is prior to the 
applicable life limits specified in figure 1 to paragraph (g) of 
this AD, or within 90 days after the effective date of this AD, 
whichever occurs later. The term ``FH'' in figure 1 to paragraph (g) 
of this AD means total flight hours. The term ``LDG'' in figure 1 to 
paragraph (g) of this AD means total airplane landings.
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(h) No Alternative Actions or Intervals

    After the maintenance or inspection program has been revised as 
required by paragraph (g) of this AD, no alternative actions (e.g., 
inspections) or intervals may be used unless the actions or 
intervals are approved as an alternative method of compliance (AMOC) 
in accordance with the procedures specified in paragraph (j)(1) of 
this AD.

(i) Terminating Action for AD 2014-16-13

    Accomplishing the actions required by this AD terminates all 
requirements of AD 2014-16-13.

(j) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Section, send it to the attention of 
the person identified in paragraph (k)(2) of this AD. Information 
may be emailed to: [email protected]. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Section, Transport Standards Branch, FAA; or the European Aviation 
Safety Agency (EASA); or Airbus's EASA Design Organization Approval 
(DOA). If approved by the DOA, the approval must include the DOA-
authorized signature.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2017-0145, dated August 31, 
2017, 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-2018-0390.
    (2) For more information about this AD, contact Dan Rodina, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 2200 South 216th Street, Des Moines, WA 98198; 
telephone and fax 206-231-3225.
    (3) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email [email protected]; internet http://www.airbus.com. You may view this service information at the FAA, 
Transport Standards Branch, 2200 South 216th Street, Des Moines, WA. 
For information on the availability of this material at the FAA, 
call 206-231-3195.

    Issued in Des Moines, Washington, on April 27, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-09847 Filed 5-10-18; 8:45 am]
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