Airworthiness Directives; Airbus Airplanes, 21196-21199 [2018-09743]

Download as PDF 21196 Federal Register / Vol. 83, No. 90 / Wednesday, May 9, 2018 / Proposed Rules Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed, 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 to the extent that it justifies making a regulatory distinction; 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 prepared an economic evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. 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: amozie on DSK3GDR082PROD with PROPOSALS ■ 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): ■ Airbus Helicopters: Docket No. FAA–2018– 0384; Product Identifier 2017–SW–061– AD. VerDate Sep<11>2014 17:09 May 08, 2018 Jkt 244001 (a) Applicability This AD applies to Model AS–365N2, AS 365 N3, EC 155B, EC155B1, SA–365N1, and SA–366G1 helicopters, certificated in any category. (b) Unsafe Condition This AD defines the unsafe condition as disbonding of the aft fuselage outer skin. This condition could result in loss of aft fuselage structural integrity and subsequent loss of control of the helicopter. (c) Comments Due Date We must receive comments by July 9, 2018. (d) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (e) Required Actions (1) Within 110 hours time-in-service (TIS), tap inspect the aft fuselage outer skin for disbonding between frames X4630 and X6630 in the areas depicted in Figure 1 of Airbus Helicopters Alert Service Bulletin (ASB) No. AS365–05.00.77, ASB No. SA366– 05.48, or ASB No. EC155–05A033, all Revision 0 and dated July 21, 2017 (ASB AS365–05.00.77, ASB SA366–05.48, or ASB EC155–05A033), as applicable for your model helicopter. Examples of acceptable and unacceptable disbonding areas are depicted in Figure 2 of ASB AS365–05.00.77, ASB SA366–05.48, and ASB EC155–05A033, as applicable for your model helicopter. (i) If there is no disbonding, repeat the tap inspection at intervals not to exceed 660 hours TIS. (ii) If there is disbonding within one square-shaped area measuring 3.94 in. x 3.94 in. (10 cm x 10 cm) that does not cross two skin panels, repeat the tap inspection at intervals not to exceed 110 hours TIS. (iii) If there is disbonding that exceeds one square-shaped area measuring 3.94 in. x 3.94 in. (10 cm x 10 cm) or crosses two skin panels, before further flight, repair or replace the panel. Thereafter, tap inspect the panel at intervals not to exceed 660 hours TIS. (2) Within 220 hours TIS, and thereafter at intervals not to exceed 110 hours TIS, clean the aft fuselage outer skin and using a light, visually inspect for distortion, wrinkling, and corrosion between frames X4630 and X6630 as depicted in Figure 1 of ASB AS365– 05.00.77, ASB SA366–05.48, or ASB EC155– 05A033, as applicable for your model helicopter. If there is any distortion, wrinkling, or corrosion, before further flight, tap inspect the area for disbonding by following the inspection instructions in paragraph (e)(1) of this AD. (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Section, Rotorcraft Standards Branch, FAA, may approve AMOCs for this AD. Send your proposal to: Matt Fuller, Senior Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email 9-ASWFTW-AMOC-Requests@faa.gov. PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC. (g) Additional Information The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2017–0165, dated September 5, 2017. You may view the EASA AD on the internet at https://www.regulations.gov in the AD Docket. (h) Subject Joint Aircraft Service Component (JASC) Code: 5302, Rotorcraft tail boom. Issued in Fort Worth, Texas, on April 26, 2018. Lance T. Gant, Director, Compliance & Airworthiness Division,Aircraft Certification Service. [FR Doc. 2018–09742 Filed 5–8–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0395; Product Identifier 2017–NM–136–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 A330–200 Freighter series airplanes, Model A330–200 series airplanes, Model A330–300 series airplanes, Model A340–200 series airplanes, Model A340–300 series airplanes, Model A340–500 series airplanes, and Model A340–600 series airplanes. This proposed AD was prompted by a report of deficient fatigue performance of high strength steel used in forgings. Components made from the affected high strength steel are installed on the main landing gear (MLG), nose landing gear (NLG), and center landing gear (CLG). This proposed AD would require identifying the part number and serial number of certain components installed on the MLG, NLG, and CLG; replacing affected parts; identifying the airplane’s weight variant; and determining the applicable life limit for SUMMARY: E:\FR\FM\09MYP1.SGM 09MYP1 Federal Register / Vol. 83, No. 90 / Wednesday, May 9, 2018 / Proposed Rules certain components installed on the MLG, NLG, and CLG. 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 https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330–A340@airbus.com; internet https://www.airbus.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. amozie on DSK3GDR082PROD with PROPOSALS Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0395; 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: Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198–6547; telephone and fax 206–231–3229. 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– 2018–0395; Product Identifier 2017– VerDate Sep<11>2014 17:09 May 08, 2018 Jkt 244001 21197 NM–136–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this NPRM. part numbers and serial numbers of the main fitting, bogie beam and sliding piston of the MLG, NLG, and CLG, and the airplane’s weight variant], and implementation of the reduced life limits for the affected parts and replacement of any parts that are close to, or have exceeded the applicable reduced life limit. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2017–0185, dated September 22, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A330–200 Freighter series airplanes, Model A330– 200 series airplanes, Model A330–300 series airplanes, Model A340–200 series airplanes, Model A340–300 series airplanes, Model A340–500 series airplanes, and Model A340–600 series airplanes. The MCAI states: Airbus has issued the following service information. These documents are distinct since they apply to different airplane models. • Service Bulletin A330–32–3281, Revision 02, dated June 16, 2017, including Appendixes 01 through 06; and Service Bulletin A340–32–4310, Revision 02, dated June 16, 2017, including Appendixes 01 through 06. This service information includes procedures for inspections to identify the part numbers and serial numbers of the main fittings, bogie beams, and sliding pistons of the MLG; and procedures for determining the airplane’s weight variant. This service information also describes the reduced life limits for affected parts. These documents are distinct since they apply to different airplane models. • Service Bulletin A340–32–5119, Revision 01, dated January 31, 2017, including Appendixes 01 through 07. This service information includes procedures for inspections to identify the part numbers and serial numbers of the main fittings and bogie beams of the MLG, NLG, and CLG; and procedures for determining the airplane’s weight variant. This service information also describes the reduced life limits for affected parts. In addition, Airbus has issued the following service information, which describes life limits for affected parts. These documents are distinct since they apply to different airplane models and to different life limited parts. • A330 Airworthiness Limitations Section (ALS) Part 1, ‘‘Safe Life Airworthiness Limitation Items (SL– ALI),’’ Revision 09, dated September 18, 2017. • A330 ALS Part 1, ‘‘Safe Life Airworthiness Limitation Items (SL– ALI),’’ Variation 9.2, dated November 28, 2017. • A340 Airworthiness Limitations Section (ALS) Part 1, ‘‘Safe Life Airworthiness Limitation Items (SL– ALI),’’ Revision 09, dated September 18, 2017. In 2006, Messier-Dowty identified a deficiency in the fatigue performance of 300M high strength steel used in forgings. The root cause for this fatigue deficiency was the processing during preparation of the material. After investigation, it was determined that the following material sources (S) were affected by this fatigue deficiency: Electralloy (S1), RSM (S2A, S2B or S2C), Latrobe (S3) and Aubert et Duval (S4). Consequently, reduced lives were calculated for certain landing gear main fittings, bogie beams and sliding pistons, determined to be affected by the 300M material properties quality issue. These components are installed on Main, Nose and Centre Landing Gears (MLG, NLG, CLG) of A330 and A340 aeroplanes. This condition, if not corrected, could lead to structural failure of a landing gear, possibly resulting in loss of control of the aeroplane during take-off or landing. To initially address this potential unsafe condition, Airbus published reduced life limits for the affected parts from material sources S1, S2 and S3 in the applicable Airworthiness Limitation Section (ALS) Part 1. Later, it was determined that ALS Part 1 was an inappropriate place for recording the reduced lives and Airbus published Service Bulletin (SB) A330–32–3281, SB A340–32– 4310, and SB A340–32–5119, as applicable, to provide identification and replacement instructions for affected parts made of all material sources S1, S2, S3 and S4. This action was also accomplished to simplify Airbus ALS Part 1. For the reasons described above, this [EASA] AD requires [identification of the PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 You may examine the MCAI in the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0395. Related Service Information Under 1 CFR Part 51 E:\FR\FM\09MYP1.SGM 09MYP1 21198 Federal Register / Vol. 83, No. 90 / Wednesday, May 9, 2018 / Proposed Rules • A340 ALS Part 1, ‘‘Safe Life Airworthiness Limitation Items (SL– ALI),’’ Variation 9.2, dated November 28, 2017. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of these same type designs. Costs of Compliance We estimate that this proposed AD affects 103 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Inspection ........................................................ 4 work-hours × $85 per hour = $340 ............. amozie on DSK3GDR082PROD with PROPOSALS We have received no definitive data that would enable us to provide cost estimates for the on-condition part replacements specified in this proposed AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. 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 VerDate Sep<11>2014 17:09 May 08, 2018 Jkt 244001 Cost per product Parts cost $0 Cost on U.S. operators $340 $35,020 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. (b) Affected ADs None. List of Subjects in 14 CFR Part 39 (e) Reason This AD was prompted by a report of deficient fatigue performance of 300M high strength steel used in forgings. Components made of 300M high strength steel are installed on the main landing gear (MLG), nose landing gear (NLG), and center landing gear (CLG). We are issuing this AD to detect and correct parts made from 300M high strength steel, which if uncorrected, could lead to structural failure of the landing gear, and possibly loss of control of the airplane during take-off or landing. 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): ■ Airbus: Docket No. FAA–2018–0395; Product Identifier 2017–NM–136–AD. (a) Comments Due Date We must receive comments by June 25, 2018. PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(7) of this AD; certificated in any category; all manufacturer serial numbers. (1) Model A330–201, –202, –203, –223, and –243 airplanes. (2) Model A330–223F and –243F airplanes. (3) Model A330–301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes. (4) Model A340–211, –212, and –213 airplanes. (5) Model A340–311, –312, and –313 airplanes. (6) Model A340–541 airplanes. (7) Model A340–642 airplanes. (d) Subject Air Transport Association (ATA) of America Code 32, Landing Gear. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definitions (1) For the purpose of this AD, an affected part is any main fitting, bogie beam, or sliding piston of the MLG, NLG, or CLG installed on the airplane, having a part number and serial number combination specified in the applicable service information identified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD. (2) For the purpose of this AD, a serviceable part is any main fitting, bogie beam, or sliding piston of the MLG, NLG, or E:\FR\FM\09MYP1.SGM 09MYP1 Federal Register / Vol. 83, No. 90 / Wednesday, May 9, 2018 / Proposed Rules CLG that has not exceeded the applicable life limit specified in paragraph (g)(2)(i), (g)(2)(ii), or (g)(2)(iii) of this AD, since first installation on an airplane. (i) The life limit specified in the applicable service information identified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD. (ii) The life limit specified in Airbus A330 Airworthiness Limitations Section (ALS) Part 1, ‘‘Safe Life Airworthiness Limitation Items (SL–ALI),’’ Revision 09, dated September 18, 2017, and A330 ALS Part 1, ‘‘Safe Life Airworthiness Limitation Items (SL–ALI),’’ Variation 9.2, dated November 28, 2017. (iii) The life limit specified in Airbus A340 Airworthiness Limitations Section (ALS) Part 1, ‘‘Safe Life Airworthiness Limitation Items (SL–ALI),’’ Revision 09, dated September 18, 2017, and A340 ALS Part 1, ‘‘Safe Life Airworthiness Limitation Items (SL–ALI),’’ Variation 9.2, dated November 28, 2017. (h) Identification of Part Number, Serial Number, Weight Variant, and Reduced Life Limit Within 3 months after the effective date of this AD: Identify the part number and serial number of each main fitting, bogie beam, and sliding piston of the MLG, NLG, and CLG installed on the airplane; identify the airplane’s weight variant; and determine the applicable reduced life limit; in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (h)(1), (h)(2), or (h)(3) of this AD. A review of airplane maintenance records is acceptable for identification of the installed main fittings, bogie beams, and sliding pistons of the MLG, NLG, and CLG, provided the part number and serial number of each component can be conclusively identified by that review. (1) Airbus Service Bulletin A330–32–3281, Revision 02, dated June 16, 2017, including Appendixes 01 through 06. (2) Airbus Service Bulletin A340–32–4310, Revision 02, dated June 16, 2017, including Appendixes 01 through 06. (3) Airbus Service Bulletin A340–32–5119, Revision 01, dated January 31, 2017, including Appendixes 01 through 07. amozie on DSK3GDR082PROD with PROPOSALS (i) Replacement of Affected Parts Prior to exceeding the applicable life limit, as specified in the applicable service information identified in paragraph (h)(1), (h)(2), or (h)(3) of this AD, or within 3 months after the effective date of this AD, whichever occurs later: Replace each affected part (as defined in paragraph (g)(1) of this AD) with a serviceable part (as defined in paragraph (g)(2) of this AD). (j) Parts Installation Specification As of the effective date of this AD, any affected part (as defined in paragraph (g)(1) of this AD) may be used as a replacement part, provided the affected part is also a serviceable part (as defined in paragraph (g)(2) of this AD), and following installation, the affected part is replaced prior to exceeding the applicable life limit as specified in paragraph (g)(2) of this AD. (k) Other FAA AD Provisions The following provisions also apply to this AD: VerDate Sep<11>2014 17:09 May 08, 2018 Jkt 244001 (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 (l)(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. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017–0185, dated September 22, 2017, for related information. This MCAI may be found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2018–0395. (2) For more information about this AD, contact Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198–6547; telephone and fax 206–231–3229. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; internet https://www.airbus.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. PO 00000 Frm 00012 Fmt 4702 Issued in Des Moines, Washington, on April 30, 2018. Dionne Palermo, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–09743 Filed 5–8–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0326; Product Identifier 2018–CE–006–AD] RIN 2120–AA64 Airworthiness Directives; SOCATA Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 98–16–03 for SOCATA Models TB 9 and TB 10 airplanes. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as fatigue cracking of the wing front attachments on the wing and fuselage sides. We are issuing this proposed AD to require actions to address the unsafe condition on these products. SUMMARY: We must receive comments on this proposed AD by June 25, 2018. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact SOCATA, Direction des services, 65921 Tarbes Cedex 9, France; phone: +33 (0) 5 62 41 73 00; fax: +33 (0) 5 62 41 76 54; email: DATES: (l) Related Information Sfmt 4702 21199 E:\FR\FM\09MYP1.SGM 09MYP1

Agencies

[Federal Register Volume 83, Number 90 (Wednesday, May 9, 2018)]
[Proposed Rules]
[Pages 21196-21199]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-09743]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0395; Product Identifier 2017-NM-136-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Airbus Model A330-200 Freighter series airplanes, Model A330-200 series 
airplanes, Model A330-300 series airplanes, Model A340-200 series 
airplanes, Model A340-300 series airplanes, Model A340-500 series 
airplanes, and Model A340-600 series airplanes. This proposed AD was 
prompted by a report of deficient fatigue performance of high strength 
steel used in forgings. Components made from the affected high strength 
steel are installed on the main landing gear (MLG), nose landing gear 
(NLG), and center landing gear (CLG). This proposed AD would require 
identifying the part number and serial number of certain components 
installed on the MLG, NLG, and CLG; replacing affected parts; 
identifying the airplane's weight variant; and determining the 
applicable life limit for

[[Page 21197]]

certain components installed on the MLG, NLG, and CLG. 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 https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Airbus 
SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 
80; email [email protected]; internet https://www.airbus.com. You may view this service information at the FAA, 
Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For 
information on the availability of this material at the FAA, call 206-
231-3195.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0395; 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: Vladimir Ulyanov, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198-6547; telephone and fax 206-231-3229.

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-2018-0395; 
Product Identifier 2017-NM-136-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this NPRM. We will consider all 
comments received by the closing date and may amend this NPRM based on 
those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this NPRM.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2017-0185, dated September 22, 2017 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for all Airbus Model A330-200 Freighter 
series airplanes, Model A330-200 series airplanes, Model A330-300 
series airplanes, Model A340-200 series airplanes, Model A340-300 
series airplanes, Model A340-500 series airplanes, and Model A340-600 
series airplanes. The MCAI states:

    In 2006, Messier-Dowty identified a deficiency in the fatigue 
performance of 300M high strength steel used in forgings. The root 
cause for this fatigue deficiency was the processing during 
preparation of the material. After investigation, it was determined 
that the following material sources (S) were affected by this 
fatigue deficiency: Electralloy (S1), RSM (S2A, S2B or S2C), Latrobe 
(S3) and Aubert et Duval (S4).
    Consequently, reduced lives were calculated for certain landing 
gear main fittings, bogie beams and sliding pistons, determined to 
be affected by the 300M material properties quality issue. These 
components are installed on Main, Nose and Centre Landing Gears 
(MLG, NLG, CLG) of A330 and A340 aeroplanes.
    This condition, if not corrected, could lead to structural 
failure of a landing gear, possibly resulting in loss of control of 
the aeroplane during take-off or landing.
    To initially address this potential unsafe condition, Airbus 
published reduced life limits for the affected parts from material 
sources S1, S2 and S3 in the applicable Airworthiness Limitation 
Section (ALS) Part 1. Later, it was determined that ALS Part 1 was 
an inappropriate place for recording the reduced lives and Airbus 
published Service Bulletin (SB) A330-32-3281, SB A340-32-4310, and 
SB A340-32-5119, as applicable, to provide identification and 
replacement instructions for affected parts made of all material 
sources S1, S2, S3 and S4. This action was also accomplished to 
simplify Airbus ALS Part 1.
    For the reasons described above, this [EASA] AD requires 
[identification of the part numbers and serial numbers of the main 
fitting, bogie beam and sliding piston of the MLG, NLG, and CLG, and 
the airplane's weight variant], and implementation of the reduced 
life limits for the affected parts and replacement of any parts that 
are close to, or have exceeded the applicable reduced life limit.

    You may examine the MCAI in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0395.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information. These 
documents are distinct since they apply to different airplane models.
     Service Bulletin A330-32-3281, Revision 02, dated June 16, 
2017, including Appendixes 01 through 06; and Service Bulletin A340-32-
4310, Revision 02, dated June 16, 2017, including Appendixes 01 through 
06. This service information includes procedures for inspections to 
identify the part numbers and serial numbers of the main fittings, 
bogie beams, and sliding pistons of the MLG; and procedures for 
determining the airplane's weight variant. This service information 
also describes the reduced life limits for affected parts. These 
documents are distinct since they apply to different airplane models.
     Service Bulletin A340-32-5119, Revision 01, dated January 
31, 2017, including Appendixes 01 through 07. This service information 
includes procedures for inspections to identify the part numbers and 
serial numbers of the main fittings and bogie beams of the MLG, NLG, 
and CLG; and procedures for determining the airplane's weight variant. 
This service information also describes the reduced life limits for 
affected parts.
    In addition, Airbus has issued the following service information, 
which describes life limits for affected parts. These documents are 
distinct since they apply to different airplane models and to different 
life limited parts.
     A330 Airworthiness Limitations Section (ALS) Part 1, 
``Safe Life Airworthiness Limitation Items (SL-ALI),'' Revision 09, 
dated September 18, 2017.
     A330 ALS Part 1, ``Safe Life Airworthiness Limitation 
Items (SL-ALI),'' Variation 9.2, dated November 28, 2017.
     A340 Airworthiness Limitations Section (ALS) Part 1, 
``Safe Life Airworthiness Limitation Items (SL-ALI),'' Revision 09, 
dated September 18, 2017.

[[Page 21198]]

     A340 ALS Part 1, ``Safe Life Airworthiness Limitation 
Items (SL-ALI),'' Variation 9.2, dated November 28, 2017.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

Costs of Compliance

    We estimate that this proposed AD affects 103 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspection............................  4 work-hours x $85 per                $0            $340         $35,020
                                         hour = $340.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition part replacements specified in this 
proposed AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.
    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-2018-0395; Product Identifier 2017-NM-136-AD.

(a) Comments Due Date

    We must receive comments by June 25, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(7) of this AD; certificated in any category; all 
manufacturer serial numbers.
    (1) Model A330-201, -202, -203, -223, and -243 airplanes.
    (2) Model A330-223F and -243F airplanes.
    (3) Model A330-301, -302, -303, -321, -322, -323, -341, -342, 
and -343 airplanes.
    (4) Model A340-211, -212, and -213 airplanes.
    (5) Model A340-311, -312, and -313 airplanes.
    (6) Model A340-541 airplanes.
    (7) Model A340-642 airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by a report of deficient fatigue 
performance of 300M high strength steel used in forgings. Components 
made of 300M high strength steel are installed on the main landing 
gear (MLG), nose landing gear (NLG), and center landing gear (CLG). 
We are issuing this AD to detect and correct parts made from 300M 
high strength steel, which if uncorrected, could lead to structural 
failure of the landing gear, and possibly loss of control of the 
airplane during take-off or landing.

(f) Compliance

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

(g) Definitions

    (1) For the purpose of this AD, an affected part is any main 
fitting, bogie beam, or sliding piston of the MLG, NLG, or CLG 
installed on the airplane, having a part number and serial number 
combination specified in the applicable service information 
identified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD.
    (2) For the purpose of this AD, a serviceable part is any main 
fitting, bogie beam, or sliding piston of the MLG, NLG, or

[[Page 21199]]

CLG that has not exceeded the applicable life limit specified in 
paragraph (g)(2)(i), (g)(2)(ii), or (g)(2)(iii) of this AD, since 
first installation on an airplane.
    (i) The life limit specified in the applicable service 
information identified in paragraphs (h)(1), (h)(2), and (h)(3) of 
this AD.
    (ii) The life limit specified in Airbus A330 Airworthiness 
Limitations Section (ALS) Part 1, ``Safe Life Airworthiness 
Limitation Items (SL-ALI),'' Revision 09, dated September 18, 2017, 
and A330 ALS Part 1, ``Safe Life Airworthiness Limitation Items (SL-
ALI),'' Variation 9.2, dated November 28, 2017.
    (iii) The life limit specified in Airbus A340 Airworthiness 
Limitations Section (ALS) Part 1, ``Safe Life Airworthiness 
Limitation Items (SL-ALI),'' Revision 09, dated September 18, 2017, 
and A340 ALS Part 1, ``Safe Life Airworthiness Limitation Items (SL-
ALI),'' Variation 9.2, dated November 28, 2017.

(h) Identification of Part Number, Serial Number, Weight Variant, and 
Reduced Life Limit

    Within 3 months after the effective date of this AD: Identify 
the part number and serial number of each main fitting, bogie beam, 
and sliding piston of the MLG, NLG, and CLG installed on the 
airplane; identify the airplane's weight variant; and determine the 
applicable reduced life limit; in accordance with the Accomplishment 
Instructions of the applicable service information identified in 
paragraph (h)(1), (h)(2), or (h)(3) of this AD. A review of airplane 
maintenance records is acceptable for identification of the 
installed main fittings, bogie beams, and sliding pistons of the 
MLG, NLG, and CLG, provided the part number and serial number of 
each component can be conclusively identified by that review.
    (1) Airbus Service Bulletin A330-32-3281, Revision 02, dated 
June 16, 2017, including Appendixes 01 through 06.
    (2) Airbus Service Bulletin A340-32-4310, Revision 02, dated 
June 16, 2017, including Appendixes 01 through 06.
    (3) Airbus Service Bulletin A340-32-5119, Revision 01, dated 
January 31, 2017, including Appendixes 01 through 07.

(i) Replacement of Affected Parts

    Prior to exceeding the applicable life limit, as specified in 
the applicable service information identified in paragraph (h)(1), 
(h)(2), or (h)(3) of this AD, or within 3 months after the effective 
date of this AD, whichever occurs later: Replace each affected part 
(as defined in paragraph (g)(1) of this AD) with a serviceable part 
(as defined in paragraph (g)(2) of this AD).

(j) Parts Installation Specification

    As of the effective date of this AD, any affected part (as 
defined in paragraph (g)(1) of this AD) may be used as a replacement 
part, provided the affected part is also a serviceable part (as 
defined in paragraph (g)(2) of this AD), and following installation, 
the affected part is replaced prior to exceeding the applicable life 
limit as specified in paragraph (g)(2) of this AD.

(k) 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 (l)(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.
    (3) Required for Compliance (RC): If any service information 
contains procedures or tests that are identified as RC, those 
procedures and tests must be done to comply with this AD; any 
procedures or tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2017-0185, dated September 22, 2017, for related 
information. This MCAI may be found in the AD docket on the internet 
at https://www.regulations.gov by searching for and locating Docket 
No. FAA-2018-0395.
    (2) For more information about this AD, contact Vladimir 
Ulyanov, Aerospace Engineer, International Section, Transport 
Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198-
6547; telephone and fax 206-231-3229.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email [email protected]; 
internet https://www.airbus.com. You may view this service 
information at the FAA, Transport Standards Branch, 2200 South 216th 
St., Des Moines, WA. For information on the availability of this 
material at the FAA, call 206-231-3195.

    Issued in Des Moines, Washington, on April 30, 2018.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-09743 Filed 5-8-18; 8:45 am]
 BILLING CODE 4910-13-P
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