Airworthiness Directives; Airbus Airplanes, 18727-18730 [2018-08654]

Download as PDF 18727 Rules and Regulations Federal Register Vol. 83, No. 83 Monday, April 30, 2018 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. FEDERAL HOUSING FINANCE AGENCY 12 CFR Part 1238 [No. 2018–N–04] Orders: Reporting by Regulated Entities of Stress Testing Results as of December 31, 2017; Summary Instructions and Guidance Federal Housing Finance Agency. ACTION: Orders. AGENCY: In this document, the Federal Housing Finance Agency (FHFA) provides notice that it issued Orders, dated March 1, 2018, with respect to stress test reporting as of December 31, 2017, under section 165(i)(2) of the Dodd-Frank Wall Street Reform and Consumer Protection Act (Dodd-Frank Act). Summary Instructions and Guidance accompanied the Orders to provide testing scenarios. DATES: Effective April 30, 2018. Each Order is applicable March 1, 2018. FOR FURTHER INFORMATION CONTACT: John Williams, Manager, Financial Performance Reporting, Enterprise Financial Reporting Section, (202) 649– 3159, John.Williams@fhfa.gov; Stefan Szilagyi, Examination Manager, Office of Risk Modeling, Division of Bank Regulation (202) 649–3515, Stefan.Szilagyi@fhfa.gov; Karen Heidel, Assistant General Counsel, Office of General Counsel, (202) 649–3073, Karen.Heidel@fhfa.gov; or Mark D. Laponsky, Deputy General Counsel, Office of General Counsel, (202) 649– 3054, Mark.Laponsky@fhfa.gov. The telephone number for the Telecommunications Device for the Hearing Impaired is (800) 877–8339. SUPPLEMENTARY INFORMATION: sradovich on DSK3GMQ082PROD with RULES SUMMARY: I. Background FHFA is responsible for ensuring that the regulated entities operate in a safe and sound manner, including the VerDate Sep<11>2014 17:01 Apr 27, 2018 Jkt 244001 maintenance of adequate capital and internal controls, that their operations and activities foster liquid, efficient, competitive, and resilient national housing finance markets, and that they carry out their public policy missions through authorized activities. See 12 U.S.C. 4513. These Orders are being issued under 12 U.S.C. 4516(a), which authorizes the Director of FHFA to require by Order that the regulated entities submit regular or special reports to FHFA and establishes remedies and procedures for failing to make reports required by Order. The Orders, through the accompanying Summary Instructions and Guidance, prescribe for the regulated entities the scenarios to be used for stress testing. The Summary Instructions and Guidance also provides to the regulated entities advice concerning the content and format of reports required by the Orders and the rule. II. Orders, Summary Instructions and Guidance For the convenience of the affected parties and the public, the text of the Orders follows below in its entirety. The Orders and Summary Instructions and Guidance are also available for public inspection and copying at the Federal Housing Finance Agency’s Freedom of Information Act (FOIA) Reading Room at https://www.fhfa.gov/AboutUs/ FOIAPrivacy/Pages/Reading-Room.aspx by clicking on ‘‘Click here to view Orders’’ under the Final Opinions and Orders heading. You may also access these documents at http://www.fhfa.gov/ SupervisionRegulation/ DoddFrankActStressTests. The text of the Orders is as follows: Federal Housing Finance Agency Order Nos. 2018–OR–B–1, 2018–OR– FNMA–1, and 2018–FHLMC–1 Reporting by Regulated Entities of Stress Testing Results as of December 31, 2017 Whereas, section 165(i)(2) of the Dodd-Frank Wall Street Reform and Consumer Protection Act (‘‘Dodd-Frank Act’’) requires certain financial companies with total consolidated assets of more than $10 billion, and which are regulated by a primary Federal financial regulatory agency, to conduct annual stress tests to determine whether the companies have the capital necessary to absorb losses as a result of adverse economic conditions; PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 Whereas, FHFA’s rule implementing section 165(i)(2) of the Dodd-Frank Act is codified as 12 CFR 1238 and requires that ‘‘[e]ach regulated entity must file a report in the manner and form established by FHFA.’’ 12 CFR 1238.5(b); Whereas, The Board of Governors of the Federal Reserve System issued stress testing scenarios on February 1, 2018; and Whereas, section 1314 of the Safety and Soundness Act, 12 U.S.C. 4514(a) authorizes the Director of FHFA to require regulated entities, by general or specific order, to submit such reports on their management, activities, and operation as the Director considers appropriate. Now therefore, it is hereby Ordered as follows: Each regulated entity shall report to FHFA and to the Board of Governors of the Federal Reserve System the results of the stress testing as required by 12 CFR 1238, in the form and with the content described therein and in the Summary Instructions and Guidance, with Appendices 1 through 12 thereto, accompanying this Order and dated March 1, 2018. It is so ordered, this the 1st day of March, 2018. This Order is effective immediately. Signed at Washington, DC, this 1st day of March, 2018. Melvin L. Watt, Director, Federal Housing Finance Agency. Dated: April 23, 2018. Melvin L. Watt, Director, Federal Housing Finance Agency. [FR Doc. 2018–09072 Filed 4–27–18; 8:45 am] BILLING CODE 8070–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0305; Product Identifier 2013–NM–226–AD; Amendment 39–19259; AD 2018–09–03] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. AGENCY: E:\FR\FM\30APR1.SGM 30APR1 18728 Federal Register / Vol. 83, No. 83 / Monday, April 30, 2018 / Rules and Regulations Final rule; request for comments. ACTION: We are superseding Airworthiness Directive (AD) 2009–11– 08, which applied to certain Airbus Model A330–202, –223, –243, –301, –322, and –342 airplanes. AD 2009–11– 08 required repetitive special detailed (high frequency eddy current) inspections to detect cracking of the keel beam fitting horizontal flange edge at a certain frame (FR) on the left- and right-hand sides of the fuselage, and repair if necessary. This AD was prompted by a new fatigue and damage tolerance evaluation that concluded the current inspection thresholds and intervals had to be modified. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. We are issuing this AD to address the unsafe condition on these products. DATES: This AD becomes effective May 15, 2018. We must receive comments on this AD by June 14, 2018. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. sradovich on DSK3GMQ082PROD with RULES SUMMARY: 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– 0305; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, VerDate Sep<11>2014 17:01 Apr 27, 2018 Jkt 244001 International Section, Transport Standards Branch, FAA, 2200 South 216th Street, Des Moines, WA 98198; telephone and fax: 206–231–3229. SUPPLEMENTARY INFORMATION: Discussion We issued AD 2009–11–08, Amendment 39–15918 (74 FR 25404, May 28, 2009) (‘‘AD 2009–11–08’’), which applied to certain Airbus Model A330–202, –223, –243, –301, –322, and –342 airplanes. AD 2009–11–08 was prompted by reports of cracks on the left- and right-hand sides between the crossing area of the keel angle fitting and the front spar of the center wing box. AD 2009–11–08 required a special detailed (high frequency eddy current) inspection to detect cracking of the keel beam fitting horizontal flange edge at FR40 on the left- and right-hand sides of the fuselage, and repair if necessary. We issued AD 2009–11–08 to detect and correct cracking on the left- and righthand sides, between the crossing area of the keel angle fitting and the front spar of the center wing box, which if not corrected, could affect the structural integrity of the airplane. Since we issued AD 2009–11–08, a new fatigue and damage tolerance evaluation was conducted by the manufacturer. It was concluded that, due to airplane utilization, the current inspection thresholds and intervals had to be modified. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2013–0247, dated October 10, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A330–202, –223, –243, –301, –322, and –342 airplanes. The MCAI states: During the A330 and A340 aeroplane fatigue test, cracks appeared on the right and left sides between the crossing area of the keel angle fitting and the front spar of the Centre Wing Box (CWB). Several modifications were introduced in the fleet in the area of frame (FR) 40 keel angle assembly in order to prevent these cracks. However, the new design caused interference between one fastener and the keel angle which was corrected by further local reprofiling of the keel angle horizontal flange. This condition, if not detected and corrected, could result in reduced structural integrity of the area. Prompted by these findings, EASA issued AD 2008–0213 [which corresponds to FAA AD 2009–11–08] to require accomplishment of repetitive special detailed inspection on the horizontal flange of the keel beam in the area of first fastener hole aft of FR40 and, depending on findings, accomplishment of a repair. PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 Since that [EASA] AD was issued, a new fatigue and damage tolerance evaluation was conducted by Airbus. It was concluded that, due to aeroplane utilisation, the current inspection thresholds and intervals had to be modified. For the reason described above, this [EASA] AD retains the requirements of EASA AD 2008–0213, which is superseded, and redefines the thresholds and intervals. You may examine the MCAI on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2018–0305. FAA’s Determination and Requirements of This 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. We are issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. FAA’s Determination of the Effective Date Since there are currently no domestic operators of this product, we find good cause that notice and opportunity for prior public comment are unnecessary. In addition, for the reason(s) stated above, we find that good cause exists for making this amendment effective in less than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2018–0305; Product Identifier 2013–NM–226–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD based on those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. E:\FR\FM\30APR1.SGM 30APR1 Federal Register / Vol. 83, No. 83 / Monday, April 30, 2018 / Rules and Regulations Costs of Compliance Currently, there are no affected U.S.registered airplanes. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition, and doing the actions specified in those instructions. Based on 18729 the actions specified in the MCAI AD, we are providing the following cost estimates for an affected airplane that is placed on the U.S. Register in the future: ESTIMATED COSTS Action Labor cost Inspection [new action] ................................... 9 work-hours × $85 per hour = $765 ............. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in the MCAI 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 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. sradovich on DSK3GMQ082PROD with RULES Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: VerDate Sep<11>2014 17:01 Apr 27, 2018 Jkt 244001 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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] 2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2009–11–08, Amendment 39–15918 (74 FR 25404, May 28, 2009), and adding the following new AD: ■ 2018–09–03 Airbus: Amendment 39–19259; Docket No. FAA–2018–0305; Product Identifier 2013–NM–226–AD. (a) Effective Date This AD becomes effective May 15, 2018. (b) Affected ADs This AD replaces AD 2009–11–08, Amendment 39–15918 (74 FR 25404, May 28, 2009) (‘‘AD 2009–11–08’’). (c) Applicability This AD applies to Airbus Model A330– 202, –223, –243, –301, –322, and –342 airplanes, certificated in any category, manufacturer serial numbers: 0177, 0181, 0183, 0184, 0188, 0189, 0191, 0195, 0198, 0200, 0203, 0205, 0206, 0209, 0211, 0219, 0222, 0223, 0224, 0226, 0229, 0230, 0231, 0232, 0234, 0238, 0240, 0241, 0244, 0247, PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 $0 Cost on U.S. operators $765 $0 0248, 0249, 0250, 0251, 0253, 0254, and 0255. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by reports of cracks on the left- and right-hand sides between the crossing area of the keel angle fitting and the front spar of the center wing box and by a new fatigue and damage tolerance evaluation that concluded the current inspection thresholds and intervals had to be modified. We are issuing this AD to detect and correct cracking on the left- and right-hand sides between the crossing area of the keel angle fitting and the front spar of the center wing box, which if not corrected, could affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions ■ § 39.13 Cost per product Parts cost Within 30 days after the effective date of this AD, request instructions from the Manager, International Section, Transport Standards Branch, FAA, to address the unsafe condition specified in paragraph (e) of this AD; and accomplish the actions at the times specified in, and in accordance with, those instructions. Guidance can be found in Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency (EASA) AD 2013–0247, dated October 10, 2013. (h) 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 (i)(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. E:\FR\FM\30APR1.SGM 30APR1 18730 Federal Register / Vol. 83, No. 83 / Monday, April 30, 2018 / Rules and Regulations (i) Related Information (1) Refer to MCAI EASA AD 2013–0247, dated October 10, 2013, for related information. You may examine the MCAI on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA– 2018–0305. (2) For more information about this AD, contact Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th Street, Des Moines, WA 98198; telephone and fax: 206–231–3229. (j) Material Incorporated by Reference None. Issued in Des Moines, Washington, on April 17, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–08654 Filed 4–27–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0302; Product Identifier 2013–NM–228–AD; Amendment 39–19258; AD 2018–09–02] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are superseding Airworthiness Directive (AD) 99–23–16, which applied to certain Airbus Model A330 and A340 series airplanes. AD 99– 23–16 required repetitive detailed visual inspections to detect cracking of the vertical flange of the inboard Z-stiffeners of the centerline panel of the fuselage belly fairing; and corrective actions, if necessary. This AD was prompted by a new fatigue and damage tolerance evaluation that concluded that the current inspection thresholds and intervals had to be more restrictive. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. We are issuing this AD to address the unsafe condition on these products. DATES: This AD becomes effective May 15, 2018. We must receive comments on this AD by June 14, 2018. ADDRESSES: You may send comments, using the procedures found in 14 CFR sradovich on DSK3GMQ082PROD with RULES SUMMARY: VerDate Sep<11>2014 17:01 Apr 27, 2018 Jkt 244001 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 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– 0302; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th Street, Des Moines, WA 98198; telephone and fax: 206–231–3229. SUPPLEMENTARY INFORMATION: Discussion We issued AD 99–23–16, Amendment 39–11412 (64 FR 61485, November 12, 1999) (‘‘AD 99–23–16’’), which applied to certain Airbus Model A330 and A340 series airplanes. AD 99–23–16 was prompted by issuance of mandatory continuing airworthiness information by a foreign civil aviation authority. AD 99–23–16 required repetitive detailed visual inspections to detect cracking of the vertical flange of the inboard Z-stiffeners of the centerline panel of the fuselage belly fairing; and corrective actions, if necessary. We issued AD 99– 23–16 to detect and correct fatigue cracking of the vertical flange of the inboard Z-stiffeners of the centerline panel of the fuselage belly fairing, which could result in reduced structural integrity of the belly fairing. Since we issued AD 99–23–16, a new fatigue and damage tolerance evaluation was conducted by the manufacturer. It was concluded that, due to airplane PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 utilization, the current inspection thresholds and intervals had to be more restrictive. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2013–0241, dated October 1, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A330 and A340 series airplanes. The MCAI states: In order to prevent a damage in the inboard Z profile at the Center Landing Gear (CLG) door fitting location (Frame 49 to 53.2) caused by cracks evidenced during fatigue tests and which could lead to a reduced structural integrity, DGAC France AD 96– 056–029(B) and DGAC France AD 96–057– 042(B) [which corresponds to FAA AD 99– 23–16] were issued to require a repetitive inspection of the inboard Z profile on both Left Hand (LH) and Right Hand (RH) sides. An optional terminating action of the repetitive inspection of this [EASA] AD exists by modification of the aeroplane in accordance with the instructions of Airbus Service Bulletin (SB) A330–53–3019 or Airbus SB A340–53–4028, as applicable. Since those [EASA] ADs were issued, in the frame of a new fatigue and damage tolerance evaluation, taking into account the aeroplane utilisation, the threshold and intervals were reassessed. This resulted in the conclusion that, in this specific case, certain thresholds and intervals are more restrictive. For the reasons described above, this [EASA] AD retains the requirements of both DGAC France AD 96–056–029(B) and DGAC France AD 96–057–042(B), which are superseded, and requires accomplishment of repetitive inspections of the inboard Z profile (LH/RH) within the new thresholds and intervals. You may examine the MCAI on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2018–0302. FAA’s Determination and Requirements of This 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. We are issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of these same type designs. FAA’s Determination of the Effective Date Since there are currently no domestic operators of this product, we find good E:\FR\FM\30APR1.SGM 30APR1

Agencies

[Federal Register Volume 83, Number 83 (Monday, April 30, 2018)]
[Rules and Regulations]
[Pages 18727-18730]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-08654]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0305; Product Identifier 2013-NM-226-AD; Amendment 
39-19259; AD 2018-09-03]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

[[Page 18728]]


ACTION: Final rule; request for comments.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2009-11-08, 
which applied to certain Airbus Model A330-202, -223, -243, -301, -322, 
and -342 airplanes. AD 2009-11-08 required repetitive special detailed 
(high frequency eddy current) inspections to detect cracking of the 
keel beam fitting horizontal flange edge at a certain frame (FR) on the 
left- and right-hand sides of the fuselage, and repair if necessary. 
This AD was prompted by a new fatigue and damage tolerance evaluation 
that concluded the current inspection thresholds and intervals had to 
be modified. This AD requires contacting the FAA to obtain instructions 
for addressing the unsafe condition on these products, and doing the 
actions specified in those instructions. We are issuing this AD to 
address the unsafe condition on these products.

DATES: This AD becomes effective May 15, 2018.
    We must receive comments on this AD by June 14, 2018.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.

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-
0305; or in person at the Docket Operations office between 9 a.m. and 5 
p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Operations office 
(telephone: 800-647-5527) is in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th Street, Des Moines, WA 98198; telephone and fax: 206-231-3229.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued AD 2009-11-08, Amendment 39-15918 (74 FR 25404, May 28, 
2009) (``AD 2009-11-08''), which applied to certain Airbus Model A330-
202, -223, -243, -301, -322, and -342 airplanes. AD 2009-11-08 was 
prompted by reports of cracks on the left- and right-hand sides between 
the crossing area of the keel angle fitting and the front spar of the 
center wing box. AD 2009-11-08 required a special detailed (high 
frequency eddy current) inspection to detect cracking of the keel beam 
fitting horizontal flange edge at FR40 on the left- and right-hand 
sides of the fuselage, and repair if necessary. We issued AD 2009-11-08 
to detect and correct cracking on the left- and right-hand sides, 
between the crossing area of the keel angle fitting and the front spar 
of the center wing box, which if not corrected, could affect the 
structural integrity of the airplane.
    Since we issued AD 2009-11-08, a new fatigue and damage tolerance 
evaluation was conducted by the manufacturer. It was concluded that, 
due to airplane utilization, the current inspection thresholds and 
intervals had to be modified.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2013-0247, dated October 10, 2013 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for certain Airbus Model A330-202, -223, -
243, -301, -322, and -342 airplanes. The MCAI states:

    During the A330 and A340 aeroplane fatigue test, cracks appeared 
on the right and left sides between the crossing area of the keel 
angle fitting and the front spar of the Centre Wing Box (CWB). 
Several modifications were introduced in the fleet in the area of 
frame (FR) 40 keel angle assembly in order to prevent these cracks. 
However, the new design caused interference between one fastener and 
the keel angle which was corrected by further local reprofiling of 
the keel angle horizontal flange.
    This condition, if not detected and corrected, could result in 
reduced structural integrity of the area.
    Prompted by these findings, EASA issued AD 2008-0213 [which 
corresponds to FAA AD 2009-11-08] to require accomplishment of 
repetitive special detailed inspection on the horizontal flange of 
the keel beam in the area of first fastener hole aft of FR40 and, 
depending on findings, accomplishment of a repair.
    Since that [EASA] AD was issued, a new fatigue and damage 
tolerance evaluation was conducted by Airbus. It was concluded that, 
due to aeroplane utilisation, the current inspection thresholds and 
intervals had to be modified.
    For the reason described above, this [EASA] AD retains the 
requirements of EASA AD 2008-0213, which is superseded, and 
redefines the thresholds and intervals.

    You may examine the MCAI on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0305.

FAA's Determination and Requirements of This 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. We are 
issuing this AD because we evaluated all pertinent information and 
determined the unsafe condition exists and is likely to exist or 
develop on other products of the same type design.

FAA's Determination of the Effective Date

    Since there are currently no domestic operators of this product, we 
find good cause that notice and opportunity for prior public comment 
are unnecessary. In addition, for the reason(s) stated above, we find 
that good cause exists for making this amendment effective in less than 
30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2018-0305; Product 
Identifier 2013-NM-226-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD based on 
those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

[[Page 18729]]

Costs of Compliance

    Currently, there are no affected U.S.-registered airplanes. This AD 
requires contacting the FAA to obtain instructions for addressing the 
unsafe condition, and doing the actions specified in those 
instructions. Based on the actions specified in the MCAI AD, we are 
providing the following cost estimates for an affected airplane that is 
placed on the U.S. Register in the future:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspection [new action]...............  9 work-hours x $85 per                $0            $765              $0
                                         hour = $765.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in the MCAI 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 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 AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. 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.

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by removing airworthiness directive (AD) 
2009-11-08, Amendment 39-15918 (74 FR 25404, May 28, 2009), and adding 
the following new AD:

2018-09-03 Airbus: Amendment 39-19259; Docket No. FAA-2018-0305; 
Product Identifier 2013-NM-226-AD.

(a) Effective Date

    This AD becomes effective May 15, 2018.

(b) Affected ADs

    This AD replaces AD 2009-11-08, Amendment 39-15918 (74 FR 25404, 
May 28, 2009) (``AD 2009-11-08'').

(c) Applicability

    This AD applies to Airbus Model A330-202, -223, -243, -301, -
322, and -342 airplanes, certificated in any category, manufacturer 
serial numbers: 0177, 0181, 0183, 0184, 0188, 0189, 0191, 0195, 
0198, 0200, 0203, 0205, 0206, 0209, 0211, 0219, 0222, 0223, 0224, 
0226, 0229, 0230, 0231, 0232, 0234, 0238, 0240, 0241, 0244, 0247, 
0248, 0249, 0250, 0251, 0253, 0254, and 0255.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by reports of cracks on the left- and 
right-hand sides between the crossing area of the keel angle fitting 
and the front spar of the center wing box and by a new fatigue and 
damage tolerance evaluation that concluded the current inspection 
thresholds and intervals had to be modified. We are issuing this AD 
to detect and correct cracking on the left- and right-hand sides 
between the crossing area of the keel angle fitting and the front 
spar of the center wing box, which if not corrected, could affect 
the structural integrity of the airplane.

(f) Compliance

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

(g) Required Actions

    Within 30 days after the effective date of this AD, request 
instructions from the Manager, International Section, Transport 
Standards Branch, FAA, to address the unsafe condition specified in 
paragraph (e) of this AD; and accomplish the actions at the times 
specified in, and in accordance with, those instructions. Guidance 
can be found in Mandatory Continuing Airworthiness Information 
(MCAI) European Aviation Safety Agency (EASA) AD 2013-0247, dated 
October 10, 2013.

(h) 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 (i)(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.

[[Page 18730]]

(i) Related Information

    (1) Refer to MCAI EASA AD 2013-0247, dated October 10, 2013, for 
related information. You may examine the MCAI on the internet at 
http://www.regulations.gov by searching for and locating Docket No. 
FAA-2018-0305.
    (2) For more information about this AD, contact Vladimir 
Ulyanov, Aerospace Engineer, International Section, Transport 
Standards Branch, FAA, 2200 South 216th Street, Des Moines, WA 
98198; telephone and fax: 206-231-3229.

(j) Material Incorporated by Reference

    None.

    Issued in Des Moines, Washington, on April 17, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-08654 Filed 4-27-18; 8:45 am]
BILLING CODE 4910-13-P