Airworthiness Directives; Airbus Airplanes, 5301-5304 [2018-02350]

Download as PDF Federal Register / Vol. 83, No. 26 / Wednesday, February 7, 2018 / Rules and Regulations 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 1. The authority citation for part 39 continues to read as follows: ■ sradovich on DSK3GMQ082PROD with RULES 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): ■ 2018–03–09 Airbus: Amendment 39–19182; Docket No. FAA–2018–0070; Product Identifier 2015–NM–146–AD. VerDate Sep<11>2014 17:31 Feb 06, 2018 Jkt 244001 (a) Effective Date This AD becomes effective February 22, 2018. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A321– 211 and –231 airplanes, certificated in any category, manufacturer serial numbers 3191, 3217, 3241, 3251, 3267, 3334, 3459, 3493, 3507, 3552, 3566, 3587, 3645, 3681, 3764, 3784, 3847, 3867, 3920, 3934, 3938, 3951, 3981, 4058, 4074, 4099, 4103, 4116, 4148, 4184, 4189, 4194, 4217, 4224, 4230, 4266, 4271, 4274, 4292, 4299, 4338, 4341, 4369, 4387, 4416, 4430, 4461, and 4500. (d) Subject Air Transport Association (ATA) of America Code 25, Equipment/furnishings. (e) Reason This AD was prompted by a determination that the flat-headed pin at the upper attachment point of the overhead stowage compartments (OHSCs) at a certain frame may not sustain the maximum weight load for each flight phase. We are issuing this AD to prevent OHSC detachment during flight, which could cause injury to the crew or passengers. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Action(s) 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 action(s) 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 2015–0164, dated August 10, 2015. (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. (i) Related Information (1) Refer to MCAI EASA AD 2015–0164, dated August 10, 2015, for related PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 5301 information. You may examine the MCAI on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA– 2018–0070. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057–3356; telephone: 425– 227–1405; fax: 425–227–1149. (j) Material Incorporated by Reference None. Issued in Renton, Washington, on January 26, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–02357 Filed 2–6–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0029; Product Identifier 2015–NM–132–AD; Amendment 39–19179; AD 2018–03–06] 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) 2015–02– 18, which applied to all Airbus Model A330–201, –202, –203, –301, –302, and –303 airplanes. AD 2015–02–18 required a one-time ultrasonic inspection for fractures of all aft mountpylon bolts of each engine. This new AD was prompted by the failure of a bolt on the aft engine mount upper beam, which was found to be caused by inappropriate in-production upper beam installation. 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 February 22, 2018. We must receive comments on this AD by March 26, 2018. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. SUMMARY: E:\FR\FM\07FER1.SGM 07FER1 5302 Federal Register / Vol. 83, No. 26 / Wednesday, February 7, 2018 / Rules and Regulations • 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– 0029; 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, 1601 Lind Avenue SW, Renton, WA 98057–3356; telephone: 425–227–1138; fax: 425– 227–1149. SUPPLEMENTARY INFORMATION: sradovich on DSK3GMQ082PROD with RULES Discussion We issued AD 2015–02–18, Amendment 39–18085 (80 FR 5020, January 30, 2015) (‘‘AD 2015–02–18’’), which applied to all Airbus Model A330–201, –202, –203, –301, –302, and –303 airplanes. AD 2015–02–18 was prompted by a report of one bolt on the aft engine mount upper beam found totally broken. AD 2015–02–18 required a one-time ultrasonic inspection for fractures of all aft mount-pylon bolts of each engine. We issued AD 2015–02–18 to detect and correct fracture of the aft mount-pylon bolts, which could result in failure of the engine mount and consequent detachment of the engine. Since we issued AD 2015–02–18, further investigation showed that the pylon bolt failure was caused by inappropriate upper beam installation during production. We have determined that repetitive inspections are necessary to address the unsafe condition. VerDate Sep<11>2014 17:31 Feb 06, 2018 Jkt 244001 The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2015–0126, dated July 1, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A330–200 and –300 series airplanes. The MCAI states: During a scheduled replacement of a CF6– 80E1 engine on an A330 aeroplane, a bolt on the aft engine mount upper beam was found sheared. The affected bolt is one out of four bolts that attach the upper beam to the pylon. Investigation results revealed an unusual contact with the counter-bore edge of the beam which induced a significant groove on the bolt during its installation in production. It is suspected that the induced groove led to a fatigue crack initiation and subsequent quick propagation leading to the complete fracture of the bolt. In case of multiple bolt fractures, the remaining bolts would be insufficient to sustain the residual fatigue and limit loads. This condition, if not detected and corrected, could lead, in case of multiple bolt fracture, to loss of an engine mount structural integrity and possible in-flight engine detachment, resulting in reduced control of the aeroplane and/or injury to persons on the ground. To address this potential unsafe condition, EASA issued AD 2013–0094 to require a onetime ultrasonic (US) inspection of the four aft mount-pylon bolts of both engines to detect sheared bolts and, depending on findings, accomplishment of applicable corrective actions. Since EASA AD 2013–0094 was issued, further investigation results revealed that the pylon bolt failure was caused by inappropriate upper beam installation during production. An abnormal bending load applied on the bolt during installation of the upper beam could have increased the stress close to or beyond the limit strength, high enough to fracture the bolt. Prompted by these findings, Airbus issued Service Bulletin (SB) A330–71–3031 providing instructions for repetitive inspections and the applicable corrective actions. For the reasons described above, this [EASA] AD, which supersedes EASA AD 2013–0094, requires repetitive US inspections of the aft mount-pylons bolts of each engine and, depending on findings, corrective actions. You may examine the MCAI on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2018–0029. FAA’s Determination and Requirements of This AD This product has been approved by the aviation authority of another PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 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–2018–0029; Product Identifier 2015–NM–132–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. 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: E:\FR\FM\07FER1.SGM 07FER1 5303 Federal Register / Vol. 83, No. 26 / Wednesday, February 7, 2018 / Rules and Regulations ESTIMATED COSTS Action Labor cost Inspections (new action) .......................... 8 work-hours × $85 per hour = $680 per inspection cycle.. We estimate the following costs to do any necessary on-condition repairs that Parts cost Cost per product $0 $680 per inspection cycle. would be required based on the results of the required actions: ON-CONDITION COSTS Action Labor cost Repair (new action) ......................................... Up to 337 work-hours × $85 per hour = $28,645 .................... 1We (1) Up to $28,645. have received no definitive data that would enable us to provide parts cost estimates for the on-condition actions specified in this 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 sradovich on DSK3GMQ082PROD with RULES Cost per product Parts cost 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. VerDate Sep<11>2014 17:31 Feb 06, 2018 Jkt 244001 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2015–02–18, Amendment 39–18085 (80 FR 5020, January 30, 2015), and adding the following new AD: ■ 2018–03–06 Airbus: Amendment 39–19179; Docket No. FAA–2018–0029; Product Identifier 2015–NM–132–AD. (a) Effective Date This AD becomes effective February 22, 2018. (b) Affected ADs This AD replaces AD 2015–02–18, Amendment 39–18085 (80 FR 5020, January 30, 2015) (‘‘AD 2015–02–18’’). PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 (c) Applicability This AD applies to Airbus Model A330– 201, –202, –203, –301, –302, and –303 airplanes, certificated in any category, all manufacturer serial numbers, except those on which Airbus modification 203947 has been embodied in production. (d) Subject Air Transport Association (ATA) of America Code 71, Powerplant. (e) Reason This AD was prompted by the failure of a bolt on the aft engine mount upper beam, which was found to be caused by inappropriate in-production upper beam installation. We are issuing this AD to detect and correct fracture of the aft mount-pylon bolts, which could result in loss of engine mount structural integrity, consequent detachment of the engine and reduced control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Action(s) 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 action(s) 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 2015–0126, dated July 1, 2015. (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 E:\FR\FM\07FER1.SGM 07FER1 5304 Federal Register / Vol. 83, No. 26 / Wednesday, February 7, 2018 / Rules and Regulations 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. (i) Related Information (1) Refer to MCAI EASA AD 2015–0126, dated July 1, 2015, for related information. You may examine the MCAI on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2018–0029. (2) For more information about this AD, contact Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057–3356; telephone: 425–227–1138; fax: 425–227–1149. (j) Material Incorporated by Reference None. Issued in Renton, Washington, on January 25, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–02350 Filed 2–6–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0030; Product Identifier 2014–NM–161–AD; Amendment 39–19180; AD 2018–03–07] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330–202, –203, –223, and –243 airplanes; and Model A340– 211, –212, –311, and –313 airplanes. 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. This AD was prompted by a report of a hard contact that was found between the constant speed motor/ generator feeder line route 6G/6E and the optional cabin temperature control pipe on the upper shell between certain frames. We are issuing this AD to address the unsafe condition on these products. DATES: This AD becomes effective February 22, 2018. sradovich on DSK3GMQ082PROD with RULES SUMMARY: VerDate Sep<11>2014 17:31 Feb 06, 2018 Jkt 244001 We must receive comments on this AD by March 26, 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– 0030; 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, 1601 Lind Avenue SW, Renton, WA 98057–3356; telephone: 425–227–1138; fax: 425– 227–1149. SUPPLEMENTARY INFORMATION: Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2014–0161, dated July 10, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A330–202, –203, –223, and –243 airplanes; and Model A340–211, –212, –311, and –313 airplanes. The MCAI states: A hard contact was found on an A330 aeroplane during production between the Constant Speed Motor/Generator (CSM/G) feeder line route 6G/6E (Functional Item Number 1526VB) and the optional cabin temperature control pipe on the upper shell between Frame (FR)37.4 and FR38 on stringer 5, right hand (RH) side. PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 This condition, if not corrected, may lead to chafing and, consequently, a short circuit when the emergency generation is activated, resulting in the loss of emergency generation. The loss of normal generation combined with the loss of emergency generation jeopardizes the aeroplane safe flight. To address this potential unsafe condition, Airbus developed a modification to provide adequate clearance between harness 1526VB and the affected (optional) air-conditioning temperature control pipe. A340–200/–300 aeroplanes equipped with this optional cabin temperature control pipe are also affected by this issue. The modification can be embodied in service through Airbus Service Bulletin (SB) A330–92–3125, or SB A340–92–4097, as applicable. For the reasons described above, this [EASA] AD requires modification of the CSM/G mounting with installation of new stacking and/or longer bracket, depending on aeroplane configuration. You may examine the MCAI on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2018–0030. 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 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–2018–0030; Product Identifier 2014–NM–161–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 E:\FR\FM\07FER1.SGM 07FER1

Agencies

[Federal Register Volume 83, Number 26 (Wednesday, February 7, 2018)]
[Rules and Regulations]
[Pages 5301-5304]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-02350]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0029; Product Identifier 2015-NM-132-AD; Amendment 
39-19179; AD 2018-03-06]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2015-02-18, 
which applied to all Airbus Model A330-201, -202, -203, -301, -302, and 
-303 airplanes. AD 2015-02-18 required a one-time ultrasonic inspection 
for fractures of all aft mount-pylon bolts of each engine. This new AD 
was prompted by the failure of a bolt on the aft engine mount upper 
beam, which was found to be caused by inappropriate in-production upper 
beam installation. 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 February 22, 2018.
    We must receive comments on this AD by March 26, 2018.

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

[[Page 5302]]

     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-
0029; 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, 1601 Lind 
Avenue SW, Renton, WA 98057-3356; telephone: 425-227-1138; fax: 425-
227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued AD 2015-02-18, Amendment 39-18085 (80 FR 5020, January 
30, 2015) (``AD 2015-02-18''), which applied to all Airbus Model A330-
201, -202, -203, -301, -302, and -303 airplanes. AD 2015-02-18 was 
prompted by a report of one bolt on the aft engine mount upper beam 
found totally broken. AD 2015-02-18 required a one-time ultrasonic 
inspection for fractures of all aft mount-pylon bolts of each engine. 
We issued AD 2015-02-18 to detect and correct fracture of the aft 
mount-pylon bolts, which could result in failure of the engine mount 
and consequent detachment of the engine.
    Since we issued AD 2015-02-18, further investigation showed that 
the pylon bolt failure was caused by inappropriate upper beam 
installation during production. We have determined that repetitive 
inspections are necessary to address the unsafe condition.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2015-0126, dated July 1, 2015 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for certain Airbus Model A330-200 and -300 series 
airplanes. The MCAI states:

    During a scheduled replacement of a CF6-80E1 engine on an A330 
aeroplane, a bolt on the aft engine mount upper beam was found 
sheared. The affected bolt is one out of four bolts that attach the 
upper beam to the pylon.
    Investigation results revealed an unusual contact with the 
counter-bore edge of the beam which induced a significant groove on 
the bolt during its installation in production. It is suspected that 
the induced groove led to a fatigue crack initiation and subsequent 
quick propagation leading to the complete fracture of the bolt. In 
case of multiple bolt fractures, the remaining bolts would be 
insufficient to sustain the residual fatigue and limit loads.
    This condition, if not detected and corrected, could lead, in 
case of multiple bolt fracture, to loss of an engine mount 
structural integrity and possible in-flight engine detachment, 
resulting in reduced control of the aeroplane and/or injury to 
persons on the ground.
    To address this potential unsafe condition, EASA issued AD 2013-
0094 to require a one-time ultrasonic (US) inspection of the four 
aft mount-pylon bolts of both engines to detect sheared bolts and, 
depending on findings, accomplishment of applicable corrective 
actions.
    Since EASA AD 2013-0094 was issued, further investigation 
results revealed that the pylon bolt failure was caused by 
inappropriate upper beam installation during production. An abnormal 
bending load applied on the bolt during installation of the upper 
beam could have increased the stress close to or beyond the limit 
strength, high enough to fracture the bolt.
    Prompted by these findings, Airbus issued Service Bulletin (SB) 
A330-71-3031 providing instructions for repetitive inspections and 
the applicable corrective actions.
    For the reasons described above, this [EASA] AD, which 
supersedes EASA AD 2013-0094, requires repetitive US inspections of 
the aft mount-pylons bolts of each engine and, depending on 
findings, corrective actions.

    You may examine the MCAI on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0029.

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-2018-0029; Product 
Identifier 2015-NM-132-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.

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:

[[Page 5303]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                 Action                           Labor cost            Parts cost         Cost per product
----------------------------------------------------------------------------------------------------------------
Inspections (new action)................  8 work-hours x $85 per                  $0  $680 per inspection cycle.
                                           hour = $680 per
                                           inspection cycle..
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary on-condition 
repairs that would be required based on the results of the required 
actions:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                Action                           Labor cost             Parts cost         Cost per product
----------------------------------------------------------------------------------------------------------------
Repair (new action)..................  Up to 337 work-hours x $85              \(1)\  Up to $28,645.
                                        per hour = $28,645.
----------------------------------------------------------------------------------------------------------------
\1\We have received no definitive data that would enable us to provide parts cost estimates for the on-condition
  actions specified in this 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) 
2015-02-18, Amendment 39-18085 (80 FR 5020, January 30, 2015), and 
adding the following new AD:

2018-03-06 Airbus: Amendment 39-19179; Docket No. FAA-2018-0029; 
Product Identifier 2015-NM-132-AD.

(a) Effective Date

    This AD becomes effective February 22, 2018.

(b) Affected ADs

    This AD replaces AD 2015-02-18, Amendment 39-18085 (80 FR 5020, 
January 30, 2015) (``AD 2015-02-18'').

(c) Applicability

    This AD applies to Airbus Model A330-201, -202, -203, -301, -
302, and -303 airplanes, certificated in any category, all 
manufacturer serial numbers, except those on which Airbus 
modification 203947 has been embodied in production.

(d) Subject

    Air Transport Association (ATA) of America Code 71, Powerplant.

(e) Reason

    This AD was prompted by the failure of a bolt on the aft engine 
mount upper beam, which was found to be caused by inappropriate in-
production upper beam installation. We are issuing this AD to detect 
and correct fracture of the aft mount-pylon bolts, which could 
result in loss of engine mount structural integrity, consequent 
detachment of the engine and reduced control of the airplane.

(f) Compliance

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

(g) Required Action(s)

    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 action(s) 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 2015-0126, dated 
July 1, 2015.

(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

[[Page 5304]]

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.

(i) Related Information

    (1) Refer to MCAI EASA AD 2015-0126, dated July 1, 2015, for 
related information. You may examine the MCAI on the internet at 
http://www.regulations.gov by searching for and locating Docket No. 
FAA-2018-0029.
    (2) For more information about this AD, contact Vladimir 
Ulyanov, Aerospace Engineer, International Section, Transport 
Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356; 
telephone: 425-227-1138; fax: 425-227-1149.

(j) Material Incorporated by Reference

    None.

    Issued in Renton, Washington, on January 25, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-02350 Filed 2-6-18; 8:45 am]
 BILLING CODE 4910-13-P