83 FR 5297 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 26 (February 7, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 26 (February 7, 2018)
| Page Range | 5297-5299 | |
| FR Document | 2018-02352 |
[Federal Register Volume 83, Number 26 (Wednesday, February 7, 2018)] [Rules and Regulations] [Pages 5297-5299] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-02352] ======================================================================== Rules and Regulations Federal Register ________________________________________________________________________ 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 Register / Vol. 83, No. 26 / Wednesday, February 7, 2018 / Rules and Regulations [[Page 5297]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0069; Product Identifier 2013-NM-090-AD; Amendment 39-19181; AD 2018-03-08] 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) 2005-19-28, which applied to certain Airbus Model A330-301, -321, -322, -341, and - 342 airplanes; and Model A340-200 and A340-300 series airplanes. AD 2005-19-28 required repetitive inspections for cracks in the aft face of the rear spar at the area adjacent to the bolt holes and the end of the build slot, and repair if necessary. AD 2005-19-28 also provided an optional terminating action for the repetitive inspections. This new AD was prompted by the results of a new fatigue and damage tolerance assessment, which determined that several compliance thresholds and intervals needed to be reduced. 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. 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- 0069; 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 As described in FAA Advisory Circular 120-104 (http://www.faa.gov/documentLibrary/media/Advisory_Circular/120-104.pdf), several programs have been developed to support initiatives that will ensure the continued airworthiness of aging airplane structure. The last element of those initiatives is the requirement to establish a limit of validity (LOV) of the engineering data that support the structural maintenance program under 14 CFR 26.21. This AD is the result of an assessment of the previously established programs by the design approval holder (DAH) during the process of establishing the LOV for the affected airplanes. The actions specified in this AD are necessary to complete certain programs to ensure the continued airworthiness of aging airplane structure and to support an airplane reaching its LOV. We issued AD 2005-19-28, Amendment 39-14293 (70 FR 57493, October 3, 2005) (``AD 2005-19-28''), which applied to certain Airbus Model A330-301, -321, -322, -341, and -342 airplanes; and Model A340-200 and A340-300 series airplanes. AD 2005-19-28 was prompted by a report that, during fatigue tests of the wing, cracks were found in the vertical web of the rear spar between ribs 1 and 2 having initiated at the build slot. AD 2005-19-28 required repetitive inspections for cracks in the aft face of the rear spar at the area adjacent to the bolt holes and the end of the build slot, and repair if necessary. AD 2005-19-28 also provided an optional terminating action for the repetitive inspections. We issued AD 2005-19-28 to detect and correct fatigue cracking in the vertical web of the wing rear spar, which could result in reduced structural integrity of the wing. Since we issued AD 2005-19-28, a new fatigue and damage tolerance assessment was done, taking into account airplane utilization and widespread fatigue damage analysis. This analysis led to the determination that several compliance thresholds and intervals needed to be reduced. We have also determined that the unsafe condition is not applicable to Airbus Model A330-341 airplanes. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2013-0101, dated April 30, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A330-301, -321, - 322, and -342 airplanes; and Model A340-200 and A340-300 series airplanes. The MCAI states: During wing fatigue test, a crack was detected which propagated from the tip of the build slot in the vertical web of the wing inner rear spar between rib 1 and 2. This condition, if not detected and corrected, could lead to reduced structural integrity of the wing. To address this potentially unsafe condition, [Direction G[eacute]n[eacute]rale de l'Aviation Civile] DGAC France issued AD 2001-268(B)R1 and AD 2001-269(B) [which correspond to FAA AD 2005- 19-28] to [[Page 5298]] require repetitive High Frequency Eddy Current (HFEC) inspections of the aft face of the inner rear spar web in the area adjacent to the outboard end of the build slot and, depending of findings, repair of the inner rear spar web. Since these [DGAC France] ADs were issued, in the frame of a new fatigue and damage tolerance evaluation, taking into account aeroplane utilization and Widespread Fatigue Damage (WFD) analysis, the thresholds and intervals of the affected inspections have been reassessed. This reassessment led to the amendment of several thresholds and to the reduction of inspection intervals to allow timely detection of cracks and to the accomplishment of applicable corrective actions. EASA issued AD 2013-0092, which retained the requirements of DGAC France AD 2001-268(B)R1 and AD 2001-269(B), which were superseded, but required those actions within the new thresholds and intervals. Since issuance of EASA AD 2013-0092, it has been discovered that certain A330 aeroplanes, incorporating another modification in production, must be excluded from the Applicability. In addition, it has been found necessary to clarify that for the initial inspection, the previous thresholds (to be counted from aeroplane first flight) or intervals, as required by [DGAC France] AD 2001-268(B)R1 and [DGAC France] AD 2001-269(B), cannot be exceeded. For the reasons described above, this [EASA] AD partially retains the requirements of EASA AD 2013-0092, which is superseded, and introduces the changes as outlined above. You may examine the MCAI on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018- 0069. 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-2018-0069; Product Identifier 2013-NM-090-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: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- HFEC inspection [retained action 4 work-hours x $85 per $0 $340 per inspection cycle. from AD 2005-19-28 with reduced hour = $340 per threshold and intervals]. inspection cycle. Modification [retained action 153 work-hours x $85 per 0 $13,005. from AD 2005-19-28]. hour = $13,005. ---------------------------------------------------------------------------------------------------------------- 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 ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Repair [retained action from AD 85 work-hours x $85 per Unavailable..................... $7,225 2005-19-28]. hour = $7,225. ---------------------------------------------------------------------------------------------------------------- We acknowledge that since the above actions are retained from AD 2005-19-28, but with reduced threshold and intervals, operators would essentially revise their maintenance or inspection program, as applicable, to incorporate the reduced threshold and intervals. We estimate the revision to an operator's maintenance and inspection program would take approximately 1 work-hour x $85 per hour. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on [[Page 5299]] 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) 2005-19-28, Amendment 39-14293 (70 FR 57493, October 3, 2005), and adding the following new AD: 2018-03-08 Airbus: Amendment 39-19181; Docket No. FAA-2018-0069; Product Identifier 2013-NM-090-AD. (a) Effective Date This AD becomes effective February 22, 2018. (b) Affected ADs This AD replaces AD 2005-19-28, Amendment 39-14293 (70 FR 57493, October 3, 2005) (``AD 2005-19-28''). (c) Applicability This AD applies to the Airbus airplanes specified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category. (1) Model A330-301, -321, -322, and -342 airplanes, all manufacturers serial numbers, except those on which Airbus modification 42547 or 44599 has been embodied in production. (2) Model A340-211, -212, -213, -311, -312, and -313 airplanes, all manufacturer serial numbers, except those on which Airbus modification 42547 or 41300 has been embodied in production. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by a report that, during fatigue tests of the wing, cracks were found in the vertical web of the rear spar between ribs 1 and 2 having initiated at the build slot, and a determination that several compliance thresholds and intervals need to be reduced. We are issuing this AD to detect and correct fatigue cracking in the vertical web of the wing rear spar, which could result in reduced structural integrity of the wing. (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 2013-0101, dated April 30, 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-AMOC-REQUESTS@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 2013-0101, dated April 30, 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-2018-0069. (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 26, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-02352 Filed 2-6-18; 8:45 am] BILLING CODE 4910-13-P
![5297
Rules and Regulations Federal Register
Vol. 83, No. 26
Wednesday, February 7, 2018
This section of the FEDERAL REGISTER • Federal eRulemaking Portal: Go to certain programs to ensure the
contains regulatory documents having general http://www.regulations.gov. Follow the continued airworthiness of aging
applicability and legal effect, most of which instructions for submitting comments. airplane structure and to support an
are keyed to and codified in the Code of • Fax: 202–493–2251. airplane reaching its LOV.
Federal Regulations, which is published under • Mail: U.S. Department of We issued AD 2005–19–28,
50 titles pursuant to 44 U.S.C. 1510.
Transportation, Docket Operations, M– Amendment 39–14293 (70 FR 57493,
The Code of Federal Regulations is sold by 30, West Building Ground Floor, Room October 3, 2005) (‘‘AD 2005–19–28’’),
the Superintendent of Documents. W12–140, 1200 New Jersey Avenue SE, which applied to certain Airbus Model
Washington, DC 20590. A330–301, –321, –322, –341, and –342
• Hand Delivery: U.S. Department of airplanes; and Model A340–200 and
DEPARTMENT OF TRANSPORTATION Transportation, Docket Operations, M– A340–300 series airplanes. AD 2005–
30, West Building Ground Floor, Room 19–28 was prompted by a report that,
Federal Aviation Administration W12–140, 1200 New Jersey Avenue SE, during fatigue tests of the wing, cracks
Washington, DC, between 9 a.m. and 5 were found in the vertical web of the
14 CFR Part 39 p.m., Monday through Friday, except rear spar between ribs 1 and 2 having
Federal holidays. initiated at the build slot. AD 2005–19–
[Docket No. FAA–2018–0069; Product
28 required repetitive inspections for
Identifier 2013–NM–090–AD; Amendment Examining the AD Docket
39–19181; AD 2018–03–08] cracks in the aft face of the rear spar at
You may examine the AD docket on the area adjacent to the bolt holes and
RIN 2120–AA64 the internet at http:// the end of the build slot, and repair if
www.regulations.gov by searching for necessary. AD 2005–19–28 also
Airworthiness Directives; Airbus and locating Docket No. FAA–2018– provided an optional terminating action
Airplanes 0069; or in person at the Docket for the repetitive inspections. We issued
Operations office between 9 a.m. and 5 AD 2005–19–28 to detect and correct
AGENCY: Federal Aviation p.m., Monday through Friday, except fatigue cracking in the vertical web of
Administration (FAA), DOT. Federal holidays. The AD docket the wing rear spar, which could result
ACTION: Final rule; request for contains this AD, the regulatory in reduced structural integrity of the
comments. evaluation, any comments received, and wing.
other information. The street address for Since we issued AD 2005–19–28, a
SUMMARY: We are superseding the Docket Operations office (telephone: new fatigue and damage tolerance
Airworthiness Directive (AD) 2005–19– 800–647–5527) is in the ADDRESSES assessment was done, taking into
28, which applied to certain Airbus section. Comments will be available in account airplane utilization and
Model A330–301, –321, –322, –341, and the AD docket shortly after receipt. widespread fatigue damage analysis.
–342 airplanes; and Model A340–200
FOR FURTHER INFORMATION CONTACT: This analysis led to the determination
and A340–300 series airplanes. AD
Vladimir Ulyanov, Aerospace Engineer, that several compliance thresholds and
2005–19–28 required repetitive
International Section, Transport intervals needed to be reduced. We have
inspections for cracks in the aft face of
Standards Branch, FAA, 1601 Lind also determined that the unsafe
the rear spar at the area adjacent to the
Avenue SW, Renton, WA 98057–3356; condition is not applicable to Airbus
bolt holes and the end of the build slot,
telephone: 425–227–1138; fax: 425– Model A330–341 airplanes.
and repair if necessary. AD 2005–19–28 The European Aviation Safety Agency
also provided an optional terminating 227–1149.
SUPPLEMENTARY INFORMATION: (EASA), which is the Technical Agent
action for the repetitive inspections. for the Member States of the European
This new AD was prompted by the Discussion Union, has issued EASA AD 2013–0101,
results of a new fatigue and damage dated April 30, 2013 (referred to after
tolerance assessment, which determined As described in FAA Advisory
Circular 120–104 (http://www.faa.gov/ this as the Mandatory Continuing
that several compliance thresholds and Airworthiness Information, or ‘‘the
intervals needed to be reduced. This AD documentLibrary/media/Advisory_
Circular/120-104.pdf), several programs MCAI’’), to correct an unsafe condition
requires contacting the FAA to obtain for certain Airbus Model A330–301,
instructions for addressing the unsafe have been developed to support
initiatives that will ensure the –321, –322, and –342 airplanes; and
condition on these products, and doing Model A340–200 and A340–300 series
the actions specified in those continued airworthiness of aging
airplane structure. The last element of airplanes. The MCAI states:
instructions. We are issuing this AD to
address the unsafe condition on these those initiatives is the requirement to During wing fatigue test, a crack was
products. establish a limit of validity (LOV) of the detected which propagated from the tip of
engineering data that support the the build slot in the vertical web of the wing
DATES: This AD becomes effective structural maintenance program under inner rear spar between rib 1 and 2.
sradovich on DSK3GMQ082PROD with RULES
February 22, 2018. 14 CFR 26.21. This AD is the result of This condition, if not detected and
We must receive comments on this an assessment of the previously corrected, could lead to reduced structural
AD by March 26, 2018. integrity of the wing.
established programs by the design To address this potentially unsafe
ADDRESSES: You may send comments, approval holder (DAH) during the condition, [Direction Générale de l’Aviation
using the procedures found in 14 CFR process of establishing the LOV for the Civile] DGAC France issued AD 2001–
11.43 and 11.45, by any of the following affected airplanes. The actions specified 268(B)R1 and AD 2001–269(B) [which
methods: in this AD are necessary to complete correspond to FAA AD 2005–19–28] to
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![5298 Federal Register / Vol. 83, No. 26 / Wednesday, February 7, 2018 / Rules and Regulations
require repetitive High Frequency Eddy You may examine the MCAI on the we did not precede it by notice and
Current (HFEC) inspections of the aft face of internet at http://www.regulations.gov opportunity for public comment. We
the inner rear spar web in the area adjacent by searching for and locating Docket No. invite you to send any written relevant
to the outboard end of the build slot and,
FAA–2018–0069. data, views, or arguments about this AD.
depending of findings, repair of the inner
rear spar web. Send your comments to an address
FAA’s Determination and Requirements
Since these [DGAC France] ADs were listed under the ADDRESSES section.
of This AD
issued, in the frame of a new fatigue and Include ‘‘Docket No. FAA–2018–0069;
damage tolerance evaluation, taking into This product has been approved by Product Identifier 2013–NM–090–AD’’
account aeroplane utilization and the aviation authority of another at the beginning of your comments. We
Widespread Fatigue Damage (WFD) analysis, country, and is approved for operation specifically invite comments on the
the thresholds and intervals of the affected in the United States. Pursuant to our overall regulatory, economic,
inspections have been reassessed. This
bilateral agreement with the State of environmental, and energy aspects of
reassessment led to the amendment of several
thresholds and to the reduction of inspection Design Authority, we have been notified this AD. We will consider all comments
intervals to allow timely detection of cracks of the unsafe condition described in the received by the closing date and may
and to the accomplishment of applicable MCAI. We are issuing this AD because amend this AD based on those
corrective actions. EASA issued AD 2013– we evaluated all pertinent information comments.
0092, which retained the requirements of and determined the unsafe condition We will post all comments we
DGAC France AD 2001–268(B)R1 and AD exists and is likely to exist or develop receive, without change, to http://
2001–269(B), which were superseded, but on other products of these same type www.regulations.gov, including any
required those actions within the new designs. personal information you provide. We
thresholds and intervals.
will also post a report summarizing each
Since issuance of EASA AD 2013–0092, it FAA’s Determination of the Effective
has been discovered that certain A330 substantive verbal contact we receive
Date
aeroplanes, incorporating another about this AD.
modification in production, must be Since there are currently no domestic
Costs of Compliance
excluded from the Applicability. In addition, operators of this product, we find good
it has been found necessary to clarify that for cause that notice and opportunity for Currently, there are no affected U.S.-
the initial inspection, the previous thresholds prior public comment are unnecessary. registered airplanes. This AD requires
(to be counted from aeroplane first flight) or In addition, for the reason(s) stated contacting the FAA to obtain
intervals, as required by [DGAC France] AD above, we find that good cause exists for instructions for addressing the unsafe
2001–268(B)R1 and [DGAC France] AD
making this amendment effective in less condition, and doing the actions
2001–269(B), cannot be exceeded.
For the reasons described above, this than 30 days. specified in those instructions. Based on
[EASA] AD partially retains the requirements the actions specified in the MCAI AD,
Comments Invited
of EASA AD 2013–0092, which is we are providing the following cost
superseded, and introduces the changes as This AD is a final rule that involves estimates for an affected airplane that is
outlined above. requirements affecting flight safety, and placed on the U.S. Register in the future:
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product
HFEC inspection [retained action from AD 4 work-hours × $85 per hour = $340 per in- $0 $340 per inspection cycle.
2005–19–28 with reduced threshold and in- spection cycle.
tervals].
Modification [retained action from AD 2005–19– 153 work-hours × $85 per hour = $13,005 ....... 0 $13,005.
28].
We estimate the following costs to do would be required based on the results
any necessary on-condition repairs that of the required actions:
ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product
Repair [retained action from AD 2005–19–28] ....... 85 work-hours × $85 per hour = $7,225 ................ Unavailable ................ $7,225
We acknowledge that since the above Authority for This Rulemaking Part A, Subpart III, Section 44701:
actions are retained from AD 2005–19– Title 49 of the United States Code General requirements.’’ Under that
28, but with reduced threshold and specifies the FAA’s authority to issue section, Congress charges the FAA with
intervals, operators would essentially rules on aviation safety. Subtitle I, promoting safe flight of civil aircraft in
sradovich on DSK3GMQ082PROD with RULES
revise their maintenance or inspection section 106, describes the authority of air commerce by prescribing regulations
program, as applicable, to incorporate the FAA Administrator. ‘‘Subtitle VII: for practices, methods, and procedures
the reduced threshold and intervals. We Aviation Programs,’’ describes in more the Administrator finds necessary for
estimate the revision to an operator’s detail the scope of the Agency’s safety in air commerce. This regulation
maintenance and inspection program authority. is within the scope of that authority
would take approximately 1 work-hour We are issuing this rulemaking under because it addresses an unsafe condition
× $85 per hour. the authority described in ‘‘Subtitle VII, that is likely to exist or develop on
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![Federal Register / Vol. 83, No. 26 / Wednesday, February 7, 2018 / Rules and Regulations 5299
products identified in this rulemaking (a) Effective Date standards district office/certificate holding
action. This AD becomes effective February 22, district office.
This AD is issued in accordance with 2018. (i) Related Information
authority delegated by the Executive (b) Affected ADs (1) Refer to MCAI EASA AD 2013–0101,
Director, Aircraft Certification Service, dated April 30, 2013, for related information.
This AD replaces AD 2005–19–28,
as authorized by FAA Order 8000.51C. Amendment 39–14293 (70 FR 57493, October You may examine the MCAI on the internet
In accordance with that order, issuance 3, 2005) (‘‘AD 2005–19–28’’). at http://www.regulations.gov by searching
of ADs is normally a function of the for and locating Docket No. FAA–2018–0069.
Compliance and Airworthiness (c) Applicability (2) For more information about this AD,
Division, but during this transition This AD applies to the Airbus airplanes contact Vladimir Ulyanov, Aerospace
period, the Executive Director has specified in paragraphs (c)(1) and (c)(2) of Engineer, International Section, Transport
this AD, certificated in any category. Standards Branch, FAA, 1601 Lind Avenue
delegated the authority to issue ADs SW, Renton, WA 98057–3356; telephone
(1) Model A330–301, –321, –322, and –342
applicable to transport category airplanes, all manufacturers serial numbers, 425–227–1138; fax 425–227–1149.
airplanes to the Director of the System except those on which Airbus modification
Oversight Division. (j) Material Incorporated by Reference
42547 or 44599 has been embodied in
production. None.
Regulatory Findings
(2) Model A340–211, –212, –213, –311, Issued in Renton, Washington, on January
We determined that this AD will not –312, and –313 airplanes, all manufacturer 26, 2018.
have federalism implications under serial numbers, except those on which
Michael Kaszycki,
Executive Order 13132. This AD will Airbus modification 42547 or 41300 has been
embodied in production. Acting Director, System Oversight Division,
not have a substantial direct effect on Aircraft Certification Service.
the States, on the relationship between (d) Subject
[FR Doc. 2018–02352 Filed 2–6–18; 8:45 am]
the national government and the States, Air Transport Association (ATA) of BILLING CODE 4910–13–P
or on the distribution of power and America Code 57, Wings.
responsibilities among the various (e) Reason
levels of government. DEPARTMENT OF TRANSPORTATION
This AD was prompted by a report that,
For the reasons discussed above, I
during fatigue tests of the wing, cracks were
certify that this AD: found in the vertical web of the rear spar Federal Aviation Administration
1. Is not a ‘‘significant regulatory between ribs 1 and 2 having initiated at the
action’’ under Executive Order 12866; build slot, and a determination that several 14 CFR Part 39
2. Is not a ‘‘significant rule’’ under the compliance thresholds and intervals need to
DOT Regulatory Policies and Procedures be reduced. We are issuing this AD to detect [Docket No. FAA–2018–0070; Product
(44 FR 11034, February 26, 1979); and correct fatigue cracking in the vertical Identifier 2015–NM–146–AD; Amendment
web of the wing rear spar, which could result 39–19182; AD 2018–03–09]
3. Will not affect intrastate aviation in in reduced structural integrity of the wing.
Alaska; and RIN 2120–AA64
4. Will not have a significant (f) Compliance
economic impact, positive or negative, Comply with this AD within the Airworthiness Directives; Airbus
on a substantial number of small entities compliance times specified, unless already Airplanes
under the criteria of the Regulatory done.
Flexibility Act. AGENCY: Federal Aviation
(g) Required Action(s)
Administration (FAA), DOT.
List of Subjects in 14 CFR Part 39 Within 30 days after the effective date of
ACTION: Final rule; request for
this AD, request instructions from the
Air transportation, Aircraft, Aviation Manager, International Section, Transport comments.
safety, Incorporation by reference, Standards Branch, FAA, to address the
Safety. unsafe condition specified in paragraph (e) of SUMMARY: We are adopting a new
this AD; and accomplish the action(s) at the airworthiness directive (AD) for certain
Adoption of the Amendment times specified in, and in accordance with, Airbus Model A321–211 and –231
Accordingly, under the authority those instructions. Guidance can be found in airplanes. This AD requires contacting
Mandatory Continuing Airworthiness the FAA to obtain instructions for
delegated to me by the Administrator,
Information (MCAI) European Aviation addressing the unsafe condition on
the FAA amends 14 CFR part 39 as Safety Agency (EASA) AD 2013–0101, dated
follows: these products, and doing the actions
April 30, 2013.
specified in those instructions. This AD
PART 39—AIRWORTHINESS (h) Alternative Methods of Compliance was prompted by a determination that
DIRECTIVES (AMOCs) the flat-headed pin at the upper
The Manager, International Section, attachment point of the overhead
■ 1. The authority citation for part 39 Transport Standards Branch, FAA, has the stowage compartments at a certain
continues to read as follows: authority to approve AMOCs for this AD, if frame may not sustain the maximum
requested using the procedures found in 14 weight load for each flight phase. We
Authority: 49 U.S.C. 106(g), 40113, 44701. CFR 39.19. In accordance with 14 CFR 39.19,
are issuing this AD to address the unsafe
§ 39.13 [Amended] send your request to your principal inspector
or local Flight Standards District Office, as condition on these products.
■ 2. The FAA amends § 39.13 by appropriate. If sending information directly DATES: This AD becomes effective
sradovich on DSK3GMQ082PROD with RULES
removing airworthiness directive (AD) to the International Section, send it to the February 22, 2018.
2005–19–28, Amendment 39–14293 (70 attention of the person identified in We must receive comments on this
FR 57493, October 3, 2005), and adding paragraph (i)(2) of this AD. Information may AD by March 26, 2018.
be emailed to: 9-ANM-116-AMOC-
the following new AD: REQUESTS@faa.gov. Before using any ADDRESSES: You may send comments,
2018–03–08 Airbus: Amendment 39–19181; approved AMOC, notify your appropriate using the procedures found in 14 CFR
Docket No. FAA–2018–0069; Product principal inspector, or lacking a principal 11.43 and 11.45, by any of the following
Identifier 2013–NM–090–AD. inspector, the manager of the local flight methods:
VerDate Sep<11>2014 17:31 Feb 06, 2018 Jkt 244001 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 E:\FR\FM\07FER1.SGM 07FER1](https://thefederalregister.org/doc/83_FR_5323/page/3.svg)
Document Created: 2018-10-26 13:56:59
Document Modified: 2018-10-26 13:56:59
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule; request for comments. | |
| Dates | This AD becomes effective February 22, 2018. | |
| 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. | |
| FR Citation | 83 FR 5297 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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