83 FR 5584 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 27 (February 8, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 27 (February 8, 2018)
| Page Range | 5584-5587 | |
| FR Document | 2018-02018 |
[Federal Register Volume 83, Number 27 (Thursday, February 8, 2018)] [Proposed Rules] [Pages 5584-5587] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-02018] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0025; Product Identifier 2017-NM-101-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for all Airbus Model A310-203, -221, -222, -304, -322, -324, and -325 airplanes. This proposed AD was prompted by a design approval holder (DAH) evaluation indicating that the outer wing lower junction is subject to widespread fatigue damage (WFD). This proposed AD would require modifying the fastener holes at certain locations, which includes related investigative actions and applicable corrective actions. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed 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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: [email protected]; internet: http://www.airbus.com. You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW, Renton, WA. For information on the availability of this material at the FAA, call 425- 227-1221. 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- 0025; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone: 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356; telephone: 425-227-2125; fax: 425- 227-1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2018-0025; Product Identifier 2017-NM-101-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM based on those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this NPRM. Discussion Fatigue damage can occur locally, in small areas or structural design details, or globally, in widespread areas. Multiple-site damage is widespread damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Widespread damage can also occur in multiple elements such as adjacent frames or stringers. Multiple-site damage and multiple-element damage cracks are typically too small initially to be reliably detected with normal inspection methods. Without intervention, these cracks will grow, and eventually compromise the structural integrity of the airplane. This condition is known as widespread fatigue damage. It is associated with general degradation of large areas of structure with similar structural details and stress levels. As an airplane ages, WFD will likely occur, and will certainly occur if the airplane is operated long enough without any intervention. The FAA's WFD final rule (75 FR 69746, November 15, 2010) became effective on January 14, 2011. The WFD rule requires certain actions to prevent structural failure due to WFD throughout the operational life of certain existing transport category airplanes and all of these airplanes that will be certificated in the future. For existing and future airplanes subject to the WFD rule, the rule requires that DAHs establish a limit of validity (LOV) of the engineering data that support the structural maintenance program. Operators affected by the WFD rule may not fly an airplane beyond its LOV, unless an extended LOV is approved. The WFD rule (75 FR 69746, November 15, 2010) does not require identifying and developing maintenance actions if the DAHs can show that such actions are not necessary to prevent WFD before the airplane reaches the LOV. Many LOVs, however, do depend on accomplishment of future maintenance actions. As stated in the WFD rule, any maintenance actions necessary to reach the LOV will be mandated by airworthiness directives through separate rulemaking actions. In the context of WFD, this action is necessary to enable DAHs to propose LOVs that allow operators the longest operational lives for their airplanes, and still ensure that WFD will not occur. This approach allows for an implementation strategy that provides flexibility to DAHs in determining the timing of service information development (with FAA approval), while providing operators with certainty [[Page 5585]] regarding the LOV applicable to their airplanes. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2017-0122, dated July 18, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for all Airbus Model A310-203, -221, -222, -304, -308, -322, -324, and -325 airplanes. The MCAI states: In response to the FAA Part 26 rule, wing structural items of the Airbus A310 design were assessed regarding Widespread Fatigue Damage (WFD) phenomenon. One outcome was that the outer wing lower junction is prone to WFD at level of the first fasteners row, close to Rib 1 between Frame (FR) 40 and FR 47. This condition, if not corrected, could reduce the structural integrity of the wing. Prompted by the conclusion of WFD analysis, Airbus issued Service Bulletin (SB) A310-57-2105 to provide modification instructions. The accomplishment of this modification at the specified time will recondition/renovate/extend the life of the fasteners holes at Rib 1, in order to reach the Limit Of Validity. For the reasons described above, this [EASA] AD requires cold working of the affected holes at Rib 1, stiffeners 1 to 14, on both outer wings between FR 40 and FR 47. Required actions include a modification of the fastener holes at rib 1, stiffeners 1 to 14, on both outer wings between FR 40 and FR 47 by cold-working. The modification includes related investigative actions and applicable corrective actions. The related investigative actions include a rotating probe test of the fastener holes for cracks and checking the hole diameter for certain diameters. The corrective action is repair. You may examine the MCAI in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018- 0025. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A310-57-2105, Revision 00, dated November 23, 2016. The service information describes procedures for a modification of the fastener holes at rib 1, stiffeners 1 to 14, on both outer wings between FR 40 and FR 47 by cold-working and includes related investigative actions and corrective actions. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA's Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Costs of Compliance We estimate that this proposed AD affects 13 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Modification, including related 66 work-hours x $85 per $24,200 $29,810 $387,530 investigative actions. hour = $5,610. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repair that would be required based on the results of the proposed inspection. We have no way of determining the number of aircraft that might need this repair: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Repair........................................ 9 work-hours x $85 per hour = $254 $1,019 $765. ---------------------------------------------------------------------------------------------------------------- Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. This proposed AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: [[Page 5586]] 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): Airbus: Docket No. FAA-2018-0025; Product Identifier 2017-NM-101-AD. (a) Comments Due Date We must receive comments by March 26, 2018. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus Model A310-203, -221, -222, -304, -322, -324, and -325 airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by a design approval holder (DAH) evaluation indicating that the outer wing lower junction is subject to widespread fatigue damage (WFD). We are issuing this AD to prevent WFD at the outer wing lower junction, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Modification Before exceeding the compliance time specified in figure 1 to paragraph (g) of this AD, as applicable, or within 30 days after the effective date of this AD, whichever occurs later: Modify the fastener holes at rib 1, stiffeners 1 to 14, on both outer wings between frame (FR) 40 and FR 47, including doing all related investigative and applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-57- 2105, Revision 00, dated November 23, 2016, except as required by paragraph (h) of this AD. Do all related investigative and applicable corrective actions before further flight. [GRAPHIC] [TIFF OMITTED] TP08FE18.001 (h) Service Information Exception Where Airbus Service Bulletin A310-57-2105, Revision 00, dated November 23, 2016, specifies to contact Airbus for appropriate action, and specifies that action as ``RC'' (Required for Compliance): Before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (i)(2) of this AD. (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Section, send it to the attention of the person identified in paragraph (j)(2) of this AD. Information may be emailed to: [email protected]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA- authorized signature. (3) Required for Compliance (RC): Except as required by paragraph (h) of this AD: If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. [[Page 5587]] (j) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017-0122, dated July 18, 2017, for related information. This MCAI may be found in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-0025. (2) For more information about this AD, contact Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356; telephone: 425-227-2125; fax: 425-227-1149. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: [email protected]; internet: http://www.airbus.com. You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW, Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on January 25, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-02018 Filed 2-7-18; 8:45 am] BILLING CODE 4910-13-P
![5584 Federal Register / Vol. 83, No. 27 / Thursday, February 8, 2018 / Proposed Rules
International Section, Transport Standards M–30, West Building Ground Floor, Discussion
Branch, FAA, 1601 Lind Avenue SW, Room W12–140, 1200 New Jersey
Renton, WA 98057–3356; telephone: 425– Fatigue damage can occur locally, in
Avenue SE, Washington, DC 20590. small areas or structural design details,
227–2125; fax: 425–227–1149.
(3) For service information identified in
• Hand Delivery: Deliver to Mail or globally, in widespread areas.
this AD, contact Airbus SAS, Airworthiness address above between 9 a.m. and 5 Multiple-site damage is widespread
Office—EAW, 1 Rond Point Maurice p.m., Monday through Friday, except damage that occurs in a large structural
Bellonte, 31707 Blagnac Cedex, France; Federal holidays. element such as a single rivet line of a
telephone: +33 5 61 93 36 96; fax: +33 5 61 For service information identified in lap splice joining two large skin panels.
93 44 51; email: account.airworth-eas@ this NPRM, contact Airbus SAS,
airbus.com; internet: http://www.airbus.com. Widespread damage can also occur in
Airworthiness Office—EAW, 1 Rond multiple elements such as adjacent
You may view this service information at the
Point Maurice Bellonte, 31707 Blagnac frames or stringers. Multiple-site
FAA, Transport Standards Branch, 1601 Lind
Avenue SW, Renton, WA. For information on Cedex, France; telephone: +33 5 61 93 damage and multiple-element damage
the availability of this material at the FAA, 36 96; fax: +33 5 61 93 44 51; email: cracks are typically too small initially to
call 425–227–1221. account.airworth-eas@airbus.com; be reliably detected with normal
Issued in Renton, Washington, on January
internet: http://www.airbus.com. You inspection methods. Without
25, 2018. may view this service information at the intervention, these cracks will grow,
Michael Kaszycki, FAA, Transport Standards Branch, 1601 and eventually compromise the
Lind Avenue SW, Renton, WA. For structural integrity of the airplane. This
Acting Director, System Oversight Division,
Aircraft Certification Service. information on the availability of this condition is known as widespread
material at the FAA, call 425–227–1221. fatigue damage. It is associated with
[FR Doc. 2018–02084 Filed 2–7–18; 8:45 am]
BILLING CODE 4910–13–P Examining the AD Docket general degradation of large areas of
structure with similar structural details
You may examine the AD docket on and stress levels. As an airplane ages,
the internet at http:// WFD will likely occur, and will
DEPARTMENT OF TRANSPORTATION
www.regulations.gov by searching for certainly occur if the airplane is
Federal Aviation Administration and locating Docket No. FAA–2018– operated long enough without any
0025; or in person at the Docket intervention.
14 CFR Part 39 Management Facility between 9 a.m. The FAA’s WFD final rule (75 FR
and 5 p.m., Monday through Friday, 69746, November 15, 2010) became
[Docket No. FAA–2018–0025; Product except Federal holidays. The AD docket
Identifier 2017–NM–101–AD] effective on January 14, 2011. The WFD
contains this NPRM, the regulatory rule requires certain actions to prevent
RIN 2120–AA64 evaluation, any comments received, and structural failure due to WFD
other information. The street address for throughout the operational life of
Airworthiness Directives; Airbus the Docket Operations office (telephone:
Airplanes certain existing transport category
800–647–5527) is in the ADDRESSES airplanes and all of these airplanes that
AGENCY: Federal Aviation section. Comments will be available in will be certificated in the future. For
Administration (FAA), DOT. the AD docket shortly after receipt. existing and future airplanes subject to
ACTION: Notice of proposed rulemaking FOR FURTHER INFORMATION CONTACT: Dan the WFD rule, the rule requires that
(NPRM). Rodina, Aerospace Engineer, DAHs establish a limit of validity (LOV)
International Section, Transport of the engineering data that support the
SUMMARY: We propose to adopt a new Standards Branch, FAA, 1601 Lind structural maintenance program.
airworthiness directive (AD) for all Avenue SW, Renton, WA 98057–3356; Operators affected by the WFD rule may
Airbus Model A310–203, –221, –222, telephone: 425–227–2125; fax: 425– not fly an airplane beyond its LOV,
–304, –322, –324, and –325 airplanes. 227–1149. unless an extended LOV is approved.
This proposed AD was prompted by a SUPPLEMENTARY INFORMATION: The WFD rule (75 FR 69746,
design approval holder (DAH) November 15, 2010) does not require
evaluation indicating that the outer Comments Invited identifying and developing maintenance
wing lower junction is subject to We invite you to send any written actions if the DAHs can show that such
widespread fatigue damage (WFD). This relevant data, views, or arguments about actions are not necessary to prevent
proposed AD would require modifying this proposed AD. Send your comments WFD before the airplane reaches the
the fastener holes at certain locations, to an address listed under the LOV. Many LOVs, however, do depend
which includes related investigative ADDRESSES section. Include ‘‘Docket No. on accomplishment of future
actions and applicable corrective FAA–2018–0025; Product Identifier maintenance actions. As stated in the
actions. We are proposing this AD to 2017–NM–101–AD’’ at the beginning of WFD rule, any maintenance actions
address the unsafe condition on these your comments. We specifically invite necessary to reach the LOV will be
products. comments on the overall regulatory, mandated by airworthiness directives
DATES: We must receive comments on economic, environmental, and energy through separate rulemaking actions.
this proposed AD by March 26, 2018. aspects of this NPRM. We will consider In the context of WFD, this action is
ADDRESSES: You may send comments, all comments received by the closing necessary to enable DAHs to propose
using the procedures found in 14 CFR date and may amend this NPRM based LOVs that allow operators the longest
daltland on DSKBBV9HB2PROD with PROPOSALS
11.43 and 11.45, by any of the following on those comments. operational lives for their airplanes, and
methods: We will post all comments we still ensure that WFD will not occur.
• Federal eRulemaking Portal: Go to receive, without change, to http:// This approach allows for an
http://www.regulations.gov. Follow the www.regulations.gov, including any implementation strategy that provides
instructions for submitting comments. personal information you provide. We flexibility to DAHs in determining the
• Fax: 202–493–2251. will also post a report summarizing each timing of service information
• Mail: U.S. Department of substantive verbal contact we receive development (with FAA approval),
Transportation, Docket Operations, about this NPRM. while providing operators with certainty
VerDate Sep<11>2014 16:37 Feb 07, 2018 Jkt 244001 PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 E:\FR\FM\08FEP1.SGM 08FEP1](https://thefederalregister.org/doc/83_FR_5611/page/1.svg)
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regarding the LOV applicable to their affected holes at Rib 1, stiffeners 1 to 14, on actions. This service information is
airplanes. both outer wings between FR 40 and FR 47. reasonably available because the
The European Aviation Safety Agency Required actions include a interested parties have access to it
(EASA), which is the Technical Agent modification of the fastener holes at rib through their normal course of business
for the Member States of the European 1, stiffeners 1 to 14, on both outer wings or by the means identified in the
Union, has issued EASA AD 2017–0122, between FR 40 and FR 47 by cold- ADDRESSES section.
dated July 18, 2017 (referred to after this working. The modification includes
as the Mandatory Continuing related investigative actions and FAA’s Determination and Requirements
Airworthiness Information, or ‘‘the applicable corrective actions. The of This Proposed AD
MCAI’’), to correct an unsafe condition related investigative actions include a
for all Airbus Model A310–203, –221, This product has been approved by
rotating probe test of the fastener holes
–222, –304, –308, –322, –324, and –325 the aviation authority of another
for cracks and checking the hole
airplanes. The MCAI states: country, and is approved for operation
diameter for certain diameters. The
in the United States. Pursuant to our
In response to the FAA Part 26 rule, wing corrective action is repair.
structural items of the Airbus A310 design You may examine the MCAI in the bilateral agreement with the State of
were assessed regarding Widespread Fatigue AD docket on the internet at http:// Design Authority, we have been notified
Damage (WFD) phenomenon. One outcome www.regulations.gov by searching for of the unsafe condition described in the
was that the outer wing lower junction is and locating Docket No. FAA–2018– MCAI and service information
prone to WFD at level of the first fasteners referenced above. We are proposing this
row, close to Rib 1 between Frame (FR) 40
0025.
and FR 47.
AD because we evaluated all pertinent
Related Service Information Under 1 information and determined an unsafe
This condition, if not corrected, could CFR Part 51
reduce the structural integrity of the wing. condition exists and is likely to exist or
Prompted by the conclusion of WFD Airbus has issued Service Bulletin develop on other products of the same
analysis, Airbus issued Service Bulletin (SB) A310–57–2105, Revision 00, dated type design.
A310–57–2105 to provide modification November 23, 2016. The service
instructions. The accomplishment of this information describes procedures for a Costs of Compliance
modification at the specified time will modification of the fastener holes at rib
recondition/renovate/extend the life of the We estimate that this proposed AD
fasteners holes at Rib 1, in order to reach the 1, stiffeners 1 to 14, on both outer wings
affects 13 airplanes of U.S. registry.
Limit Of Validity. between FR 40 and FR 47 by cold-
For the reasons described above, this working and includes related We estimate the following costs to
[EASA] AD requires cold working of the investigative actions and corrective comply with this proposed AD:
ESTIMATED COSTS
Parts Cost per Cost on U.S.
Action Labor cost cost product operators
Modification, including related investigative 66 work-hours × $85 per hour = $5,610 ........ $24,200 $29,810 $387,530
actions.
We estimate the following costs to do required based on the results of the determining the number of aircraft that
any necessary repair that would be proposed inspection. We have no way of might need this repair:
ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product
Repair ........................................................................... 9 work-hours × $85 per hour = $765 ........................... $254 $1,019
Authority for This Rulemaking the Administrator finds necessary for issue ADs applicable to transport
Title 49 of the United States Code safety in air commerce. This regulation category airplanes to the Director of the
specifies the FAA’s authority to issue is within the scope of that authority System Oversight Division.
rules on aviation safety. Subtitle I, because it addresses an unsafe condition
Regulatory Findings
section 106, describes the authority of that is likely to exist or develop on
the FAA Administrator. ‘‘Subtitle VII: products identified in this rulemaking We determined that this proposed AD
Aviation Programs,’’ describes in more action. would not have federalism implications
detail the scope of the Agency’s This proposed AD is issued in under Executive Order 13132. This
authority. accordance with authority delegated by proposed AD would not have a
daltland on DSKBBV9HB2PROD with PROPOSALS
We are issuing this rulemaking under the Executive Director, Aircraft substantial direct effect on the States, on
the authority described in ‘‘Subtitle VII, Certification Service, as authorized by the relationship between the national
Part A, Subpart III, Section 44701: FAA Order 8000.51C. In accordance Government and the States, or on the
General requirements.’’ Under that with that order, issuance of ADs is distribution of power and
section, Congress charges the FAA with normally a function of the Compliance responsibilities among the various
promoting safe flight of civil aircraft in and Airworthiness Division, but during levels of government.
air commerce by prescribing regulations this transition period, the Executive For the reasons discussed above, I
for practices, methods, and procedures Director has delegated the authority to certify this proposed regulation:
VerDate Sep<11>2014 16:37 Feb 07, 2018 Jkt 244001 PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 E:\FR\FM\08FEP1.SGM 08FEP1](https://thefederalregister.org/doc/83_FR_5611/page/2.svg)
![Federal Register / Vol. 83, No. 27 / Thursday, February 8, 2018 / Proposed Rules 5587
(j) Related Information serialization of the HSTA attachment this proposed AD. Send your comments
(1) Refer to Mandatory Continuing pins and trunnions, and repair or to an address listed under the
Airworthiness Information (MCAI) EASA AD replacement of damaged HSTA ADDRESSES section. Include ‘‘Docket No.
2017–0122, dated July 18, 2017, for related attachment pins and trunnions. We are FAA–2018–0028; Product Identifier
information. This MCAI may be found in the proposing this AD to address the unsafe 2017–NM–143–AD’’ at the beginning of
AD docket on the internet at http:// condition on these products. your comments. We specifically invite
www.regulations.gov by searching for and comments on the overall regulatory,
DATES: We must receive comments on
locating Docket No. FAA–2018–0025.
(2) For more information about this AD, this proposed AD by March 26, 2018. economic, environmental, and energy
contact Dan Rodina, Aerospace Engineer, ADDRESSES: You may send comments, aspects of this NPRM. We will consider
International Section, Transport Standards using the procedures found in 14 CFR all comments received by the closing
Branch, FAA, 1601 Lind Avenue SW, 11.43 and 11.45, by any of the following date and may amend this NPRM based
Renton, WA 98057–3356; telephone: 425– methods: on those comments.
227–2125; fax: 425–227–1149. • Federal eRulemaking Portal: Go to We will post all comments we
(3) For service information identified in http://www.regulations.gov. Follow the receive, without change, to http://
this AD, contact Airbus SAS, Airworthiness instructions for submitting comments. www.regulations.gov, including any
Office—EAW, 1 Rond Point Maurice • Fax: 202–493–2251. personal information you provide. We
Bellonte, 31707 Blagnac Cedex, France; • Mail: U.S. Department of
telephone: +33 5 61 93 36 96; fax: +33 5 61
will also post a report summarizing each
93 44 51; email: account.airworth-eas@
Transportation, Docket Operations, substantive verbal contact we receive
airbus.com; internet: http://www.airbus.com. M–30, West Building Ground Floor, about this NPRM.
You may view this service information at the Room W12–140, 1200 New Jersey
Avenue SE, Washington, DC 20590. Discussion
FAA, Transport Standards Branch, 1601 Lind
Avenue SW, Renton, WA. For information on • Hand Delivery: Deliver to Mail Transport Canada Civil Aviation
the availability of this material at the FAA, address above between 9 a.m. and 5 (TCCA), which is the aviation authority
call 425–227–1221. p.m., Monday through Friday, except for Canada, has issued Canadian
Issued in Renton, Washington, on January Federal holidays. Airworthiness Directive CF–2017–24,
25, 2018. For service information identified in dated July 12, 2017 (referred to after this
Michael Kaszycki, this NPRM, contact Bombardier, Inc., as the Mandatory Continuing
400 Côte Vertu Road West, Dorval, Airworthiness Information, or ‘‘the
Acting Director, System Oversight Division,
Aircraft Certification Service. Québec H4S 1Y9, Canada; Widebody MCAI’’), to correct an unsafe condition
Customer Response Center North for certain Bombardier, Inc., Model CL–
[FR Doc. 2018–02018 Filed 2–7–18; 8:45 am]
America toll-free telephone 1–866–538– 600–1A11 (CL–600), CL–600–2A12 (CL–
BILLING CODE 4910–13–P
1247 or direct-dial telephone 1–514– 601 Variant), and CL–600–2B16 (CL–
855–2999; fax 514–855–7401; email 601–3A, CL–601–3R, and CL–604
ac.yul@aero.bombardier.com; internet Variants) airplanes. The MCAI states:
DEPARTMENT OF TRANSPORTATION
http://www.bombardier.com. You may
view this service information at the During a review of the Horizontal
Federal Aviation Administration Stabilizer Trim Actuator (HSTA) system, it
FAA, Transport Standards Branch, 1601
was discovered that the safe life limits of the
14 CFR Part 39 Lind Avenue SW, Renton, WA. For HSTA attachment pins and trunnions were
information on the availability of this not listed in the Airworthiness Limitation
[Docket No. FAA–2018–0028; Product material at the FAA, call 425–227–1221. (AWL) Section of the Instructions for
Identifier 2017–NM–143–AD] Continued Airworthiness. Also, the HSTA
Examining the AD Docket
RIN 2120–AA64 attachment pins and trunnions were not
You may examine the AD docket on serialized making it impossible to keep
Airworthiness Directives; Bombardier, the internet at http:// accurate records of the life of these parts.
www.regulations.gov by searching for Failure of these pins and trunnions could
Inc., Airplanes lead to a disconnect of the horizontal
and locating Docket No. FAA–2018–
AGENCY: Federal Aviation 0028; or in person at the Docket stabilizer and subsequent loss of the
Administration (FAA), DOT. Management Facility between 9 a.m. aeroplane.
This [Canadian] AD mandates the
ACTION: Notice of proposed rulemaking and 5 p.m., Monday through Friday, incorporation of AWL tasks into the
(NPRM). except Federal holidays. The AD docket maintenance schedule and serialization of
contains this NPRM, the regulatory HSTA attachment pins and trunnions. Some
SUMMARY: We propose to adopt a new evaluation, any comments received, and aircraft require AWL tasks and serialization
airworthiness directive (AD) for certain other information. The street address for of the attachment pins only, while others
Bombardier, Inc., Model CL–600–1A11 the Docket Operations office (telephone require AWL tasks and serialization of the
(CL–600), CL–600–2A12 (CL–601 800–647–5527) is in the ADDRESSES trunnions and attachment pins [and repair or
Variant), and CL–600–2B16 (CL–601– section. Comments will be available in replacement if damaged (including linear
3A, CL–601–3R, and CL–604 Variants) the AD docket shortly after receipt. scratches, pits, spalling, dents, or surface
airplanes. This proposed AD was texture variations)].
FOR FURTHER INFORMATION CONTACT: Aziz
prompted by a determination that the Ahmed, Aerospace Engineer, Airframe This proposed AD would require
safe life limits of the horizontal and Mechanical Systems Section, FAA, revisions to certain operator
stabilizer trim actuator (HSTA) New York ACO Branch, 1600 Stewart maintenance documents to include new
daltland on DSKBBV9HB2PROD with PROPOSALS
attachment pins and trunnions were not Avenue, Suite 410, Westbury, NY actions (e.g., inspections). Compliance
listed in certain airworthiness 11590; telephone 516–228–7239; fax with these actions is required by 14 CFR
limitations (AWLs) and that the HSTA 516–794–5531. 91.403(c). For airplanes that have been
attachment pins and trunnions were not SUPPLEMENTARY INFORMATION: previously modified, altered, or repaired
serialized. This proposed AD would in the areas addressed by this proposed
require revision of the maintenance or Comments Invited AD, the operator may not be able to
inspection program, as applicable, to We invite you to send any written accomplish the actions described in the
include the latest revision of the AWLs, relevant data, views, or arguments about revisions. In this situation, to comply
VerDate Sep<11>2014 16:37 Feb 07, 2018 Jkt 244001 PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 E:\FR\FM\08FEP1.SGM 08FEP1](https://thefederalregister.org/doc/83_FR_5611/page/4.svg)
Document Created: 2018-02-08 00:16:10
Document Modified: 2018-02-08 00:16:10
| 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 | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by March 26, 2018. | |
| Contact | Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356; telephone: 425-227-2125; fax: 425- 227-1149. | |
| FR Citation | 83 FR 5584 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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