82 FR 40683 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 165 (August 28, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 165 (August 28, 2017)
| Page Range | 40683-40686 | |
| FR Document | 2017-17537 |
[Federal Register Volume 82, Number 165 (Monday, August 28, 2017)] [Rules and Regulations] [Pages 40683-40686] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-17537] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0472; Product Identifier 2016-NM-148-AD; Amendment 39-19002; AD 2017-17-12] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for all Airbus Model A310-203, -221, -222, -304, -322, -324, and -325 airplanes. This AD was prompted by an evaluation by the design approval holder indicating that the wing bottom skin at the main landing gear (MLG) reinforcing plate is subject to widespread fatigue damage (WFD). This AD requires a modification of the wing bottom skin at the MLG reinforcing plate. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective October 2, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of October 2, 2017. ADDRESSES: For service information identified in this final rule, 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 referenced 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017- 0472. [[Page 40684]] 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-2017- 0472; 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 AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800-647-5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. 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: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus Model A310-203, -221, -222, -304, -322, -324, and -325 airplanes. The NPRM published in the Federal Register on May 19, 2017 (82 FR 22904) (``the NPRM''). The NPRM was prompted by an evaluation by the design approval holder indicating that the wing bottom skin at the MLG reinforcing plate is subject to WFD. The NPRM proposed to require a modification of the wing bottom skin at the MLG reinforcing plate. We are issuing this AD to prevent multi-site damage in the bottom skin at the MLG reinforcing plate, which could result in reduced structural integrity of the wing. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2016-0170, dated August 19, 2016 (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, -322, -324, and -325 airplanes. The MCAI states: In response to the FAA Part 26 rule, wing structural items of the Airbus A310 design that are deemed potentially susceptible to Widespread Fatigue Damage (WFD) have been assessed. The bottom skin at the main landing gear (MLG) reinforcing plate has been highlighted as an area susceptible to Multi Site Damage (MSD). This condition, if not corrected, could reduce the structural integrity of the wing. Airbus performed a detailed widespread fatigue damage tolerance analysis of the bottom skin at the MLG reinforcing plate, and concluded that a modification is necessary to the fastener holes at the inboard edge of the reinforcing plate forward of the rear spar. The modification consists of inspection [related investigative actions of a check and a rotating probe inspection] and a first oversize of the critical holes on the first two rows of fasteners [and corrective actions, e.g., repair]. Airbus modification 13751 was introduced and Service Bulletin (SB) A310-57-2104 was issued to provide in-service modification instructions. The accomplishment of this modification at the specified time will recondition/renovate/ extend the life of the fastener holes in the bottom skin at the MLG reinforcing plate and prevent the development of MSD up to the Extended Service Goal (ESG). For the reasons described above, this [EASA] AD requires certain modifications to the wing bottom skin at the MLG reinforcing plate, forward of the wing rear spar [including related investigative actions of a check and a rotating probe inspection and corrective actions, e.g., 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-2017- 0472. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A310-57-2104, dated December 15, 2015. This service information describes procedures for modification of the left-hand and right-hand wing bottom skin at the MLG reinforcing plate, including related investigative actions and applicable 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. Costs of Compliance We estimate that this AD affects 8 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Modification....................... 52 work-hours x $85 per $12,000 $16,420 $131,360 hour = $4,420. ---------------------------------------------------------------------------------------------------------------- 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 [[Page 40685]] 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 adding the following new airworthiness directive (AD): 2017-17-12 Airbus: Amendment 39-19002; Docket No. FAA-2017-0472; Product Identifier 2016-NM-148-AD. (a) Effective Date This AD is effective October 2, 2017. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A310-203, -221, -222, -304, - 322, -324, and -325 airplanes, certificated in any category, all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by an evaluation by the design approval holder indicating that the wing bottom skin at the main landing gear (MLG) reinforcing plate is subject to widespread fatigue damage. We are issuing this AD to prevent multi-site damage in the bottom skin at the MLG reinforcing plate, 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) Modification Within the compliance times defined in table 1 to paragraph (g) of this AD, table 2 to paragraph (g) of this AD, or table 3 to paragraph (g) of this AD, as applicable to airplane type and utilization: Do a modification of the left-hand and right-hand wing bottom skin at the MLG reinforcing plate, including all related investigative actions and applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-57-2104, dated December 15, 2015, except as required by paragraph (h) of this AD. Do all related investigative and applicable corrective actions before further flight. For the purpose of this AD, the term ``short range'' applies to airplanes with an average flight time (AFT) lower than 1.5 flight hours per flight cycle, and the term ``long range'' applies to airplanes with an average flight time equal to or higher than 1.5 flight hours per flight cycle. For determining the ``short range'' and ``long range'' airplanes, the AFT is the total accumulated flight hours, counted from take-off to touch-down, divided by the total accumulated flight cycles at the effective date of this AD. Table 1 to Paragraph (g) of This AD--Model A310-200 Series Airplanes ------------------------------------------------------------------------ Compliance time (whichever occurs later, A or B) ------------------------------------------------------------------------- A Before exceeding 28,800 flight cycles (FC) or 57,600 flight hours (FH), whichever occurs first since first flight of the airplane. B Within 960 FC, or 1,920 FH, or 12 months, whichever occurs first after the effective date of this AD. ------------------------------------------------------------------------ Table 2 to Paragraph (g) of This AD--Model A310-300 ``Short-Range'' Airplanes ------------------------------------------------------------------------ Compliance time (whichever occurs later, A or B) ------------------------------------------------------------------------- A Before exceeding 27,700 FC or 77,700 FH, whichever occurs first since first flight of the airplane. B Within 920 FC, or 2,580 FH, or 12 months, whichever occurs first after the effective date of this AD. ------------------------------------------------------------------------ Table 3 to Paragraph (g) of This AD--Model A310-300 ``Long-Range'' Airplanes ------------------------------------------------------------------------ Compliance time (whichever occurs later, A or B) ------------------------------------------------------------------------- A Before exceeding 20,500 FC or 102,500 FH, whichever occurs first since first flight of the airplane. B Within 680 FC, or 3,420 FH, or 12 months, whichever occurs first after the effective date of this AD. ------------------------------------------------------------------------ (h) Exception to Service Information Specifications Where Airbus Service Bulletin A310-57-2104, dated December 15, 2015, 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 40686]] (j) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2016-0170, dated August 19, 2016, 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-2017-0472. (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. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Service Bulletin A310-57-2104, dated December 15, 2015. (ii) Reserved. (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. (4) 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on August 9, 2017. Dionne Palermo, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017-17537 Filed 8-25-17; 8:45am] BILLING CODE 4910-13-P
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(b) Affected ADs paragraph 3.B.(3), of RR Alert NMSB Trent the availability of this material at NARA, call
None. XWB 72–AJ738 dated April 11, 2017, to 202–741–6030, or go to: http://
disposition the engine. www.archives.gov/federal-register/cfr/ibr-
(c) Applicability locations.html.
(g) Installation Prohibition
This AD applies to Rolls-Royce plc (RR) Issued in Burlington, Massachusetts, on
Trent XWB–75, Trent XWB–79, Trent XWB– After the effective date of this AD, do not
August 16, 2017.
79B, and Trent XWB–84 turbofan engines install an engine unless the IP turbine stage
2 locking plates were inspected using the Robert J. Ganley,
with an engine serial number (S/N) listed in
Appendix 1 of RR Alert Non-Modification Accomplishment Instructions, paragraph 3.A. Manager, Engine and Propeller Standards
Service Bulletin (NMSB) Trent XWB 72– or 3.B., of RR Alert NMSB Trent XWB 72– Branch, Aircraft Certification Service.
AJ738, dated April 11, 2017, and with AJ738, dated April 11, 2017. [FR Doc. 2017–18133 Filed 8–25–17; 8:45 am]
intermediate-pressure (IP) turbine stage 2 (h) Definition BILLING CODE 4910–13–P
locking plates, part number (P/N) KH12922
For the purpose of this AD, an ESV is when
or KH16183, installed.
the engine is subject to a serviceability check
(d) Subject and repair, rebuild, or overhaul. DEPARTMENT OF TRANSPORTATION
Joint Aircraft System Component (JASC) (i) Alternative Methods of Compliance Federal Aviation Administration
7250, Turbine/Turboprop Engine/Turbine (AMOCs)
Section.
(1) The Manager, FAA, ECO Branch, 14 CFR Part 39
(e) Reason Compliance and Airworthiness Division, may
approve AMOCs for this AD. Use the [Docket No. FAA–2017–0472; Product
This AD was prompted by a report of Identifier 2016–NM–148–AD; Amendment
several IP turbine stage 2 locking plates procedures found in 14 CFR 39.19 to make
your request. You may email your request to: 39–19002; AD 2017–17–12]
cracked during module assembly. We are
ANE-AD-AMOC@faa.gov. RIN 2120–AA64
issuing this AD to prevent failure of the IP
(2) Before using any approved AMOC,
turbine stage 2 locking plates, uncontained
notify your appropriate principal inspector, Airworthiness Directives; Airbus
release of the IP turbine stage 2 blades,
or lacking a principal inspector, the manager Airplanes
damage to the engine, and damage to the
of the local flight standards district office/
airplane.
certificate holding district office. AGENCY: Federal Aviation
(f) Compliance
(j) Related Information
Administration (FAA), Department of
Comply with this AD within the Transportation (DOT).
(1) For more information about this AD,
compliance times specified, unless already ACTION: Final rule.
contact Robert Green, Aerospace Engineer,
done. FAA, ECO Branch, Compliance and
(1) Inspect the IP turbine stage 2 locking SUMMARY: We are adopting a new
Airworthiness Division, 1200 District
plates on-wing before exceeding 750 engine Avenue, Burlington, MA 01803; phone: 781–
airworthiness directive (AD) for all
flight cycles (FCs) since new, or within 100 238–7754; fax: 781–238–7199; email: Airbus Model A310–203, –221, –222,
engine FCs after the effective date of this AD, robert.green@faa.gov. –304, –322, –324, and –325 airplanes.
whichever occurs later. Use the (2) Refer to MCAI European Aviation This AD was prompted by an evaluation
Accomplishment Instructions, paragraph Safety Agency AD 2017–0088, dated May 16, by the design approval holder indicating
3.A., of RR Alert NMSB Trent XWB 72– 2017, for more information. You may that the wing bottom skin at the main
AJ738, dated April 11, 2017, to do the examine the MCAI in the AD docket on the
inspection.
landing gear (MLG) reinforcing plate is
Internet at http://www.regulations.gov by subject to widespread fatigue damage
(2) Thereafter, re-inspect the IP turbine searching for and locating it in Docket No.
stage 2 locking plates at intervals not to (WFD). This AD requires a modification
FAA–2017–0642.
exceed 750 engine FCs since the last locking of the wing bottom skin at the MLG
plate inspection. Use the Accomplishment (k) Material Incorporated by Reference reinforcing plate. We are issuing this AD
Instructions, paragraph 3.A., of RR Alert (1) The Director of the Federal Register to address the unsafe condition on these
NMSB Trent XWB 72–AJ738, dated April 11, approved the incorporation by reference products.
2017, to do the inspection. (IBR) of the service information listed in this DATES: This AD is effective October 2,
(i) If all IP turbine stage 2 locking plates paragraph under 5 U.S.C. 552(a) and 1 CFR
installed on the engine have an S/N
2017.
part 51. The Director of the Federal Register
beginning with 20452, or are not marked (2) You must use this service information
with an S/N, the repetitive inspection as applicable to do the actions required by
approved the incorporation by reference
required by paragraph (f)(2) of this AD is not this AD, unless the AD specifies otherwise. of a certain publication listed in this AD
required. (i) Rolls-Royce plc (RR) Alert Non- as of October 2, 2017.
(ii) If one or more IP turbine stage 2 locking Modification Service Bulletin Trent XWB 72– ADDRESSES: For service information
plates are missing, remove the engine from AJ738, dated April 11, 2017. identified in this final rule, contact
service within the compliance times (ii) Reserved. Airbus SAS, Airworthiness Office—
specified in the Accomplishment (3) For RR service information identified in EAW, 1 Rond Point Maurice Bellonte,
Instructions, paragraph 3.A.(3), of RR Alert this AD, contact Rolls-Royce plc, Corporate
NMSB Trent XWB 72–AJ738, dated April 11, Communications, P.O. Box 31, Derby,
31707 Blagnac Cedex, France; telephone
2017. England, DE24 8BJ; phone: 011–44–1332– +33 5 61 93 36 96; fax +33 5 61 93 44
(3) Inspect the IP turbine stage 2 locking 242424; fax: 011–44–1332–249936; email: 51; email account.airworth-eas@
plates during the next engine shop visit http://www.rolls-royce.com/contact/civil_ airbus.com; Internet http://
(ESV) after the effective date of this AD. team.jsp; Internet: https://customers.rolls- www.airbus.com. You may view this
(i) Use the Accomplishment Instructions, royce.com/public/rollsroycecare. referenced service information at the
asabaliauskas on DSKBBXCHB2PROD with RULES
paragraph 3.B., of RR Alert NMSB Trent (4) You may view this service information FAA, Transport Standards Branch, 1601
XWB 72–AJ738, dated April 11, 2017, to do at FAA, Engine and Propeller Standards Lind Avenue SW., Renton, WA. For
this inspection. This in-shop inspection may Branch, Policy and Innovation Division, 1200
information on the availability of this
be substituted for the on-wing inspection District Avenue, Burlington, MA 01803. For
required by paragraphs (f)(1) and (2) of this information on the availability of this material at the FAA, call 425–227–1221.
AD. material at the FAA, call 781–238–7125. It is also available on the Internet at
(ii) If one or more IP turbine stage 2 locking (5) You may view this service information http://www.regulations.gov by searching
plates are missing, use the acceptance criteria at the National Archives and Records for and locating Docket No. FAA–2017–
in the Accomplishment Instructions, Administration (NARA). For information on 0472.
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![40684 Federal Register / Vol. 82, No. 165 / Monday, August 28, 2017 / Rules and Regulations
Examining the AD Docket reinforcing plate, which could result in You may examine the MCAI in the
reduced structural integrity of the wing. AD docket on the Internet at http://
You may examine the AD docket on The European Aviation Safety Agency www.regulations.gov by searching for
the Internet at http:// (EASA), which is the Technical Agent and locating Docket No. FAA–2017–
www.regulations.gov by searching for for the Member States of the European 0472.
and locating Docket No. FAA–2017– Union, has issued EASA Airworthiness
0472; or in person at the Docket Directive 2016–0170, dated August 19, Comments
Management Facility between 9 a.m. 2016 (referred to after this as the We gave the public the opportunity to
and 5 p.m., Monday through Friday, Mandatory Continuing Airworthiness participate in developing this AD. We
except Federal holidays. The AD docket Information, or ‘‘the MCAI’’), to correct received no comments on the NPRM or
contains this AD, the regulatory an unsafe condition for all Airbus on the determination of the cost to the
evaluation, any comments received, and Model A310–203, –221, –222, –304, public.
other information. The street address for –322, –324, and –325 airplanes. The
the Docket Office (telephone 800–647– MCAI states: Conclusion
5527) is Docket Management Facility, We reviewed the relevant data and
In response to the FAA Part 26 rule, wing
U.S. Department of Transportation, structural items of the Airbus A310 design determined that air safety and the
Docket Operations, M–30, West that are deemed potentially susceptible to public interest require adopting this AD
Building Ground Floor, Room W12–140, Widespread Fatigue Damage (WFD) have as proposed except for minor editorial
1200 New Jersey Avenue SE., been assessed. The bottom skin at the main changes. We have determined that these
Washington, DC 20590. landing gear (MLG) reinforcing plate has minor changes:
been highlighted as an area susceptible to
FOR FURTHER INFORMATION CONTACT: Dan Multi Site Damage (MSD).
• Are consistent with the intent that
Rodina, Aerospace Engineer, This condition, if not corrected, could was proposed in the NPRM for
International Section, Transport reduce the structural integrity of the wing. correcting the unsafe condition; and
Standards Branch, FAA, 1601 Lind Airbus performed a detailed widespread • Do not add any additional burden
Avenue SW., Renton, WA 98057–3356; fatigue damage tolerance analysis of the upon the public than was already
telephone 425–227–2125; fax 425–227– bottom skin at the MLG reinforcing plate, and proposed in the NPRM.
concluded that a modification is necessary to
1149. the fastener holes at the inboard edge of the Related Service Information Under 1
SUPPLEMENTARY INFORMATION: reinforcing plate forward of the rear spar. The CFR Part 51
modification consists of inspection [related
Discussion investigative actions of a check and a rotating Airbus has issued Service Bulletin
probe inspection] and a first oversize of the A310–57–2104, dated December 15,
We issued a notice of proposed critical holes on the first two rows of 2015. This service information describes
rulemaking (NPRM) to amend 14 CFR fasteners [and corrective actions, e.g., repair]. procedures for modification of the left-
part 39 by adding an AD that would Airbus modification 13751 was introduced hand and right-hand wing bottom skin
apply to all Airbus Model A310–203, and Service Bulletin (SB) A310–57–2104 was at the MLG reinforcing plate, including
–221, –222, –304, –322, -324, and -325 issued to provide in-service modification related investigative actions and
instructions. The accomplishment of this
airplanes. The NPRM published in the modification at the specified time will applicable corrective actions. This
Federal Register on May 19, 2017 (82 recondition/renovate/extend the life of the service information is reasonably
FR 22904) (‘‘the NPRM’’). The NPRM fastener holes in the bottom skin at the MLG available because the interested parties
was prompted by an evaluation by the reinforcing plate and prevent the have access to it through their normal
design approval holder indicating that development of MSD up to the Extended course of business or by the means
the wing bottom skin at the MLG Service Goal (ESG). identified in the ADDRESSES section.
reinforcing plate is subject to WFD. The For the reasons described above, this
NPRM proposed to require a [EASA] AD requires certain modifications to Costs of Compliance
the wing bottom skin at the MLG reinforcing
modification of the wing bottom skin at plate, forward of the wing rear spar We estimate that this AD affects 8
the MLG reinforcing plate. We are [including related investigative actions of a airplanes of U.S. registry.
issuing this AD to prevent multi-site check and a rotating probe inspection and We estimate the following costs to
damage in the bottom skin at the MLG corrective actions, e.g., repair]. comply with this AD:
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Modification ............................. 52 work-hours × $85 per hour = $4,420 ................................ $12,000 $16,420 $131,360
Authority for This Rulemaking Part A, Subpart III, Section 44701: products identified in this rulemaking
General requirements.’’ Under that action.
Title 49 of the United States Code section, Congress charges the FAA with This AD is issued in accordance with
specifies the FAA’s authority to issue promoting safe flight of civil aircraft in authority delegated by the Executive
asabaliauskas on DSKBBXCHB2PROD with RULES
rules on aviation safety. Subtitle I, Director, Aircraft Certification Service,
air commerce by prescribing regulations
section 106, describes the authority of as authorized by FAA Order 8000.51C.
for practices, methods, and procedures
the FAA Administrator. ‘‘Subtitle VII: In accordance with that order, issuance
Aviation Programs,’’ describes in more the Administrator finds necessary for
safety in air commerce. This regulation of ADs is normally a function of the
detail the scope of the Agency’s Compliance and Airworthiness
authority. is within the scope of that authority
because it addresses an unsafe condition Division, but during this transition
We are issuing this rulemaking under that is likely to exist or develop on period, the Executive Director has
the authority described in ‘‘Subtitle VII, delegated the authority to issue ADs
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applicable to transport category (e) Reason TABLE 3 TO PARAGRAPH (g) OF THIS
airplanes to the Director of the System This AD was prompted by an evaluation by AD—MODEL A310–300 ‘‘LONG-
Oversight Division. the design approval holder indicating that RANGE’’ AIRPLANES
the wing bottom skin at the main landing
Regulatory Findings gear (MLG) reinforcing plate is subject to Compliance time
We determined that this AD will not widespread fatigue damage. We are issuing (whichever occurs later, A or B)
have federalism implications under this AD to prevent multi-site damage in the
Executive Order 13132. This AD will bottom skin at the MLG reinforcing plate, A Before exceeding 20,500 FC or 102,500
not have a substantial direct effect on which could result in reduced structural FH, whichever occurs first since first flight
integrity of the wing. of the airplane.
the States, on the relationship between B Within 680 FC, or 3,420 FH, or 12
the national government and the States, (f) Compliance months, whichever occurs first after the ef-
or on the distribution of power and Comply with this AD within the fective date of this AD.
responsibilities among the various compliance times specified, unless already
levels of government. done. (h) Exception to Service Information
For the reasons discussed above, I Specifications
(g) Modification
certify that this AD: Where Airbus Service Bulletin A310–57–
1. Is not a ‘‘significant regulatory Within the compliance times defined in
2104, dated December 15, 2015, specifies to
table 1 to paragraph (g) of this AD, table 2
action’’ under Executive Order 12866; contact Airbus for appropriate action, and
to paragraph (g) of this AD, or table 3 to specifies that action as ‘‘RC’’ (Required for
2. Is not a ‘‘significant rule’’ under the paragraph (g) of this AD, as applicable to
DOT Regulatory Policies and Procedures Compliance): Before further flight,
airplane type and utilization: Do a accomplish corrective actions in accordance
(44 FR 11034, February 26, 1979); modification of the left-hand and right-hand with the procedures specified in paragraph
3. Will not affect intrastate aviation in wing bottom skin at the MLG reinforcing (i)(2) of this AD.
Alaska; and plate, including all related investigative
4. Will not have a significant actions and applicable corrective actions, in (i) Other FAA AD Provisions
economic impact, positive or negative, accordance with the Accomplishment The following provisions also apply to this
on a substantial number of small entities Instructions of Airbus Service Bulletin A310– AD:
under the criteria of the Regulatory 57–2104, dated December 15, 2015, except as (1) Alternative Methods of Compliance
required by paragraph (h) of this AD. Do all (AMOCs): The Manager, International
Flexibility Act. related investigative and applicable Section, Transport Standards Branch, FAA,
List of Subjects in 14 CFR Part 39 corrective actions before further flight. For has the authority to approve AMOCs for this
the purpose of this AD, the term ‘‘short AD, if requested using the procedures found
Air transportation, Aircraft, Aviation range’’ applies to airplanes with an average in 14 CFR 39.19. In accordance with 14 CFR
safety, Incorporation by reference, flight time (AFT) lower than 1.5 flight hours 39.19, send your request to your principal
Safety. per flight cycle, and the term ‘‘long range’’ inspector or local Flight Standards District
applies to airplanes with an average flight Office, as appropriate. If sending information
Adoption of the Amendment time equal to or higher than 1.5 flight hours directly to the International Section, send it
Accordingly, under the authority per flight cycle. For determining the ‘‘short to the attention of the person identified in
range’’ and ‘‘long range’’ airplanes, the AFT paragraph (j)(2) of this AD. Information may
delegated to me by the Administrator,
is the total accumulated flight hours, counted be emailed to: 9-ANM-116-AMOC-
the FAA amends 14 CFR part 39 as REQUESTS@faa.gov. Before using any
follows: from take-off to touch-down, divided by the
total accumulated flight cycles at the approved AMOC, notify your appropriate
effective date of this AD. principal inspector, or lacking a principal
PART 39—AIRWORTHINESS inspector, the manager of the local flight
DIRECTIVES standards district office/certificate holding
TABLE 1 TO PARAGRAPH (g) OF THIS district office.
■ 1. The authority citation for part 39 AD—MODEL A310–200 SERIES (2) Contacting the Manufacturer: For any
continues to read as follows: AIRPLANES requirement in this AD to obtain corrective
Authority: 49 U.S.C. 106(g), 40113, 44701. actions from a manufacturer, the action must
Compliance time be accomplished using a method approved
§ 39.13 [Amended] (whichever occurs later, A or B) by the Manager, International Section,
Transport Standards Branch, FAA; or the
■ 2. The FAA amends § 39.13 by adding A Before exceeding 28,800 flight cycles European Aviation Safety Agency (EASA); or
the following new airworthiness (FC) or 57,600 flight hours (FH), whichever Airbus’s EASA Design Organization
directive (AD): occurs first since first flight of the airplane. Approval (DOA). If approved by the DOA,
B Within 960 FC, or 1,920 FH, or 12 the approval must include the DOA-
2017–17–12 Airbus: Amendment 39–19002;
months, whichever occurs first after the ef- authorized signature.
Docket No. FAA–2017–0472; Product
fective date of this AD. (3) Required for Compliance (RC): Except
Identifier 2016–NM–148–AD.
as required by paragraph (h) of this AD, if
(a) Effective Date any service information contains procedures
This AD is effective October 2, 2017.
TABLE 2 TO PARAGRAPH (g) OF THIS or tests that are identified as RC, those
AD—MODEL A310–300 ‘‘SHORT- procedures and tests must be done to comply
(b) Affected ADs RANGE’’ AIRPLANES with this AD; any procedures or tests that are
None. not identified as RC are recommended. Those
procedures and tests that are not identified
Compliance time
asabaliauskas on DSKBBXCHB2PROD with RULES
(c) Applicability as RC may be deviated from using accepted
(whichever occurs later, A or B)
This AD applies to Airbus Model A310– methods in accordance with the operator’s
203, –221, –222, –304, –322, –324, and –325 A Before exceeding 27,700 FC or 77,700 maintenance or inspection program without
airplanes, certificated in any category, all FH, whichever occurs first since first flight obtaining approval of an AMOC, provided
manufacturer serial numbers. of the airplane. the procedures and tests identified as RC can
B Within 920 FC, or 2,580 FH, or 12 be done and the airplane can be put back in
(d) Subject an airworthy condition. Any substitutions or
months, whichever occurs first after the ef-
Air Transport Association (ATA) of fective date of this AD. changes to procedures or tests identified as
America Code 57, Wings. RC require approval of an AMOC.
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![40686 Federal Register / Vol. 82, No. 165 / Monday, August 28, 2017 / Rules and Regulations
(j) Related Information ACTION: Final rule. Discussion
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA SUMMARY: We are adopting a new We issued a notice of proposed
Airworthiness Directive 2016–0170, dated airworthiness directive (AD) for certain rulemaking (NPRM) to amend 14 CFR
August 19, 2016, for related information. Bombardier, Inc., Model CL–600–2E25 part 39 by adding an AD that would
This MCAI may be found in the AD docket (Regional Jet Series 1000) airplanes. apply to certain Bombardier, Inc., Model
on the Internet at http://www.regulations.gov This AD was prompted by reports of CL–600–2E25 (Regional Jet Series 1000)
by searching for and locating Docket No. failures of the landing gear alternate- airplanes. The NPRM published in the
FAA–2017–0472. extension system. This AD requires Federal Register on June 2, 2017 (82 FR
(2) For more information about this AD,
contact Dan Rodina, Aerospace Engineer,
replacement of certain nose landing gear 25545) (‘‘the NPRM’’). The NPRM was
International Section, Transport Standards and main landing gear electro- prompted by reports of failures of the
Branch, FAA, 1601 Lind Avenue SW., mechanical actuators. We are issuing landing gear alternate-extension system
Renton, WA 98057–3356; telephone 425– this AD to address the unsafe condition (AES). The NPRM proposed to require
227–2125; fax 425–227–1149. on these products. replacement of certain nose landing gear
(k) Material Incorporated by Reference DATES: This AD is effective October 2, and main landing gear electro-
2017. mechanical actuators. We are issuing
(1) The Director of the Federal Register
approved the incorporation by reference The Director of the Federal Register this AD to prevent failure of the landing
(IBR) of the service information listed in this approved the incorporation by reference gear AES and consequent landing with
paragraph under 5 U.S.C. 552(a) and 1 CFR of a certain publication listed in this AD some or all of the landing gear not
part 51. as of October 2, 2017. extended.
(2) You must use this service information ADDRESSES: For service information Transport Canada Civil Aviation
as applicable to do the actions required by
identified in this final rule, contact (TCCA), which is the aviation authority
this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A310–57–2104, Bombardier, Inc., 400 Côte-Vertu Road for Canada, has issued Canadian AD
dated December 15, 2015. West, Dorval, Québec H4S 1Y9, Canada; CF–2017–08, dated February 22, 2017
(ii) Reserved. Widebody Customer Response Center (referred to after this as the Mandatory
(3) For service information identified in North America toll-free telephone 1– Continuing Airworthiness Information,
this AD, contact Airbus SAS, Airworthiness 866–538–1247 or direct-dial telephone: or ‘‘the MCAI’’), to correct an unsafe
Office—EAW, 1 Rond Point Maurice 1–514–855–2999; fax: 514–855–7401; condition for certain Bombardier, Inc.,
Bellonte, 31707 Blagnac Cedex, France; email: ac.yul@aero.bombardier.com; Model CL–600–2E25 (Regional Jet Series
telephone +33 5 61 93 36 96; fax +33 5 61
Internet: http://www.bombardier.com. 1000) airplanes. The MCAI states:
93 44 51; email account.airworth-eas@
airbus.com; Internet http://www.airbus.com. You may view this referenced service Malfunctions of the landing gear Alternate-
(4) You may view this service information information at the FAA, Transport Extension System (AES) have been
at the FAA, Transport Standards Branch, Standards Branch, 1601 Lind Avenue experienced. Failure of the landing gear AES
1601 Lind Avenue SW., Renton, WA. For SW., Renton, WA. For information on could prevent the landing gear from
information on the availability of this the availability of this material at the extending in the case of a failure of the
material at the FAA, call 425–227–1221. FAA, call 425–227–1221. It is also primary landing gear extension system.
(5) You may view this service information available on the Internet at http:// This [Canadian] AD is issued to mandate
that is incorporated by reference at the www.regulations.gov by searching for the replacement of the [nose landing gear]
National Archives and Records NLG and [main landing gear] MLG [electro-
and locating Docket No. FAA–2017–
Administration (NARA). For information on mechanical actuators] EMA [part numbers] P/
the availability of this material at NARA, call 0512. Ns BA698–85006–1 and BA698–85007–1.
202–741–6030, or go to: http:// Examining the AD Docket
www.archives.gov/federal-register/cfr/ibr- You may examine the MCAI in the
locations.html. You may examine the AD docket on AD docket on the Internet at http://
the Internet at http:// www.regulations.gov by searching for
Issued in Renton, Washington, on August
9, 2017. www.regulations.gov by searching for and locating Docket No. FAA–2017–
and locating Docket No. FAA–2017– 0512.
Dionne Palermo,
0512; or in person at the Docket
Acting Director, System Oversight Division, Comments
Management Facility between 9 a.m.
Aircraft Certification Service.
and 5 p.m., Monday through Friday,
[FR Doc. 2017–17537 Filed 8–25–17; 8:45am] We gave the public the opportunity to
except Federal holidays. The AD docket
BILLING CODE 4910–13–P participate in developing this AD. We
contains this AD, the regulatory
received no comments on the NPRM or
evaluation, any comments received, and
on the determination of the cost to the
other information. The street address for
DEPARTMENT OF TRANSPORTATION public.
the Docket Office (telephone 800–647–
Federal Aviation Administration 5527) is Docket Management Facility, Conclusion
U.S. Department of Transportation,
Docket Operations, M–30, West We reviewed the relevant data and
14 CFR Part 39 determined that air safety and the
Building Ground Floor, Room W12–140,
[Docket No. FAA–2017–0512; Product 1200 New Jersey Avenue SE., public interest require adopting this AD
Identifier 2017–NM–031–AD; Amendment Washington, DC 20590. as proposed except for minor editorial
39–19005; AD 2017–17–15] changes. We have determined that these
asabaliauskas on DSKBBXCHB2PROD with RULES
FOR FURTHER INFORMATION CONTACT:
RIN 2120–AA64 minor changes:
Cesar Gomez, Aerospace Engineer,
Airframe and Mechanical Systems • Are consistent with the intent that
Airworthiness Directives; Bombardier, Section, FAA, New York ACO Branch, was proposed in the NPRM for
Inc., Airplanes 1600 Stewart Avenue, Suite 410, correcting the unsafe condition; and
AGENCY: Federal Aviation Westbury, NY 11590; telephone: 516– • Do not add any additional burden
Administration (FAA), Department of 228–7318; fax: 516–794–5531. upon the public than was already
Transportation (DOT). SUPPLEMENTARY INFORMATION: proposed in the NPRM.
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Document Created: 2017-08-28 11:30:11
Document Modified: 2017-08-28 11:30:11
| 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. | |
| Dates | This AD is effective October 2, 2017. | |
| 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 | 82 FR 40683 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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