82 FR 4773 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 10 (January 17, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 10 (January 17, 2017)
| Page Range | 4773-4775 | |
| FR Document | 2016-31961 |
[Federal Register Volume 82, Number 10 (Tuesday, January 17, 2017)] [Rules and Regulations] [Pages 4773-4775] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-31961] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-9110; Directorate Identifier 2015-NM-196-AD; Amendment 39-18773; AD 2017-01-06] 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 certain Airbus Model A319-115, A319-132, A320-214, A320-232, A321-211, A321- 213, and A321-231 airplanes. This AD was prompted by a report of certain tie rod assemblies installed on the hinged fairing assembly of the main landing gear (MLG) with no cadmium plating on the rod end threads. This AD requires inspection and replacement of certain tie rod assemblies installed on the hinged fairing assembly of the MLG. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective February 21, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 21, 2017. ADDRESSES: For service information identified in this final rule, contact Airbus, Airworthiness Office--EIAS, 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 Airplane Directorate, 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-2016- 9110. 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-2016- 9110; 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; 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 certain Airbus Model A319- 115, A319-132, A320-214, A320-232, A321-211, A321-213, and A321-231 airplanes. The NPRM published in the Federal Register on September 19, 2016 (81 FR 64083). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015-0234, dated December 8, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A319-115, A319-132, A320-214, A320-232, A321-211, A321-213, and A321- 231 airplanes. The MCAI states: A production quality issue was identified concerning tie rod assemblies, having Part Number (P/N) starting with D52840212000 or D52840212002, which are installed on the main landing gear (MLG) hinged fairing assembly. This quality issue affects the cadmium plating surface treatment which [[Page 4774]] was inadvertently omitted from the rod end threads of the assembly. The absence of cadmium plating reduces the corrosion protection scheme. This condition, if not detected and corrected, could lead to galvanic corrosion of the tie rod end threads, possibly resulting in rod end failure, loss of a MLG door, and consequent injury to persons on ground. To address this unsafe condition, Airbus identified the affected [manufacturer serial number] MSN and issued [service bulletin] SB A320-52-1167 to provide inspection instructions. For the reason described above, this [EASA] AD requires a one- time inspection of the affected MLG hinged fairing tie rod assemblies [for the presence of cadmium plating], and, depending on findings, replacement of the affected tie rod assembly. 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-2016- 9110. 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 A320-52-1167, dated August 6, 2015. The service information describes procedures for a detailed inspection for the presence of cadmium plating on tie rod assemblies having certain part numbers, and procedures for replacement of tie rod assemblies with no cadmium plating on the rod end threads. 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 20 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 ---------------------------------------------------------------------------------------------------------------- Inspection......................... 2 work-hours x $85 per hour = $0 $170 $3,400 $170. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary replacements that will be required based on the results of the inspection. We have no way of determining the number of airplanes that might need these replacements: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Replacement........................... 13 work-hours x $85 per hour = Not available........... $1,105 $1,105. ---------------------------------------------------------------------------------------------------------------- According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all available costs in our cost estimate. 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. 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: [[Page 4775]] 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): 2017-01-06 Airbus: Amendment 39-18773; Docket No. FAA-2016-9110; Directorate Identifier 2015-NM-196-AD. (a) Effective Date This AD is effective February 21, 2017. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A319-115, A319-132, A320-214, A320-232, A321-211, A321-213, and A321-231 airplanes, certificated in any category, as identified in Airbus Service Bulletin A320-52- 1167, dated August 6, 2015. (d) Subject Air Transport Association (ATA) of America Code 52, Doors. (e) Reason This AD was prompted by a report of certain tie rod assemblies installed on the hinged fairing assembly of the main landing gear (MLG) with no cadmium plating on the rod end threads. We are issuing this AD to detect and correct the absence of cadmium plating on the rod end threads of the tie rod assemblies. The absence of cadmium plating could lead to galvanic corrosion of the tie rod end threads, resulting in rod end failure, loss of a MLG door, and consequent damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection and Corrective Action Within 80 months after the airplane's first flight, do a detailed inspection of each tie rod assembly having a part number (P/N) D52840212000 or D52840212002 at the MLG hinged fairing for the presence of cadmium plating (gold colored threads), in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1167, dated August 6, 2015. If during the inspection any tie rod assembly is found that does not have cadmium plating, before further flight, replace the tie rod assembly with a serviceable part having the same part number and cadmium plating, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52- 1167, dated August 6, 2015. (h) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, 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 Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone 425-227-1405; fax 425-227-1149. 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. The AMOC approval letter must specifically reference this AD. (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 Branch, ANM-116, Transport Airplane Directorate, 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): 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. (i) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015-0234, dated December 8, 2015, 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-2016-9110. (j) 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 A320-52-1167, dated August 6, 2015. (ii) Reserved. (3) For service information identified in this AD, contact Airbus, Airworthiness Office--EIAS, 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 Airplane Directorate, 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 December 23, 2016. Thomas Groves, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-31961 Filed 1-13-17; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 82, No. 10 / Tuesday, January 17, 2017 / Rules and Regulations 4773
of the Unfunded Mandates Reform Act 1225, 1226, 1228, 1365a note, 1379, 1731–32; Internet http://www.airbus.com. You
of 1995. Title VII of Public Law 110–229; 8 U.S.C. may view this referenced service
1185 note (section 7209 of Pub. L. 108–458). information at the FAA, Transport
E. Small Business Regulatory
■ 2. Revise § 1235.3(b)(1)(i) to read as Airplane Directorate, 1601 Lind Avenue
Enforcement Fairness Act of 1996
follows: SW., Renton, WA. For information on
This rule is not a major rule as the availability of this material at the
defined by section 251 of the Small § 1235.3 Inadmissible aliens and expedited FAA, call 425–227–1221. It is also
Business Regulatory Enforcement removal. available on the Internet at http://
Fairness Act of 1996. See 5 U.S.C. 804. * * * * * www.regulations.gov by searching for
This rule will not result in an annual (b) * * * and locating Docket No. FAA–2016–
effect on the economy of $100 million (1) * * * 9110.
or more; a major increase in costs or (i) Arriving aliens, as defined in
§ 1001.1(q) of this chapter; Examining the AD Docket
prices; or significant adverse effects on
competition, employment, investment, * * * * * You may examine the AD docket on
productivity, innovation, or on the the Internet at http://
Dated: January 11, 2017. www.regulations.gov by searching for
ability of United States-based
Loretta E. Lynch, and locating Docket No. FAA–2016–
enterprises to compete with foreign-
based enterprises in domestic and Attorney General. 9110; or in person at the Docket
export markets. [FR Doc. 2017–00902 Filed 1–13–17; 8:45 am] Management Facility between 9 a.m.
BILLING CODE 4410–30–P and 5 p.m., Monday through Friday,
F. Executive Order 13132: Federalism except Federal holidays. The AD docket
This rule will not have substantial contains this AD, the regulatory
direct effects on the States, on the DEPARTMENT OF TRANSPORTATION evaluation, any comments received, and
relationship between the National other information. The street address for
Government and the States, or on the Federal Aviation Administration the Docket Office (telephone 800–647–
distribution of power and 5527) is Docket Management Facility,
responsibilities among the various 14 CFR Part 39 U.S. Department of Transportation,
levels of government. Therefore, in Docket Operations, M–30, West
[Docket No. FAA–2016–9110; Directorate
accordance with section 6 of Executive Identifier 2015–NM–196–AD; Amendment Building Ground Floor, Room W12–140,
Order 13132, it is determined that this 39–18773; AD 2017–01–06] 1200 New Jersey Avenue SE.,
rule does not have sufficient federalism Washington, DC 20590.
implications to warrant the preparation RIN 2120–AA64 FOR FURTHER INFORMATION CONTACT:
of a federalism summary impact Sanjay Ralhan, Aerospace Engineer,
Airworthiness Directives; Airbus
statement. International Branch, ANM–116,
Airplanes
G. Executive Order 12988: Civil Justice Transport Airplane Directorate, FAA,
Reform AGENCY: Federal Aviation 1601 Lind Avenue SW., Renton, WA
Administration (FAA), Department of 98057–3356; telephone 425–227–1405;
This rule meets the applicable Transportation (DOT). fax 425–227–1149.
standards set forth in sections 3(a) and SUPPLEMENTARY INFORMATION:
ACTION: Final rule.
3(b)(2) of Executive Order 12988.
SUMMARY: We are adopting a new Discussion
H. Paperwork Reduction Act
airworthiness directive (AD) for certain We issued a notice of proposed
The provisions of the Paperwork Airbus Model A319–115, A319–132, rulemaking (NPRM) to amend 14 CFR
Reduction Act of 1995, Public Law 104– A320–214, A320–232, A321–211, A321– part 39 by adding an AD that would
13, 44 U.S.C. chapter 35, and its 213, and A321–231 airplanes. This AD apply to certain Airbus Model A319–
implementing regulations, 5 CFR part was prompted by a report of certain tie 115, A319–132, A320–214, A320–232,
1320, do not apply to this rule because rod assemblies installed on the hinged A321–211, A321–213, and A321–231
there are no new or revised fairing assembly of the main landing airplanes. The NPRM published in the
recordkeeping or reporting gear (MLG) with no cadmium plating on Federal Register on September 19, 2016
requirements. the rod end threads. This AD requires (81 FR 64083).
List of Subjects in 8 CFR Part 1235 inspection and replacement of certain The European Aviation Safety Agency
tie rod assemblies installed on the (EASA), which is the Technical Agent
Administrative practice and for the Member States of the European
hinged fairing assembly of the MLG. We
procedure, Aliens, Immigration, Union, has issued EASA Airworthiness
are issuing this AD to address the unsafe
Reporting and recordkeeping Directive 2015–0234, dated December 8,
condition on these products.
requirements. 2015 (referred to after this as the
DATES: This AD is effective February 21,
Accordingly, for the reasons stated in Mandatory Continuing Airworthiness
2017.
the preamble, part 1235 of title 8 of the Information, or ‘‘the MCAI’’), to correct
The Director of the Federal Register
Code of Federal Regulations is amended an unsafe condition for certain Airbus
approved the incorporation by reference
as follows: Model A319–115, A319–132, A320–214,
of a certain publication listed in this AD
as of February 21, 2017. A320–232, A321–211, A321–213, and
PART 1235—EXECUTIVE OFFICE FOR A321–231 airplanes. The MCAI states:
sradovich on DSK3GMQ082PROD with RULES
IMMIGRATION REVIEW ADDRESSES: For service information
identified in this final rule, contact A production quality issue was identified
■ 1. The authority citation for part 1235 Airbus, Airworthiness Office—EIAS, 1 concerning tie rod assemblies, having Part
Number (P/N) starting with D52840212000 or
continues to read: Rond Point Maurice Bellonte, 31707 D52840212002, which are installed on the
Authority: 8 U.S.C. 1101 and note, 1103, Blagnac Cedex, France; telephone +33 5 main landing gear (MLG) hinged fairing
1183, 1185 (pursuant to E.O. 13323, 69 FR 61 93 36 96; fax +33 5 61 93 44 51; email assembly. This quality issue affects the
241, 3 CFR, 2003 Comp., p. 278), 1201, 1224, account.airworth-eas@airbus.com; cadmium plating surface treatment which
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![4774 Federal Register / Vol. 82, No. 10 / Tuesday, January 17, 2017 / Rules and Regulations
was inadvertently omitted from the rod end Comments Related Service Information Under 1
threads of the assembly. The absence of CFR Part 51
cadmium plating reduces the corrosion We gave the public the opportunity to
protection scheme. participate in developing this AD. We Airbus has issued Service Bulletin
This condition, if not detected and received no comments on the NPRM or A320–52–1167, dated August 6, 2015.
corrected, could lead to galvanic corrosion of
on the determination of the cost to the The service information describes
the tie rod end threads, possibly resulting in procedures for a detailed inspection for
rod end failure, loss of a MLG door, and public.
the presence of cadmium plating on tie
consequent injury to persons on ground. Conclusion rod assemblies having certain part
To address this unsafe condition, Airbus
numbers, and procedures for
identified the affected [manufacturer serial We reviewed the relevant data and
number] MSN and issued [service bulletin] replacement of tie rod assemblies with
determined that air safety and the no cadmium plating on the rod end
SB A320–52–1167 to provide inspection
instructions. public interest require adopting this AD threads. This service information is
For the reason described above, this as proposed except for minor editorial reasonably available because the
[EASA] AD requires a one-time inspection of changes. We have determined that these interested parties have access to it
the affected MLG hinged fairing tie rod minor changes: through their normal course of business
assemblies [for the presence of cadmium or by the means identified in the
plating], and, depending on findings,
• Are consistent with the intent that
was proposed in the NPRM for ADDRESSES section.
replacement of the affected tie rod assembly.
correcting the unsafe condition; and Costs of Compliance
You may examine the MCAI in the
AD docket on the Internet at http:// • Do not add any additional burden We estimate that this AD affects 20
www.regulations.gov by searching for upon the public than was already airplanes of U.S. registry.
and locating Docket No. FAA–2016– proposed in the NPRM. We estimate the following costs to
9110. comply with this AD:
ESTIMATED COSTS
Cost on
Cost per
Action Labor cost Parts cost U.S. opera-
product tors
Inspection ..... 2 work-hours × $85 per hour = $170 ............................................................................ $0 $170 $3,400
We estimate the following costs to do required based on the results of the determining the number of airplanes
any necessary replacements that will be inspection. We have no way of that might need these replacements:
ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product
Replacement ........................... 13 work-hours × $85 per hour = $1,105 .................................. Not available ........................... $1,105
According to the manufacturer, some for practices, methods, and procedures 2. Is not a ‘‘significant rule’’ under the
of the costs of this AD may be covered the Administrator finds necessary for DOT Regulatory Policies and Procedures
under warranty, thereby reducing the safety in air commerce. This regulation (44 FR 11034, February 26, 1979);
cost impact on affected individuals. We is within the scope of that authority 3. Will not affect intrastate aviation in
do not control warranty coverage for because it addresses an unsafe condition Alaska; and
affected individuals. As a result, we that is likely to exist or develop on
have included all available costs in our 4. Will not have a significant
products identified in this rulemaking
cost estimate. economic impact, positive or negative,
action.
on a substantial number of small entities
Authority for This Rulemaking Regulatory Findings under the criteria of the Regulatory
Title 49 of the United States Code Flexibility Act.
specifies the FAA’s authority to issue We determined that this AD will not
have federalism implications under List of Subjects in 14 CFR Part 39
rules on aviation safety. Subtitle I,
section 106, describes the authority of Executive Order 13132. This AD will
Air transportation, Aircraft, Aviation
the FAA Administrator. ‘‘Subtitle VII: not have a substantial direct effect on
safety, Incorporation by reference,
Aviation Programs,’’ describes in more the States, on the relationship between
Safety.
detail the scope of the Agency’s the national government and the States,
authority. or on the distribution of power and Adoption of the Amendment
sradovich on DSK3GMQ082PROD with RULES
We are issuing this rulemaking under responsibilities among the various
the authority described in ‘‘Subtitle VII, levels of government. Accordingly, under the authority
Part A, Subpart III, Section 44701: delegated to me by the Administrator,
For the reasons discussed above, I
General requirements.’’ Under that the FAA amends 14 CFR part 39 as
certify that this AD:
section, Congress charges the FAA with follows:
promoting safe flight of civil aircraft in 1. Is not a ‘‘significant regulatory
air commerce by prescribing regulations action’’ under Executive Order 12866;
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PART 39—AIRWORTHINESS Branch, ANM–116, Transport Airplane telephone +33 5 61 93 36 96; fax +33 5 61
DIRECTIVES Directorate, FAA, has the authority to 93 44 51; email account.airworth-eas@
approve AMOCs for this AD, if requested airbus.com; Internet http://www.airbus.com.
■ 1. The authority citation for part 39 using the procedures found in 14 CFR 39.19. (4) You may view this service information
continues to read as follows: In accordance with 14 CFR 39.19, send your at the FAA, Transport Airplane Directorate,
request to your principal inspector or local 1601 Lind Avenue SW., Renton, WA. For
Authority: 49 U.S.C. 106(g), 40113, 44701. Flight Standards District Office, as information on the availability of this
appropriate. If sending information directly material at the FAA, call 425–227–1221.
§ 39.13 [Amended]
to the International Branch, send it to ATTN: (5) You may view this service information
■ 2. The FAA amends § 39.13 by adding Sanjay Ralhan, Aerospace Engineer, that is incorporated by reference at the
the following new airworthiness International Branch, ANM–116, Transport National Archives and Records
directive (AD): Airplane Directorate, FAA, 1601 Lind Administration (NARA). For information on
Avenue SW., Renton, WA 98057–3356; the availability of this material at NARA, call
2017–01–06 Airbus: Amendment 39–18773; telephone 425–227–1405; fax 425–227–1149. 202–741–6030, or go to: http://
Docket No. FAA–2016–9110; Directorate Information may be emailed to: 9-ANM-116- www.archives.gov/federal-register/cfr/ibr-
Identifier 2015–NM–196–AD. AMOC-REQUESTS@faa.gov. Before using locations.html.
(a) Effective Date any approved AMOC, notify your appropriate
Issued in Renton, Washington, on
principal inspector, or lacking a principal
This AD is effective February 21, 2017. December 23, 2016.
inspector, the manager of the local flight
(b) Affected ADs standards district office/certificate holding Thomas Groves,
None. district office. The AMOC approval letter Acting Manager, Transport Airplane
must specifically reference this AD. Directorate, Aircraft Certification Service.
(c) Applicability (2) Contacting the Manufacturer: For any [FR Doc. 2016–31961 Filed 1–13–17; 8:45 am]
This AD applies to Airbus Model A319– requirement in this AD to obtain corrective BILLING CODE 4910–13–P
115, A319–132, A320–214, A320–232, A321– actions from a manufacturer, the action must
211, A321–213, and A321–231 airplanes, be accomplished using a method approved
certificated in any category, as identified in by the Manager, International Branch, ANM–
DEPARTMENT OF TRANSPORTATION
Airbus Service Bulletin A320–52–1167, 116, Transport Airplane Directorate, FAA; or
dated August 6, 2015. the European Aviation Safety Agency
Federal Aviation Administration
(EASA); or Airbus’s EASA Design
(d) Subject Organization Approval (DOA). If approved by
Air Transport Association (ATA) of the DOA, the approval must include the 14 CFR Part 39
America Code 52, Doors. DOA-authorized signature.
[Docket No. FAA–2016–7419; Directorate
(e) Reason (3) Required for Compliance (RC): If any
Identifier 2015–NM–189–AD; Amendment
service information contains procedures or
This AD was prompted by a report of 39–18769; AD 2017–01–02]
tests that are identified as RC, those
certain tie rod assemblies installed on the procedures and tests must be done to comply RIN 2120–AA64
hinged fairing assembly of the main landing with this AD; any procedures or tests that are
gear (MLG) with no cadmium plating on the not identified as RC are recommended. Those
rod end threads. We are issuing this AD to Airworthiness Directives; The Boeing
procedures and tests that are not identified Company Airplanes
detect and correct the absence of cadmium as RC may be deviated from using accepted
plating on the rod end threads of the tie rod methods in accordance with the operator’s
assemblies. The absence of cadmium plating
AGENCY: Federal Aviation
maintenance or inspection program without Administration (FAA), DOT.
could lead to galvanic corrosion of the tie rod
obtaining approval of an AMOC, provided
end threads, resulting in rod end failure, loss ACTION: Final rule.
the procedures and tests identified as RC can
of a MLG door, and consequent damage to
be done and the airplane can be put back in
the airplane. SUMMARY: We are adopting a new
an airworthy condition. Any substitutions or
(f) Compliance changes to procedures or tests identified as airworthiness directive (AD) for certain
RC require approval of an AMOC. The Boeing Company Model 787–8 and
Comply with this AD within the
compliance times specified, unless already
787–9 airplanes. This AD was prompted
(i) Related Information by a report that some inboard and
done.
Refer to Mandatory Continuing outboard trailing edge flap rotary
(g) Inspection and Corrective Action Airworthiness Information (MCAI) EASA actuators may have been assembled
Within 80 months after the airplane’s first Airworthiness Directive 2015–0234, dated with an incorrect no-back brake rotor-
flight, do a detailed inspection of each tie rod December 8, 2015, for related information.
stator stack sequence during
assembly having a part number (P/N) This MCAI may be found in the AD docket
on the Internet at http://www.regulations.gov manufacturing. This AD requires
D52840212000 or D52840212002 at the MLG
by searching for and locating Docket No. inspecting the trailing edge flap rotary
hinged fairing for the presence of cadmium
plating (gold colored threads), in accordance FAA–2016–9110. actuator, and replacing the rotary
with the Accomplishment Instructions of actuator or doing related investigative
(j) Material Incorporated by Reference
Airbus Service Bulletin A320–52–1167, and corrective actions if necessary. We
dated August 6, 2015. If during the (1) The Director of the Federal Register are issuing this AD to address the unsafe
inspection any tie rod assembly is found that approved the incorporation by reference condition on these products.
does not have cadmium plating, before (IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR DATES: This AD is effective February 21,
further flight, replace the tie rod assembly
with a serviceable part having the same part part 51. 2017.
number and cadmium plating, in accordance (2) You must use this service information The Director of the Federal Register
with the Accomplishment Instructions of as applicable to do the actions required by approved the incorporation by reference
sradovich on DSK3GMQ082PROD with RULES
Airbus Service Bulletin A320–52–1167, this AD, unless this AD specifies otherwise. of a certain publication listed in this AD
dated August 6, 2015. (i) Airbus Service Bulletin A320–52–1167, as of February 21, 2017.
dated August 6, 2015.
(h) Other FAA AD Provisions ADDRESSES: For service information
(ii) Reserved.
The following provisions also apply to this (3) For service information identified in identified in this final rule, contact
AD: this AD, contact Airbus, Airworthiness Boeing Commercial Airplanes,
(1) Alternative Methods of Compliance Office—EIAS, 1 Rond Point Maurice Attention: Contractual & Data Services
(AMOCs): The Manager, International Bellonte, 31707 Blagnac Cedex, France; (C&DS), 2600 Westminster Blvd., MC
VerDate Sep<11>2014 16:30 Jan 13, 2017 Jkt 241001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 E:\FR\FM\17JAR1.SGM 17JAR1](https://thefederalregister.org/doc/82_FR_4783/page/3.svg)
Document Created: 2017-01-14 01:44:49
Document Modified: 2017-01-14 01:44:49
| 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 February 21, 2017. | |
| Contact | Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. | |
| FR Citation | 82 FR 4773 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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