Airworthiness Directives; Airbus Airplanes, 56167-56169 [2017-25253]

Download as PDF Federal Register / Vol. 82, No. 227 / Tuesday, November 28, 2017 / Rules and Regulations Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2017–19–01 Sikorsky Aircraft Corporation: Amendment 39–19031; Docket No. FAA–2017–0491; Product Identifier 2016–SW–020–AD. (a) Applicability This AD applies to Model S–76A, S–76B, S–76C, and S–76D helicopters, serial numbers up to and including 761075, with a main rotor (M/R) servo pushrod (pushrod) assembly part number (P/N) 76400–00034– 059, 76400–00014–074, 76400–00014–076, or 76400–00014–077 installed, certificated in any category. Note 1 to paragraph (a) of this AD: M/R pushrod P/N 76400–00034–059 is included in the Applicability section of AD 2015–19– 51, Amendment 39–18300 (80 FR 65128, October 26, 2015). This AD does not affect AD 2015–19–51. (b) Unsafe Condition This AD defines the unsafe condition as a loose jamnut. This condition could result in failure of a pushrod assembly, loss of M/R flight control, and subsequent loss of control of the helicopter. (c) Effective Date This AD becomes effective January 2, 2018. jstallworth on DSKBBY8HB2PROD with RULES (d) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (e) Required Actions Within 300 hours time-in-service: (1) Inspect the control rod of each pushrod assembly (control rod) to determine whether 0.020 inch diameter lockwire can pass through the inspection hole. (i) If the lockwire passes through the inspection hole, before further flight, replace the pushrod assembly. (ii) If the lockwire does not pass through the inspection hole, inspect the jamnut to determine whether it is seated against the control rod and whether it can be turned with finger pressure. (A) If the jamnut is not seated against the control rod or can be turned with finger pressure, before further flight, replace the pushrod assembly. (B) If the jamnut is seated against the control rod and cannot be turned with finger VerDate Sep<11>2014 15:23 Nov 27, 2017 Jkt 244001 pressure, using a pushrod tool, apply 140 inch-pounds of torque to the jamnut. (2) Apply two slippage marks across each control rod and jamnut as follows: (i) Clean the area where a slippage mark is to be applied. (ii) Apply two slippage marks across the control rod and jamnut, parallel and on opposite sides of each other. Each slippage mark must extend at least 0.5 inch onto the control rod and must not cover the inspection hole. Figure 1 (Sheet 2) of Sikorsky S–76 Helicopter Alert Service Bulletin 76–67–58, Basic Issue, dated November 19, 2015, illustrates a slippage mark across a control rod and jamnut. (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Boston ACO Branch, FAA, may approve AMOCs for this AD. Send your proposal to: Blaine Williams, Aerospace Engineer, Boston ACO Branch, Compliance and Airworthiness Division, 1200 District Avenue, Burlington, Massachusetts 01803; telephone (781) 238–7161; email blaine.williams@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC. (g) Additional Information Sikorksy S–76 Helicopter Alert Service Bulletin 76–67–58, Basic Issue, dated November 19, 2015, which is not incorporated by reference, contains additional information about the subject of this AD. For service information identified in this AD, contact Sikorsky Aircraft Corporation, Customer Service Engineering, 124 Quarry Road, Trumbull, CT 06611; telephone 1–800-Winged-S or 203–416–4299; email: wcs_cust_service_eng.gr-sik@ lmco.com. You may review a copy of this service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N–321, Fort Worth, TX 76177. (h) Subject Joint Aircraft Service Component (JASC) Code: 6700, Rotorcraft Flight Control. Issued in Fort Worth, Texas, on November 17, 2017. Scott A. Horn, Deputy Director for Regulatory Operations, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2017–25558 Filed 11–27–17; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 56167 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0690; Product Identifier 2017–NM–061–AD; Amendment 39–19107; AD 2017–24–03] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are removing Airworthiness Directive (AD) 2017–01– 06, which applied to certain Airbus Model A319–115, A319–132, A320–214, A320–232, A321–211, A321–213, and A321–231 airplanes. AD 2017–01–06 required inspection and replacement of certain tie rod assemblies installed on the hinged fairing assembly of the main landing gear (MLG). We issued AD 2017–01–06 to detect and correct the absence of cadmium plating on the rod end threads of the tie rod assemblies. Since we issued AD 2017–01–06, we have determined that although cadmium plating might be absent, the rod end threads of the tie rod assemblies can withstand the expected environmental conditions, therefore the unsafe condition, as initially determined, does not exist. DATES: This AD is effective January 2, 2018. SUMMARY: 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 account.airworth-eas@airbus.com; 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– 0690. ADDRESSES: 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– 0690; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, E:\FR\FM\28NOR1.SGM 28NOR1 56168 Federal Register / Vol. 82, No. 227 / Tuesday, November 28, 2017 / Rules and Regulations except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The 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 Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227– 1149. SUPPLEMENTARY INFORMATION: Discussion jstallworth on DSKBBY8HB2PROD with RULES We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to remove AD 2017–01–06, Amendment 39–18773 (82 FR 4773, January 17, 2017) (‘‘AD 2017–01–06’’). AD 2017–01–06 applied 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 July 17, 2017 (82 FR 32650). The NPRM was prompted by our determination that, although cadmium plating might be absent, the rod end threads of the tie rod assemblies installed on the hinged fairing assembly of the MLG can withstand the expected environmental conditions, therefore the unsafe condition, as initially determined, does not exist. The NPRM proposed to remove AD 2017–01–06. We are issuing this AD to remove AD 2017–01–06. 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–CN, dated April 28, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to cancel EASA AD 2015–0234–CN, which applied to 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 [a] Part Number 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 was inadvertently omitted from the rod end threads of the assembly. The absence of cadmium plating reduces the corrosion protection scheme. VerDate Sep<11>2014 15:23 Nov 27, 2017 Jkt 244001 This condition, if not detected and corrected, was initially assessed as leading 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 MSN [manufacturer serial number] and issued SB A320–52–1167 to provide inspection instructions. Consequently, EASA issued AD 2015–0234 [which corresponds to FAA AD 2017–01–06], requiring a one-time inspection of the affected MLG hinged fairing tie rod assemblies, and, depending on findings, replacement of the affected tie rod assembly. Since that [EASA] AD was issued, tests performed by the tie rod assembly manufacturers determined that the assemblies, even without cadmium plating surface treatment on the rod end threads, can withstand the expected environmental conditions. The consequence is that the unsafe condition, as initially determined, does not exist. For the reasons described above, this Notice cancels EASA AD 2015–0234. 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. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. 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– 0690. Regulatory Findings We reviewed the available 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. 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. Related Costs of Compliance List of Subjects in 14 CFR Part 39 AD 2017–01–06 affected about 20 airplanes of U.S. registry. The estimated cost of the actions required by AD 2017– 01–06 for U.S. operators was $3,400, or $170, per product. Removing AD 2017– 01–06 eliminates those costs. Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 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 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. PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. E:\FR\FM\28NOR1.SGM 28NOR1 Federal Register / Vol. 82, No. 227 / Tuesday, November 28, 2017 / Rules and Regulations § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2017–01–06, Amendment 39–18773 (82 FR 4773, January 17, 2017), and adding the following new AD: ■ 2017–24–03 Airbus: Amendment 39–19107; Docket No. FAA–2017–0690; Product Identifier 2017–NM–061–AD. (a) Effective Date This rescission is effective January 2, 2018. (b) Affected AD This action removes AD 2017–01–06, Amendment 39–18773 (82 FR 4773, January 17, 2017). (c) Applicability This action 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) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) AD 2015– 0234–CN, dated April 28, 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–2017–0690. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425– 227–1405; fax 425–227–1149. (e) Material Incorporated by Reference None. Issued in Renton, Washington, on November 15, 2017. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017–25253 Filed 11–27–17; 8:45 am] BILLING CODE 4910–13–P COMMODITY FUTURES TRADING COMMISSION 17 CFR Part 23 RIN 3038–AC97 Margin Requirements for Uncleared Swaps for Swap Dealers and Major Swap Participants; Correction Commodity Futures Trading Commission. ACTION: Correcting amendments. AGENCY: The Commodity Futures Trading Commission (CFTC or Commission) is correcting a final rule published in the Federal Register on January 6, 2016. The rule, concerning margin requirements for uncleared swaps for swap dealers and major swap participants, took effect on April 1, 2016. This correction rectifies errors in cross-references in a particular section of the final rule. DATES: Effective on November 28, 2017. FOR FURTHER INFORMATION CONTACT: Thomas Smith, Deputy Director, 202– 418–5495, tsmith@cftc.gov, or Mark Bretscher, Attorney-Advisor, 312–596– 0529, mbretscher@cftc.gov, Division of Swap Dealer and Intermediary Oversight, Commodity Futures Trading Commission, Three Lafayette Centre, 1155 21st Street NW., Washington, DC 20581. SUPPLEMENTARY INFORMATION: In the Federal Register of January 6, 2016 (81 FR 636), the CFTC published final rules adopting new regulations to implement a particular provision of the Commodity Exchange Act (CEA), as added by the Dodd-Frank Wall Street Reform and Consumer Protection Act (Dodd-Frank Act).1 This provision requires the Commission to adopt initial and SUMMARY: 56169 variation margin requirements for certain swap dealers and major swap participants. In implementing the regulations, staff has discovered crossreference errors in § 23.156 of the regulations. As published, 17 CFR 23.156(a)(3) includes erroneous crossreferences to 17 CFR 23.156(a)(1)(iv). Instead, the cross-references should be to 17 CFR 23.156(a)(1)(v). Accordingly, the Commission is making a correcting amendment to 17 CFR 23.156(a)(3) that removes the erroneous cross-references to 17 CFR 23.156(a)(1)(iv) and replaces them with corrected cross-references to 17 CFR 23.156(a)(1)(v). List of Subjects in 17 CFR Part 23 Swaps, Swap dealers, Major swap participants, Capital and margin requirements. Accordingly, 17 CFR part 23 is corrected by making the following correcting amendments: PART 23—SWAP DEALERS AND MAJOR SWAP PARTICIPANTS 1. The authority citation for part 23 continues to read as follows: ■ Authority: 7 U.S.C. 1a, 2, 6, 6a, 6b, 6b–1, 6c, 6p, 6r, 6s, 6t, 9, 9a, 12, 12a, 13b, 13c, 16a, 18, 19, 21. 2. In § 23.156, revise paragraph (a)(3)(i)(B) to read as follows: ■ § 23.156 Forms of margin. (a) * * * (3) * * * (i) * * * (B) The discounts set forth in the following table: jstallworth on DSKBBY8HB2PROD with RULES STANDARDIZED HAIRCUT SCHEDULE Cash in same currency as swap obligation .......................................................................................................................................................................... Eligible government and related debt (e.g., central bank, multilateral development bank, GSE securities identified in paragraph (a)(1)(v) of this section): Residual maturity less than one-year ...................................................................................................................................................................... Eligible government and related debt (e.g., central bank, multilateral development bank, GSE securities identified in paragraph (a)(1)(v) of this section): Residual maturity between one and five years ........................................................................................................................................................ Eligible government and related debt (e.g., central bank, multilateral development bank, GSE securities identified in paragraph (a)(1)(v) of this section): Residual maturity greater than five years ................................................................................................................................................................ Eligible corporate debt (including eligible GSE debt securities not identified in paragraph (a)(1)(v) of this section): Residual maturity less than oneyear .................................................................................................................................................................................................................................... Eligible corporate debt (including eligible GSE debt securities not identified in paragraph (a)(1)(v) of this section): Residual maturity between one and five years ........................................................................................................................................................................................................................... Eligible corporate debt (including eligible GSE debt securities not identified in paragraph (a)(1)(v) of this section): Residual maturity greater than five years .................................................................................................................................................................................................................................. Equities included in S&P 500 or related index ..................................................................................................................................................................... Equities included in S&P 1500 Composite or related index but not S&P 500 or related index .......................................................................................... Gold ....................................................................................................................................................................................................................................... Additional (additive) haircut on asset in which the currency of the swap obligation differs from that of the collateral asset ............................................. 1 See Dodd-Frank Wall Street Reform and Consumer Protection Act, Public Law 111–203, 124 Stat. 1376 (2010). VerDate Sep<11>2014 15:23 Nov 27, 2017 Jkt 244001 PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 E:\FR\FM\28NOR1.SGM 28NOR1 0.0 0.5 2.0 4.0 1.0 4.0 8.0 15.0 25.0 15.0 8.0

Agencies

[Federal Register Volume 82, Number 227 (Tuesday, November 28, 2017)]
[Rules and Regulations]
[Pages 56167-56169]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-25253]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0690; Product Identifier 2017-NM-061-AD; Amendment 
39-19107; AD 2017-24-03]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are removing Airworthiness Directive (AD) 2017-01-06, which 
applied to certain Airbus Model A319-115, A319-132, A320-214, A320-232, 
A321-211, A321-213, and A321-231 airplanes. AD 2017-01-06 required 
inspection and replacement of certain tie rod assemblies installed on 
the hinged fairing assembly of the main landing gear (MLG). We issued 
AD 2017-01-06 to detect and correct the absence of cadmium plating on 
the rod end threads of the tie rod assemblies. Since we issued AD 2017-
01-06, we have determined that although cadmium plating might be 
absent, the rod end threads of the tie rod assemblies can withstand the 
expected environmental conditions, therefore the unsafe condition, as 
initially determined, does not exist.

DATES: This AD is effective January 2, 2018.

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 account.airworth-eas@airbus.com; 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-
0690.

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-
0690; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday,

[[Page 56168]]

except Federal holidays. The AD docket contains this AD, the regulatory 
evaluation, any comments received, and other information. The 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 Section, Transport Standards Branch, 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 to remove AD 2017-01-06, Amendment 39-18773 (82 FR 4773, 
January 17, 2017) (``AD 2017-01-06''). AD 2017-01-06 applied 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 July 17, 2017 (82 FR 32650). The NPRM was prompted by our 
determination that, although cadmium plating might be absent, the rod 
end threads of the tie rod assemblies installed on the hinged fairing 
assembly of the MLG can withstand the expected environmental 
conditions, therefore the unsafe condition, as initially determined, 
does not exist. The NPRM proposed to remove AD 2017-01-06. We are 
issuing this AD to remove AD 2017-01-06.
    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-CN, dated April 28, 2017 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to cancel EASA AD 2015-0234-CN, which applied to 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 [a] Part Number 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 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, was initially 
assessed as leading 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 
MSN [manufacturer serial number] and issued SB A320-52-1167 to 
provide inspection instructions.
    Consequently, EASA issued AD 2015-0234 [which corresponds to FAA 
AD 2017-01-06], requiring a one-time inspection of the affected MLG 
hinged fairing tie rod assemblies, and, depending on findings, 
replacement of the affected tie rod assembly.
    Since that [EASA] AD was issued, tests performed by the tie rod 
assembly manufacturers determined that the assemblies, even without 
cadmium plating surface treatment on the rod end threads, can 
withstand the expected environmental conditions. The consequence is 
that the unsafe condition, as initially determined, does not exist.
    For the reasons described above, this Notice cancels EASA AD 
2015-0234.

    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-
0690.

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 available 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 Costs of Compliance

    AD 2017-01-06 affected about 20 airplanes of U.S. registry. The 
estimated cost of the actions required by AD 2017-01-06 for U.S. 
operators was $3,400, or $170, per product. Removing AD 2017-01-06 
eliminates those costs.

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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes to 
the Director of the System Oversight Division.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.

[[Page 56169]]

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2017-01-06, Amendment 39-18773 (82 FR 4773, January 17, 2017), and 
adding the following new AD:

2017-24-03 Airbus: Amendment 39-19107; Docket No. FAA-2017-0690; 
Product Identifier 2017-NM-061-AD.

(a) Effective Date

    This rescission is effective January 2, 2018.

(b) Affected AD

    This action removes AD 2017-01-06, Amendment 39-18773 (82 FR 
4773, January 17, 2017).

(c) Applicability

    This action 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) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) AD 2015-0234-CN, dated April 28, 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-2017-0690.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 
425-227-1405; fax 425-227-1149.

(e) Material Incorporated by Reference

    None.

    Issued in Renton, Washington, on November 15, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-25253 Filed 11-27-17; 8:45 am]
 BILLING CODE 4910-13-P