82 FR 56167 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 82, Issue 227 (November 28, 2017)

Page Range		56167-56169
FR Document		2017-25253

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.

Federal Register, Volume 82 Issue 227 (Tuesday, November 28, 2017)

[Federal Register Volume 82, Number 227 (Tuesday, November 28, 2017)]
[Rules and Regulations]
[Pages 56167-56169]
From the Federal Register Online  [www.thefederalregister.org]
[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 [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-
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

Federal Register / Vol. 82, No. 227 / Tuesday, November 28, 2017 / Rules and Regulations 56167

Adoption of the Amendment pressure, using a pushrod tool, apply 140 DEPARTMENT OF TRANSPORTATION
inch-pounds of torque to the jamnut.
Accordingly, under the authority
(2) Apply two slippage marks across each Federal Aviation Administration
delegated to me by the Administrator,
control rod and jamnut as follows:
the FAA amends 14 CFR part 39 as
(i) Clean the area where a slippage mark is 14 CFR Part 39
follows:
to be applied.
[Docket No. FAA–2017–0690; Product
PART 39—AIRWORTHINESS (ii) Apply two slippage marks across the
Identifier 2017–NM–061–AD; Amendment
DIRECTIVES control rod and jamnut, parallel and on 39–19107; AD 2017–24–03]
opposite sides of each other. Each slippage
■ 1. The authority citation for part 39 mark must extend at least 0.5 inch onto the RIN 2120–AA64
continues to read as follows: control rod and must not cover the
inspection hole. Figure 1 (Sheet 2) of Airworthiness Directives; Airbus
Authority: 49 U.S.C. 106(g), 40113, 44701. Airplanes
Sikorsky S–76 Helicopter Alert Service
§ 39.13 [Amended] Bulletin 76–67–58, Basic Issue, dated AGENCY: Federal Aviation
November 19, 2015, illustrates a slippage Administration (FAA), Department of
■ 2. The FAA amends § 39.13 by adding
mark across a control rod and jamnut. Transportation (DOT).
the following new airworthiness
directive (AD): (f) Alternative Methods of Compliance ACTION: Final rule.
2017–19–01 Sikorsky Aircraft Corporation: (AMOCs)
Amendment 39–19031; Docket No.
SUMMARY: We are removing
(1) The Manager, Boston ACO Branch,
FAA–2017–0491; Product Identifier Airworthiness Directive (AD) 2017–01–
FAA, may approve AMOCs for this AD. Send
2016–SW–020–AD. 06, which applied to certain Airbus
your proposal to: Blaine Williams, Aerospace
Engineer, Boston ACO Branch, Compliance
Model A319–115, A319–132, A320–214,
(a) Applicability
and Airworthiness Division, 1200 District
A320–232, A321–211, A321–213, and
This AD applies to Model S–76A, S–76B, A321–231 airplanes. AD 2017–01–06
S–76C, and S–76D helicopters, serial Avenue, Burlington, Massachusetts 01803;
telephone (781) 238–7161; email required inspection and replacement of
numbers up to and including 761075, with a
main rotor (M/R) servo pushrod (pushrod) blaine.williams@faa.gov. certain tie rod assemblies installed on
assembly part number (P/N) 76400–00034– (2) For operations conducted under a 14 the hinged fairing assembly of the main
059, 76400–00014–074, 76400–00014–076, or CFR part 119 operating certificate or under landing gear (MLG). We issued AD
76400–00014–077 installed, certificated in 14 CFR part 91, subpart K, we suggest that 2017–01–06 to detect and correct the
any category. you notify your principal inspector, or absence of cadmium plating on the rod
Note 1 to paragraph (a) of this AD: M/R lacking a principal inspector, the manager of end threads of the tie rod assemblies.
pushrod P/N 76400–00034–059 is included the local flight standards district office or Since we issued AD 2017–01–06, we
in the Applicability section of AD 2015–19– certificate holding district office before have determined that although
51, Amendment 39–18300 (80 FR 65128, cadmium plating might be absent, the
operating any aircraft complying with this
October 26, 2015). This AD does not affect rod end threads of the tie rod assemblies
AD 2015–19–51. AD through an AMOC.
can withstand the expected
(g) Additional Information environmental conditions, therefore the
(b) Unsafe Condition
This AD defines the unsafe condition as a Sikorksy S–76 Helicopter Alert Service unsafe condition, as initially
loose jamnut. This condition could result in Bulletin 76–67–58, Basic Issue, dated determined, does not exist.
failure of a pushrod assembly, loss of M/R November 19, 2015, which is not DATES: This AD is effective January 2,
flight control, and subsequent loss of control incorporated by reference, contains 2018.
of the helicopter. additional information about the subject of
this AD. For service information identified in ADDRESSES: For service information
(c) Effective Date identified in this final rule, contact
this AD, contact Sikorsky Aircraft
This AD becomes effective January 2, 2018. Corporation, Customer Service Engineering, Airbus, Airworthiness Office—EIAS, 1
(d) Compliance 124 Quarry Road, Trumbull, CT 06611; Rond Point Maurice Bellonte, 31707
telephone 1–800-Winged-S or 203–416–4299; Blagnac Cedex, France; telephone +33 5
You are responsible for performing each
action required by this AD within the email: wcs_cust_service_eng.gr-sik@ 61 93 36 96; fax +33 5 61 93 44 51; email
specified compliance time unless it has lmco.com. You may review a copy of this account.airworth-eas@airbus.com;
already been accomplished prior to that time. service information at the FAA, Office of the Internet http://www.airbus.com. You
Regional Counsel, Southwest Region, 10101 may view this referenced service
(e) Required Actions
Hillwood Pkwy, Room 6N–321, Fort Worth, information at the FAA, Transport
Within 300 hours time-in-service: TX 76177. Standards Branch, 1601 Lind Avenue
(1) Inspect the control rod of each pushrod SW., Renton, WA. For information on
assembly (control rod) to determine whether (h) Subject
0.020 inch diameter lockwire can pass
the availability of this material at the
Joint Aircraft Service Component (JASC) FAA, call 425–227–1221. It is also
through the inspection hole.
(i) If the lockwire passes through the Code: 6700, Rotorcraft Flight Control. available on the Internet at http://
inspection hole, before further flight, replace Issued in Fort Worth, Texas, on November www.regulations.gov by searching for
the pushrod assembly. 17, 2017. and locating Docket No. FAA–2017–
(ii) If the lockwire does not pass through 0690.
the inspection hole, inspect the jamnut to Scott A. Horn,
determine whether it is seated against the Deputy Director for Regulatory Operations, Examining the AD Docket
jstallworth on DSKBBY8HB2PROD with RULES

control rod and whether it can be turned Compliance & Airworthiness Division, You may examine the AD docket on
with finger pressure. Aircraft Certification Service.
the Internet at http://
(A) If the jamnut is not seated against the [FR Doc. 2017–25558 Filed 11–27–17; 8:45 am]
control rod or can be turned with finger www.regulations.gov by searching for
pressure, before further flight, replace the
BILLING CODE 4910–13–P and locating Docket No. FAA–2017–
pushrod assembly. 0690; or in person at the Docket
(B) If the jamnut is seated against the Management Facility between 9 a.m.
control rod and cannot be turned with finger and 5 p.m., Monday through Friday,

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56168 Federal Register / Vol. 82, No. 227 / Tuesday, November 28, 2017 / Rules and Regulations

except Federal holidays. The AD docket This condition, if not detected and We are issuing this rulemaking under
contains this AD, the regulatory corrected, was initially assessed as leading to the authority described in ‘‘Subtitle VII,
evaluation, any comments received, and galvanic corrosion of the tie rod end threads, Part A, Subpart III, Section 44701:
other information. The address for the possibly resulting in rod end failure, loss of General requirements.’’ Under that
a MLG door, and consequent injury to
Docket Office (telephone 800–647–5527) persons on ground.
section, Congress charges the FAA with
is Docket Management Facility, U.S. To address this unsafe condition, Airbus promoting safe flight of civil aircraft in
Department of Transportation, Docket identified the affected MSN [manufacturer air commerce by prescribing regulations
Operations, M–30, West Building serial number] and issued SB A320–52–1167 for practices, methods, and procedures
Ground Floor, Room W12–140, 1200 to provide inspection instructions. the Administrator finds necessary for
New Jersey Avenue SE., Washington, Consequently, EASA issued AD 2015–0234 safety in air commerce. This regulation
DC 20590. [which corresponds to FAA AD 2017–01–06], is within the scope of that authority.
requiring a one-time inspection of the
FOR FURTHER INFORMATION CONTACT: affected MLG hinged fairing tie rod
This AD is issued in accordance with
Sanjay Ralhan, Aerospace Engineer, assemblies, and, depending on findings, authority delegated by the Executive
International Section, Transport replacement of the affected tie rod assembly. Director, Aircraft Certification Service,
Standards Branch, FAA, 1601 Lind Since that [EASA] AD was issued, tests as authorized by FAA Order 8000.51C.
Avenue SW., Renton, WA 98057–3356; performed by the tie rod assembly In accordance with that order, issuance
telephone 425–227–1405; fax 425–227– manufacturers determined that the of ADs is normally a function of the
1149. assemblies, even without cadmium plating Compliance and Airworthiness
surface treatment on the rod end threads, can Division, but during this transition
SUPPLEMENTARY INFORMATION: withstand the expected environmental period, the Executive Director has
conditions. The consequence is that the
Discussion unsafe condition, as initially determined,
delegated the authority to issue ADs
does not exist. applicable to transport category
We issued a notice of proposed airplanes to the Director of the System
rulemaking (NPRM) to amend 14 CFR For the reasons described above, this
Notice cancels EASA AD 2015–0234. Oversight Division.
part 39 to remove AD 2017–01–06,
Amendment 39–18773 (82 FR 4773, You may examine the MCAI in the Regulatory Findings
January 17, 2017) (‘‘AD 2017–01–06’’). AD docket on the Internet at http://
We determined that this AD will not
AD 2017–01–06 applied to certain www.regulations.gov by searching for
have federalism implications under
Airbus Model A319–115, A319–132, and locating Docket No. FAA–2017–
Executive Order 13132. This AD will
A320–214, A320–232, A321–211, A321– 0690.
not have a substantial direct effect on
213, and A321–231 airplanes. The Comments the States, on the relationship between
NPRM published in the Federal
We gave the public the opportunity to the national government and the States,
Register on July 17, 2017 (82 FR 32650).
participate in developing this AD. We or on the distribution of power and
The NPRM was prompted by our
received no comments on the NPRM or responsibilities among the various
determination that, although cadmium
on the determination of the cost to the levels of government.
plating might be absent, the rod end
threads of the tie rod assemblies public. For the reasons discussed above, I
installed on the hinged fairing assembly certify that this AD:
Conclusion
of the MLG can withstand the expected 1. Is not a ‘‘significant regulatory
environmental conditions, therefore the We reviewed the available data and action’’ under Executive Order 12866;
unsafe condition, as initially determined that air safety and the 2. Is not a ‘‘significant rule’’ under the
determined, does not exist. The NPRM public interest require adopting this AD DOT Regulatory Policies and Procedures
proposed to remove AD 2017–01–06. as proposed except for minor editorial (44 FR 11034, February 26, 1979);
We are issuing this AD to remove AD changes. We have determined that these 3. Will not affect intrastate aviation in
2017–01–06. minor changes: Alaska; and
• Are consistent with the intent that
The European Aviation Safety Agency 4. Will not have a significant
was proposed in the NPRM for
(EASA) which is the Technical Agent economic impact, positive or negative,
correcting the unsafe condition; and
for the Member States of the European on a substantial number of small entities
• Do not add any additional burden
Union, has issued EASA Airworthiness under the criteria of the Regulatory
upon the public than was already
Directive 2015–0234–CN, dated April Flexibility Act.
proposed in the NPRM.
28, 2017 (referred to after this as the
Mandatory Continuing Airworthiness Related Costs of Compliance List of Subjects in 14 CFR Part 39
Information, or ‘‘the MCAI’’), to cancel AD 2017–01–06 affected about 20 Air transportation, Aircraft, Aviation
EASA AD 2015–0234–CN, which airplanes of U.S. registry. The estimated safety, Incorporation by reference,
applied to certain Airbus Model A319– cost of the actions required by AD 2017– Safety.
115, A319–132, A320–214, A320–232, 01–06 for U.S. operators was $3,400, or
A321–211, A321–213, and A321–231 Adoption of the Amendment
$170, per product. Removing AD 2017–
airplanes. The MCAI states: 01–06 eliminates those costs. Accordingly, under the authority
A production quality issue was identified delegated to me by the Administrator,
concerning tie rod assemblies, having [a] Part Authority for This Rulemaking the FAA amends 14 CFR part 39 as
Number starting with D52840212000 or Title 49 of the United States Code follows:
jstallworth on DSKBBY8HB2PROD with RULES

D52840212002, which are installed on the specifies the FAA’s authority to issue
main landing gear (MLG) hinged fairing rules on aviation safety. Subtitle I, PART 39—AIRWORTHINESS
assembly. This quality issue affects the DIRECTIVES
cadmium plating surface treatment which
section 106, describes the authority of
was inadvertently omitted from the rod end the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more ■ 1. The authority citation for part 39
threads of the assembly. The absence of
cadmium plating reduces the corrosion detail the scope of the Agency’s continues to read as follows:
protection scheme. authority. Authority: 49 U.S.C. 106(g), 40113, 44701.

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Federal Register / Vol. 82, No. 227 / Tuesday, November 28, 2017 / Rules and Regulations 56169

§ 39.13 [Amended] COMMODITY FUTURES TRADING variation margin requirements for
■ 2. The FAA amends § 39.13 by COMMISSION certain swap dealers and major swap
removing Airworthiness Directive (AD) participants. In implementing the
2017–01–06, Amendment 39–18773 (82 17 CFR Part 23 regulations, staff has discovered cross-
FR 4773, January 17, 2017), and adding RIN 3038–AC97 reference errors in § 23.156 of the
the following new AD: regulations. As published, 17 CFR
2017–24–03 Airbus: Amendment 39–19107; Margin Requirements for Uncleared 23.156(a)(3) includes erroneous cross-
Docket No. FAA–2017–0690; Product Swaps for Swap Dealers and Major references to 17 CFR 23.156(a)(1)(iv).
Identifier 2017–NM–061–AD. Swap Participants; Correction Instead, the cross-references should be
(a) Effective Date AGENCY: Commodity Futures Trading to 17 CFR 23.156(a)(1)(v). Accordingly,
This rescission is effective January 2, 2018. Commission. the Commission is making a correcting
amendment to 17 CFR 23.156(a)(3) that
(b) Affected AD ACTION: Correcting amendments.
removes the erroneous cross-references
This action removes AD 2017–01–06, SUMMARY: The Commodity Futures to 17 CFR 23.156(a)(1)(iv) and replaces
Amendment 39–18773 (82 FR 4773, January Trading Commission (CFTC or them with corrected cross-references to
17, 2017).
Commission) is correcting a final rule 17 CFR 23.156(a)(1)(v).
(c) Applicability published in the Federal Register on
January 6, 2016. The rule, concerning List of Subjects in 17 CFR Part 23
This action applies to Airbus Model A319–
115, A319–132, A320–214, A320–232, A321– margin requirements for uncleared Swaps, Swap dealers, Major swap
211, A321–213, and A321–231 airplanes, swaps for swap dealers and major swap
certificated in any category, as identified in participants, Capital and margin
participants, took effect on April 1, requirements.
Airbus Service Bulletin A320–52–1167,
2016. This correction rectifies errors in
dated August 6, 2015.
cross-references in a particular section Accordingly, 17 CFR part 23 is
(d) Related Information of the final rule. corrected by making the following
(1) Refer to Mandatory Continuing DATES: Effective on November 28, 2017. correcting amendments:
Airworthiness Information (MCAI) AD 2015–
FOR FURTHER INFORMATION CONTACT:
0234–CN, dated April 28, 2017, for related PART 23—SWAP DEALERS AND
information. This MCAI may be found in the Thomas Smith, Deputy Director, 202–
MAJOR SWAP PARTICIPANTS
AD docket on the Internet at http:// 418–5495, tsmith@cftc.gov, or Mark
www.regulations.gov by searching for and Bretscher, Attorney-Advisor, 312–596–
locating Docket No. FAA–2017–0690. 0529, mbretscher@cftc.gov, Division of ■ 1. The authority citation for part 23
(2) For more information about this AD, Swap Dealer and Intermediary continues to read as follows:
contact Sanjay Ralhan, Aerospace Engineer, Oversight, Commodity Futures Trading Authority: 7 U.S.C. 1a, 2, 6, 6a, 6b, 6b–1,
International Section, Transport Standards
Commission, Three Lafayette Centre, 6c, 6p, 6r, 6s, 6t, 9, 9a, 12, 12a, 13b, 13c, 16a,
Branch, FAA, 1601 Lind Avenue SW.,
Renton, WA 98057–3356; telephone 425– 1155 21st Street NW., Washington, DC 18, 19, 21.
227–1405; fax 425–227–1149. 20581.
■ 2. In § 23.156, revise paragraph
SUPPLEMENTARY INFORMATION: In the
(e) Material Incorporated by Reference (a)(3)(i)(B) to read as follows:
Federal Register of January 6, 2016 (81
None. FR 636), the CFTC published final rules § 23.156 Forms of margin.
Issued in Renton, Washington, on adopting new regulations to implement
November 15, 2017. a particular provision of the Commodity (a) * * *
Jeffrey E. Duven, Exchange Act (CEA), as added by the (3) * * *
Director, System Oversight Division, Aircraft Dodd-Frank Wall Street Reform and (i) * * *
Certification Service. Consumer Protection Act (Dodd-Frank
[FR Doc. 2017–25253 Filed 11–27–17; 8:45 am] Act).1 This provision requires the (B) The discounts set forth in the
BILLING CODE 4910–13–P Commission to adopt initial and following table:

STANDARDIZED HAIRCUT SCHEDULE
Cash in same currency as swap obligation .......................................................................................................................................................................... 0.0
Eligible government and related debt (e.g., central bank, multilateral development bank, GSE securities identified in paragraph (a)(1)(v) of this sec-
tion): Residual maturity less than one-year ...................................................................................................................................................................... 0.5
Eligible government and related debt (e.g., central bank, multilateral development bank, GSE securities identified in paragraph (a)(1)(v) of this sec-
tion): Residual maturity between one and five years ........................................................................................................................................................ 2.0
Eligible government and related debt (e.g., central bank, multilateral development bank, GSE securities identified in paragraph (a)(1)(v) of this sec-
tion): Residual maturity greater than five years ................................................................................................................................................................ 4.0
Eligible corporate debt (including eligible GSE debt securities not identified in paragraph (a)(1)(v) of this section): Residual maturity less than one-
year .................................................................................................................................................................................................................................... 1.0
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 ........................................................................................................................................................................................................................... 4.0
Eligible corporate debt (including eligible GSE debt securities not identified in paragraph (a)(1)(v) of this section): Residual maturity greater than five
years .................................................................................................................................................................................................................................. 8.0
Equities included in S&P 500 or related index ..................................................................................................................................................................... 15.0
Equities included in S&P 1500 Composite or related index but not S&P 500 or related index .......................................................................................... 25.0
jstallworth on DSKBBY8HB2PROD with RULES

Gold ....................................................................................................................................................................................................................................... 15.0
Additional (additive) haircut on asset in which the currency of the swap obligation differs from that of the collateral asset ............................................. 8.0

1 See Dodd-Frank Wall Street Reform and

Consumer Protection Act, Public Law 111–203, 124
Stat. 1376 (2010).

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Document Created: 2017-11-28 01:50:49
Document Modified: 2017-11-28 01:50:49

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 January 2, 2018.
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.
FR Citation		82 FR 56167
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety

82 FR 56167 - Airworthiness Directives; Airbus Airplanes

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 82, Issue 227 (November 28, 2017)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration