Airworthiness Directives; Airbus Airplanes, 56167-56169 [2017-25253]
Download as PDF
<![CDATA[
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 https://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 https://
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 https://
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 https://
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 https://
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]
-----------------------------------------------------------------------
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
https://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 https://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 https://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 https://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 https://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
