[Federal Register Volume 83, Number 73 (Monday, April 16, 2018)]
[Proposed Rules]
[Pages 16251-16256]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-07656]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0298; Product Identifier 2017-NM-179-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
Airbus Model A318 and A319 series airplanes; Model A320-211, A320-212,
A320-214, A320-216, A320-231, A320-232, and A320-233 airplanes; and
Model A321-111, A321-112, A321-131, A321-211, A321-212, A321-213, A321-
231, and A321-232 airplanes. This proposed AD was prompted by reports
of missing assembly hardware on the trimmable horizontal stabilizer
actuator (THSA). This proposed AD would require repetitive inspections
and checks of the lower and upper THSA attachments and applicable
related investigative and corrective actions; a one-time inspection of
the THSA lower attachment and replacement as applicable; and, for
certain airplanes, activation of the electrical load sensing device
(ELSD) and concurrent modifications. We are proposing this AD to
address the unsafe condition on these products.
DATES: We must receive comments on this proposed AD by May 31, 2018.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For Airbus service information identified in this NPRM, 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.
For United Technologies Corporation Aerospace Systems (UTAS)
service information identified in this AD, contact United Technologies
Corporation Aerospace Systems (UTAS): Goodrich Corporation, Actuation
Systems, Stafford Road, Fordhouses, Wolverhampton WV10 7EH, England;
phone: +44 (0) 1902 624938; fax: +44 (0) 1902 788100; email:
[email protected]; internet: http://www.goodrich.com/TechPubs.
You may view this service information at the FAA, Transport
Standards Branch, 2200 South 216th Street, Des Moines, WA. For
information on the availability of this material at the FAA, call 206-
231-3195.
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-2018-
0298; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this NPRM, the regulatory evaluation, any comments received,
and other information. The street address for the Docket Operations
office (telephone 800-647-5527) is in the ADDRESSES section. Comments
will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 2200 South
216th Street, Des Moines, WA 98198; phone and fax: 206-231-3223.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2018-0298;
Product Identifier 2017-NM-179-AD'' at the beginning of your comments.
We specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this NPRM. We will consider all
comments received by the closing date and may amend this NPRM based on
those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this NPRM.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2017-0237, dated December 4, 2017 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model A318
and A319 series airplanes; Model A320-211, A320-212, A320-214, A320-
216, A320-231, A320-232, A320-233 airplanes; and Model A321-111, A321-
112, A321-131, A321-211, A321-212, A321-213, A321-231, and A321-232
airplanes. The MCAI states:
The Trimmable Horizontal Stabilizer Actuator (THSA) of Airbus
A320 Family aeroplanes has been rig-tested to check secondary load
path behaviour in case of primary load path failure. In that
configuration, the loads are transferred to the secondary load path,
which should jam, preventing any Trimmable Horizontal Stabilizer
motion. The test results showed that the secondary load path did not
jam as expected, preventing detection of the primary load path
failure. To verify the integrity of the THSA primary load path and
the correct installation of the THSA, Airbus issued Service Bulletin
(SB) A320-27-1164, later revised multiple times, and SB A320-
27A1179, and EASA issued AD 2006-0223 [which corresponds to FAA AD
2007-06-02, Amendment 39-14983 (72 FR 12072, March 15, 2007) (``AD
2007-06-02'')], AD 2007-0178 [which corresponds to FAA AD 2008-09-
16, Amendment 39-15497 (73 FR 24160, May 2, 2008)(``AD 2008-09-
16'')], AD 2008-0150, and AD 2014-0147, each AD superseding the
previous one, requiring one-time and repetitive inspections.
Since EASA AD 2014-0147 was issued, Airbus designed a new
device, called Electrical Load Sensing Device (ELSD), to introduce a
new mean of THSA upper secondary load path engagement detection.
Consequently, Airbus issued several SBs (Airbus SB A320-27-1245,
A320-27-1246, and A320-27-1247, depending on aeroplane
configuration) providing instructions to install the wiring
provision for ELSD installation and to install ELSD on the THSA, and
SB A320-27-1248, providing instructions to activate the ELSD. Airbus
also revised SB A320-27-1164, now at Revision 13, including
instructions applicable for aircraft equipped with ELSD.
Furthermore, following a visual inspection of the THSA, an
operator reported that the THSA was found with a bush missing,
inducing torqueing of the THSA lower attachment primary bolt against
the THSA lug, which resulted in the application of a transverse
force on the lug.
[[Page 16252]]
Prompted by several other identical findings, Airbus released
Alert Operator Transmission (AOT) A27N010-17 to provide instructions
for inspection and associated corrective actions.
For the reasons described above, this AD retains the
requirements of EASA AD 2014-0147, which is superseded, and requires
installation of ELSD on the THSA, ELSD activation, and a one-time
inspection to verify the bush presence on the THSA lower attachment.
The unsafe condition is uncontrolled movement of the horizontal
stabilizer as a result of the latent (undetected) failure of the THSA's
primary load path and consequent loss of control of the airplane.
The required actions include repetitive inspections and checks of
the lower and upper THSA attachments and applicable related
investigative and corrective actions; a one-time inspection of the THSA
lower attachment and replacement as applicable; and, for certain
airplanes, activation of the ELSD and concurrent modifications.
Related investigative actions include an inspection of the upper
THSA attachment, an inspection of the lower attachment, and a check of
the upper and lower clearance between the secondary nut trunnion and
the junction plate. Corrective actions include replacement of the THSA
and repair.
You may examine the MCAI in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0298.
Relationship Between Proposed AD and AD 2007-06-02 and AD 2008-09-16
Accomplishment of the certain proposed actions would terminate all
requirements of AD 2007-06-02 and AD 2008-09-16.
Related Service Information Under 1 CFR Part 51
Airbus has issued Alert Operators Transmission (AOT) A27N010-17,
Revision 01, dated October 17, 2017, including AOT Appendix_A27N010-17.
This service information describes the procedure for a one-time general
visual inspection of the THSA lower attachment to measure the gap
between the THSA lower attachment tab washer and attachment plates and
replacement of the THSA lower attachment if the measured gap is less
than 0.5 mm. The replacement includes doing an inspection of the THSA
parts to confirm the bushing is missing and applicable corrective
actions (i.e., repair).
Airbus has issued Service Bulletin A320-27-1164, Revision 13, dated
August 8, 2016. This service information describes procedures for a
general visual inspection of the upper THSA attachments for correct
installation, cracks, damage and metallic particles; a general visual
inspection of the upper attachment for correct installation; a check of
the clearance between secondary nut trunnions and junction plates and
correct installation of the lower THSA attachment; a general visual
inspection of the THSA ball screw to check for the absence of dents;
and applicable related investigative and corrective actions.
Airbus has issued Service Bulletin A320-27-1245, Revision 00, dated
March 6, 2017. This service information describes the procedure to
modify the wiring provisions for the ELSD.
Airbus has issued Service Bulletin A320-27-1246, Revision 01, dated
November 4, 2016. This service information describes the procedures to
adapt the wiring provision of the ELSD and THSA to accommodate the
correct installation of the ELSD.
Airbus has issued Service Bulletin A320-27-1247, Revision 00, dated
March 6, 2017. This service information describes the procedure to
modify the upper attachment secondary load path of the THSA to
accommodate the correct installation of the ELSD.
Airbus has issued Service Bulletin A320-27-1248, Revision 00, dated
March 6, 2017. This service information describes the procedure to
activate the ELSD.
UTAS has issued United Technologies Corporation (UTC) Aerospace
Systems Repair Instructions RF-DSC-1361-17, Version 00, including
Appendix A, dated May 24, 2017. This service information describes
repair instructions to follow if the bushing is missing as specified in
AOT A27N010-17, Revision 01, dated October 17, 2017.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of these
same type designs.
Costs of Compliance
We estimate that this proposed AD affects 1,180 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspections, Check, Up to 59 work-hours x $85 Up to $15,353... Up to $20,368... Up to
Activation, and Modifications. per hour = $5,015. $24,034,240.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacements
that would be required based on the results of the proposed
inspections. We have no way of determining the number of aircraft that
might need this replacement:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Replacement............................. 11 work-hours x $85 per hour = $240,000 $240,935
$935.
----------------------------------------------------------------------------------------------------------------
[[Page 16253]]
We have received no definitive data that would enable us to provide
cost estimates for the on-condition repairs specified in this proposed
AD.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this NPRM is 2120-
0056. The paperwork cost associated with this NPRM has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this NPRM is mandatory. Comments concerning the accuracy of this burden
and suggestions for reducing the burden should be directed to the FAA
at 800 Independence Ave. SW, Washington, DC 20591, ATTN: Information
Collection Clearance Officer, AES-200.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
This proposed 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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
regulation:
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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
Airbus: Docket No. FAA-2018-0298; Product Identifier 2017-NM-179-AD.
(a) Comments Due Date
We must receive comments by May 31, 2018.
(b) Affected ADs
This AD affects AD 2007-06-02, Amendment 39-14983 (72 FR 12072,
March 15, 2007) (``AD 2007-06-02'') and AD 2008-09-16, Amendment 39-
15497 (73 FR 24160, May 2, 2008) (``AD 2008-09-16'').
(c) Applicability
This AD applies to Airbus Model A318-111, A318-112, A318-121,
and A318-122 airplanes; Model A319-111, A319-112, A319-113, A319-
114, A319-115, A319-131, A319-132, and A319-133 airplanes; Model
A320-211, A320-212, A320-214, A320-216, A320-231, A320-232, and
A320-233 airplanes; and Model A321-111, A321-112, A321-131, A321-
211, A321-212, A321-213, A321-231, and A321-232 airplanes;
certificated in any category, all manufacturer serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
controls.
(e) Reason
This AD was prompted by reports of missing assembly hardware on
the trimmable horizontal stabilizer actuator (THSA). We are issuing
this AD to address uncontrolled movement of the horizontal
stabilizer as a result of the latent (undetected) failure of the
THSA's primary load path and consequent loss of control of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Actions: Lower THSA Attachment
Before exceeding 20 months since airplane first flight, or since
airplane first flight following last THSA replacement, or within 20
months after the last inspection of the lower THSA attachment as
specified in the instructions of Airbus Service Bulletin A320-27-
1164, Revision 02 up to Revision 09, whichever occurs latest, do the
actions specified in paragraphs (g)(1), (g)(2), and (g)(3) of this
AD concurrently, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A320-27-1164, Revision 13, dated August
8, 2016, Repeat the actions thereafter at intervals not to exceed 20
months.
(1) Check the clearance between the secondary nut trunnions and
the junction plates at the lower THSA attachment.
(2) Do a general visual inspection of the lower THSA attachment
for correct installation of attachment parts.
(3) Do a general visual inspection of the ball screw for dents.
(h) Repetitive Inspections: Upper THSA Attachment
Before exceeding 10 months since airplane first flight, or since
airplane first flight following last THSA replacement, or within 10
months after the last inspection of the upper THSA attachment as
specified in the instructions of Airbus Service Bulletin A320-27-
1164, Revision 02 up to Revision 09, whichever occurs latest, do the
actions specified in paragraphs (h)(1) and (h)(2) of this AD
concurrently, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-27-1164, Revision 13, dated August 8,
2016. Repeat the inspections thereafter at intervals not to exceed
10 months.
(1) Do a general visual inspection of the upper THSA attachment
for correct installation, cracks, damage, and metallic particles.
(2) Do a general visual inspection of the upper attachment for
correct installation of attachment parts.
[[Page 16254]]
(i) Related Investigative and Corrective Actions
If, during any action required by paragraph (g) or (h) of this
AD, any discrepancy is detected (e.g., any installation deviation,
cracking, damage, metallic particle, or dent is found), before
further flight, accomplish all applicable related investigative and
corrective actions in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-27-1164, Revision 13,
dated August 8, 2016; except as required by paragraph (o)(1) of this
AD.
(j) Reporting Requirements for Actions Required by Paragraphs (g) and
(h) of This AD
In case of any findings during any action required by paragraph
(g) or (h) of this AD, report the inspection results to Airbus using
the applicable ``Inspection Reporting Sheet'' of Airbus Service
Bulletin A320-27-1164, Revision 13, dated August 8, 2016, at the
applicable time specified in paragraph (j)(1) or (j)(2) of this AD.
If operators have reported findings as part of obtaining any
corrective actions approved by the EASA Design Organization Approval
(DOA), operators are not required to report those findings as
specified in this paragraph.
(1) If the inspection or check was done on or after the
effective date of this AD: Submit the report within 30 days after
the inspection.
(2) If the inspection or check was done before the effective
date of this AD: Submit the report within 30 days after the
effective date of this AD.
(k) One-Time Inspection and Replacement
For airplanes on which the THSA has been replaced or reinstalled
since the date of issuance of the original certificate of
airworthiness or the date of issuance of the original export
certificate of airworthiness: Within 6 months after the effective
date of this AD, accomplish a detailed inspection of the THSA lower
attachment gap clearances, in accordance with the instructions of
Airbus Alert Operators Transmission (AOT) A27N010-17, Revision 01,
dated October 17, 2017, including AOT Appendix_A27N010-17. If the
measured gap is less than 0.5 mm, before further flight, replace the
THSA, including doing an inspection of the THSA parts to confirm the
bushing is missing and applicable corrective actions, in accordance
with the instructions of Airbus AOT A27N010-17, Revision 01, dated
October 17, 2017, including AOT Appendix_A27N010-17; and United
Technologies Corporation (UTC) Aerospace Systems Repair Instructions
RF-DSC-1361-17, Version 00, including Appendix A, dated May 24,
2017, as applicable, except as required by paragraph (o)(2) of this
AD.
(l) Definition of Groups
For the purpose of this AD: Group 1 airplanes are those that, on
the effective date of this AD, do not have the electrical load
sensing device (ELSD) activated. Group 2 airplanes are those that,
on the effective date of this AD, have the ELSD activated.
(m) Activation and Concurrent Modification
For Group 1 airplanes (see paragraph (l) of this AD): Do the
actions specified in paragraphs (m)(1) and (m)(2) of this AD.
(1) Within 4 years after the effective date of this AD, activate
the ELSD of the THSA on the airplane, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-27-1248,
Revision 00, dated March 6, 2017.
(2) Concurrently with or before the activation of the ELSD
required by paragraph (m)(1) of this AD, modify the airplane, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-27-1245, Revision 00, dated March 6, 2017; or Airbus
Service Bulletin A320-27-1246, Revision 01, dated November 4, 2016;
as applicable.
(n) Concurrent Requirement for Airplanes Equipped With THSAs That Do
Not Have ELSDs
For an airplane equipped with a THSA having a part number listed
in Figure 1 to paragraphs (n), (p), and (q) of this AD: Concurrently
with or before the activation required by paragraph (m)(1) of this
AD, modify the airplane, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-27-1247, Revision 00,
dated March 6, 2017.
[[Page 16255]]
[GRAPHIC] [TIFF OMITTED] TP16AP18.025
(o) Exceptions to Service Information
(1) Where Airbus Service Bulletin A320-27-1164, Revision 13,
dated August 8, 2016, specifies to contact Airbus for appropriate
action, and specifies that action as ``RC'' (Required for
Compliance): Before further flight, accomplish corrective actions in
accordance with the procedures specified in paragraph (v)(2) of this
AD.
(2) Where Airbus AOT A27N010-17, Revision 01, dated October 17,
2017, specifies to contact Airbus for appropriate action: Before
further flight, accomplish corrective actions in accordance with the
procedures specified in paragraph (v)(2) of this AD.
(p) Parts Installation
Do not install on any airplane a THSA with a part number listed
in Figure 1 to paragraphs (n), (p), and (q) of this AD and do not
deactivate the ELSD at the times specified in paragraph (p)(1) or
(p)(2) of this AD, as applicable.
(1) Group 1 airplanes (see paragraph (l) of this AD): After
modification of the airplane as required by paragraph (m)(1) of this
AD.
(2) Group 2 airplanes (see paragraph (l) of this AD): From the
effective date of this AD.
(q) Method of Compliance
An airplane on which Airbus modification 155955 has been
embodied in production is considered compliant with paragraphs
(m)(1), (m)(2), and (n) of this AD, provided that it is determined
that no THSA with a part number listed in Figure 1 to paragraphs
(n), (p), and (q) of this AD is installed on that airplane, and that
the ELSD remains activated. A review of airplane maintenance records
is acceptable to make this determination, provided those records can
be relied upon for that purpose.
(r) Airplanes Not Affected by the Requirements of Paragraph (k) of This
AD
The inspection required by paragraph (k) of this AD is not
required for airplanes on which the THSA has been installed as
specified in the instructions of Airbus A320 Airplane Maintenance
Manual (AMM) 27-44-51-400-001, dated May 2017, or subsequent.
(s) Credit for Previous Actions
(1) This paragraph provides credit for initial actions required
by paragraphs (g), (h), (i), and (j) of this AD, if those actions
were performed before the effective date of this AD using the Airbus
Service Bulletin A320-27-1164, Revision 10, dated March 2017, 2014;
Revision 11, dated December 15, 2014; or Revision 12, dated March
23, 2016.
(2) This paragraph provides credit for actions required by
paragraph (k) of this AD, if those actions were performed before the
effective date of this AD using Airbus AOT A27N010-17, dated March
27, 2017.
(3) This paragraph provides credit for actions required by
paragraph (m)(2) of this AD, if those actions were performed before
the effective date of this AD using Airbus Service Bulletin A320-27-
1246, dated March 20, 2015.
(t) No Terminating Action for Repetitive Inspections in This AD
Accomplishment on an airplane of the one-time inspection and
replacement, as applicable, specified in paragraph (k) of this AD
and the modifications specified in paragraphs (m)(1), (m)(2), and
(n) of this AD,
[[Page 16256]]
as applicable, do not constitute terminating action for the
repetitive inspections required by paragraphs (g) and (h) of this AD
for that airplane.
(u) Terminating Action for Other FAA ADs
Accomplishing the initial actions required by paragraphs (g) and
(h) of this AD, and accomplishing the applicable actions required by
paragraphs (i) and (j) of this AD, terminates all requirements of AD
2007-06-02 and AD 2008-09-16.
(v) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Section, Transport Standards Branch, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Section, send it to the attention of
the person identified in paragraph (x)(2) of this AD. Information
may be emailed to: [email protected]. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Section, Transport Standards Branch, FAA; or the European Aviation
Safety Agency (EASA); or Airbus's EASA DOA. If approved by the DOA,
the approval must include the DOA-authorized signature.
(3) Paperwork Reduction Act Burden Statement: A federal agency
may not conduct or sponsor, and a person is not required to respond
to, nor shall a person be subject to a penalty for failure to comply
with a collection of information subject to the requirements of the
Paperwork Reduction Act unless that collection of information
displays a current valid OMB Control Number. The OMB Control Number
for this information collection is 2120-0056. Public reporting for
this collection of information is estimated to be approximately 1
hour per response, including the time for reviewing instructions,
completing and reviewing the collection of information. All
responses to this collection of information are mandatory. Comments
concerning the accuracy of this burden and suggestions for reducing
the burden should be directed to the FAA at: 800 Independence Ave.
SW, Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.
(4) Required for Compliance (RC): Except as specified in
paragraph in (o)(1) of this AD, if any service information contains
procedures or tests that are identified as RC, those procedures and
tests must be done to comply with this AD; any procedures or tests
that are not identified as RC are recommended. Those procedures and
tests that are not identified as RC may be deviated from using
accepted methods in accordance with the operator's maintenance or
inspection program without obtaining approval of an AMOC, provided
the procedures and tests identified as RC can be done and the
airplane can be put back in an airworthy condition. Any
substitutions or changes to procedures or tests identified as RC
require approval of an AMOC.
(w) Special Flight Permits
Special flight permits, as described in Section 21.197 and
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.
(x) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2017-0237, dated December 4,
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-2018-0298.
(2) For more information about this AD, contact Sanjay Ralhan,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone
and fax: 206-231-3223.
(3) For Airbus service information identified in this AD,
contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 44 51; email [email protected];
internet http://www.airbus.com.
(4) For UTAS service information identified in this AD, contact
United Technologies Corporation Aerospace Systems (UTAS): Goodrich
Corporation, Actuation Systems, Stafford Road, Fordhouses,
Wolverhampton WV10 7EH, England; phone: +44 (0) 1902 624938; fax:
+44 (0) 1902 788100; email: [email protected];
internet: http://www.goodrich.com/TechPubs.
(5) You may view this service information at the FAA, Transport
Standards Branch, 2200 South 216th Street, Des Moines, WA. For
information on the availability of this material at the FAA, call
206-231-3195.
Issued in Des Moines, Washington, on March 30, 2018.
Chris Spangenberg,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-07656 Filed 4-13-18; 8:45 am]
BILLING CODE 4910-13-P