Airworthiness Directives; Airbus SAS Airplanes, 6317-6321 [2019-03256]
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Federal Register / Vol. 84, No. 39 / Wednesday, February 27, 2019 / Rules and Regulations
could result in a hazardous or catastrophic
failure condition.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Revision of Maintenance or Inspection
Program
Within 90 days after the effective date of
this AD, revise the operator’s maintenance or
inspection program, as applicable, to
incorporate the information specified in
Airbus A318/A319/A320/A321
Airworthiness Limitations Section (ALS) Part
3, Certification Maintenance Requirements
(CMR), Revision 06, dated June 13, 2018
(‘‘ALS Part 3, CMR, R6’’). The initial
compliance time for accomplishing the tasks
specified in ALS Part 3, CMR, R6, is at the
applicable time specified in ALS Part 3,
CMR, R6, or within 90 days after the effective
date of this AD, whichever occurs later.
(h) Terminating Actions for AD 2017–25–04
Accomplishing the actions required by
paragraph (g) of this AD terminates all of the
requirements of AD 2017–25–04.
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(i) No Alternative Actions or Intervals
After the operator’s maintenance or
inspection program, as applicable, has been
revised as required by paragraph (g) of this
AD, no alternative actions (e.g., inspections)
or intervals may be used unless the actions
and intervals are approved as an alternative
method of compliance (AMOC) in
accordance with the procedures specified in
paragraph (j)(1) of this AD.
(j) 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 (k)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov.
(i) 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.
(ii) AMOCs approved previously for AD
2017–25–04, or AD 2014–22–08, Amendment
39–18013 (79 FR 67042, November 12, 2014),
that allow incorporation of ALS Part 3, CMR,
R6, are considered approved as AMOCs for
the corresponding provisions of this AD.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Section,
Transport Standards Branch, FAA; or the
European Aviation Safety Agency (EASA); or
Airbus SAS’s EASA Design Organization
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Approval (DOA). If approved by the DOA,
the approval must include the DOAauthorized signature.
(3) Required for Compliance (RC): If any
service information contains procedures or
tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(k) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2018–0180, dated August 27, 2018, 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–2018–0554.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des
Moines, WA 98198; telephone and fax 206–
231–3223.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Airbus A318/A319/A320/A321
Airworthiness Limitations Section (ALS) Part
3, Certification Maintenance Requirements
(CMR), Revision 06, dated June 13, 2018.
(ii) [Reserved]
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EIAS, Rond-Point Emile Dewoitine
No: 2, 31700 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.
(4) You may view this service information
at the FAA, Transport Standards Branch,
2200 South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Des Moines, Washington, on
February 14, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–03268 Filed 2–26–19; 8:45 am]
BILLING CODE 4910–13–P
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6317
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0904; Product
Identifier 2018–NM–108–AD; Amendment
39–19575; AD 2019–03–23]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Airbus SAS Model A330–200, –200
Freighter, and –300 series airplanes, and
Model A340–200, –300, –500, and –600
series airplanes. This AD was prompted
by a report that certain sensor struts, in
the case of down drive element
disconnection, would be unable to
provide failure detection information for
flap movements. This AD requires
repetitive inspections of certain drive
station elements and sensor struts; an
inspection of certain other drive station
elements if necessary; and corrective
actions if necessary. We are issuing this
AD to address the unsafe condition on
these products.
DATES: This AD is effective April 3,
2019.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of April 3, 2019.
ADDRESSES: For service information
identified in this final rule, contact
Airbus SAS, Airworthiness Office—
EAL, Rond-Point Emile Dewoitine No:
2, 31700 Blagnac Cedex, France; phone:
+33 5 61 93 36 96; fax: +33 5 61 93 45
80; email: airworthiness.A330-A340@
airbus.com; internet: https://
www.airbus.com. You may view this
service information at the FAA,
Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available on the internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2018–
0904.
SUMMARY:
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–2018–
0904; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
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Federal Register / Vol. 84, No. 39 / Wednesday, February 27, 2019 / Rules and Regulations
through Friday, except Federal holidays.
The AD docket contains this final rule,
the regulatory evaluation, any
comments received, and other
information. The address for Docket
Operations (phone: 800–647–5527) is
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:
Vladimir Ulyanov, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
phone and fax: 206–231–3229.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Airbus SAS Model A330–
200, –200 Freighter, and –300 series
airplanes, and Model A340–200, –300,
–500, and –600 series airplanes. The
NPRM published in the Federal
Register on November 5, 2018 (83 FR
55303). The NPRM was prompted by a
report that certain sensor struts, in the
case of down drive element
disconnection, would be unable to
provide failure detection information.
The NPRM proposed to require
repetitive inspections of certain drive
station elements and sensor struts; an
inspection of certain other drive station
elements if necessary; and corrective
actions if necessary.
We are issuing this AD to address
abnormal flap movement due to
mechanical drive station element
disconnection at flap track station 4 or
station 5 which could lead to
undetected down drive shaft
disconnection. Such a condition could
result in complete flap disconnection in
the case of additional failure on the
remaining flap drive station, and could
ultimately result in loss of control of the
airplane.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2018–0151,
dated July 16, 2018 (referred to after this
as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for all Airbus SAS Model A330–200
Freighter series, Model A330–200 series,
Model A330–300 series, Model A340–
200 series, Model A340–300 series,
Model A340–500 series, and Model
A340–600 series airplanes. The MCAI
states:
Design features of the track station 4 sensor
struts, respectively installed on the right
hand (RH) and left hand (LH) wings of an
aeroplane, ensure detection of any abnormal
flap movement in case of a mechanical DSE
[drive station element] disconnection at the
level of the flap track station 4 or flap track
station 5. Evidence was collected revealing
that the track station 4 sensor strut, in case
of a down drive element disconnection,
would be unable to provide failure detection
information.
This condition, if not detected and
corrected, in the case of an additional failure
on the remaining flap drive station, could
lead to a complete flap disconnection,
possibly resulting in loss of control of the
aeroplane.
To address this potential unsafe condition,
Airbus published the applicable SB [Airbus
Service Bulletin A330–27–3226, dated April
5, 2018; Airbus Service Bulletin A340–27–
4206, dated April 3, 2018; or Airbus Service
Bulletin A340–27–5071, dated April 3, 2018;
as applicable] to provide inspection
instructions of the track station 4 and track
station 5 DSE and sensor struts of the LH and
RH wings.
For the reasons described above, this
[EASA] AD requires repetitive [detailed]
inspections of the LH and RH track station
4 [DSE, repetitive general visual inspections
of the LH and RH track station 4 sensor
struts,] and [for certain airplanes, a one-time
detailed inspection of the LH or RH, as
applicable] track station 5 DSE * * * and,
depending on findings, accomplishment of
applicable corrective action(s).
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–2018–
0904.
Comments
We gave the public the opportunity to
participate in developing this final rule.
We received no comments on the NPRM
or on the determination of the cost to
the public.
Conclusion
We reviewed the relevant data and
determined that air safety and the
public interest require adopting this
final rule 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
addressing the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information.
• Airbus Service Bulletin A330–27–
3226, dated April 5, 2018.
• Airbus Service Bulletin A340–27–
4206, dated April 3, 2018.
• Airbus Service Bulletin A340–27–
5071, dated April 3, 2018.
This service information describes
procedures for repetitive detailed
inspections of the LH and RH track
station 4 drive station elements;
repetitive general visual inspections of
the LH and RH track station 4 sensor
struts; a detailed inspection of the track
station 5 drive station elements if any
discrepancy is found during a general
visual inspection; and corrective actions
(i.e., replacement of affected parts).
These documents are distinct since they
apply to different models. This service
information is reasonably available
because the interested parties have
access to it through their normal course
of business or by the means identified
in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 105
airplanes of U.S. registry. We estimate
the following costs to comply with this
AD:
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ESTIMATED COSTS FOR REQUIRED ACTIONS *
Labor cost
Parts cost
Cost per product
Up to 7 work-hours × $85 per hour = $595 ............................................
$0
Up to $595 ......................................
Cost on
U.S. operators
Up to $62,475.
* Table does not include estimated costs for reporting.
We estimate that it would take about
1 work-hour per product to comply with
the reporting requirement in this AD.
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The average labor rate is $85 per hour.
Based on these figures, we estimate the
cost of reporting the inspection results
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on U.S. operators to be $8,925, or $85
per product.
We have received no definitive data
that would enable us to provide cost
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Federal Register / Vol. 84, No. 39 / Wednesday, February 27, 2019 / Rules and Regulations
estimates for the on-condition actions
specified in this AD.
According to the manufacturer, some
or all of the costs of this AD may be
covered under warranty, thereby
reducing the cost impact on affected
individuals. We do not control warranty
coverage for affected individuals. As a
result, we have included all known
costs in our cost estimate.
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 and associated appliances to
the Director of the System Oversight
Division.
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 AD is 2120–0056. The
paperwork cost associated with this AD
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 AD 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.
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.
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 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
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Regulatory Findings
6319
(c) Applicability
This AD applies to the Airbus SAS
airplanes identified in paragraphs (c)(1)
through (c)(7) of this AD, certificated in any
category, all manufacturer serial numbers.
(1) Model A330–223F and –243F airplanes.
(2) Model A330–201, –202, –203, –223, and
–243 airplanes.
(3) Model A330–301, –302, –303, –321,
–322, –323, –341, –342, and –343 airplanes.
(4) Model A340–211, –212, and –213
airplanes.
(5) Model A340–311, –312, and –313
airplanes.
(6) Model A340–541 airplanes.
(7) Model A340–642 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight controls.
(e) Reason
This AD was prompted by a report that the
right-hand (RH) and left-hand (LH) track
station 4 sensor struts, in the case of down
drive element disconnection, would be
unable to provide failure detection
information for flap movements. We are
issuing this AD to address abnormal flap
movement due to mechanical drive station
element disconnection at flap track station 4
or station 5 which could lead to undetected
down drive shaft disconnection. Such a
condition could result in complete flap
disconnection in the case of additional
failure on the remaining flap drive station,
and could ultimately result in loss of control
of the airplane.
List of Subjects in 14 CFR Part 39
(f) Compliance
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Comply with this AD within the
compliance times specified, unless already
done.
Adoption of the Amendment
(g) Definitions
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
(h) Detailed and General Visual Inspections
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):
■
2019–03–23 Airbus SAS: Amendment 39–
19575; Docket No. FAA–2018–0904;
Product Identifier 2018–NM–108–AD.
(a) Effective Date
This AD is effective April 3, 2019.
(b) Affected ADs
None.
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For the purpose of this AD, the drive
station elements are defined as the down
drive, down drive shaft, geared rotary
actuator (gearbox), geared rotary actuator
(output lever and fork end), and drive strut.
(1) At the applicable times specified in
paragraphs (h)(1)(i) and (h)(1)(ii) of this AD,
and thereafter not to exceed the applicable
intervals specified in table 1 to paragraph
(h)(1) of this AD, do a detailed inspection of
the LH and RH track station 4 drive station
elements for corrosion or ruptured, loose, or
missing components (including any attached
bolts and nuts that are loose, broken, or
missing) and a general visual inspection of
the LH and RH track station 4 sensor struts
for corrosion or ruptured, loose, or missing
components (including any attached bolts
that are loose, broken, or missing), in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330–
27–3226, dated April 5, 2018; Airbus Service
Bulletin A340–27–4206, dated April 3, 2018;
or Airbus Service Bulletin A340–27–5071,
dated April 3, 2018; as applicable.
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(i) For airplanes that, as of the effective
date of this AD, have accumulated less than
1,000 flight cycles since first flight: Before
exceeding 24 months since first flight or
within 18 months after the effective date of
this AD, whichever occurs later, but without
exceeding 2,300 flight cycles since first flight.
(ii) For airplanes that, as of the effective
date of this AD, have accumulated 1,000 or
more flight cycles since first flight: Within
1,000 flight cycles or 12 months, whichever
occurs first after the effective date of this AD.
(2) If, during any general visual inspection
required by paragraph (h)(1) of this AD, any
corrosion is detected or any ruptured, loose,
or missing components (including any
attached bolts that are loose, broken, or
missing) are detected, before further flight,
accomplish a detailed inspection of the
applicable LH or RH track station 5 drive
station elements for corrosion or ruptured,
loose, or missing components (including any
attached bolts and nuts that are loose,
broken, or missing) in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–27–3226, dated April
5, 2018; Airbus Service Bulletin A340–27–
4206, dated April 3, 2018; or Airbus Service
Bulletin A340–27–5071, dated April 3, 2018;
as applicable.
(i) Corrective Actions
(1) If, during any detailed inspection
required by paragraph (h)(1) of this AD, any
corrosion is detected or any ruptured, loose,
or missing components (including any
attached bolts and nuts that are loose,
broken, or missing) are detected, before
further flight, replace each affected part with
a serviceable part in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–27–3226, dated April
5, 2018; Airbus Service Bulletin A340–27–
4206, dated April 3, 2018; or Airbus Service
Bulletin A340–27–5071, dated April 3, 2018;
as applicable, or using a method approved by
the Manager, International Section, Transport
Standards Branch, FAA; or the European
Aviation Safety Agency (EASA); or Airbus
SAS’s EASA Design Organization Approval
(DOA). If approved by the DOA, the approval
must include the DOA-authorized signature.
(2) If, during any general visual inspection
required by paragraph (h)(1) of this AD, any
corrosion is detected or any ruptured, loose,
or missing components (including any
attached bolts that are loose, broken, or
missing) are detected, before further flight,
replace each affected part with a serviceable
part in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330–
27–3226, dated April 5, 2018; Airbus Service
Bulletin A340–27–4206, dated April 3, 2018;
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or Airbus Service Bulletin A340–27–5071,
dated April 3, 2018; as applicable, or using
a method approved by the Manager,
International Section, Transport Standards
Branch, FAA; or EASA; or Airbus SAS’s
EASA DOA. If approved by the DOA, the
approval must include the DOA-authorized
signature.
(3) If, during any detailed inspection
required by paragraph (h)(2) of this AD, any
corrosion is detected or any ruptured, loose,
or missing components (including any
attached bolts and nuts that are loose,
broken, or missing) are detected, before
further flight, replace each affected part with
a serviceable part in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A330–27–3226, dated April
5, 2018; Airbus Service Bulletin A340–27–
4206, dated April 3, 2018; or Airbus Service
Bulletin A340–27–5071, dated April 3, 2018;
as applicable, or using a method approved by
the Manager, International Section, Transport
Standards Branch, FAA; or EASA; or Airbus
SAS’s EASA DOA. If approved by the DOA,
the approval must include the DOAauthorized signature.
(j) Reporting
At the applicable time specified in
paragraph (j)(1) or (j)(2) of this AD: Report the
results (positive or negative) of each
inspection required by paragraphs (h)(1) and
(h)(2) of this AD to Airbus Service Bulletin
Reporting Online Application on Airbus
World (https://w3.airbus.com/), or submit the
results to Airbus in accordance with the
instructions of Airbus Service Bulletin A330–
27–3226, dated April 5, 2018; Airbus Service
Bulletin A340–27–4206, dated April 3, 2018;
or Airbus Service Bulletin A340–27–5071,
dated April 3, 2018.
(1) If the inspection was done on or after
the effective date of this AD: Submit the
report within 90 days after the inspection.
(2) If the inspection was done before the
effective date of this AD: Submit the report
within 90 days after the effective date of this
AD.
(k) 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
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to the attention of the person identified in
paragraph (l)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. 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 using
a method approved by the Manager,
International Section, Transport Standards
Branch, FAA; or EASA; or Airbus SAS’s
EASA DOA. If approved by the DOA, the
approval must include the DOA-authorized
signature.
(3) Required for Compliance (RC): If any
service information contains procedures or
tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(4) Reporting Requirements: 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.
E:\FR\FM\27FER1.SGM
27FER1
ER27FE19.000</GPH>
6320
Federal Register / Vol. 84, No. 39 / Wednesday, February 27, 2019 / Rules and Regulations
(l) Related Information
DEPARTMENT OF TRANSPORTATION
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2018–0151, dated July 16, 2018, 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–2018–0904.
(2) For more information about this AD,
contact Vladimir Ulyanov, Aerospace
Engineer, International Section, Transport
Standards Branch, FAA, 2200 South 216th
St., Des Moines, WA 98198; phone and fax:
206–231–3229.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A330–27–3226,
dated April 5, 2018.
(ii) Airbus Service Bulletin A340–27–4206,
dated April 3, 2018.
(iii) Airbus Service Bulletin A340–27–
5071, dated April 3, 2018.
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAL, Rond-Point Emile Dewoitine
No: 2, 31700 Blagnac Cedex, France; phone:
+33 5 61 93 36 96; fax: +33 5 61 93 45 80;
email: airworthiness.A330–A340@
airbus.com; internet: https://www.airbus.com.
(4) You may view this service information
at the FAA, Transport Standards Branch,
2200 South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Des Moines, Washington, on
February 14, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–03256 Filed 2–26–19; 8:45 am]
BILLING CODE 4910–13–P
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–1003; Product
Identifier 2018–NM–133–AD; Amendment
39–19567; AD 2019–03–15]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Airbus SAS Model A330–201, –202, and
–203 airplanes, and Model A330–301,
–302, and –303 airplanes. This AD was
prompted by reports of damaged drain
pipes located above the lower aft pylon
fairing (LAPF), caused by a contact
between the drain pipe and the two ushape ribs of the LAPF. This AD
requires a special detailed inspection for
damage, and corrective actions if
necessary. We are issuing this AD to
address the unsafe condition on these
products.
SUMMARY:
This AD is effective April 3,
2019.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of April 3, 2019.
ADDRESSES: For service information
identified in this final rule, contact
Airbus SAS, Airworthiness Office—
EAL, Rond-Point Emile Dewoitine No:
2, 31700 Blagnac Cedex, France; phone:
+33 5 61 93 36 96; fax: +33 5 61 93 45
80; email: airworthiness.A330-A340@
airbus.com; internet: https://
www.airbus.com. You may view this
service information at the FAA,
Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available on the internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2018–
1003.
DATES:
amozie on DSK3GDR082PROD with RULES
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–2018–
1003; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this final rule,
the regulatory evaluation, any
VerDate Sep<11>2014
16:10 Feb 26, 2019
Jkt 247001
PO 00000
Frm 00009
Fmt 4700
Sfmt 4700
6321
comments received, and other
information. The address for Docket
Operations (phone: 800–647–5527) is
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:
Vladimir Ulyanov, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
phone and fax: 206–231–3229.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Airbus SAS Model
A330–201, –202, and –203 airplanes,
and Model A330–301, –302, and –303
airplanes. The NPRM published in the
Federal Register on December 6, 2018
(83 FR 62738). The NPRM was
prompted by reports of damaged drain
pipes located above the LAPF, caused
by a contact between the drain pipe and
the two u-shape ribs of the LAPF. The
NPRM proposed to require a special
detailed inspection for damage, and
corrective actions if necessary.
We are issuing this AD to address
damaged drain pipes located above the
LAPF, which, combined with an
additional independent failure, could
lead to hydraulic leakage in the LAPF
box, possibly resulting in a temporary
uncontrolled fire and consequent
reduced control of the airplane.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2018–0198,
dated September 6, 2018 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Airbus SAS Model A330–
201, –202, and –203 airplanes, and
Model A330–301, –302, and –303
airplanes. The MCAI states:
Some cases of damaged drain pipes, Part
Number F7173000700000, located above the
Lower Aft Pylon Fairing (LAPF) and
dedicated to drain pylon compartment A in
case of hydraulic fluid leakage, were
reported. Subsequent examination identified
that the cracks were caused by a contact
between the drain pipe and the two U-Shape
Ribs of the LAPF. This interference condition
can be present during the installation of the
LAPF assembly to the pylon. The trailing
edge assembly of the fairing has an internal
frame bracket and shear clip which can cause
chafing with the hydraulic drain pipes.
This condition, if not detected and
corrected, combined with an additional
independent failure as hydraulic leakage in
E:\FR\FM\27FER1.SGM
27FER1
]]>Agencies
[Federal Register Volume 84, Number 39 (Wednesday, February 27, 2019)]
[Rules and Regulations]
[Pages 6317-6321]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-03256]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0904; Product Identifier 2018-NM-108-AD; Amendment
39-19575; AD 2019-03-23]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
Airbus SAS Model A330-200, -200 Freighter, and -300 series airplanes,
and Model A340-200, -300, -500, and -600 series airplanes. This AD was
prompted by a report that certain sensor struts, in the case of down
drive element disconnection, would be unable to provide failure
detection information for flap movements. This AD requires repetitive
inspections of certain drive station elements and sensor struts; an
inspection of certain other drive station elements if necessary; and
corrective actions if necessary. We are issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective April 3, 2019.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of April 3,
2019.
ADDRESSES: For service information identified in this final rule,
contact Airbus SAS, Airworthiness Office--EAL, Rond-Point Emile
Dewoitine No: 2, 31700 Blagnac Cedex, France; phone: +33 5 61 93 36 96;
fax: +33 5 61 93 45 80; email: airworthiness.A330-A340@airbus.com;
internet: https://www.airbus.com. You may view this service information
at the FAA, Transport Standards Branch, 2200 South 216th St., Des
Moines, WA. For information on the availability of this material at the
FAA, call 206-231-3195. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0904.
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-2018-
0904; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday
[[Page 6318]]
through Friday, except Federal holidays. The AD docket contains this
final rule, the regulatory evaluation, any comments received, and other
information. The address for Docket Operations (phone: 800-647-5527) is
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: Vladimir Ulyanov, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; phone and fax: 206-231-3229.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to all Airbus SAS Model A330-
200, -200 Freighter, and -300 series airplanes, and Model A340-200, -
300, -500, and -600 series airplanes. The NPRM published in the Federal
Register on November 5, 2018 (83 FR 55303). The NPRM was prompted by a
report that certain sensor struts, in the case of down drive element
disconnection, would be unable to provide failure detection
information. The NPRM proposed to require repetitive inspections of
certain drive station elements and sensor struts; an inspection of
certain other drive station elements if necessary; and corrective
actions if necessary.
We are issuing this AD to address abnormal flap movement due to
mechanical drive station element disconnection at flap track station 4
or station 5 which could lead to undetected down drive shaft
disconnection. Such a condition could result in complete flap
disconnection in the case of additional failure on the remaining flap
drive station, and could ultimately result in loss of control of the
airplane.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2018-0151, dated July 16, 2018 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition for all Airbus SAS Model A330-200 Freighter series,
Model A330-200 series, Model A330-300 series, Model A340-200 series,
Model A340-300 series, Model A340-500 series, and Model A340-600 series
airplanes. The MCAI states:
Design features of the track station 4 sensor struts,
respectively installed on the right hand (RH) and left hand (LH)
wings of an aeroplane, ensure detection of any abnormal flap
movement in case of a mechanical DSE [drive station element]
disconnection at the level of the flap track station 4 or flap track
station 5. Evidence was collected revealing that the track station 4
sensor strut, in case of a down drive element disconnection, would
be unable to provide failure detection information.
This condition, if not detected and corrected, in the case of an
additional failure on the remaining flap drive station, could lead
to a complete flap disconnection, possibly resulting in loss of
control of the aeroplane.
To address this potential unsafe condition, Airbus published the
applicable SB [Airbus Service Bulletin A330-27-3226, dated April 5,
2018; Airbus Service Bulletin A340-27-4206, dated April 3, 2018; or
Airbus Service Bulletin A340-27-5071, dated April 3, 2018; as
applicable] to provide inspection instructions of the track station
4 and track station 5 DSE and sensor struts of the LH and RH wings.
For the reasons described above, this [EASA] AD requires
repetitive [detailed] inspections of the LH and RH track station 4
[DSE, repetitive general visual inspections of the LH and RH track
station 4 sensor struts,] and [for certain airplanes, a one-time
detailed inspection of the LH or RH, as applicable] track station 5
DSE * * * and, depending on findings, accomplishment of applicable
corrective action(s).
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-2018-
0904.
Comments
We gave the public the opportunity to participate in developing
this final rule. We received no comments on the NPRM or on the
determination of the cost to the public.
Conclusion
We reviewed the relevant data and determined that air safety and
the public interest require adopting this final rule 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 addressing the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information.
Airbus Service Bulletin A330-27-3226, dated April 5, 2018.
Airbus Service Bulletin A340-27-4206, dated April 3, 2018.
Airbus Service Bulletin A340-27-5071, dated April 3, 2018.
This service information describes procedures for repetitive
detailed inspections of the LH and RH track station 4 drive station
elements; repetitive general visual inspections of the LH and RH track
station 4 sensor struts; a detailed inspection of the track station 5
drive station elements if any discrepancy is found during a general
visual inspection; and corrective actions (i.e., replacement of
affected parts). These documents are distinct since they apply to
different models. This service information is reasonably available
because the interested parties have access to it through their normal
course of business or by the means identified in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 105 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:
Estimated Costs for Required Actions *
----------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Cost per product Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Up to 7 work-hours x $85 per hour = $0 Up to $595.............. Up to $62,475.
$595.
----------------------------------------------------------------------------------------------------------------
* Table does not include estimated costs for reporting.
We estimate that it would take about 1 work-hour per product to
comply with the reporting requirement in this AD. The average labor
rate is $85 per hour. Based on these figures, we estimate the cost of
reporting the inspection results on U.S. operators to be $8,925, or $85
per product.
We have received no definitive data that would enable us to provide
cost
[[Page 6319]]
estimates for the on-condition actions specified in this AD.
According to the manufacturer, some or all of the costs of this AD
may be covered under warranty, thereby reducing the cost impact on
affected individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all known costs in our cost
estimate.
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 AD is 2120-
0056. The paperwork cost associated with this AD 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 AD 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 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 and
associated appliances to the Director of the System Oversight Division.
Regulatory Findings
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.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2019-03-23 Airbus SAS: Amendment 39-19575; Docket No. FAA-2018-0904;
Product Identifier 2018-NM-108-AD.
(a) Effective Date
This AD is effective April 3, 2019.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus SAS airplanes identified in
paragraphs (c)(1) through (c)(7) of this AD, certificated in any
category, all manufacturer serial numbers.
(1) Model A330-223F and -243F airplanes.
(2) Model A330-201, -202, -203, -223, and -243 airplanes.
(3) Model A330-301, -302, -303, -321, -322, -323, -341, -342,
and -343 airplanes.
(4) Model A340-211, -212, and -213 airplanes.
(5) Model A340-311, -312, and -313 airplanes.
(6) Model A340-541 airplanes.
(7) Model A340-642 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
controls.
(e) Reason
This AD was prompted by a report that the right-hand (RH) and
left-hand (LH) track station 4 sensor struts, in the case of down
drive element disconnection, would be unable to provide failure
detection information for flap movements. We are issuing this AD to
address abnormal flap movement due to mechanical drive station
element disconnection at flap track station 4 or station 5 which
could lead to undetected down drive shaft disconnection. Such a
condition could result in complete flap disconnection in the case of
additional failure on the remaining flap drive station, and could
ultimately result in loss of control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Definitions
For the purpose of this AD, the drive station elements are
defined as the down drive, down drive shaft, geared rotary actuator
(gearbox), geared rotary actuator (output lever and fork end), and
drive strut.
(h) Detailed and General Visual Inspections
(1) At the applicable times specified in paragraphs (h)(1)(i)
and (h)(1)(ii) of this AD, and thereafter not to exceed the
applicable intervals specified in table 1 to paragraph (h)(1) of
this AD, do a detailed inspection of the LH and RH track station 4
drive station elements for corrosion or ruptured, loose, or missing
components (including any attached bolts and nuts that are loose,
broken, or missing) and a general visual inspection of the LH and RH
track station 4 sensor struts for corrosion or ruptured, loose, or
missing components (including any attached bolts that are loose,
broken, or missing), in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A330-27-3226, dated April 5,
2018; Airbus Service Bulletin A340-27-4206, dated April 3, 2018; or
Airbus Service Bulletin A340-27-5071, dated April 3, 2018; as
applicable.
[[Page 6320]]
[GRAPHIC] [TIFF OMITTED] TR27FE19.000
(i) For airplanes that, as of the effective date of this AD,
have accumulated less than 1,000 flight cycles since first flight:
Before exceeding 24 months since first flight or within 18 months
after the effective date of this AD, whichever occurs later, but
without exceeding 2,300 flight cycles since first flight.
(ii) For airplanes that, as of the effective date of this AD,
have accumulated 1,000 or more flight cycles since first flight:
Within 1,000 flight cycles or 12 months, whichever occurs first
after the effective date of this AD.
(2) If, during any general visual inspection required by
paragraph (h)(1) of this AD, any corrosion is detected or any
ruptured, loose, or missing components (including any attached bolts
that are loose, broken, or missing) are detected, before further
flight, accomplish a detailed inspection of the applicable LH or RH
track station 5 drive station elements for corrosion or ruptured,
loose, or missing components (including any attached bolts and nuts
that are loose, broken, or missing) in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A330-27-3226,
dated April 5, 2018; Airbus Service Bulletin A340-27-4206, dated
April 3, 2018; or Airbus Service Bulletin A340-27-5071, dated April
3, 2018; as applicable.
(i) Corrective Actions
(1) If, during any detailed inspection required by paragraph
(h)(1) of this AD, any corrosion is detected or any ruptured, loose,
or missing components (including any attached bolts and nuts that
are loose, broken, or missing) are detected, before further flight,
replace each affected part with a serviceable part in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A330-27-3226, dated April 5, 2018; Airbus Service Bulletin A340-27-
4206, dated April 3, 2018; or Airbus Service Bulletin A340-27-5071,
dated April 3, 2018; as applicable, or using a method approved by
the Manager, International Section, Transport Standards Branch, FAA;
or the European Aviation Safety Agency (EASA); or Airbus SAS's EASA
Design Organization Approval (DOA). If approved by the DOA, the
approval must include the DOA-authorized signature.
(2) If, during any general visual inspection required by
paragraph (h)(1) of this AD, any corrosion is detected or any
ruptured, loose, or missing components (including any attached bolts
that are loose, broken, or missing) are detected, before further
flight, replace each affected part with a serviceable part in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A330-27-3226, dated April 5, 2018; Airbus Service Bulletin
A340-27-4206, dated April 3, 2018; or Airbus Service Bulletin A340-
27-5071, dated April 3, 2018; as applicable, or using a method
approved by the Manager, International Section, Transport Standards
Branch, FAA; or EASA; or Airbus SAS's EASA DOA. If approved by the
DOA, the approval must include the DOA-authorized signature.
(3) If, during any detailed inspection required by paragraph
(h)(2) of this AD, any corrosion is detected or any ruptured, loose,
or missing components (including any attached bolts and nuts that
are loose, broken, or missing) are detected, before further flight,
replace each affected part with a serviceable part in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A330-27-3226, dated April 5, 2018; Airbus Service Bulletin A340-27-
4206, dated April 3, 2018; or Airbus Service Bulletin A340-27-5071,
dated April 3, 2018; as applicable, or using a method approved by
the Manager, International Section, Transport Standards Branch, FAA;
or EASA; or Airbus SAS's EASA DOA. If approved by the DOA, the
approval must include the DOA-authorized signature.
(j) Reporting
At the applicable time specified in paragraph (j)(1) or (j)(2)
of this AD: Report the results (positive or negative) of each
inspection required by paragraphs (h)(1) and (h)(2) of this AD to
Airbus Service Bulletin Reporting Online Application on Airbus World
(https://w3.airbus.com/), or submit the results to Airbus in
accordance with the instructions of Airbus Service Bulletin A330-27-
3226, dated April 5, 2018; Airbus Service Bulletin A340-27-4206,
dated April 3, 2018; or Airbus Service Bulletin A340-27-5071, dated
April 3, 2018.
(1) If the inspection was done on or after the effective date of
this AD: Submit the report within 90 days after the inspection.
(2) If the inspection was done before the effective date of this
AD: Submit the report within 90 days after the effective date of
this AD.
(k) 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 (l)(2) of this AD. Information
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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 using a method approved
by the Manager, International Section, Transport Standards Branch,
FAA; or EASA; or Airbus SAS's EASA DOA. If approved by the DOA, the
approval must include the DOA-authorized signature.
(3) Required for Compliance (RC): If any service information
contains procedures or tests that are identified as RC, those
procedures and tests must be done to comply with this AD; any
procedures or tests that are not identified as RC are recommended.
Those procedures and tests that are not identified as RC may be
deviated from using accepted methods in accordance with the
operator's maintenance or inspection program without obtaining
approval of an AMOC, provided the procedures and tests identified as
RC can be done and the airplane can be put back in an airworthy
condition. Any substitutions or changes to procedures or tests
identified as RC require approval of an AMOC.
(4) Reporting Requirements: 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.
[[Page 6321]]
(l) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2018-0151, dated July 16, 2018, 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-2018-0904.
(2) For more information about this AD, contact Vladimir
Ulyanov, Aerospace Engineer, International Section, Transport
Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198;
phone and fax: 206-231-3229.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A330-27-3226, dated April 5, 2018.
(ii) Airbus Service Bulletin A340-27-4206, dated April 3, 2018.
(iii) Airbus Service Bulletin A340-27-5071, dated April 3, 2018.
(3) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAL, Rond-Point Emile Dewoitine
No: 2, 31700 Blagnac Cedex, France; phone: +33 5 61 93 36 96; fax:
+33 5 61 93 45 80; email: airworthiness.A330-A340@airbus.com;
internet: https://www.airbus.com.
(4) You may view this service information at the FAA, Transport
Standards Branch, 2200 South 216th St., Des Moines, WA. For
information on the availability of this material at the FAA, call
206-231-3195.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Des Moines, Washington, on February 14, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-03256 Filed 2-26-19; 8:45 am]
BILLING CODE 4910-13-P
