Airworthiness Directives; Airbus SAS Airplanes, 50721-50725 [2019-20893]
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Federal Register / Vol. 84, No. 187 / Thursday, September 26, 2019 / Rules and Regulations
delegated the authority to issue ADs
applicable to engines, propellers, and
associated appliances to the Manager,
Engine and Propeller Standards Branch,
Policy and Innovation 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,
and
(2) Will not affect intrastate aviation
in Alaska.
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
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):
■
2019–19–11 Pratt & Whitney: Amendment
39–19747; Docket No. FAA–2019–0771;
Product Identifier 2019–NE–27–AD.
(a) Effective Date
This AD is effective September 26, 2019.
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(b) Affected ADs
None.
(c) Applicability
This AD applies to Pratt & Whitney Models
PW1519G, PW1521G, PW1521GA, PW1524G,
PW1525G, PW1521G–3, PW1524G–3,
PW1525G–3, PW1919G, PW1921G,
PW1922G, PW1923G, and PW1923G–A
turbofan engines that have accumulated
fewer than 300 flight cycles.
(d) Subject
Joint Aircraft System Component (JASC)
Code 7230, Turbine Engine Compressor
Section.
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(e) Unsafe Condition
This AD was prompted by two recent inflight shutdowns on PW PW1524G–3 model
turbofan engines, due to failure of the lowpressure compressor (LPC) rotor 1 (R1). The
FAA is issuing this AD to prevent failure of
the LPC R1. The unsafe condition, if not
addressed, could result in uncontained
release of the LPC R1, damage to the engine,
damage to the airplane, and loss of control
of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) Within 50 flight cycles from the
effective date of this AD, and thereafter at
intervals not to exceed 50 flight cycles until
the engine accumulates 300 flight cycles,
borescope inspect each LPC inlet guide vane
(IGV) stem for proper alignment.
(2) Within 50 flight cycles from the
effective date of this AD, and thereafter at
intervals not to exceed 50 flight cycles until
the engine accumulates 300 flight cycles,
borescope inspect the LPC R1 for damage and
cracks at the following locations:
(i) The blades tips;
(ii) the leading edge;
(iii) the leading edge fillet to rotor platform
radius; and
(iv) the airfoil convex side root fillet to
rotor platform radius.
(3) As the result of the inspections required
by paragraphs (g)(1) and (2) of this AD, before
further flight, remove and replace the LPC if:
(i) An IGV is misaligned; or
(ii) there is damage on an LPC R1 that
exceeds serviceable limits; or
(iii) there is any crack in the LPC R1.
Note 1 to paragraph (g): Guidance on
determining serviceable limits can be found
in PW Service Bulletin (SB) PW1000G–A–
72–00–0125–00A–930A–D, Issue No. 001,
dated September 23, 2019, and PW SB
PW1000G–A–72–00–0075–00B–930A–D,
Issue No. 001, dated September 23, 2019.
(h) Definition
For the purpose of this AD, a misaligned
IGV is an IGV that is rotated about its radial
axis at a different angle than the remainder
of the IGVs in the circumferential set.
(i) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, ECO 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 manager of the certification office,
send it to the attention of the person
identified in paragraph (j) of this AD. You
may email your request to: ANE-AD-AMOC@
faa.gov.
(2) 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.
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50721
(j) Related Information
For more information about this AD,
contact Kevin M. Clark, Aerospace Engineer,
ECO Branch, FAA, 1200 District Avenue,
Burlington, MA 01803; phone: 781–238–
7088; fax: 781–238–7199; email:
kevin.m.clark@faa.gov.
(k) Material Incorporated by Reference
None.
Issued in Burlington, Massachusetts, on
September 24, 2019.
Robert J. Ganley,
Manager, Engine & Propeller Standards
Branch, Aircraft Certification Service.
[FR Doc. 2019–21010 Filed 9–25–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0250; Product
Identifier 2018–NM–157–AD; Amendment
39–19734; AD 2019–18–07]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2015–17–
14, which applied to all Airbus SAS
Model A319 series airplanes; Model
A320–211, –212, –214, –231, –232, and
–233 airplanes, and Model A321–111,
–112, –131, –211, –212, –213, –231, and
–232 airplanes. AD 2015–17–14
required repetitive rototest inspections
of the open tack holes and rivet holes at
the cargo floor support fittings of the
fuselage, including doing all applicable
related investigative actions, and repair
if necessary. This AD continues to
require the actions of AD 2015–17–14,
adds actions for certain airplanes, and
reduces the compliance times for certain
airplanes, as specified in an European
Aviation Safety Agency (EASA) AD,
which is incorporated by reference. This
AD also reduces the applicability. This
AD was prompted by further analysis
and widespread fatigue damage (WFD)
evaluations which identified the need to
reduce the initial compliance times and
repetitive intervals for the inspections
for certain airplanes, and to add work
for certain airplanes. The FAA is issuing
this AD to address the unsafe condition
on these products.
DATES: This AD is effective October 31,
2019.
SUMMARY:
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The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of October 31, 2019.
For the material
incorporated by reference (IBR) in this
AD, contact the EASA, at KonradAdenauer-Ufer 3, 50668 Cologne,
Germany; telephone +49 221 89990
1000; email ADs@easa.europa.eu;
internet www.easa.europa.eu. You may
find this IBR material on the EASA
website at https://ad.easa.europa.eu.
You may view this IBR material 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 in the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2019–
0250.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2019–
0250; 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
comments received, and other
information. The address for Docket
Operations 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.
modifications. Therefore, no change to
this AD is necessary in this regard.
Request To Change Method for
Obtaining Corrective Actions
DAL asked that the method for
obtaining corrective actions, as required
by paragraph (g) of the proposed AD, be
changed. DAL stated that those
requirements entail complying with all
required actions and compliance times
specified in, and in accordance with,
EASA AD 2018–0233R1. DAL added
that, specifically, this means the method
for obtaining all corrective actions is to
contact Airbus. DAL asked that the
method for obtaining corrective actions
be changed as follows:
If any crack is found during any inspection
required by this AD: Before further flight,
repair using a method approved by the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA); or
Airbus’s EASA Design Organization
Approval (DOA). If approved by the DOA,
the approval must include the DOAauthorized signature.
FOR FURTHER INFORMATION CONTACT:
Request To Change Applicability
DAL noted that, as written, the
proposed AD will limit authorization for
corrective action solely to Airbus (EASA
DOA), which restricts operator
flexibility to obtain corrective action
directly from the FAA or from the
EASA.
The FAA disagrees with the
commenter’s request because the
method proposed by the commenter is
already provided in paragraph (i)(2) of
this AD (as restated from the proposed
AD), which in turn applies to paragraph
(g) of this AD. Therefore, no change to
this AD is necessary in this regard.
Sanjay Ralhan, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3223.
Delta TechOps (DAL) asked that the
applicability identified in paragraph (c)
of the proposed AD be changed by
adding the following language: ‘‘Serial
number exceptions for Airbus
production [modification] MOD status,
as defined within the Applicability
paragraph of EASA AD 2018–0233R1,
are likewise acceptable for FAA AD
applicability definition.’’ DAL stated
that paragraph (c) applies to certain
A320 family aircraft identified in the
EASA AD, and noted that paragraph 2
of the EASA AD provides additional
applicability details, namely, excluding
serial numbers from the applicability
based on the Airbus MOD status.
The FAA acknowledges the
commenter’s request and offers the
following clarification: The intent of the
applicability identified in paragraph (c)
of this AD is to match the applicability
in EASA AD 2018–0233R1, for airplanes
with an FAA-approved type certificate,
including exceptions based on
Request To Include Certain Deviations
DAL asked that a deviation paragraph
be added to the exceptions in paragraph
(h) of the proposed AD as follows: ‘‘If
accomplishing inspections according to
a non-RC [required for compliance]
revision of manufacturer Service
Information, deviations from paragraphs
other than paragraph 3.C. ‘Procedures’
do not require an [alternative method of
compliance] AMOC.’’ DAL stated that
the inspection can be done using any
revision of Airbus Service Bulletin
A320–53–1257, and the original issue
was not written in RC format. DAL
added that operators have by now
performed the initial inspection using
the original issue of that service
information. DAL noted that these
inspections comply with the final rule
because credit is allowed in EASA AD
2018–0233R1. DAL stated that it is
possible that operators deviated from
procedures outside of paragraph 3.C.
when accomplishing a non-RC
SUPPLEMENTARY INFORMATION:
Discussion
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for and locating Docket No. FAA–2019–
0250.
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2015–17–14,
Amendment 39–18247 (80 FR 52182,
August 28, 2015) (‘‘AD 2015–17–14’’).
AD 2015–17–14 applied to all Airbus
SAS Model A319 series airplanes;
Model A320–211, –212, –214, –231,
–232, and –233 airplanes, and Model
A321–111, –112, –131, –211, –212,
–213, –231, and –232 airplanes. The
NPRM published in the Federal
Register on April 24, 2019 (84 FR
17102). The NPRM was prompted by
further analysis and WFD evaluations
which identified the need to reduce the
initial compliance times and repetitive
intervals for the inspections for certain
airplanes, and to add work for certain
airplanes. The NPRM proposed to
continue to require the actions of AD
2015–17–14. The NPRM also proposed
to add actions for certain airplanes, and
reduce the compliance times for certain
airplanes. The FAA is issuing this AD
to address cracking in the open tack
holes and rivet holes at the cargo floor
support fittings of the fuselage, which
could affect the structural integrity of
the airplane. See the MCAI for
additional background information.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2018–
0233R1, dated November 28, 2018
(‘‘EASA AD 2018–0233R1’’) (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Airbus SAS Model A319
series airplanes; Model A320–211, –212,
–214, –216, –231, –232, and –233
airplanes; and Model A321–111, –112,
–131, –211, –212, –213, –231, and –232
airplanes. You may examine the MCAI
in the AD docket on the internet at
https://www.regulations.gov by searching
VerDate Sep<11>2014
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Comments
The FAA gave the public the
opportunity to participate in developing
this final rule. The following presents
the comments received on the NPRM
and the FAA’s response to each
comment.
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formatted service information revision,
or may never have incorporated
Revision 01 or Revision 02.
The FAA disagrees with the
commenter’s request. EASA AD 2018–
0233R1 requires inspecting in
accordance with Revision 02 of Airbus
Service Bulletin A320–53–1257. If the
inspection is done using the original
issue or Revision 01 of the service
information, credit is given for
compliance in EASA AD 2018–0233R1.
Any deviation from the service
information must comply with the
procedures found in 14 CFR 39.19.
Therefore, no change to this AD is
necessary in this regard.
Request To Remove Corrosion
Prevention Requirement
DAL stated that the application of
CML 12ADB1 Corrosion Preventative
Compound should not be considered an
RC step. DAL noted that operators are
responsible for maintaining their own
corrosion prevention programs, and
application of corrosion inhibiting
compounds (CICs) during embodiment
of ADs should not be included with the
RC steps.
The FAA does not agree to remove the
requirement to apply CIC. The
application of CIC is necessary to
address the unsafe condition, and to
ensure that the correct CIC is used, this
AD requires use of the CIC referenced in
the service information that is identified
in the MCAI for the applicable product.
However, under the provisions of
paragraph (i)(1) of this AD, the FAA will
consider requests for approval of
another corrosion prevention compound
if sufficient data are submitted to
substantiate that it would provide an
acceptable level of safety. The FAA has
not changed this AD regarding this
issue.
Request To Clarify Requirements
United Airlines (UAL) asked if the
intent of paragraph (g) of the proposed
AD is that operators are required to
comply with EASA AD 2018–0233R1 in
its entirety, except as noted in
paragraph (h) of the proposed AD, or
just compliance with the section in
EASA AD 2018–0233R1 titled
‘‘Required Action(s) and Compliance
Time(s).’’ UAL stated that the proposed
AD should provide clarification so
operators know the specific parts of the
EASA AD necessary for compliance.
The FAA agrees to clarify the
requirements in paragraph (g) of this
AD. This AD requires compliance with
EASA AD 2018–0233R1 in its entirety,
through that incorporation, except for
any differences identified as exceptions
in the regulatory text of this AD. Using
common terms that are the same as the
heading of a particular section in the
EASA AD does not mean that operators
need comply only with that section. For
example, where the AD requirement
refers to ‘‘all required actions and
compliance times,’’ compliance with
this AD requirement is not limited to
the section titled ‘‘Required Action(s)
and Compliance Time(s)’’ in the EASA
AD. The FAA has not changed this AD
in this regard.
Request To Include Terminating Action
and Credit for Previous Actions
JetBlue asked that the modification
required by paragraph (8) of EASA AD
2018–0233R1 be added to the proposed
AD as terminating action. The
commenter also asked that credit be
provided for actions done in accordance
with FAA AD 2015–17–14 through
related AMOCs.
The FAA acknowledges the
commenter’s request. However, the
terminating action found in paragraph
(8) of EASA AD 2018–0233R1 is already
50723
provided for in paragraph (g) of this AD,
which requires complying with all
required actions and compliance times
specified in, and in accordance with,
EASA AD 2018–0233R1. In addition,
paragraph (i)(1)(ii) of this AD provides
credit for AMOCs approved previously
for AD 2015–17–14. Unless otherwise
noted in this AD, all provisions of EASA
AD 2018–0233R1 apply to the
corresponding provisions of this AD.
Therefore, the FAA has made no
changes to this AD in this regard.
Conclusion
The FAA reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this
final rule as proposed, except for minor
editorial changes. The FAA has
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 IBR Material Under 1 CFR Part
51
EASA AD 2018–0233R1 describes
procedures for repetitive inspections of
the open tack holes and rivet holes of
the fuselage frames below the cargo
floor support fittings for cracking. This
material 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, and it is publicly
available through the EASA website.
Costs of Compliance
The FAA estimates that this AD
affects 1,009 airplanes of U.S. registry.
The FAA estimates the following costs
to comply with this AD:
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ESTIMATED COSTS FOR REQUIRED ACTIONS
Action
Labor cost
Retained actions from AD 2015–17–
14.
New actions .......................................
Up to 471 work-hours × $85 per hour
= Up to $40,035.
Up to 474 work-hours × 85 per hour
= Up to $40,290.
The FAA has received no definitive
data that enables the agency to provide
cost estimates for the on-condition
actions specified in this AD.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
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Jkt 247001
Parts cost
Cost per product
$0
Up to $40,035 ............
Up to $40,395,315.
13,000
Up to $53,290 ............
Up to $53,769,610.
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
The FAA is issuing this rulemaking
under the authority described in
Subtitle VII, Part A, Subpart III, Section
44701: ‘‘General requirements.’’ Under
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Cost on U.S.
operators
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
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Federal Register / Vol. 84, No. 187 / Thursday, September 26, 2019 / Rules and Regulations
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
The FAA determined that this AD
will not have federalism implications
under Executive Order 13132. This AD
will not have a substantial direct effect
on the States, on the relationship
between the national government and
the States, or on the distribution of
power and responsibilities among the
various levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Will not affect intrastate aviation
in Alaska, and
(3) 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
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
removing Airworthiness Directive (AD)
2015–17–14, Amendment 39–18247 (80
FR 52182, August 28, 2015), and adding
the following new AD:
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■
2019–18–07 Airbus SAS: Amendment 39–
19734; Docket No. FAA–2019–0250;
Product Identifier 2018–NM–157–AD.
(a) Effective Date
This AD is effective October 31, 2019.
VerDate Sep<11>2014
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(b) Affected ADs
This AD replaces AD 2015–17–14,
Amendment 39–18247 (80 FR 52182, August
28, 2015) (‘‘AD 2015–17–14’’).
(c) Applicability
This AD applies to Airbus SAS Model
A319–111, –112, –113, –114, –115, –131,
–132, and –133 airplanes; Model A320–211,
–212, –214, –216, –231, –232, and –233
airplanes; and Model A321–111, –112, –131,
–211, –212, –213, –231, and –232 airplanes;
certificated in any category, as identified in
European Aviation Safety Agency (EASA) AD
2018–0233R1, dated November 28, 2018
(‘‘EASA AD 2018–0233R1’’).
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by further analysis
and widespread fatigue damage (WFD)
evaluations and full-scale fatigue testing that
indicated that several broken frames in
certain areas of the cargo compartment were
found, especially on the cargo floor support
fittings and open tack holes on the left-hand
side, which identified the need to reduce the
initial compliance times and repetitive
intervals for the inspections for certain
airplanes, and to add work for certain
airplanes. The FAA is issuing this AD to
address cracking in the open tack holes and
rivet holes at the cargo floor support fittings
of the fuselage, which could affect the
structural integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Requirements
Except as specified in paragraph (h) of this
AD: Comply with all required actions and
compliance times specified in, and in
accordance with, EASA AD 2018–0233R1.
(h) Exceptions to EASA AD 2018–0233R1
(1) For purposes of determining
compliance with the requirements of this AD:
Where EASA AD 2018–0233R1 refers to ‘‘the
effective date of the original issue of this
AD,’’ this AD requires using the effective date
of this AD, and where EASA AD 2018–
0233R1 refers to ‘‘the effective date of EASA
AD 2013–0310,’’ this AD requires using
October 2, 2015 (the effective date of AD
2015–17–14).
(2) The ‘‘Remarks’’ section of EASA AD
2018–0233R1 does not apply to this AD.
(i) 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 (j) of this AD. Information may be
emailed to: 9-ANM-116-AMOC-REQUESTS@
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
2015–17–14 are approved as AMOCs for the
corresponding provisions of EASA AD 2018–
0233R1 that are required by paragraph (g) of
this AD.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain instructions
from a manufacturer, the instructions must
be accomplished using a method approved
by the Manager, International Section,
Transport Standards Branch, FAA; or EASA;
or Airbus SAS’s EASA Design Organization
Approval (DOA). If approved by the DOA,
the approval must include the DOAauthorized signature.
(3) Required for Compliance (RC): For any
service information referenced in EASA AD
2018–0233R1 that contains RC procedures
and tests: Except as required by paragraph
(i)(2) of this AD, RC 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.
(j) Related Information
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.
(k) 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) European Aviation Safety Agency
(EASA) AD 2018–0233R1, dated November
28, 2018.
(ii) [Reserved]
(3) For EASA AD 2018–0233R1, contact the
EASA, Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221 89990
6017; email ADs@easa.europa.eu; internet
www.easa.europa.eu. You may find this
EASA AD on the EASA website at https://
ad.easa.europa.eu.
(4) You may view this EASA AD 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.
E:\FR\FM\26SER1.SGM
26SER1
Federal Register / Vol. 84, No. 187 / Thursday, September 26, 2019 / Rules and Regulations
EASA AD 2018–0233R1 may be found in the
AD docket on the internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2019–0250.
(5) You may view this material that is
incorporated by reference at the National
Archives and Records Administration
(NARA). For information on the availability
of this material at NARA, email fedreg.legal@
nara.gov, or go to: https://www.archives.gov/
federal-register/cfr/ibr-locations.html.
Issued in Des Moines, Washington, on
September 16, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
AB, Saab Aeronautics, SE–581 88,
Linko¨ping, Sweden; telephone +46 13
18 5591; fax +46 13 18 4874; email
saab2000.techsupport@saabgroup.com;
internet https://www.saabgroup.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–2019–
0521.
July 3, 2019 (84 FR 31775). The NPRM
was prompted by reports of cracks in
the o-ring groove of magnetic fuel level
indicators. The NPRM proposed to
require a one-time detailed inspection of
the magnetic fuel level indicator for
cracks and replacement of cracked
magnetic fuel level indicators.
The FAA is issuing this AD to address
cracks in the o-ring groove of magnetic
fuel level indicators, which, if not
detected and corrected, could result in
a severe fuel leak and consequent risk
of fuel starvation. See the MCAI for
additional background information.
[FR Doc. 2019–20893 Filed 9–25–19; 8:45 am]
Examining the AD Docket
Comments
BILLING CODE 4910–13–P
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2019–
0521; 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
comments received, and other
information. The address for Docket
Operations 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:
Shahram Daneshmandi, Aerospace
Engineer, International Section,
Transport Standards Branch, FAA, 2200
South 216th St., Des Moines, WA 98198;
telephone and fax 206–231–3220.
SUPPLEMENTARY INFORMATION:
The FAA gave the public the
opportunity to participate in developing
this final rule. The FAA received no
comments on the NPRM or on the
determination of the cost to the public.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0521; Product
Identifier 2019–NM–047–AD; Amendment
39–19740; AD 2019–19–04]
RIN 2120–AA64
Airworthiness Directives; Saab AB,
Saab Aeronautics (Formerly Known as
Saab AB, Saab Aerosystems)
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for all Saab
AB, Saab Aeronautics Model SAAB
2000 airplanes. This AD was prompted
by reports of cracks in the o-ring groove
of magnetic fuel level indicators. This
AD requires a one-time detailed
inspection of the magnetic fuel level
indicator for cracks and replacement of
cracked magnetic fuel level indicators.
The FAA is issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective October 31,
2019.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of October 31, 2019.
ADDRESSES: For service information
identified in this final rule, contact Saab
SUMMARY:
khammond on DSKJM1Z7X2PROD with RULES
50725
Discussion
The European Union Aviation Safety
Agency (EASA), which is the Technical
Agent for the Member States of the
European Union, has issued EASA AD
2019–0053, dated March 14, 2019
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition for all Saab AB, Saab
Aeronautics Model SAAB 2000
airplanes.
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Saab AB, Saab Aeronautics
Model SAAB 2000 airplanes. The NPRM
published in the Federal Register on
Conclusion
The FAA 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. The FAA has
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
Saab AB, Saab Aeronautics (Formerly
Known as Saab AB, Saab Aerosystems)
has issued Service Bulletin 2000–28–
027, dated January 15, 2019. This
service information describes
procedures for a one-time detailed
inspection of the magnetic fuel level
indicator for cracks and replacement of
cracked magnetic fuel level indicators.
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
The FAA estimates that this AD
affects 11 airplanes of U.S. registry. The
agency estimates 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
6 work-hours × $85 per hour = $510 ..........................................................................................
$0
$510
$5,610
VerDate Sep<11>2014
17:19 Sep 25, 2019
Jkt 247001
PO 00000
Frm 00015
Fmt 4700
Sfmt 4700
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26SER1
]]>Agencies
[Federal Register Volume 84, Number 187 (Thursday, September 26, 2019)]
[Rules and Regulations]
[Pages 50721-50725]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-20893]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0250; Product Identifier 2018-NM-157-AD; Amendment
39-19734; AD 2019-18-07]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2015-17-
14, which applied to all Airbus SAS Model A319 series airplanes; Model
A320-211, -212, -214, -231, -232, and -233 airplanes, and Model A321-
111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2015-
17-14 required repetitive rototest inspections of the open tack holes
and rivet holes at the cargo floor support fittings of the fuselage,
including doing all applicable related investigative actions, and
repair if necessary. This AD continues to require the actions of AD
2015-17-14, adds actions for certain airplanes, and reduces the
compliance times for certain airplanes, as specified in an European
Aviation Safety Agency (EASA) AD, which is incorporated by reference.
This AD also reduces the applicability. This AD was prompted by further
analysis and widespread fatigue damage (WFD) evaluations which
identified the need to reduce the initial compliance times and
repetitive intervals for the inspections for certain airplanes, and to
add work for certain airplanes. The FAA is issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective October 31, 2019.
[[Page 50722]]
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of October 31,
2019.
ADDRESSES: For the material incorporated by reference (IBR) in this AD,
contact the EASA, at Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany;
telephone +49 221 89990 1000; email [email protected]; internet
www.easa.europa.eu. You may find this IBR material on the EASA website
at https://ad.easa.europa.eu. You may view this IBR material 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 in the AD docket on the internet at
https://www.regulations.gov by searching for and locating Docket No.
FAA-2019-0250.
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-2019-
0250; 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 comments received, and
other information. The address for Docket Operations 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: Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; telephone and fax 206-231-3223.
SUPPLEMENTARY INFORMATION:
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2018-0233R1, dated November 28, 2018 (``EASA AD 2018-0233R1'')
(referred to after this as the Mandatory Continuing Airworthiness
Information, or ``the MCAI''), to correct an unsafe condition for
certain Airbus SAS Model A319 series airplanes; Model A320-211, -212, -
214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -
131, -211, -212, -213, -231, and -232 airplanes. 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-2019-0250.
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2015-17-14, Amendment 39-18247 (80 FR
52182, August 28, 2015) (``AD 2015-17-14''). AD 2015-17-14 applied to
all Airbus SAS Model A319 series airplanes; Model A320-211, -212, -214,
-231, -232, and -233 airplanes, and Model A321-111, -112, -131, -211, -
212, -213, -231, and -232 airplanes. The NPRM published in the Federal
Register on April 24, 2019 (84 FR 17102). The NPRM was prompted by
further analysis and WFD evaluations which identified the need to
reduce the initial compliance times and repetitive intervals for the
inspections for certain airplanes, and to add work for certain
airplanes. The NPRM proposed to continue to require the actions of AD
2015-17-14. The NPRM also proposed to add actions for certain
airplanes, and reduce the compliance times for certain airplanes. The
FAA is issuing this AD to address cracking in the open tack holes and
rivet holes at the cargo floor support fittings of the fuselage, which
could affect the structural integrity of the airplane. See the MCAI for
additional background information.
Comments
The FAA gave the public the opportunity to participate in
developing this final rule. The following presents the comments
received on the NPRM and the FAA's response to each comment.
Request To Change Applicability
Delta TechOps (DAL) asked that the applicability identified in
paragraph (c) of the proposed AD be changed by adding the following
language: ``Serial number exceptions for Airbus production
[modification] MOD status, as defined within the Applicability
paragraph of EASA AD 2018-0233R1, are likewise acceptable for FAA AD
applicability definition.'' DAL stated that paragraph (c) applies to
certain A320 family aircraft identified in the EASA AD, and noted that
paragraph 2 of the EASA AD provides additional applicability details,
namely, excluding serial numbers from the applicability based on the
Airbus MOD status.
The FAA acknowledges the commenter's request and offers the
following clarification: The intent of the applicability identified in
paragraph (c) of this AD is to match the applicability in EASA AD 2018-
0233R1, for airplanes with an FAA-approved type certificate, including
exceptions based on modifications. Therefore, no change to this AD is
necessary in this regard.
Request To Change Method for Obtaining Corrective Actions
DAL asked that the method for obtaining corrective actions, as
required by paragraph (g) of the proposed AD, be changed. DAL stated
that those requirements entail complying with all required actions and
compliance times specified in, and in accordance with, EASA AD 2018-
0233R1. DAL added that, specifically, this means the method for
obtaining all corrective actions is to contact Airbus. DAL asked that
the method for obtaining corrective actions be changed as follows:
If any crack is found during any inspection required by this AD:
Before further flight, repair using a method approved by the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or the European Aviation Safety Agency (EASA); or
Airbus's EASA Design Organization Approval (DOA). If approved by the
DOA, the approval must include the DOA-authorized signature.
DAL noted that, as written, the proposed AD will limit
authorization for corrective action solely to Airbus (EASA DOA), which
restricts operator flexibility to obtain corrective action directly
from the FAA or from the EASA.
The FAA disagrees with the commenter's request because the method
proposed by the commenter is already provided in paragraph (i)(2) of
this AD (as restated from the proposed AD), which in turn applies to
paragraph (g) of this AD. Therefore, no change to this AD is necessary
in this regard.
Request To Include Certain Deviations
DAL asked that a deviation paragraph be added to the exceptions in
paragraph (h) of the proposed AD as follows: ``If accomplishing
inspections according to a non-RC [required for compliance] revision of
manufacturer Service Information, deviations from paragraphs other than
paragraph 3.C. `Procedures' do not require an [alternative method of
compliance] AMOC.'' DAL stated that the inspection can be done using
any revision of Airbus Service Bulletin A320-53-1257, and the original
issue was not written in RC format. DAL added that operators have by
now performed the initial inspection using the original issue of that
service information. DAL noted that these inspections comply with the
final rule because credit is allowed in EASA AD 2018-0233R1. DAL stated
that it is possible that operators deviated from procedures outside of
paragraph 3.C. when accomplishing a non-RC
[[Page 50723]]
formatted service information revision, or may never have incorporated
Revision 01 or Revision 02.
The FAA disagrees with the commenter's request. EASA AD 2018-0233R1
requires inspecting in accordance with Revision 02 of Airbus Service
Bulletin A320-53-1257. If the inspection is done using the original
issue or Revision 01 of the service information, credit is given for
compliance in EASA AD 2018-0233R1. Any deviation from the service
information must comply with the procedures found in 14 CFR 39.19.
Therefore, no change to this AD is necessary in this regard.
Request To Remove Corrosion Prevention Requirement
DAL stated that the application of CML 12ADB1 Corrosion
Preventative Compound should not be considered an RC step. DAL noted
that operators are responsible for maintaining their own corrosion
prevention programs, and application of corrosion inhibiting compounds
(CICs) during embodiment of ADs should not be included with the RC
steps.
The FAA does not agree to remove the requirement to apply CIC. The
application of CIC is necessary to address the unsafe condition, and to
ensure that the correct CIC is used, this AD requires use of the CIC
referenced in the service information that is identified in the MCAI
for the applicable product. However, under the provisions of paragraph
(i)(1) of this AD, the FAA will consider requests for approval of
another corrosion prevention compound if sufficient data are submitted
to substantiate that it would provide an acceptable level of safety.
The FAA has not changed this AD regarding this issue.
Request To Clarify Requirements
United Airlines (UAL) asked if the intent of paragraph (g) of the
proposed AD is that operators are required to comply with EASA AD 2018-
0233R1 in its entirety, except as noted in paragraph (h) of the
proposed AD, or just compliance with the section in EASA AD 2018-0233R1
titled ``Required Action(s) and Compliance Time(s).'' UAL stated that
the proposed AD should provide clarification so operators know the
specific parts of the EASA AD necessary for compliance.
The FAA agrees to clarify the requirements in paragraph (g) of this
AD. This AD requires compliance with EASA AD 2018-0233R1 in its
entirety, through that incorporation, except for any differences
identified as exceptions in the regulatory text of this AD. Using
common terms that are the same as the heading of a particular section
in the EASA AD does not mean that operators need comply only with that
section. For example, where the AD requirement refers to ``all required
actions and compliance times,'' compliance with this AD requirement is
not limited to the section titled ``Required Action(s) and Compliance
Time(s)'' in the EASA AD. The FAA has not changed this AD in this
regard.
Request To Include Terminating Action and Credit for Previous Actions
JetBlue asked that the modification required by paragraph (8) of
EASA AD 2018-0233R1 be added to the proposed AD as terminating action.
The commenter also asked that credit be provided for actions done in
accordance with FAA AD 2015-17-14 through related AMOCs.
The FAA acknowledges the commenter's request. However, the
terminating action found in paragraph (8) of EASA AD 2018-0233R1 is
already provided for in paragraph (g) of this AD, which requires
complying with all required actions and compliance times specified in,
and in accordance with, EASA AD 2018-0233R1. In addition, paragraph
(i)(1)(ii) of this AD provides credit for AMOCs approved previously for
AD 2015-17-14. Unless otherwise noted in this AD, all provisions of
EASA AD 2018-0233R1 apply to the corresponding provisions of this AD.
Therefore, the FAA has made no changes to this AD in this regard.
Conclusion
The FAA reviewed the relevant data, considered the comments
received, and determined that air safety and the public interest
require adopting this final rule as proposed, except for minor
editorial changes. The FAA has 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 IBR Material Under 1 CFR Part 51
EASA AD 2018-0233R1 describes procedures for repetitive inspections
of the open tack holes and rivet holes of the fuselage frames below the
cargo floor support fittings for cracking. This material 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, and it is publicly available through the EASA
website.
Costs of Compliance
The FAA estimates that this AD affects 1,009 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
--------------------------------------------------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Retained actions from AD 2015-17-14.. Up to 471 work-hours x $0 Up to $40,035...................... Up to $40,395,315.
$85 per hour = Up to
$40,035.
New actions.......................... Up to 474 work-hours x 13,000 Up to $53,290...................... Up to $53,769,610.
85 per hour = Up to
$40,290.
--------------------------------------------------------------------------------------------------------------------------------------------------------
The FAA has received no definitive data that enables the agency to
provide cost estimates for the on-condition actions specified in this
AD.
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.
The FAA is 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
[[Page 50724]]
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
The FAA determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) 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 removing Airworthiness Directive (AD)
2015-17-14, Amendment 39-18247 (80 FR 52182, August 28, 2015), and
adding the following new AD:
2019-18-07 Airbus SAS: Amendment 39-19734; Docket No. FAA-2019-0250;
Product Identifier 2018-NM-157-AD.
(a) Effective Date
This AD is effective October 31, 2019.
(b) Affected ADs
This AD replaces AD 2015-17-14, Amendment 39-18247 (80 FR 52182,
August 28, 2015) (``AD 2015-17-14'').
(c) Applicability
This AD applies to Airbus SAS Model A319-111, -112, -113, -114,
-115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -
216, -231, -232, and -233 airplanes; and Model A321-111, -112, -131,
-211, -212, -213, -231, and -232 airplanes; certificated in any
category, as identified in European Aviation Safety Agency (EASA) AD
2018-0233R1, dated November 28, 2018 (``EASA AD 2018-0233R1'').
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by further analysis and widespread fatigue
damage (WFD) evaluations and full-scale fatigue testing that
indicated that several broken frames in certain areas of the cargo
compartment were found, especially on the cargo floor support
fittings and open tack holes on the left-hand side, which identified
the need to reduce the initial compliance times and repetitive
intervals for the inspections for certain airplanes, and to add work
for certain airplanes. The FAA is issuing this AD to address
cracking in the open tack holes and rivet holes at the cargo floor
support fittings of the fuselage, which could affect the structural
integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Requirements
Except as specified in paragraph (h) of this AD: Comply with all
required actions and compliance times specified in, and in
accordance with, EASA AD 2018-0233R1.
(h) Exceptions to EASA AD 2018-0233R1
(1) For purposes of determining compliance with the requirements
of this AD: Where EASA AD 2018-0233R1 refers to ``the effective date
of the original issue of this AD,'' this AD requires using the
effective date of this AD, and where EASA AD 2018-0233R1 refers to
``the effective date of EASA AD 2013-0310,'' this AD requires using
October 2, 2015 (the effective date of AD 2015-17-14).
(2) The ``Remarks'' section of EASA AD 2018-0233R1 does not
apply to this AD.
(i) 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 (j) of this AD. Information may
be emailed to: [email protected].
(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 2015-17-14 are approved as
AMOCs for the corresponding provisions of EASA AD 2018-0233R1 that
are required by paragraph (g) of this AD.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain instructions from a manufacturer, the instructions must be
accomplished using a method approved by the Manager, International
Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's
EASA Design Organization Approval (DOA). If approved by the DOA, the
approval must include the DOA-authorized signature.
(3) Required for Compliance (RC): For any service information
referenced in EASA AD 2018-0233R1 that contains RC procedures and
tests: Except as required by paragraph (i)(2) of this AD, RC
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.
(j) Related Information
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.
(k) 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) European Aviation Safety Agency (EASA) AD 2018-0233R1, dated
November 28, 2018.
(ii) [Reserved]
(3) For EASA AD 2018-0233R1, contact the EASA, Konrad-Adenauer-
Ufer 3, 50668 Cologne, Germany; telephone +49 221 89990 6017; email
[email protected]a.europa.eu; internet www.easa.europa.eu. You may find this
EASA AD on the EASA website at https://ad.easa.europa.eu.
(4) You may view this EASA AD 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.
[[Page 50725]]
EASA AD 2018-0233R1 may be found in the AD docket on the internet at
https://www.regulations.gov by searching for and locating Docket No.
FAA-2019-0250.
(5) You may view this material that is incorporated by reference
at the National Archives and Records Administration (NARA). For
information on the availability of this material at NARA, email
[email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Des Moines, Washington, on September 16, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-20893 Filed 9-25-19; 8:45 am]
BILLING CODE 4910-13-P
