Airworthiness Directives; Airbus SAS Airplanes, 5960-5968 [2019-02929]
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Federal Register / Vol. 84, No. 37 / Monday, February 25, 2019 / Proposed Rules
• Confirm or confirmation refers to a
written verification with a third-party
(person or organization) pertaining to an
account balance or condition. Examples of
confirmation letters are bank/corporate credit
union account confirmation, investment
account confirmation, borrowing or line of
credit confirmation, attorney letter
confirmation, and member share/loan
account confirmation.
• Materiality refers to a statement, fact or
item, which, giving full consideration to the
surrounding circumstances as they exist at
the time, it is of such a nature that its
disclosure, or the method of treating it,
would be likely to influence or to make a
difference in the judgment and conduct of a
reasonable person. Materiality should take
into account ending balances as well as the
volume of transactions in an account.
Typically, balances or transaction volume
greater than 5 percent of the credit union’s
net worth should be considered material for
purposes of this Appendix.
• Review refers to the examination of
policies and procedures, and a review of a
sample portion of activities, rather than all of
the activities.
• Test refers to procedures applied to the
individual items that compose an account
balance or class of transactions. The tests
involve confirmation, inspection, or
observation procedures to provide evidence
about the recorded amount.
The supervisory committee, internal
auditor, or other qualified person must
perform and document the following
minimum procedures:
• Test and confirm material asset and
liability accounts including, at a
minimum:
Æ Loans
Æ Cash on deposit
Æ Investments
Æ Shares
Æ Borrowings
• Test material equity, income, and expense
accounts
• Review key internal controls including, at
a minimum:
Æ Bank reconciliation procedures
Æ Cash controls
Æ Dormant account controls
Æ Wire and ACH transfer controls
Æ Loan approval and disbursement
procedures
Æ Inside account controls
Æ Other real estate owned
Æ Foreclosed and repossessed assets
• Test the mathematical accuracy of the
allowance for loan and lease loss account
and ensure the methodology is properly
applied
• Test loan delinquency and charge-offs
[FR Doc. 2019–03164 Filed 2–22–19; 8:45 am]
BILLING CODE 7535–01–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0017; Product
Identifier 2018–NM–112–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2007–11–
11 and AD 2017–01–11, which apply to
all Airbus SAS Model A318 and Model
A319 series airplanes; Model A320–211,
–212, –214, –231, –232, and –233
airplanes; and Model A321 series
airplanes. AD 2007–11–11 requires an
inspection to determine the serial
number of both main landing gear
(MLG) sliding tubes, repetitive
inspections for cracking of the affected
MLG sliding tubes and corrective
actions if necessary, and eventual
replacement of both MLG shock
absorbers. AD 2017–01–11 requires
identification of the part number and
serial number of the MLG sliding tubes;
inspection of affected chromium plates
and sliding tube axles for damage; and
replacement of the sliding tube if
necessary. Since we issued AD 2007–
11–11 and AD 2017–01–11, it was
determined that cracks were found in
the MLG sliding tubes due to certain
manufacturing defects that might not be
identified using the current on-wing
scheduled inspections. This proposed
AD would retain certain requirements of
AD 2007–11–11 and AD 2017–01–11.
This proposed AD would also require
repetitive inspections of affected MLG
sliding tubes for cracking, replacement
of cracked MLG sliding tubes, and
eventual replacement of each affected
MLG sliding tube. We are proposing this
AD to address the unsafe condition on
these products.
DATES: We must receive comments on
this proposed AD by April 11, 2019.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
SUMMARY:
PO 00000
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W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Airbus SAS,
Airworthiness Office—EIAS, RondPoint 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. You
may view this referenced 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.
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–
0017; 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 NPRM, the
regulatory evaluation, any comments
received, and other information. The
street address for Docket Operations
(phone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3223.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2019–0017; Product Identifier 2018–
NM–112–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
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Federal Register / Vol. 84, No. 37 / Monday, February 25, 2019 / Proposed Rules
Discussion
We issued AD 2007–11–11,
Amendment 39–15068 (72 FR 29241,
May 25, 2007) (‘‘AD 2007–11–11’’), for
all Model A318 and Model A319 series
airplanes; Model A320–211, –212, –214,
–231, –232, and –233 airplanes; and
Model A321 series airplanes. AD 2007–
11–11 requires a one-time inspection to
determine the serial number of both
MLG sliding tubes, repetitive detailed
inspections for cracking of the affected
MLG sliding tubes and corrective
actions if necessary, and eventual
replacement of both MLG shock
absorbers, which terminates the
repetitive inspection requirements. AD
2007–11–11 resulted from a
determination that inspections and
mandatory replacement of the MLG
shock absorbers are necessary. We
issued AD 2007–11–11 to address
cracking in an MLG sliding tube, which
could result in failure of the sliding
tube, loss of one axle, and consequent
reduced controllability of the airplane.
We also issued AD 2017–01–11,
Amendment 39–18778 (82 FR 5362,
January 18, 2017) (‘‘AD 2017–01–11’’),
for all Model A318 and Model A319
series airplanes; Model A320–211, –212,
–214, –231, –232, and –233 airplanes;
and Model A321 series airplanes. AD
2017–01–11 requires identification of
the part number and serial number of
the MLG sliding tubes; inspection of
affected chromium plates and sliding
tube axles for damage; and replacement
of the sliding tube if necessary. AD
2017–01–11 resulted from a report of a
rupture of an MLG sliding tube axle. We
issued AD 2017–01–11 to address cracks
in the axle and (partial) detachment of
the axle and wheel from the sliding
tube, which could result in failure of an
MLG.
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Actions Since AD 2007–11–11 and AD
2017–01–11 Were Issued
Since AD 2007–11–11 and AD 2017–
01–11 were issued, during MLG
overhaul, cracks were found in the
lower slave link bracket lug holes on
two MLG sliding tubes. Subsequent
investigations determined that these
cracks may have developed due to
burrs, which could have been present
since manufacture, and it was
determined that cracks in the affected
sliding tubes may not be found during
the existing on-wing scheduled
inspections.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2018–0135,
dated June 26, 2018 (referred to after
this as the Mandatory Continuing
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Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for all Airbus SAS Model A318 and
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. The MCAI states:
Cracks were reported on [main landing
gear] MLG sliding tubes and the
investigations determined metallic inclusion
during production and abnormal grinding
operation during overhaul as cause of these
cracks. Prompted by these reports,
respectively, [Direction Generale de
l’Aviation Civile] DGAC France issued
[French] AD F–2005–115 (EASA approval
2005–6032) [which corresponds to FAA AD
2007–11–11] and EASA issued AD 2014–
0058 [which corresponds to FAA AD 2017–
01–11], both requiring inspections and
replacement of certain MLG sliding tubes.
More recently, during overhaul, cracks
were found in the lower slave link bracket
lug holes on two MLG sliding tubes.
Subsequent investigations determined that
these cracks may have developed due to
burrs, which could have been present since
manufacture. Based on the fact that the
sliding tube is certified as a safe life part, this
is considered to be a non-compliance with
the requirements of [Joint Aviation
Requirements] JAR 25.571(c). Cracks in the
affected sliding tubes may not be found
during the existing on-wing scheduled
inspections.
This condition, if not detected and
corrected, could lead to sliding tube failure,
possibly resulting in MLG collapse, damage
to the aeroplane and injury to occupants.
Prompted by these findings, Safran
Landing Systems, the MLG manufacturer
(formerly Messier-Dowty, Messier-BugattiDowty, and hereafter referred to as ‘‘Safran’’
in this AD), introduced additional quality
steps to eliminate burrs in the manufacturing
process. To address this potential unsafe
condition on delivered MLG sliding tubes,
Airbus issued SB [service bulletin] A320–32–
1441, providing instructions for on-wing
repetitive inspections, and Safran issued SB
200–32–321 and SB 201–32–68, as applicable
to MLG configuration, providing instructions
for inspection in shop.
For the reason described above, this
[EASA] AD partially retains the requirements
of DGAC France AD F–2005–115 (EASA
approval 2005–6032) and EASA AD 2014–
0058, which are superseded, requires
repetitive inspections of the affected MLG
sliding tubes [for cracking] and, depending
on findings, accomplishment of applicable
corrective action(s) [replacement of a cracked
MLG sliding tube with a serviceable MLG
sliding tube]. This [EASA] AD also defines
criteria for installation on an aeroplane of an
affected MLG sliding tube.
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–
0017.
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Explanation of Change to Restated Text
in Paragraph (g) of This Proposed AD
Paragraph (g) of this proposed AD is
a restatement of paragraph (i) of AD
2007–11–11. We have revised the
restated text to remove the reference to
Airbus A318/A319/A320/A321 Aircraft
Maintenance Manual Chapter 32–11–13,
page block 401. Instead, we have added
Note 1 to paragraph (g) of this proposed
AD to specify that guidance on the
replacement specified in paragraph (g)
of this proposed AD can be found in
Airbus A318/A319/A320/A321 Aircraft
Maintenance Manual Chapter 32–11–13,
page block 401.
Model A320–216 Airplanes
The Airbus SAS Model A320–216 was
U.S. type certificated on December 19,
2016. Before that date, any EASA ADs
that affected Model A320–216 airplanes
were included on the Required
Airworthiness Actions List (RAAL). One
or more Model A320–216 airplanes have
subsequently been placed on the U.S.
Register, and will now be included in
FAA AD actions. For Model A320–216
airplanes, the requirements that
correspond to AD 2007–11–11 and AD
2017–01–11 were mandated by the
MCAI via the RAAL. Although that
RAAL requirement is still in effect, for
continuity and clarity we have
identified Model A320–216 airplanes in
paragraph (c) of this AD; the restated
requirements of paragraphs (g) through
(m) in this proposed AD would
therefore apply to those airplanes.
Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information.
• Service Bulletin A320–32–1441,
Revision 01, dated December 14, 2017.
The service information describes
procedures for inspections of the MLG
sliding tubes for cracking and corrective
actions (which includes replacing the
MLG sliding tubes).
• Service Bulletin A320–32A1273,
Revision 02, including Appendix 01,
dated May 26, 2005. The service
information specifies the serial numbers
of the MLG sliding tubes that must be
replaced.
Safran has issued the following
service information. These documents
are distinct since they apply to different
airplane models.
• Service Bulletin 200–32–321,
Revision 2, dated October 3, 2017; and
Service Bulletin 201–32–68, Revision 2,
dated October 3, 2017. These documents
specify the part numbers and serial
numbers of the affected MLG sliding
tubes. These documents are distinct
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since they apply to different airplane
models.
• Service Bulletin 200–32–286,
Revision 3, dated October 3, 2008; and
Service Bulletin 201–32–43, Revision 3,
dated October 3, 2008. These documents
specify the part numbers and serial
numbers of the affected MLG shock
absorbers. These documents are distinct
since they apply to different airplane
models.
This proposed AD would also require
Airbus Service Bulletin A320–32–1416,
including Appendix 01, dated March
10, 2014, which the Director of the
Federal Register approved for
incorporation by reference as of
February 22, 2017 (82 FR 5362, January
18, 2017).
The service information is reasonably
available because the interested parties
Proposed Requirements of This NPRM
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
FAA’s Determination
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all the
relevant information and determined
the unsafe condition described
previously is likely to exist or develop
on other products of the same type
design.
This proposed AD would retain
certain requirements of AD 2007–11–11
and AD 2017–01–11. This proposed AD
would also require repetitive
inspections of affected MLG sliding
tubes for cracking, replacing cracked
MLG sliding tubes with serviceable
MLG sliding tubes, and eventual
replacement of each affected MLG
sliding tube with a MLG sliding tube
that is not affected, which is terminating
action for the repetitive inspections.
Costs of Compliance
We estimate that this proposed AD
affects 1,186 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS
Action
Labor cost
Parts cost
Cost per product
Cost on U.S. operators
Retained actions from AD
2007–11–11 (297 airplanes) [*].
Retained actions from AD
2017–01–11.
New proposed actions ...........
8 work-hours × $85 per hour
= $680.
Up to $45,310 .............
Up to $45,990 .............
Up to $13,659,030 [*].
18 work-hours × $85 per
hour = $1,530.
13 work-hours × $85 per
hour = $1,105.
$0 ................................
$1,530 .........................
$1,814,580.
$0 [**] ...........................
$1,105 .........................
$1,310,530.
* Operators should note that, although all U.S.-registered airplanes are subject to the requirements of AD 2007–11–11, there are only 297 possible affected MLG sliding tubes in the worldwide fleet. We have no way of knowing how many affected MLG sliding tubes, if any, are installed in
U.S.-registered airplanes.
** We have received no definitive data for the parts costs for the replacements.
We estimate the following costs to do
any necessary on-condition action that
would be required based on the results
of any required actions. We have no way
of determining the number of aircraft
that might need this on-condition
action:
ESTIMATED COSTS OF ON-CONDITION ACTION
Labor cost
Parts cost
6 work-hours × $85 per hour = $510 ......................................................................................................................
$0 [*]
Cost per
product
$510
* We have received no definitive data for the parts costs for the on-condition actions.
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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
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safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
This proposed AD is issued in
accordance with authority delegated by
the Executive Director, Aircraft
Certification Service, as authorized by
FAA Order 8000.51C. In accordance
with that order, issuance of ADs is
normally a function of the Compliance
and Airworthiness Division, but during
this transition period, the Executive
Director has delegated the authority to
issue ADs applicable to transport
category airplanes and associated
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appliances to the Director of the System
Oversight Division.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
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Federal Register / Vol. 84, No. 37 / Monday, February 25, 2019 / Proposed Rules
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
3. Will not affect intrastate aviation in
Alaska, and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
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:
a. Removing Airworthiness Directive
(AD) 2007–11–11, Amendment 39–
15068 (72 FR 29241, May 25, 2007); and
AD 2017–01–11, Amendment 39–18778
(82 FR 5362, January 18, 2017); and
■ b. Adding the following new AD:
■
■
Airbus SAS: Docket No. FAA–2019–0017;
Product Identifier 2018–NM–112–AD.
(a) Comments Due Date
We must receive comments by April 11,
2019.
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(b) Affected ADs
This AD replaces the following ADs.
(1) AD 2007–11–11, Amendment 39–15068
(72 FR 29241, May 25, 2007) (‘‘AD 2007–11–
11’’).
(2) AD 2017–01–11, Amendment 39–18778
(82 FR 5362, January 18, 2017) (‘‘AD 2017–
01–11’’).
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(c) Applicability
This AD applies to the Airbus SAS
airplanes identified in paragraphs (c)(1)
through (c)(4) of this AD, certificated in any
category, all manufacturer serial numbers.
(1) Model A318–111, -112, -121, and -122
airplanes.
(2) Model A319–111, -112, -113, -114, -115,
-131, -132, and -133 airplanes.
(3) Model A320–211, -212, -214, -216, -231,
-232, and -233 airplanes.
(4) Model A321–111, -112, -131, -211, -212,
-213, -231, and -232 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 32, Landing gear.
(e) Reason
This AD was prompted by a determination
that cracks were found in the main landing
gear (MLG) sliding tubes due to certain
manufacturing defects that might not be
identified using the current on-wing
scheduled inspections. We are issuing this
AD to address cracking in an MLG sliding
tube, which could lead to failure of an MLG
sliding tube resulting in MLG collapse,
damage to the airplane, and injury to
passengers.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Replacement of AD 2007–11–11,
With Updated References to Service
Information and Specific Delegation
Approval Language
This paragraph restates the requirements of
paragraph (i) of AD 2007–11–11, with
updated references to service information
and specific delegation approval language.
Within 41 months after June 29, 2007 (the
effective date of AD 2007–11–11), replace all
MLG shock absorbers equipped with sliding
tubes having serial numbers listed in Airbus
All Operators Telex (AOT) A320–32A1273,
Revision 01, dated May 6, 2004; or the
Accomplishment Instructions of Airbus
Service Bulletin A320–32A1273, Revision 02,
including Appendix 01, dated May 26, 2005;
with new or serviceable MLG shock
absorbers equipped with sliding tubes having
serial numbers not listed in Airbus AOT
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5963
A320–32A1273, Revision 01, dated May 6,
2004; or the Accomplishment Instructions of
Airbus Service Bulletin A320–32A1273,
Revision 02, including Appendix 01, dated
May 26, 2005; 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.
As of June 29, 2007, only Airbus Service
Bulletin A320–32A1273, Revision 02,
including Appendix 01, dated May 26, 2005,
may be used to determine the affected sliding
tubes.
Note 1 to paragraph (g) of this AD:
Guidance on the replacement specified in
paragraph (g) of this AD can be found in
Airbus A318/A319/A320/A321 Aircraft
Maintenance Manual Chapter 32–11–13, page
block 401.
(h) Retained MLG Sliding Tube Part Number
and Serial Number Identification of AD
2017–01–11, With No Changes
This paragraph restates the requirements of
paragraph (g) of AD 2017–01–11, with no
changes. Within three months after February
22, 2017 (the effective date of AD 2017–01–
11): Do an inspection to identify the part
number and serial number of the MLG
sliding tubes installed on the airplane. A
review of airplane maintenance records is
acceptable in lieu of this inspection if the
part number and serial number of the MLG
sliding tubes can be conclusively determined
from that review.
(i) Retained Identification of Airplanes of
AD 2017–01–11, With No Changes
This paragraph restates the identification
specified in paragraph (h) of AD 2017–01–11,
with no changes. An airplane with a
manufacturer serial number (MSN) not listed
in figure 1 to paragraph (i) of this AD is not
affected by the requirements of paragraph (j)
of this AD, provided it can be determined
that no MLG sliding tube having a part
number and serial number listed in table 1
to paragraphs (i), (j), (l)(1), (l)(2), (m)(1), and
(m)(2) of this AD has been installed on that
airplane since first flight of the airplane.
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Figure 1 to Paragraph (i) of this AD -Affected Airplanes Listed by MSN
Affected Airplanes Listed by MSN
0179
0214
0296
0412
0558
0604
0607
0668
0704
0720
0726
0731
0754
0771
0799
0828
0841
0855
0909
0914
0925
0939
0986
1028
1030
1041
1070
1083
1093
1098
1108
1148
1294
1356
2713
2831
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Jkt 247001
Part Number
Serial N urn ber
201160302
78B
201160302
1016B11
201160302
1144B
201371302
B4493
201371302
B4513
201371302
SS4359
201371302
B4530
201371302
B4517
201371302
B4568
201371302
B4498
201371302
4490B
201371302
B202-4598
201371302
B165-4623
201371302
B244-4766
201371302
B267-4794
201371302
B272-4813
201160302
1108B
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Table 1 to Paragraphs (i), G), (1)(1), (1)(2), (m)(1), and (m)(2) of this AD- Affected
MLG Sliding Tubes
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Part Number
Serial N urn ber
201371304
B041-4871
201371304
B045-4869
201371304
B001-4781
201371304
B051-4892
201371304
B110-1952
201371304
B054-4891
201371304
B063-4921
201371304
B071-4911
201371304
B071-4917
201371304
B080-1933
201371304
Bll7-5010
201371304
B120-4989
201371304
B132-2023
201371304
B114-1956
201371304
B208-2009
201371304
B133-1947
201371304
B154-5037
201371304
B89 4952
201371304
B129-1964
201371304
B227-2010
201371304
B170-5031
201371304
B182-5047
201371304
B239-2053
201371304
201371304
B1401-2856
B1813-3142
201371304
Bll6-5004
201522353
B011-149
201522350
B014-25
201522350
B019-56
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(j) Retained Inspections of AD 2017–01–11,
With No Changes
Service Bulletin A320–32–1416, including
Appendix 01, dated March 10, 2014.
This paragraph restates the requirements of
paragraph (i) of AD 2017–01–11, with no
changes. For each MLG sliding tube
identified as required by paragraph (h) of this
AD, having a part number and serial number
listed in table 1 to paragraphs (i), (j), (l)(1),
(l)(2), (m)(1), and (m)(2) of this AD: Within
3 months after February 22, 2017 (the
effective date of AD 2017–01–11) inspect
affected MLG axles and brake flanges by
doing a detailed visual inspection of the
chromium plates for damage, and a
Barkhausen noise inspection of the sliding
tube axles for damage, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–32–1416, including
Appendix 01, dated March 10, 2014. For
Model A318 series airplanes, use the
procedures specified for Model A319 series
airplanes in Airbus Service Bulletin A320–
32–1416, including Appendix 01, dated
March 10, 2014.
(l) Retained Definition of Serviceable MLG
Sliding Tube of AD 2017–01–11, With No
Changes
This paragraph restates the definition
specified in paragraph (k) of AD 2017–01–11,
with no changes. For the purpose of
paragraph (k) of this AD, a serviceable sliding
tube is defined as a sliding tube that meets
the criterion in either paragraph (l)(1) or (l)(2)
of this AD.
(1) A sliding tube having a part number
and serial number not listed in table 1 to
paragraphs (i), (j), (l)(1), (l)(2), (m)(1), and
(m)(2) of this AD.
(2) A sliding tube having a part number
and serial number listed in table 1 to
paragraphs (i), (j), (l)(1), (l)(2), (m)(1), and
(m)(2) of this AD that has passed the
inspections required by paragraph (j) of this
AD.
(k) Retained Corrective Action of AD 2017–
01–11, With No Changes
This paragraph restates the requirements of
paragraph (j) of AD 2017–01–11, with no
changes. If, during any inspection required
by paragraph (j) of this AD, any damage is
detected: Before further flight, replace the
MLG sliding tube with a serviceable tube, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
32–1416, including Appendix 01, dated
March 10, 2014. For Model A318 series
airplanes, use the procedures specified for
Model A319 series airplanes in Airbus
VerDate Sep<11>2014
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(m) Retained Parts Installation Prohibition
of AD 2017–01–11, With No Changes
This paragraph restates the requirements of
paragraph (l) of AD 2017–01–11, with no
changes.
(1) For airplanes that have an MLG sliding
tube installed that has a part number and
serial number listed in table 1 to paragraphs
(i), (j), (l)(1), (l)(2), (m)(1), and (m)(2) of this
AD: After an airplane is returned to service
following accomplishment of the actions
required by paragraphs (h), (i), and (j) of this
AD, no person may install on any airplane an
MLG sliding tube having a part number and
serial number listed in table 1 to paragraphs
(i), (j), (l)(1), (l)(2), (m)(1), and (m)(2) of this
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AD, unless that sliding tube has passed the
inspection required by paragraph (j) of this
AD.
(2) For airplanes that, as of February 22,
2017 (the effective date of AD 2017–01–11),
do not have an MLG sliding tube installed
that has a part number and serial number
listed in table 1 to paragraphs (i), (j), (l)(1),
(l)(2), (m)(1), and (m)(2) of this AD: No
person may install, on any airplane, an MLG
sliding tube having a part number and serial
number listed in table 1 to paragraphs (i), (j),
(l)(1), (l)(2), (m)(1), and (m)(2) of this AD
unless that sliding tube has passed the
inspection required by paragraph (j) of this
AD.
(n) New Definitions
For the purpose of paragraphs (o), (p), (q),
(r), and (s) of this AD the following
definitions apply.
(1) Affected MLG shock absorber: An MLG
shock absorber having a part number and
serial number as identified in Safran Service
Bulletin 200–32–286, Revision 3, dated
October 3, 2008, for Model A318, A319, and
A320 series airplanes; and Safran Service
Bulletin 201–32–43, Revision 3, dated
October 3, 2008, for Model A321 series
airplanes.
(2) Affected MLG sliding tube: An MLG
sliding tube having a part number and serial
number as identified in Appendix B of Safran
Service Bulletin 200–32–321, Revision 2,
dated October 3, 2017, for Model A318,
A319, and A320 series airplanes; or Safran
Service Bulletin 201–32–68, Revision 2,
dated October 3, 2017, for Model A321 series
airplanes, except those parts that passed an
inspection as specified in Safran Service
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5966
Bulletin 200–32–321; or Safran Service
Bulletin 201–32–68, as applicable, and those
parts that, after that inspection, have been
repaired, using instructions 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.
(3) Serviceable MLG sliding tube: A MLG
sliding tube that is not affected, or an affected
MLG sliding tube, that has not exceeded
10,000 flight cycle since first installation on
an airplane, or an affected MLG sliding tube
that, within the last 5,000 flight cycles before
installation on an airplane, passed an
inspection specified in Airbus Service
Bulletin A320–32–1441.
(o) New Requirement of This AD: Repetitive
Inspections
At the compliance time specified in figure
2 to paragraph (o) of this AD, and thereafter
at intervals not to exceed 5,000 flight cycles:
Do a detailed inspection of each affected
MLG sliding tube, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–32–1441, Revision 01,
dated December 14, 2017.
Note 2 to paragraph (o) of this AD: If no
reliable data regarding the number of flight
cycles accumulated by the MLG sliding tube
are available, operators may refer to the
guidance specified in Chapter 5.2,
‘‘Traceability’’, of Section 1, of Part 1 of the
Airbus A318/A319/A320/A321
Airworthiness Limitations Section.
(2) Do not install an affected MLG sliding
tube on any airplane as specified in
paragraph (r)(2)(i) or (r)(2)(ii) of this AD, as
applicable.
(i) For an airplane with an affected MLG
sliding tube installed as of the effective date
of this AD: After replacement of each affected
MLG sliding tube as required by paragraph
(q) of this AD.
(ii) For an airplane that does not have an
affected MLG sliding tube installed as of the
effective date of this AD: As of the effective
date of this AD.
(v) No Reporting Requirement
Although Airbus Service Bulletin A320–
32–1441, Revision 01, dated December 14,
2017, specifies to submit certain information
to the manufacturer, and specifies that action
as ‘‘RC,’’ (required for compliance) this AD
does not include that requirement.
(p) New Requirement of This AD: Corrective
Actions
(1) If, during any inspection required by
paragraph (o) of this AD, any crack is
detected on an MLG sliding tube: Before
further flight, replace that MLG sliding tube
with a serviceable MLG sliding tube, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
32–1441, Revision 01, dated December 14,
2017.
(2) Replacement of an MLG on an airplane
with an MLG having a serviceable MLG
sliding tube installed is an acceptable
method to comply with the requirements of
paragraph (p)(1) of this AD for that airplane.
(q) New Requirement of This AD: Part
Replacement
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(1) Within 10 years after the effective date
of this AD: Replace each affected MLG
sliding tube with an MLG sliding tube that
is not affected. Installation of an MLG sliding
tube that is not affected on an airplane
constitutes terminating action for the
repetitive inspections required by paragraph
(o) of this AD for that airplane.
(2) Replacement of an MLG on an airplane
with an MLG that does not have an affected
MLG sliding tube installed is an acceptable
method to comply with the requirement of
paragraph (q)(1) of this AD for that airplane.
(r) New Requirement of This AD: Parts
Installation Limitation
(1) As of the effective date of this AD no
person may install on any airplane an
affected MLG shock absorber.
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(s) Identification of Airplanes Not Affected
by Certain Requirements of This AD
An airplane on which Airbus Modification
161202 or Modification 161346 has been
installed in production is not affected by the
requirements of paragraphs (g), (h), (j), (o),
and (q), of this AD, provided it has been
verified that no affected MLG sliding tube is
installed on that airplane.
(t) Credit for Previous Actions
(1) This paragraph provides credit for the
actions required by paragraph (g) of this AD,
if those actions were performed before June
29, 2007, using Airbus AOT A320–32A1273,
Revision 01, dated May 6, 2004.
(2) This paragraph provides credit for the
initial inspection and applicable corrective
actions required by paragraphs (o) and (p) of
this AD if those actions were performed
before the effective date of this AD, using the
Accomplishment Instructions in Airbus
Service Bulletin A320–32–1441, dated
December 28, 2016.
(u) Service Information Exceptions
The service information specified in
paragraph (g) of this AD has instructions to
send any cracked part to Messier-Dowty. This
AD does not include such a requirement, in
accordance with the procedures specified in
paragraph (w)(2) of this AD.
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(w) Other FAA AD Provisions
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Section, Transport Standards Branch, FAA,
has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal
inspector or local Flight Standards District
Office, as appropriate. If sending information
directly to the International Section, send it
to the attention of the person identified in
paragraph (x)(2) of this AD. Information may
be emailed to: 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
2007–11–11 are approved as AMOCs for the
corresponding provisions of paragraph (g) of
this AD.
(iii) AMOCs approved previously for AD
2017–01–11 are approved as AMOCs for the
corresponding provisions of paragraphs (h),
(i), (j), (k), (l), and (m) of this AD.
(2) Contacting the Manufacturer: As of the
effective date of this AD, 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 EASA; or Airbus
SAS’s EASA DOA. If approved by the DOA,
the approval must include the DOAauthorized signature.
(3) Required for Compliance (RC): Except
as required by paragraphs (u) and (v) of this
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Federal Register / Vol. 84, No. 37 / Monday, February 25, 2019 / Proposed Rules
5968
Federal Register / Vol. 84, No. 37 / Monday, February 25, 2019 / Proposed Rules
AD: If any service information contains
procedures or tests that are identified as RC,
those procedures and tests must be done to
comply with this AD; any procedures or tests
that are not identified as RC are
recommended. Those procedures and tests
that are not identified as RC may be deviated
from using accepted methods in accordance
with the operator’s maintenance or
inspection program without obtaining
approval of an AMOC, provided the
procedures and tests identified as RC can be
done and the airplane can be put back in an
airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(x) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2018–0135, dated June 26, 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–2019–0017.
(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.
(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.
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.
[FR Doc. C1–2019–00460 Filed 2–22–19; 8:45 am]
BILLING CODE 1301–00–D
DEPARTMENT OF HEALTH AND
HUMAN SERVICES
Food and Drug Administration
21 CFR Parts 50, 312, and 812
[Docket No. FDA–2018–N–2727]
RIN 0910–AH52
Institutional Review Board Waiver or
Alteration of Informed Consent for
Minimal Risk Clinical Investigations;
Reopening of Comment Period
AGENCY:
Food and Drug Administration,
HHS.
Proposed rule; reopening of
comment period.
ACTION:
Correction
The Food and Drug
Administration (FDA or the Agency) is
reopening the comment period for the
proposed rule that appeared in the
Federal Register of November 15, 2018.
In the Federal Register of December 20,
2018, the Agency extended the
comment period until February 13,
2019. The Agency is taking this action
to reopen the comment period to allow
interested persons additional time to
submit comments due to technical
issues with the Federal eRulemaking
Portal (https://www.regulations.gov) on
February 13, 2019.
DATES: FDA is reopening the comment
period on the proposed rule published
November 15, 2018 (83 FR 57378).
Submit either electronic or written
comments by March 7, 2019.
ADDRESSES: You may submit comments
as follows. Please note that late,
untimely filed comments will not be
considered. Electronic comments must
be submitted on or before March 7,
2019. The https://www.regulations.gov
electronic filing system will accept
comments until 11:59 p.m. Eastern Time
at the end of March 7, 2019. Comments
received by mail/hand delivery/courier
(for written/paper submissions) will be
considered timely if they are
postmarked or the delivery service
acceptance receipt is on or before that
date.
In proposed rule document 2019–
00460 beginning on page 1412 in the
issue of Monday, February 4, 2019,
make the following correction:
On page 1416, in the second column,
the last line of text should read as
follows:
Electronic Submissions
Submit electronic comments in the
following way:
• Federal eRulemaking Portal:
https://www.regulations.gov. Follow the
instructions for submitting comments.
Comments submitted electronically,
Issued in Des Moines, Washington, on
February 1, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–02929 Filed 2–22–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF ENERGY
Federal Energy Regulatory
Commission
18 CFR Parts 141 and 385
[Docket No. RM19–12–000]
Revisions to the Filing Process for
Commission Forms
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‘‘ b 100 hours to prepare and submit
the first filing using XBRL; and’’.
VerDate Sep<11>2014
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SUMMARY:
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including attachments, to https://
www.regulations.gov will be posted to
the docket unchanged. Because your
comment will be made public, you are
solely responsible for ensuring that your
comment does not include any
confidential information that you or a
third party may not wish to be posted,
such as medical information, your or
anyone else’s Social Security number, or
confidential business information, such
as a manufacturing process. Please note
that if you include your name, contact
information, or other information that
identifies you in the body of your
comments, that information will be
posted on https://www.regulations.gov.
• If you want to submit a comment
with confidential information that you
do not wish to be made available to the
public, submit the comment as a
written/paper submission and in the
manner detailed (see ‘‘Written/Paper
Submissions’’ and ‘‘Instructions’’).
Written/Paper Submissions
Submit written/paper submissions as
follows:
• Mail/Hand delivery/Courier (for
written/paper submissions): Dockets
Management Staff (HFA–305), Food and
Drug Administration, 5630 Fishers
Lane, Rm. 1061, Rockville, MD 20852.
• For written/paper comments
submitted to the Dockets Management
Staff, FDA will post your comment, as
well as any attachments, except for
information submitted, marked and
identified, as confidential, if submitted
as detailed in ‘‘Instructions.’’
Instructions: All submissions received
must include the Docket No. FDA–
2018–N–2727 for ‘‘Institutional Review
Board Waiver or Alteration of Informed
Consent for Minimal Risk Clinical
Investigations.’’ Received comments,
those filed in a timely manner (see
ADDRESSES), will be placed in the docket
and, except for those submitted as
‘‘Confidential Submissions,’’ publicly
viewable at https://www.regulations.gov
or at the Dockets Management Staff
between 9 a.m. and 4 p.m., Monday
through Friday.
• Confidential Submissions—To
submit a comment with confidential
information that you do not wish to be
made publicly available, submit your
comments only as a written/paper
submission. You should submit two
copies total. One copy will include the
information you claim to be confidential
with a heading or cover note that states
‘‘THIS DOCUMENT CONTAINS
CONFIDENTIAL INFORMATION.’’ The
Agency will review this copy, including
the claimed confidential information, in
its consideration of comments. The
second copy, which will have the
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]]>Agencies
[Federal Register Volume 84, Number 37 (Monday, February 25, 2019)]
[Proposed Rules]
[Pages 5960-5968]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-02929]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0017; Product Identifier 2018-NM-112-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2007-11-
11 and AD 2017-01-11, which apply to all Airbus SAS Model A318 and
Model A319 series airplanes; Model A320-211, -212, -214, -231, -232,
and -233 airplanes; and Model A321 series airplanes. AD 2007-11-11
requires an inspection to determine the serial number of both main
landing gear (MLG) sliding tubes, repetitive inspections for cracking
of the affected MLG sliding tubes and corrective actions if necessary,
and eventual replacement of both MLG shock absorbers. AD 2017-01-11
requires identification of the part number and serial number of the MLG
sliding tubes; inspection of affected chromium plates and sliding tube
axles for damage; and replacement of the sliding tube if necessary.
Since we issued AD 2007-11-11 and AD 2017-01-11, it was determined that
cracks were found in the MLG sliding tubes due to certain manufacturing
defects that might not be identified using the current on-wing
scheduled inspections. This proposed AD would retain certain
requirements of AD 2007-11-11 and AD 2017-01-11. This proposed AD would
also require repetitive inspections of affected MLG sliding tubes for
cracking, replacement of cracked MLG sliding tubes, and eventual
replacement of each affected MLG sliding tube. We are proposing this AD
to address the unsafe condition on these products.
DATES: We must receive comments on this proposed AD by April 11, 2019.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, 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. You may view this referenced 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.
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-
0017; 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 NPRM, the regulatory evaluation, any comments received, and other
information. The street address for Docket Operations (phone 800-647-
5527) is in the ADDRESSES section. Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; telephone and fax 206-231-3223.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2019-0017;
Product Identifier 2018-NM-112-AD'' at the beginning of your comments.
We specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this proposed AD. We will consider
all comments received by the closing date and may amend this proposed
AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
[[Page 5961]]
Discussion
We issued AD 2007-11-11, Amendment 39-15068 (72 FR 29241, May 25,
2007) (``AD 2007-11-11''), for all Model A318 and Model A319 series
airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes;
and Model A321 series airplanes. AD 2007-11-11 requires a one-time
inspection to determine the serial number of both MLG sliding tubes,
repetitive detailed inspections for cracking of the affected MLG
sliding tubes and corrective actions if necessary, and eventual
replacement of both MLG shock absorbers, which terminates the
repetitive inspection requirements. AD 2007-11-11 resulted from a
determination that inspections and mandatory replacement of the MLG
shock absorbers are necessary. We issued AD 2007-11-11 to address
cracking in an MLG sliding tube, which could result in failure of the
sliding tube, loss of one axle, and consequent reduced controllability
of the airplane.
We also issued AD 2017-01-11, Amendment 39-18778 (82 FR 5362,
January 18, 2017) (``AD 2017-01-11''), for all Model A318 and Model
A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233
airplanes; and Model A321 series airplanes. AD 2017-01-11 requires
identification of the part number and serial number of the MLG sliding
tubes; inspection of affected chromium plates and sliding tube axles
for damage; and replacement of the sliding tube if necessary. AD 2017-
01-11 resulted from a report of a rupture of an MLG sliding tube axle.
We issued AD 2017-01-11 to address cracks in the axle and (partial)
detachment of the axle and wheel from the sliding tube, which could
result in failure of an MLG.
Actions Since AD 2007-11-11 and AD 2017-01-11 Were Issued
Since AD 2007-11-11 and AD 2017-01-11 were issued, during MLG
overhaul, cracks were found in the lower slave link bracket lug holes
on two MLG sliding tubes. Subsequent investigations determined that
these cracks may have developed due to burrs, which could have been
present since manufacture, and it was determined that cracks in the
affected sliding tubes may not be found during the existing on-wing
scheduled inspections.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2018-0135, dated June 26, 2018 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition for all Airbus SAS Model A318 and 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. The MCAI states:
Cracks were reported on [main landing gear] MLG sliding tubes
and the investigations determined metallic inclusion during
production and abnormal grinding operation during overhaul as cause
of these cracks. Prompted by these reports, respectively, [Direction
Generale de l'Aviation Civile] DGAC France issued [French] AD F-
2005-115 (EASA approval 2005-6032) [which corresponds to FAA AD
2007-11-11] and EASA issued AD 2014-0058 [which corresponds to FAA
AD 2017-01-11], both requiring inspections and replacement of
certain MLG sliding tubes.
More recently, during overhaul, cracks were found in the lower
slave link bracket lug holes on two MLG sliding tubes. Subsequent
investigations determined that these cracks may have developed due
to burrs, which could have been present since manufacture. Based on
the fact that the sliding tube is certified as a safe life part,
this is considered to be a non-compliance with the requirements of
[Joint Aviation Requirements] JAR 25.571(c). Cracks in the affected
sliding tubes may not be found during the existing on-wing scheduled
inspections.
This condition, if not detected and corrected, could lead to
sliding tube failure, possibly resulting in MLG collapse, damage to
the aeroplane and injury to occupants.
Prompted by these findings, Safran Landing Systems, the MLG
manufacturer (formerly Messier-Dowty, Messier-Bugatti-Dowty, and
hereafter referred to as ``Safran'' in this AD), introduced
additional quality steps to eliminate burrs in the manufacturing
process. To address this potential unsafe condition on delivered MLG
sliding tubes, Airbus issued SB [service bulletin] A320-32-1441,
providing instructions for on-wing repetitive inspections, and
Safran issued SB 200-32-321 and SB 201-32-68, as applicable to MLG
configuration, providing instructions for inspection in shop.
For the reason described above, this [EASA] AD partially retains
the requirements of DGAC France AD F-2005-115 (EASA approval 2005-
6032) and EASA AD 2014-0058, which are superseded, requires
repetitive inspections of the affected MLG sliding tubes [for
cracking] and, depending on findings, accomplishment of applicable
corrective action(s) [replacement of a cracked MLG sliding tube with
a serviceable MLG sliding tube]. This [EASA] AD also defines
criteria for installation on an aeroplane of an affected MLG sliding
tube.
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-
0017.
Explanation of Change to Restated Text in Paragraph (g) of This
Proposed AD
Paragraph (g) of this proposed AD is a restatement of paragraph (i)
of AD 2007-11-11. We have revised the restated text to remove the
reference to Airbus A318/A319/A320/A321 Aircraft Maintenance Manual
Chapter 32-11-13, page block 401. Instead, we have added Note 1 to
paragraph (g) of this proposed AD to specify that guidance on the
replacement specified in paragraph (g) of this proposed AD can be found
in Airbus A318/A319/A320/A321 Aircraft Maintenance Manual Chapter 32-
11-13, page block 401.
Model A320-216 Airplanes
The Airbus SAS Model A320-216 was U.S. type certificated on
December 19, 2016. Before that date, any EASA ADs that affected Model
A320-216 airplanes were included on the Required Airworthiness Actions
List (RAAL). One or more Model A320-216 airplanes have subsequently
been placed on the U.S. Register, and will now be included in FAA AD
actions. For Model A320-216 airplanes, the requirements that correspond
to AD 2007-11-11 and AD 2017-01-11 were mandated by the MCAI via the
RAAL. Although that RAAL requirement is still in effect, for continuity
and clarity we have identified Model A320-216 airplanes in paragraph
(c) of this AD; the restated requirements of paragraphs (g) through (m)
in this proposed AD would therefore apply to those airplanes.
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information.
Service Bulletin A320-32-1441, Revision 01, dated December
14, 2017. The service information describes procedures for inspections
of the MLG sliding tubes for cracking and corrective actions (which
includes replacing the MLG sliding tubes).
Service Bulletin A320-32A1273, Revision 02, including
Appendix 01, dated May 26, 2005. The service information specifies the
serial numbers of the MLG sliding tubes that must be replaced.
Safran has issued the following service information. These
documents are distinct since they apply to different airplane models.
Service Bulletin 200-32-321, Revision 2, dated October 3,
2017; and Service Bulletin 201-32-68, Revision 2, dated October 3,
2017. These documents specify the part numbers and serial numbers of
the affected MLG sliding tubes. These documents are distinct
[[Page 5962]]
since they apply to different airplane models.
Service Bulletin 200-32-286, Revision 3, dated October 3,
2008; and Service Bulletin 201-32-43, Revision 3, dated October 3,
2008. These documents specify the part numbers and serial numbers of
the affected MLG shock absorbers. These documents are distinct since
they apply to different airplane models.
This proposed AD would also require Airbus Service Bulletin A320-
32-1416, including Appendix 01, dated March 10, 2014, which the
Director of the Federal Register approved for incorporation by
reference as of February 22, 2017 (82 FR 5362, January 18, 2017).
The service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
FAA's Determination
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all the relevant information and determined the unsafe
condition described previously is likely to exist or develop on other
products of the same type design.
Proposed Requirements of This NPRM
This proposed AD would retain certain requirements of AD 2007-11-11
and AD 2017-01-11. This proposed AD would also require repetitive
inspections of affected MLG sliding tubes for cracking, replacing
cracked MLG sliding tubes with serviceable MLG sliding tubes, and
eventual replacement of each affected MLG sliding tube with a MLG
sliding tube that is not affected, which is terminating action for the
repetitive inspections.
Costs of Compliance
We estimate that this proposed AD affects 1,186 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2007-11- 8 work-hours x $85 Up to $45,310..... Up to $45,990..... Up to $13,659,030
11 (297 airplanes) \[*]\. per hour = $680. \[*]\.
Retained actions from AD 2017-01- 18 work-hours x $0................ $1,530............ $1,814,580.
11. $85 per hour =
$1,530.
New proposed actions............ 13 work-hours x $0 [**]........... $1,105............ $1,310,530.
$85 per hour =
$1,105.
----------------------------------------------------------------------------------------------------------------
* Operators should note that, although all U.S.-registered airplanes are subject to the requirements of AD 2007-
11-11, there are only 297 possible affected MLG sliding tubes in the worldwide fleet. We have no way of
knowing how many affected MLG sliding tubes, if any, are installed in U.S.-registered airplanes.
** We have received no definitive data for the parts costs for the replacements.
We estimate the following costs to do any necessary on-condition
action that would be required based on the results of any required
actions. We have no way of determining the number of aircraft that
might need this on-condition action:
Estimated Costs of On-Condition Action
------------------------------------------------------------------------
Cost per
Labor cost Parts cost product
------------------------------------------------------------------------
6 work-hours x $85 per hour = $510...... $0 \[*]\ $510
------------------------------------------------------------------------
* We have received no definitive data for the parts costs for the on-
condition actions.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
This proposed AD is issued in accordance with authority delegated
by the Executive Director, Aircraft Certification Service, as
authorized by FAA Order 8000.51C. In accordance with that order,
issuance of ADs is normally a function of the Compliance and
Airworthiness Division, but during this transition period, the
Executive Director has delegated the authority to issue ADs applicable
to transport category airplanes and associated appliances to the
Director of the System Oversight Division.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866,
[[Page 5963]]
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
3. Will not affect intrastate aviation in Alaska, and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by:
0
a. Removing Airworthiness Directive (AD) 2007-11-11, Amendment 39-15068
(72 FR 29241, May 25, 2007); and AD 2017-01-11, Amendment 39-18778 (82
FR 5362, January 18, 2017); and
0
b. Adding the following new AD:
Airbus SAS: Docket No. FAA-2019-0017; Product Identifier 2018-NM-
112-AD.
(a) Comments Due Date
We must receive comments by April 11, 2019.
(b) Affected ADs
This AD replaces the following ADs.
(1) AD 2007-11-11, Amendment 39-15068 (72 FR 29241, May 25,
2007) (``AD 2007-11-11'').
(2) AD 2017-01-11, Amendment 39-18778 (82 FR 5362, January 18,
2017) (``AD 2017-01-11'').
(c) Applicability
This AD applies to the Airbus SAS airplanes identified in
paragraphs (c)(1) through (c)(4) of this AD, certificated in any
category, all manufacturer serial numbers.
(1) Model A318-111, -112, -121, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes.
(3) Model A320-211, -212, -214, -216, -231, -232, and -233
airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 32, Landing
gear.
(e) Reason
This AD was prompted by a determination that cracks were found
in the main landing gear (MLG) sliding tubes due to certain
manufacturing defects that might not be identified using the current
on-wing scheduled inspections. We are issuing this AD to address
cracking in an MLG sliding tube, which could lead to failure of an
MLG sliding tube resulting in MLG collapse, damage to the airplane,
and injury to passengers.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Replacement of AD 2007-11-11, With Updated References to
Service Information and Specific Delegation Approval Language
This paragraph restates the requirements of paragraph (i) of AD
2007-11-11, with updated references to service information and
specific delegation approval language. Within 41 months after June
29, 2007 (the effective date of AD 2007-11-11), replace all MLG
shock absorbers equipped with sliding tubes having serial numbers
listed in Airbus All Operators Telex (AOT) A320-32A1273, Revision
01, dated May 6, 2004; or the Accomplishment Instructions of Airbus
Service Bulletin A320-32A1273, Revision 02, including Appendix 01,
dated May 26, 2005; with new or serviceable MLG shock absorbers
equipped with sliding tubes having serial numbers not listed in
Airbus AOT A320-32A1273, Revision 01, dated May 6, 2004; or the
Accomplishment Instructions of Airbus Service Bulletin A320-32A1273,
Revision 02, including Appendix 01, dated May 26, 2005; 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. As of June 29, 2007, only Airbus Service Bulletin A320-
32A1273, Revision 02, including Appendix 01, dated May 26, 2005, may
be used to determine the affected sliding tubes.
Note 1 to paragraph (g) of this AD: Guidance on the replacement
specified in paragraph (g) of this AD can be found in Airbus A318/
A319/A320/A321 Aircraft Maintenance Manual Chapter 32-11-13, page
block 401.
(h) Retained MLG Sliding Tube Part Number and Serial Number
Identification of AD 2017-01-11, With No Changes
This paragraph restates the requirements of paragraph (g) of AD
2017-01-11, with no changes. Within three months after February 22,
2017 (the effective date of AD 2017-01-11): Do an inspection to
identify the part number and serial number of the MLG sliding tubes
installed on the airplane. A review of airplane maintenance records
is acceptable in lieu of this inspection if the part number and
serial number of the MLG sliding tubes can be conclusively
determined from that review.
(i) Retained Identification of Airplanes of AD 2017-01-11, With No
Changes
This paragraph restates the identification specified in
paragraph (h) of AD 2017-01-11, with no changes. An airplane with a
manufacturer serial number (MSN) not listed in figure 1 to paragraph
(i) of this AD is not affected by the requirements of paragraph (j)
of this AD, provided it can be determined that no MLG sliding tube
having a part number and serial number listed in table 1 to
paragraphs (i), (j), (l)(1), (l)(2), (m)(1), and (m)(2) of this AD
has been installed on that airplane since first flight of the
airplane.
[[Page 5964]]
[GRAPHIC] [TIFF OMITTED] TP25FE19.000
[[Page 5965]]
[GRAPHIC] [TIFF OMITTED] TP25FE19.001
[[Page 5966]]
[GRAPHIC] [TIFF OMITTED] TP25FE19.002
(j) Retained Inspections of AD 2017-01-11, With No Changes
This paragraph restates the requirements of paragraph (i) of AD
2017-01-11, with no changes. For each MLG sliding tube identified as
required by paragraph (h) of this AD, having a part number and
serial number listed in table 1 to paragraphs (i), (j), (l)(1),
(l)(2), (m)(1), and (m)(2) of this AD: Within 3 months after
February 22, 2017 (the effective date of AD 2017-01-11) inspect
affected MLG axles and brake flanges by doing a detailed visual
inspection of the chromium plates for damage, and a Barkhausen noise
inspection of the sliding tube axles for damage, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A320-32-
1416, including Appendix 01, dated March 10, 2014. For Model A318
series airplanes, use the procedures specified for Model A319 series
airplanes in Airbus Service Bulletin A320-32-1416, including
Appendix 01, dated March 10, 2014.
(k) Retained Corrective Action of AD 2017-01-11, With No Changes
This paragraph restates the requirements of paragraph (j) of AD
2017-01-11, with no changes. If, during any inspection required by
paragraph (j) of this AD, any damage is detected: Before further
flight, replace the MLG sliding tube with a serviceable tube, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-32-1416, including Appendix 01, dated March 10, 2014.
For Model A318 series airplanes, use the procedures specified for
Model A319 series airplanes in Airbus Service Bulletin A320-32-1416,
including Appendix 01, dated March 10, 2014.
(l) Retained Definition of Serviceable MLG Sliding Tube of AD 2017-01-
11, With No Changes
This paragraph restates the definition specified in paragraph
(k) of AD 2017-01-11, with no changes. For the purpose of paragraph
(k) of this AD, a serviceable sliding tube is defined as a sliding
tube that meets the criterion in either paragraph (l)(1) or (l)(2)
of this AD.
(1) A sliding tube having a part number and serial number not
listed in table 1 to paragraphs (i), (j), (l)(1), (l)(2), (m)(1),
and (m)(2) of this AD.
(2) A sliding tube having a part number and serial number listed
in table 1 to paragraphs (i), (j), (l)(1), (l)(2), (m)(1), and
(m)(2) of this AD that has passed the inspections required by
paragraph (j) of this AD.
(m) Retained Parts Installation Prohibition of AD 2017-01-11, With No
Changes
This paragraph restates the requirements of paragraph (l) of AD
2017-01-11, with no changes.
(1) For airplanes that have an MLG sliding tube installed that
has a part number and serial number listed in table 1 to paragraphs
(i), (j), (l)(1), (l)(2), (m)(1), and (m)(2) of this AD: After an
airplane is returned to service following accomplishment of the
actions required by paragraphs (h), (i), and (j) of this AD, no
person may install on any airplane an MLG sliding tube having a part
number and serial number listed in table 1 to paragraphs (i), (j),
(l)(1), (l)(2), (m)(1), and (m)(2) of this AD, unless that sliding
tube has passed the inspection required by paragraph (j) of this AD.
(2) For airplanes that, as of February 22, 2017 (the effective
date of AD 2017-01-11), do not have an MLG sliding tube installed
that has a part number and serial number listed in table 1 to
paragraphs (i), (j), (l)(1), (l)(2), (m)(1), and (m)(2) of this AD:
No person may install, on any airplane, an MLG sliding tube having a
part number and serial number listed in table 1 to paragraphs (i),
(j), (l)(1), (l)(2), (m)(1), and (m)(2) of this AD unless that
sliding tube has passed the inspection required by paragraph (j) of
this AD.
(n) New Definitions
For the purpose of paragraphs (o), (p), (q), (r), and (s) of
this AD the following definitions apply.
(1) Affected MLG shock absorber: An MLG shock absorber having a
part number and serial number as identified in Safran Service
Bulletin 200-32-286, Revision 3, dated October 3, 2008, for Model
A318, A319, and A320 series airplanes; and Safran Service Bulletin
201-32-43, Revision 3, dated October 3, 2008, for Model A321 series
airplanes.
(2) Affected MLG sliding tube: An MLG sliding tube having a part
number and serial number as identified in Appendix B of Safran
Service Bulletin 200-32-321, Revision 2, dated October 3, 2017, for
Model A318, A319, and A320 series airplanes; or Safran Service
Bulletin 201-32-68, Revision 2, dated October 3, 2017, for Model
A321 series airplanes, except those parts that passed an inspection
as specified in Safran Service
[[Page 5967]]
Bulletin 200-32-321; or Safran Service Bulletin 201-32-68, as
applicable, and those parts that, after that inspection, have been
repaired, using instructions 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) Serviceable MLG sliding tube: A MLG sliding tube that is not
affected, or an affected MLG sliding tube, that has not exceeded
10,000 flight cycle since first installation on an airplane, or an
affected MLG sliding tube that, within the last 5,000 flight cycles
before installation on an airplane, passed an inspection specified
in Airbus Service Bulletin A320-32-1441.
(o) New Requirement of This AD: Repetitive Inspections
At the compliance time specified in figure 2 to paragraph (o) of
this AD, and thereafter at intervals not to exceed 5,000 flight
cycles: Do a detailed inspection of each affected MLG sliding tube,
in accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-32-1441, Revision 01, dated December 14, 2017.
[GRAPHIC] [TIFF OMITTED] TP25FE19.003
Note 2 to paragraph (o) of this AD: If no reliable data
regarding the number of flight cycles accumulated by the MLG sliding
tube are available, operators may refer to the guidance specified in
Chapter 5.2, ``Traceability'', of Section 1, of Part 1 of the Airbus
A318/A319/A320/A321 Airworthiness Limitations Section.
(p) New Requirement of This AD: Corrective Actions
(1) If, during any inspection required by paragraph (o) of this
AD, any crack is detected on an MLG sliding tube: Before further
flight, replace that MLG sliding tube with a serviceable MLG sliding
tube, in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A320-32-1441, Revision 01, dated December 14, 2017.
(2) Replacement of an MLG on an airplane with an MLG having a
serviceable MLG sliding tube installed is an acceptable method to
comply with the requirements of paragraph (p)(1) of this AD for that
airplane.
(q) New Requirement of This AD: Part Replacement
(1) Within 10 years after the effective date of this AD: Replace
each affected MLG sliding tube with an MLG sliding tube that is not
affected. Installation of an MLG sliding tube that is not affected
on an airplane constitutes terminating action for the repetitive
inspections required by paragraph (o) of this AD for that airplane.
(2) Replacement of an MLG on an airplane with an MLG that does
not have an affected MLG sliding tube installed is an acceptable
method to comply with the requirement of paragraph (q)(1) of this AD
for that airplane.
(r) New Requirement of This AD: Parts Installation Limitation
(1) As of the effective date of this AD no person may install on
any airplane an affected MLG shock absorber.
(2) Do not install an affected MLG sliding tube on any airplane
as specified in paragraph (r)(2)(i) or (r)(2)(ii) of this AD, as
applicable.
(i) For an airplane with an affected MLG sliding tube installed
as of the effective date of this AD: After replacement of each
affected MLG sliding tube as required by paragraph (q) of this AD.
(ii) For an airplane that does not have an affected MLG sliding
tube installed as of the effective date of this AD: As of the
effective date of this AD.
(s) Identification of Airplanes Not Affected by Certain Requirements of
This AD
An airplane on which Airbus Modification 161202 or Modification
161346 has been installed in production is not affected by the
requirements of paragraphs (g), (h), (j), (o), and (q), of this AD,
provided it has been verified that no affected MLG sliding tube is
installed on that airplane.
(t) Credit for Previous Actions
(1) This paragraph provides credit for the actions required by
paragraph (g) of this AD, if those actions were performed before
June 29, 2007, using Airbus AOT A320-32A1273, Revision 01, dated May
6, 2004.
(2) This paragraph provides credit for the initial inspection
and applicable corrective actions required by paragraphs (o) and (p)
of this AD if those actions were performed before the effective date
of this AD, using the Accomplishment Instructions in Airbus Service
Bulletin A320-32-1441, dated December 28, 2016.
(u) Service Information Exceptions
The service information specified in paragraph (g) of this AD
has instructions to send any cracked part to Messier-Dowty. This AD
does not include such a requirement, in accordance with the
procedures specified in paragraph (w)(2) of this AD.
(v) No Reporting Requirement
Although Airbus Service Bulletin A320-32-1441, Revision 01,
dated December 14, 2017, specifies to submit certain information to
the manufacturer, and specifies that action as ``RC,'' (required for
compliance) this AD does not include that requirement.
(w) Other FAA AD Provisions
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Section, Transport Standards Branch, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Section, send it to the attention of
the person identified in paragraph (x)(2) of this AD. Information
may be emailed to: 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 2007-11-11 are approved as
AMOCs for the corresponding provisions of paragraph (g) of this AD.
(iii) AMOCs approved previously for AD 2017-01-11 are approved
as AMOCs for the corresponding provisions of paragraphs (h), (i),
(j), (k), (l), and (m) of this AD.
(2) Contacting the Manufacturer: As of the effective date of
this AD, 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 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): Except as required by
paragraphs (u) and (v) of this
[[Page 5968]]
AD: If any service information contains procedures or tests that are
identified as RC, those procedures and tests must be done to comply
with this AD; any procedures or tests that are not identified as RC
are recommended. Those procedures and tests that are not identified
as RC may be deviated from using accepted methods in accordance with
the operator's maintenance or inspection program without obtaining
approval of an AMOC, provided the procedures and tests identified as
RC can be done and the airplane can be put back in an airworthy
condition. Any substitutions or changes to procedures or tests
identified as RC require approval of an AMOC.
(x) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2018-0135, dated June 26, 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-2019-0017.
(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.
(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. 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.
Issued in Des Moines, Washington, on February 1, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-02929 Filed 2-22-19; 8:45 am]
BILLING CODE 4910-13-P
