Airworthiness Directives; Airbus SAS Airplanes, 56704-56709 [2018-24688]
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56704
Federal Register / Vol. 83, No. 220 / Wednesday, November 14, 2018 / Rules and Regulations
under the criteria of the Regulatory
Flexibility Act.
Instructions of Airbus Service Bulletin A350–
53–P024, dated April 3, 2018.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
(h) 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 (i)(2) of this AD. Information may
be emailed to: 9-ANM–116-AMOCREQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Section,
Transport Standards Branch, FAA; or 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 DOAauthorized signature.
(3) Required for Compliance (RC): If any
service information contains procedures or
tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
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):
■
2018–23–07 Airbus SAS: Amendment 39–
19493; Docket No. FAA–2018–0758;
Product Identifier 2018–NM–093–AD.
(a) Effective Date
This AD is effective December 19, 2018.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus SAS Model
A350–941 airplanes, certificated in any
category, except those on which Airbus
modification 110319 or Airbus modification
110348 has been embodied in production.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by a review of the
Airbus A350 structure design principles
database for type definition that revealed that
the balancer fitting part, installed on the tail
cone, lower section of frame (FR) 103, has
several corrosion-resistant stainless steel nuts
installed on elementary aluminum parts, and
this configuration does not meet the
requirements for protection against corrosion.
We are issuing this AD to address this
condition, which if not corrected, could
reduce the structural integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(i) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2018–0123, dated June 4, 2018, for related
information. This MCAI may be found in the
AD docket on the internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2018–0758.
(2) For more information about this AD,
contact Kathleen Arrigotti, Aerospace
Engineer, International Section, Transport
Standards Branch, FAA, 2200 South 216th
St., Des Moines, WA 98198; telephone and
fax 206–231–3218.
(g) Required Action
Within 72 months since the date of
issuance of the original airworthiness
certificate or the date of issuance of the
original export certificate of airworthiness,
apply additional overcoat sealant and elastic
varnish to the fastener heads and the anchor
nuts of the balancer fitting at FR 103, in
accordance with the Accomplishment
(j) 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.
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(i) Airbus Service Bulletin A350–53–P024,
dated April 3, 2018.
(ii) [Reserved]
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAL, Rond-Point Emile Dewoitine
No: 2, 31700 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 45 80; email continuedairworthiness.a350@airbus.com; internet
https://www.airbus.com.
(4) You may view this service information
at the FAA, Transport Standards Branch,
2200 South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Des Moines, Washington, on
November 2, 2018.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft
Certification Service.
[FR Doc. 2018–24683 Filed 11–13–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0297; Product
Identifier 2017–NM–181–AD; Amendment
39–19497; AD 2018–23–11]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Airbus SAS Model 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.
This AD was prompted by
investigations that revealed that the
cover seal of the brake dual distribution
valve (BDDV) was damaged and did not
ensure efficient sealing. This AD
requires identifying the BDDV part
number installed on the airplane, and
modifying or replacing BDDVs having
certain part numbers. We are issuing
this AD to address the unsafe condition
on these products.
DATES: This AD is effective December
19, 2018.
SUMMARY:
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Federal Register / Vol. 83, No. 220 / Wednesday, November 14, 2018 / Rules and Regulations
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of December 19, 2018.
ADDRESSES: For service information
identified in this final rule, 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.airwortheas@airbus.com; internet https://
www.airbus.com. You may view this
service information at the FAA,
Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available on the internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2018–
0297.
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0297; 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 (phone: 800–647–5527) is
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
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
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Airbus SAS Model
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 17, 2018 (83
FR 16799). The NPRM was prompted by
investigations that revealed that the
cover seal of the BDDV was damaged
and did not ensure efficient sealing. The
NPRM proposed to require identifying
the BDDV part number installed on the
airplane, and modifying or replacing
BDDVs having certain part numbers.
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We are issuing this AD to address
water ingestion in the BDDV, freezing of
the BDDV in flight, and consequent loss
of braking system function after landing.
These conditions could possibly result
in damage to the airplane and injury to
occupants.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2017–0119,
dated July 11, 2017 (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, –231, –232, and –233 airplanes;
and Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 airplanes.
The MCAI states:
In 1998, an operator experienced a dual
loss of braking systems. Investigation results
revealed that the cover seal of the BDDV was
damaged and did not ensure the sealing
efficiency.
This condition, if not corrected, could lead
to water ingestion in the BDDV, freezing of
the BDDV in flight, and consequent loss of
braking system function after landing,
possibly resulting in damage to the aeroplane
and injury to occupants.
To address this potential unsafe condition,
Airbus issued Alert Operator Telex (AOT)
32–19 and Service Bulletin (SB) A320–32–
1199, providing instructions for repetitive
functional tests. In addition, Airbus
developed mod 28301 and published SB
A320–32–1203 to provide modification
instructions.
Consequently, DGAC [Directorate General
for Civil Aviation] France issued AD 2000–
258–146 [which corresponds to FAA AD
2001–15–10, Amendment 39–12344 (66 FR
39413, July 31, 2001) (‘‘AD 2001–15–10’’)] to
require repetitive functional tests as a
temporary solution (valid for a period of 15
months) and modification of the BDDV with
a new cover and installation of a draining
tube with a cap, which was terminating
action for the repetitive functional tests. For
pre-mod 27833 and pre-SB A320–32–1200
aeroplanes, repetitive inspections per SB
A320–32–1199 were required as interim
action, prior to the terminating action
modification per SB A320–32–1203.
After that [DGAC] AD was issued,
following a new event, Airbus developed a
new modification of the BDDV drain tube
which leaves it open, ensuring continuous
drainage of any ingested water, thereby
preventing freezing of the brake system.
Consequently, EASA issued AD 2014–0251
(later revised), partially retaining the
requirements of DGAC France AD 2000–258–
146, which was superseded, and requiring an
additional modification of the BDDV drain
tube and re-identification of the BDDV.
Since EASA AD 2014–0251R1 [which
corresponds to FAA AD 2016–06–13,
Amendment 39–18444 (81 FR 17365, March
29, 2016) (‘‘AD 2016–06–13’’)] was issued,
comments were received that indicated a
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56705
need for correction and clarification.
Consequently, this [EASA] AD retains the
requirements of EASA AD 2014–0251R1,
which is superseded, and expands the list of
BDDV Part Numbers (P/N) which must be
removed from service and are no longer
eligible for installation on an aeroplane [and
includes replacing affected part numbers as
an option]. This [EASA] AD also clarifies the
intended requirements of EASA AD 2014–
0251 and introduces editorial changes, not
affecting the requirements.
You may examine the MCAI in the
AD docket on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0297.
Comments
We 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.
Supportive Comments
Air Line Pilots Association,
International stated its support for the
NPRM. In addition, United Airlines
(UAL) stated it concurs with the
expansion of the affected BDDV part
numbers as identified in Figure 1 to
paragraphs (g) and (h) of the proposed
AD.
Request To Withdraw the NPRM
Delta Air lines (DAL) requested that
we withdraw the NPRM. DAL stated
that the NPRM does not address an
unsafe condition and, therefore, it is
unnecessary. DAL commented that
airplanes included in paragraph (c) of
the proposed AD are already required to
comply with the actions required by AD
2001–15–10, depending on modification
status. DAL also commented that the
NPRM does not add any airplanes to the
applicability of AD 2001–15–10 and
2016–06–13. DAL stated that tracking
compliance with the redundant
requirements of the proposed AD would
place an undue burden on airlines.
DAL stated that paragraphs (j)(1)(i)
and (j)(2)(i) of the proposed AD give
credit for actions accomplished using
previously issued service information.
DAL commented that FAA Letter ANM–
116–16–491, dated September 27, 2016,
gives operators the authority to
accomplish paragraph (g) of AD 2016–
06–13 as an alternative method of
compliance (AMOC), and it is also a
terminating action for the actions
required by paragraphs (e) and (f) of AD
2001–15–10. DAL stated that the
compliance times for AD 2001–15–10
and AD 2016–06–13 have passed,
therefore, all airplanes must be in
compliance.
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Federal Register / Vol. 83, No. 220 / Wednesday, November 14, 2018 / Rules and Regulations
We partially agree with the
commenter’s request. We agree that
airplanes included in paragraph (c) of
this AD are also required to comply
with AD 2001–15–10 and AD 2016–06–
13, and that this AD does not add any
new Model airplanes related to those
listed in AD 2001–15–10 and AD 2016–
06–13. However, as stated in paragraph
(i) of this AD, compliance with
paragraph (g) of this AD terminates the
requirements in paragraphs (e) and (f) of
AD 2001–15–10 (which terminates all
requirements of AD 2001–15–10 for
Model A318, A319 and A320 series
airplanes) and all requirements of AD
2016–06–13. For clarification, we have
modified paragraph (i)(1) of this AD to
state that compliance with paragraph (g)
of this AD terminates all requirements
of AD 2001–15–10 for Model A319,
A320 and A321 series airplanes. We
agree that operators will be required to
track certain ADs with expired
compliance times, but we are in process
of rescinding some of those ADs through
future rulemaking. We agree that AMOC
letter ANM–116–16–491 dated
September 27, 2016, will still be
applicable to AD 2016–06–13.
We disagree with the commenter’s
request to withdraw this AD. We, along
with EASA, have determined that water
ingestion in the BDDV, freezing of the
BDDV in flight, and consequent loss of
braking system function after landing,
could possibly result in damage to the
airplane and injury to occupants, and
therefore, does constitute an unsafe
condition, and that additional
mandatory actions in this AD are
required to mitigate the risks associated
with the unsafe condition. Further, even
if the current U.S.-Registered fleet is in
compliance with the requirements of
this AD, the issuance of the rule is still
necessary to ensure that any affected
airplane imported and placed on the
U.S. Register in the future would be
required to be in compliance as well.
This AD expands the list of BDDV part
numbers, which must be removed from
service and are no longer eligible for
installation on an airplane. Therefore,
all U.S.-Registered airplanes might not
be in compliance with the actions of
this AD even when in full compliance
with AD 2001–15–10 and AD 2016–06–
13. However, if DAL concludes that it is
in compliance with the requirements of
this AD, then it may utilize the
provision in paragraph (f) to
demonstrate compliance. We have not
changed this AD in this regard.
Request To Correct Certain Wording
DAL observed that the word ‘‘actions’’
was inadvertently omitted from the first
sentence in paragraph (g)(2) of the
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proposed AD after the word
‘‘corrective.’’ We agree and have added
the missing word accordingly.
Request To Revise Certain Wording for
Clarification
UAL requested that we revise the
wording in certain paragraphs of the
proposed AD for clarification. UAL
suggested that paragraph (g)(3) of the
proposed AD be reworded because the
way it is currently written, it could be
interpreted as ‘‘a part number specified
as new P/N in figure 2 to paragraphs
(g)(3) and (h)(2)’’ cannot be installed.
UAL also suggested that paragraph (h)
of the proposed AD be revised to
eliminate paragraphs (h)(1) and (h)(2)
and be reworded to simply prohibit the
installation of affected BDDVs as
specified in figure 1 to paragraphs (g)
and (h) of the proposed AD.
We partially agree to the commenter’s
requests. We agree to clarify paragraph
(g)(3) of this AD. We have revised
paragraph (g)(3) of this AD to clarify that
operators should replace the old part
number with a new part number as
specified in figure 2 to paragraphs (g)(3)
and (h)(2) of this AD.
However, we disagree to simply
prohibit installation of discrepant parts
that are specified in figure 1 to
paragraphs (g) and (h) of this AD from
the effective date of this AD. Paragraph
(h) provides operators flexibility by
providing the full compliance time as
specified in paragraph (g) to modify or
replace discrepant parts, unless the
discrepant part is either currently
installed as of the effective date of this
AD and is subsequently modified or
replaced (after the effective date of this
AD) as stated in paragraph (h)(1) of this
AD, or has already been modified or
replaced as of the effective date of this
AD as stated in paragraph (h)(2) of this
AD. Operators have the discretion to
prohibit operation with a discrepant
part in figure 1 to paragraphs (g) and (h)
of this AD from the effective date of this
AD. We have not changed the AD in this
regard.
Request To Clarify the Compliance
Requirements
JetBlue requested that we clarify the
compliance requirements in paragraphs
(g)(2), (g)(3), and (h)(2) of the proposed
AD because of contradictory
requirements. The commenter did not
clearly identify which requirements
needed clarification.
We do not agree to revise paragraph
(g)(2) of this AD. This AD and the
Accomplishment Instructions of Airbus
Service Bulletin A320–32–1415,
Revision 02, dated December 10, 2015,
specify that, if corrosion is found in a
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non-permitted area, replace the BDDV
before further flight. We have not
changed this AD in this regard.
As we stated previously, we have
revised paragraph (g)(3) of this AD to
clarify that operators should replace the
old part number with a new part
number as specified in figure 2 to
paragraphs (g)(3) and (h)(2) of this AD.
We agree to clarify the compliance
requirements of paragraph (h)(2) of this
AD. As stated in the previous comment
response, paragraph (h) is intended to
provide operators flexibility by
providing the full compliance time as
specified in paragraph (g) to modify or
replace discrepant parts. However,
paragraph (h)(2) of this AD specifically
prohibits installation of a discrepant
part as of the effective date of this AD
if the discrepant part has already been
modified or replaced as of the effective
date of this AD. Paragraph (h)(1) of this
AD prohibits installation of a discrepant
part as of the effective date of this AD,
if a discrepant part is currently installed
as of the effective of this AD, but is
modified or replaced after the effective
date of this AD. Operators have the
discretion to prohibit operation with a
discrepant part in figure 1 to paragraphs
(g) and (h) of this AD from the effective
date of this AD. We have not changed
the AD in this regard.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this
final rule with the changes described
previously and minor editorial changes.
We have determined that these minor
changes:
• Are consistent with the intent that
was proposed in the NPRM for
addressing the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this final rule.
Related Service Information Under 1
CFR Part 51
Airbus SAS has issued Service
Bulletin A320–32–1203, Revision 02,
dated February 9, 2001. This service
information describes procedures for
identifying the BDDV part number
installed on the airplane, and modifying
or replacing BDDVs having certain part
numbers.
Airbus SAS has also issued Service
Bulletin A320–32–1415, Revision 02,
dated December 10, 2015. This service
information describes procedures for
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modifying and re-identifying the BDDV.
The modification includes modifying
the drain hose of the BDDV, and doing
all related investigative and corrective
actions if applicable. The related
investigative actions include an
inspection for corrosion. Corrective
actions include replacing the BDDV.
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.
56707
Costs of Compliance
We estimate that this AD affects 1,136
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Parts cost
Cost per
product
Identification and modification or replacement.
Up to 6 work-hours × $85 per hour =
$510.
Up to $395 .......
Up to $905 .......
We have received no definitive data
that would enable us 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.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701:
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
This AD is issued in accordance with
authority delegated by the Executive
Director, Aircraft Certification Service,
as authorized by FAA Order 8000.51C.
In accordance with that order, issuance
of ADs is normally a function of the
Compliance and Airworthiness
Division, but during this transition
period, the Executive Director has
delegated the authority to issue ADs
applicable to transport category
airplanes and associated appliances to
the Director of the System Oversight
Division.
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
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distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
the DOT Regulatory Policies and
Procedures (44 FR 11034, February 26,
1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
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):
■
2018–23–11 Airbus SAS: Amendment 39–
19497; Docket No. FAA–2018–0297;
Product Identifier 2017–NM–181–AD.
(a) Effective Date
This AD is effective December 19, 2018.
(b) Affected ADs
This AD affects AD 2001–15–10,
Amendment 39–12344 (66 FR 39413, July 31,
2001) (‘‘AD 2001–15–10’’), and AD 2016–06–
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Cost on U.S.
operators
Up to $1,028,080.
13, Amendment 39–18444 (81 FR 17365,
March 29, 2016) (‘‘AD 2016–06–13’’).
(c) Applicability
This AD applies to the airplanes identified
in paragraphs (c)(1) through (c)(3) of this AD,
certificated in any category, all manufacturer
serial numbers, except those on which
Airbus Modification 26925 has been
embodied in production, which introduces a
modified alternate braking system that
removes the brake dual distribution valve
(BDDV).
(1) Airbus SAS Model A319–111, –112,
–113, –114, –115, –131, –132, and –133
airplanes.
(2) Airbus SAS Model A320–211, –212,
–214, –231, –232, and –233 airplanes.
(3) Airbus SAS 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 investigations
that revealed that the cover seal of the brake
dual distribution valve (BDDV) was damaged
and did not ensure efficient sealing. We are
issuing this AD to prevent water ingestion in
the BDDV, freezing of the BDDV in flight, and
consequent loss of braking system function
after landing. These conditions could
possibly result in damage to the airplane and
injury to occupants.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Identification and Modification or
Replacement
Within 3 months after the effective date of
this AD, identify the BDDV part number
installed on the airplane. For each affected
BDDV part number specified in figure 1 to
paragraphs (g) and (h) of this AD, within 3
months after the effective date of this AD, do
the actions in paragraph (g)(1), (g)(2), or (g)(3)
of this AD. A review of airplane maintenance
records is acceptable to identify the BDDV
part number if the part number of the BDDV
can be conclusively determined from that
review.
E:\FR\FM\14NOR1.SGM
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(1) Modify and re-identify the affected
BDDV, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–32–1203, Revision 02,
dated February 9, 2001.
(2) Modify and re-identify the affected
BDDV, and do all applicable related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
32–1415, Revision 02, dated December 10,
2015. Do all applicable related investigative
and corrective actions before further flight.
(3) Replace the affected BDDV with a
BDDV having a part number not specified in
figure 1 to paragraphs (g) and (h) of this AD,
or replace the old part number with a new
part number as specified in figure 2 to
paragraphs (g)(3) and (h)(2) of this AD. Do the
replacement 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.
(h) Parts Installation Prohibition
(i) Terminating Action for Other ADs
(j) Credit for Previous Actions
(1) This paragraph provides credit for
actions required by paragraph (g)(1) of this
AD, if those actions were performed before
the effective date of this AD using the service
information in paragraphs (j)(1)(i) or (j)(1)(ii)
of this AD.
(i) Airbus Service Bulletin A320–32–1203,
dated June 4, 1999, which was incorporated
by reference in AD 2001–15–10.
(ii) Airbus Service Bulletin A320–32–1203,
Revision 01, dated October 12, 2000.
(2) This paragraph provides credit for
actions required by paragraph (g)(2) of this
AD, if those actions were performed before
the effective date of this AD using the service
information in paragraphs (j)(2)(i) or (j)(2)(ii)
of this AD.
(i) Airbus Service Bulletin A320–32–1415,
dated September 2, 2014, which was
incorporated by reference in AD 2016–06–13.
(ii) Airbus Service Bulletin A320–32–1415,
Revision 01, dated April 23, 2015.
(1) Doing the actions in paragraph (g) of
this AD terminates the requirements in
paragraphs (e) and (f) of AD 2001–15–10 for
Model A319, A320 and A321 series
airplanes.
(2) Doing the actions in paragraph (g) of
this AD terminates all of the requirements of
AD 2016–06–13.
(k) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Section, Transport Standards Branch, FAA,
has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal
inspector or local Flight Standards District
Office, as appropriate. If sending information
directly to the International Section, send it
to the attention of the person identified in
paragraph (l)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Section,
Transport Standards Branch, FAA; or the
EASA; or Airbus SAS’s EASA DOA. If
approved by the DOA, the approval must
include the DOA-authorized signature.
(3) Required for Compliance (RC): If any
service information contains procedures or
tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
As of the applicable time specified in
paragraph (h)(1) or (h)(2) of this AD, no
person may install a BDDV having a part
number specified in figure 1 to paragraphs (g)
and (h) of this AD, on any airplane.
(1) For any airplane that, on the effective
date of this AD, has a BDDV installed with
a part number specified in figure 1 to
paragraphs (g) and (h) of this AD: After
modification or replacement of the BDDV, as
required by paragraph (g) of this AD.
(2) For any airplane that, on the effective
date of this AD, has a BDDV installed or
replaced with a part number specified as
‘new P/N’ in figure 2 to paragraphs (g)(3) and
(h)(2) of this AD, or has a BDDV installed or
replaced with a part number not specified in
figure 1 to paragraphs (g) and (h) of this AD:
As of the effective date of this AD.
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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.
(l) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2017–0119, dated July 11, 2017, for related
information. This MCAI may be found in the
AD docket on the internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2018–0297.
(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) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (m)(3) and (m)(4) of this AD.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A320–32–1203,
Revision 02, dated February 9, 2001.
(ii) Airbus Service Bulletin A320–32–1415,
Revision 02, dated December 10, 2015.
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EIAS, Rond-Point Emile Dewoitine
No: 2, 31700 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; internet https://www.airbus.com.
(4) You may view this service information
at the FAA, Transport Standards Branch,
2200 South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Des Moines, Washington, on
November 5, 2018.
Christopher Spangenberg,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–24688 Filed 11–13–18; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0637; Product
Identifier 2018–NM–091–AD; Amendment
39–19496; AD 2018–23–10]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Airbus SAS Model A350–941 airplanes.
This AD was prompted by leakage of
shrouded pipe T-boxes in the potable
water system. This AD requires
replacement of the affected potable
water T-boxes and clamps with new
parts. We are issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective December
19, 2018.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of December 19, 2018.
ADDRESSES: For service information
identified in this final rule, contact
Airbus SAS, Airworthiness Office—
EAL, Rond-Point Emile Dewoitine No:
2, 31700 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5
61 93 45 80; email continuedairworthiness.a350@airbus.com;
internet https://www.airbus.com. You
may view this service information at the
FAA, Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available on the internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2018–
0637.
SUMMARY:
Examining the AD Docket
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0637; 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 (phone: 800–647–5527) is
U.S. Department of Transportation,
Docket Operations, M–30, West
PO 00000
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Fmt 4700
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56709
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Kathleen Arrigotti, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3218.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Airbus SAS Model
A350–941 airplanes. The NPRM
published in the Federal Register on
August 2, 2018 (83 FR 37766). The
NPRM was prompted by leakage of
shrouded pipe T-boxes in the potable
water system. The NPRM proposed to
require replacement of the affected
potable water T-boxes and clamps with
new parts.
We are issuing this AD to address the
possible leakage of water into the
avionics bay. This condition, if not
corrected, could lead to the loss of
systems/equipment located inside the
avionics bay and possible loss of control
of the airplane.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2018–
0111R1, dated May 30, 2018 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Airbus SAS Model A350–941
airplanes. The MCAI states:
During a pressure test on the A350 Final
Assembly Line (FAL), leakage was observed
on the potable water system shrouded pipes,
due to a crack failure on the T-Boxes.
Leakage of a primary pipe may cause water
ingress into the avionics bay. Additionally,
during another pressure proof test on the
A350 FAL, loss of torque was detected on the
clamps used to attach the shrouded pipes on
the T-Boxes.
This condition, if not corrected, could lead
to loss of systems/equipment located inside
the avionics bay, possibly resulting in an
unsafe condition.
Prompted by these findings, Airbus
developed improved potable water T-Boxes
and clamps, which are embodied in
production through Airbus mod 111435 or
mod 111440, and introduced in service
through the SB [Service Bulletin A350–38–
P004].
For the reasons described above, this
[EASA] AD requires replacement of the
affected potable water shrouded pipe
T-Boxes and clamps with new parts.
This [EASA] AD was revised to exclude
post-mod 111440 aeroplanes from the
Applicability.
E:\FR\FM\14NOR1.SGM
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]]>Agencies
[Federal Register Volume 83, Number 220 (Wednesday, November 14, 2018)]
[Rules and Regulations]
[Pages 56704-56709]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-24688]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0297; Product Identifier 2017-NM-181-AD; Amendment
39-19497; AD 2018-23-11]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
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. This AD was prompted by
investigations that revealed that the cover seal of the brake dual
distribution valve (BDDV) was damaged and did not ensure efficient
sealing. This AD requires identifying the BDDV part number installed on
the airplane, and modifying or replacing BDDVs having certain part
numbers. We are issuing this AD to address the unsafe condition on
these products.
DATES: This AD is effective December 19, 2018.
[[Page 56705]]
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of December 19,
2018.
ADDRESSES: For service information identified in this final rule,
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 [email protected];
internet https://www.airbus.com. You may view this service information
at the FAA, Transport Standards Branch, 2200 South 216th St., Des
Moines, WA. For information on the availability of this material at the
FAA, call 206-231-3195. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0297.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0297; 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 (phone: 800-647-
5527) is U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: 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
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to certain Airbus SAS Model
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 17,
2018 (83 FR 16799). The NPRM was prompted by investigations that
revealed that the cover seal of the BDDV was damaged and did not ensure
efficient sealing. The NPRM proposed to require identifying the BDDV
part number installed on the airplane, and modifying or replacing BDDVs
having certain part numbers.
We are issuing this AD to address water ingestion in the BDDV,
freezing of the BDDV in flight, and consequent loss of braking system
function after landing. These conditions could possibly result in
damage to the airplane and injury to occupants.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2017-0119, dated July 11, 2017 (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, -231, -232, and -233 airplanes; and Model
A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. The
MCAI states:
In 1998, an operator experienced a dual loss of braking systems.
Investigation results revealed that the cover seal of the BDDV was
damaged and did not ensure the sealing efficiency.
This condition, if not corrected, could lead to water ingestion
in the BDDV, freezing of the BDDV in flight, and consequent loss of
braking system function after landing, possibly resulting in damage
to the aeroplane and injury to occupants.
To address this potential unsafe condition, Airbus issued Alert
Operator Telex (AOT) 32-19 and Service Bulletin (SB) A320-32-1199,
providing instructions for repetitive functional tests. In addition,
Airbus developed mod 28301 and published SB A320-32-1203 to provide
modification instructions.
Consequently, DGAC [Directorate General for Civil Aviation]
France issued AD 2000-258-146 [which corresponds to FAA AD 2001-15-
10, Amendment 39-12344 (66 FR 39413, July 31, 2001) (``AD 2001-15-
10'')] to require repetitive functional tests as a temporary
solution (valid for a period of 15 months) and modification of the
BDDV with a new cover and installation of a draining tube with a
cap, which was terminating action for the repetitive functional
tests. For pre-mod 27833 and pre-SB A320-32-1200 aeroplanes,
repetitive inspections per SB A320-32-1199 were required as interim
action, prior to the terminating action modification per SB A320-32-
1203.
After that [DGAC] AD was issued, following a new event, Airbus
developed a new modification of the BDDV drain tube which leaves it
open, ensuring continuous drainage of any ingested water, thereby
preventing freezing of the brake system.
Consequently, EASA issued AD 2014-0251 (later revised),
partially retaining the requirements of DGAC France AD 2000-258-146,
which was superseded, and requiring an additional modification of
the BDDV drain tube and re-identification of the BDDV.
Since EASA AD 2014-0251R1 [which corresponds to FAA AD 2016-06-
13, Amendment 39-18444 (81 FR 17365, March 29, 2016) (``AD 2016-06-
13'')] was issued, comments were received that indicated a need for
correction and clarification. Consequently, this [EASA] AD retains
the requirements of EASA AD 2014-0251R1, which is superseded, and
expands the list of BDDV Part Numbers (P/N) which must be removed
from service and are no longer eligible for installation on an
aeroplane [and includes replacing affected part numbers as an
option]. This [EASA] AD also clarifies the intended requirements of
EASA AD 2014-0251 and introduces editorial changes, not affecting
the requirements.
You may examine the MCAI in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0297.
Comments
We 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.
Supportive Comments
Air Line Pilots Association, International stated its support for
the NPRM. In addition, United Airlines (UAL) stated it concurs with the
expansion of the affected BDDV part numbers as identified in Figure 1
to paragraphs (g) and (h) of the proposed AD.
Request To Withdraw the NPRM
Delta Air lines (DAL) requested that we withdraw the NPRM. DAL
stated that the NPRM does not address an unsafe condition and,
therefore, it is unnecessary. DAL commented that airplanes included in
paragraph (c) of the proposed AD are already required to comply with
the actions required by AD 2001-15-10, depending on modification
status. DAL also commented that the NPRM does not add any airplanes to
the applicability of AD 2001-15-10 and 2016-06-13. DAL stated that
tracking compliance with the redundant requirements of the proposed AD
would place an undue burden on airlines.
DAL stated that paragraphs (j)(1)(i) and (j)(2)(i) of the proposed
AD give credit for actions accomplished using previously issued service
information. DAL commented that FAA Letter ANM-116-16-491, dated
September 27, 2016, gives operators the authority to accomplish
paragraph (g) of AD 2016-06-13 as an alternative method of compliance
(AMOC), and it is also a terminating action for the actions required by
paragraphs (e) and (f) of AD 2001-15-10. DAL stated that the compliance
times for AD 2001-15-10 and AD 2016-06-13 have passed, therefore, all
airplanes must be in compliance.
[[Page 56706]]
We partially agree with the commenter's request. We agree that
airplanes included in paragraph (c) of this AD are also required to
comply with AD 2001-15-10 and AD 2016-06-13, and that this AD does not
add any new Model airplanes related to those listed in AD 2001-15-10
and AD 2016-06-13. However, as stated in paragraph (i) of this AD,
compliance with paragraph (g) of this AD terminates the requirements in
paragraphs (e) and (f) of AD 2001-15-10 (which terminates all
requirements of AD 2001-15-10 for Model A318, A319 and A320 series
airplanes) and all requirements of AD 2016-06-13. For clarification, we
have modified paragraph (i)(1) of this AD to state that compliance with
paragraph (g) of this AD terminates all requirements of AD 2001-15-10
for Model A319, A320 and A321 series airplanes. We agree that operators
will be required to track certain ADs with expired compliance times,
but we are in process of rescinding some of those ADs through future
rulemaking. We agree that AMOC letter ANM-116-16-491 dated September
27, 2016, will still be applicable to AD 2016-06-13.
We disagree with the commenter's request to withdraw this AD. We,
along with EASA, have determined that water ingestion in the BDDV,
freezing of the BDDV in flight, and consequent loss of braking system
function after landing, could possibly result in damage to the airplane
and injury to occupants, and therefore, does constitute an unsafe
condition, and that additional mandatory actions in this AD are
required to mitigate the risks associated with the unsafe condition.
Further, even if the current U.S.-Registered fleet is in compliance
with the requirements of this AD, the issuance of the rule is still
necessary to ensure that any affected airplane imported and placed on
the U.S. Register in the future would be required to be in compliance
as well. This AD expands the list of BDDV part numbers, which must be
removed from service and are no longer eligible for installation on an
airplane. Therefore, all U.S.-Registered airplanes might not be in
compliance with the actions of this AD even when in full compliance
with AD 2001-15-10 and AD 2016-06-13. However, if DAL concludes that it
is in compliance with the requirements of this AD, then it may utilize
the provision in paragraph (f) to demonstrate compliance. We have not
changed this AD in this regard.
Request To Correct Certain Wording
DAL observed that the word ``actions'' was inadvertently omitted
from the first sentence in paragraph (g)(2) of the proposed AD after
the word ``corrective.'' We agree and have added the missing word
accordingly.
Request To Revise Certain Wording for Clarification
UAL requested that we revise the wording in certain paragraphs of
the proposed AD for clarification. UAL suggested that paragraph (g)(3)
of the proposed AD be reworded because the way it is currently written,
it could be interpreted as ``a part number specified as new P/N in
figure 2 to paragraphs (g)(3) and (h)(2)'' cannot be installed.
UAL also suggested that paragraph (h) of the proposed AD be revised
to eliminate paragraphs (h)(1) and (h)(2) and be reworded to simply
prohibit the installation of affected BDDVs as specified in figure 1 to
paragraphs (g) and (h) of the proposed AD.
We partially agree to the commenter's requests. We agree to clarify
paragraph (g)(3) of this AD. We have revised paragraph (g)(3) of this
AD to clarify that operators should replace the old part number with a
new part number as specified in figure 2 to paragraphs (g)(3) and
(h)(2) of this AD.
However, we disagree to simply prohibit installation of discrepant
parts that are specified in figure 1 to paragraphs (g) and (h) of this
AD from the effective date of this AD. Paragraph (h) provides operators
flexibility by providing the full compliance time as specified in
paragraph (g) to modify or replace discrepant parts, unless the
discrepant part is either currently installed as of the effective date
of this AD and is subsequently modified or replaced (after the
effective date of this AD) as stated in paragraph (h)(1) of this AD, or
has already been modified or replaced as of the effective date of this
AD as stated in paragraph (h)(2) of this AD. Operators have the
discretion to prohibit operation with a discrepant part in figure 1 to
paragraphs (g) and (h) of this AD from the effective date of this AD.
We have not changed the AD in this regard.
Request To Clarify the Compliance Requirements
JetBlue requested that we clarify the compliance requirements in
paragraphs (g)(2), (g)(3), and (h)(2) of the proposed AD because of
contradictory requirements. The commenter did not clearly identify
which requirements needed clarification.
We do not agree to revise paragraph (g)(2) of this AD. This AD and
the Accomplishment Instructions of Airbus Service Bulletin A320-32-
1415, Revision 02, dated December 10, 2015, specify that, if corrosion
is found in a non-permitted area, replace the BDDV before further
flight. We have not changed this AD in this regard.
As we stated previously, we have revised paragraph (g)(3) of this
AD to clarify that operators should replace the old part number with a
new part number as specified in figure 2 to paragraphs (g)(3) and
(h)(2) of this AD.
We agree to clarify the compliance requirements of paragraph (h)(2)
of this AD. As stated in the previous comment response, paragraph (h)
is intended to provide operators flexibility by providing the full
compliance time as specified in paragraph (g) to modify or replace
discrepant parts. However, paragraph (h)(2) of this AD specifically
prohibits installation of a discrepant part as of the effective date of
this AD if the discrepant part has already been modified or replaced as
of the effective date of this AD. Paragraph (h)(1) of this AD prohibits
installation of a discrepant part as of the effective date of this AD,
if a discrepant part is currently installed as of the effective of this
AD, but is modified or replaced after the effective date of this AD.
Operators have the discretion to prohibit operation with a discrepant
part in figure 1 to paragraphs (g) and (h) of this AD from the
effective date of this AD. We have not changed the AD in this regard.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this final rule with the changes described previously and minor
editorial changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this final
rule.
Related Service Information Under 1 CFR Part 51
Airbus SAS has issued Service Bulletin A320-32-1203, Revision 02,
dated February 9, 2001. This service information describes procedures
for identifying the BDDV part number installed on the airplane, and
modifying or replacing BDDVs having certain part numbers.
Airbus SAS has also issued Service Bulletin A320-32-1415, Revision
02, dated December 10, 2015. This service information describes
procedures for
[[Page 56707]]
modifying and re-identifying the BDDV. The modification includes
modifying the drain hose of the BDDV, and doing all related
investigative and corrective actions if applicable. The related
investigative actions include an inspection for corrosion. Corrective
actions include replacing the BDDV.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
Costs of Compliance
We estimate that this AD affects 1,136 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Identification and modification or Up to 6 work-hours x Up to $395................. Up to $905................. Up to $1,028,080.
replacement. $85 per hour = $510.
--------------------------------------------------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us 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.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to transport category airplanes and
associated appliances to the Director of the System Oversight Division.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2018-23-11 Airbus SAS: Amendment 39-19497; Docket No. FAA-2018-0297;
Product Identifier 2017-NM-181-AD.
(a) Effective Date
This AD is effective December 19, 2018.
(b) Affected ADs
This AD affects AD 2001-15-10, Amendment 39-12344 (66 FR 39413,
July 31, 2001) (``AD 2001-15-10''), and AD 2016-06-13, Amendment 39-
18444 (81 FR 17365, March 29, 2016) (``AD 2016-06-13'').
(c) Applicability
This AD applies to the airplanes identified in paragraphs (c)(1)
through (c)(3) of this AD, certificated in any category, all
manufacturer serial numbers, except those on which Airbus
Modification 26925 has been embodied in production, which introduces
a modified alternate braking system that removes the brake dual
distribution valve (BDDV).
(1) Airbus SAS Model A319-111, -112, -113, -114, -115, -131, -
132, and -133 airplanes.
(2) Airbus SAS Model A320-211, -212, -214, -231, -232, and -233
airplanes.
(3) Airbus SAS 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 investigations that revealed that the
cover seal of the brake dual distribution valve (BDDV) was damaged
and did not ensure efficient sealing. We are issuing this AD to
prevent water ingestion in the BDDV, freezing of the BDDV in flight,
and consequent loss of braking system function after landing. These
conditions could possibly result in damage to the airplane and
injury to occupants.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Identification and Modification or Replacement
Within 3 months after the effective date of this AD, identify
the BDDV part number installed on the airplane. For each affected
BDDV part number specified in figure 1 to paragraphs (g) and (h) of
this AD, within 3 months after the effective date of this AD, do the
actions in paragraph (g)(1), (g)(2), or (g)(3) of this AD. A review
of airplane maintenance records is acceptable to identify the BDDV
part number if the part number of the BDDV can be conclusively
determined from that review.
[[Page 56708]]
[GRAPHIC] [TIFF OMITTED] TR14NO18.001
(1) Modify and re-identify the affected BDDV, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A320-32-
1203, Revision 02, dated February 9, 2001.
(2) Modify and re-identify the affected BDDV, and do all
applicable related investigative and corrective actions, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-32-1415, Revision 02, dated December 10, 2015. Do all
applicable related investigative and corrective actions before
further flight.
(3) Replace the affected BDDV with a BDDV having a part number
not specified in figure 1 to paragraphs (g) and (h) of this AD, or
replace the old part number with a new part number as specified in
figure 2 to paragraphs (g)(3) and (h)(2) of this AD. Do the
replacement 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.
[GRAPHIC] [TIFF OMITTED] TR14NO18.002
(h) Parts Installation Prohibition
As of the applicable time specified in paragraph (h)(1) or
(h)(2) of this AD, no person may install a BDDV having a part number
specified in figure 1 to paragraphs (g) and (h) of this AD, on any
airplane.
(1) For any airplane that, on the effective date of this AD, has
a BDDV installed with a part number specified in figure 1 to
paragraphs (g) and (h) of this AD: After modification or replacement
of the BDDV, as required by paragraph (g) of this AD.
(2) For any airplane that, on the effective date of this AD, has
a BDDV installed or replaced with a part number specified as `new P/
N' in figure 2 to paragraphs (g)(3) and (h)(2) of this AD, or has a
BDDV installed or replaced with a part number not specified in
figure 1 to paragraphs (g) and (h) of this AD: As of the effective
date of this AD.
(i) Terminating Action for Other ADs
(1) Doing the actions in paragraph (g) of this AD terminates the
requirements in paragraphs (e) and (f) of AD 2001-15-10 for Model
A319, A320 and A321 series airplanes.
(2) Doing the actions in paragraph (g) of this AD terminates all
of the requirements of AD 2016-06-13.
(j) Credit for Previous Actions
(1) This paragraph provides credit for actions required by
paragraph (g)(1) of this AD, if those actions were performed before
the effective date of this AD using the service information in
paragraphs (j)(1)(i) or (j)(1)(ii) of this AD.
(i) Airbus Service Bulletin A320-32-1203, dated June 4, 1999,
which was incorporated by reference in AD 2001-15-10.
(ii) Airbus Service Bulletin A320-32-1203, Revision 01, dated
October 12, 2000.
(2) This paragraph provides credit for actions required by
paragraph (g)(2) of this AD, if those actions were performed before
the effective date of this AD using the service information in
paragraphs (j)(2)(i) or (j)(2)(ii) of this AD.
(i) Airbus Service Bulletin A320-32-1415, dated September 2,
2014, which was incorporated by reference in AD 2016-06-13.
(ii) Airbus Service Bulletin A320-32-1415, Revision 01, dated
April 23, 2015.
(k) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Section, Transport Standards Branch, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Section, send it to the attention of
the person identified in paragraph (l)(2) of this AD. Information
may be emailed to: [email protected]. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Section, Transport Standards Branch, FAA; or the EASA; or Airbus
SAS's EASA DOA. If approved by the DOA, the approval must include
the DOA-authorized signature.
(3) Required for Compliance (RC): If any service information
contains procedures or tests that are identified as RC, those
procedures and tests must be done to comply with this AD; any
procedures or tests that are not identified as RC are recommended.
Those procedures and tests that are not identified as RC may be
deviated from using accepted methods in accordance with the
operator's
[[Page 56709]]
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.
(l) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2017-0119, dated July 11, 2017, for related
information. This MCAI may be found in the AD docket on the internet
at https://www.regulations.gov by searching for and locating Docket
No. FAA-2018-0297.
(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) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (m)(3) and (m)(4) of this AD.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A320-32-1203, Revision 02, dated
February 9, 2001.
(ii) Airbus Service Bulletin A320-32-1415, Revision 02, dated
December 10, 2015.
(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 [email protected]; internet
https://www.airbus.com.
(4) You may view this service information at the FAA, Transport
Standards Branch, 2200 South 216th St., Des Moines, WA. For
information on the availability of this material at the FAA, call
206-231-3195.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Des Moines, Washington, on November 5, 2018.
Christopher Spangenberg,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-24688 Filed 11-13-18; 8:45 am]
BILLING CODE 4910-13-P
