[Federal Register Volume 80, Number 223 (Thursday, November 19, 2015)]
[Proposed Rules]
[Pages 72401-72404]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-29444]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-4816; Directorate Identifier 2014-NM-238-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Airbus Model A319, A320, and A321 series airplanes. This
proposed 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 proposed AD would require modifying
the BDDV having certain part numbers; modifying the drain hose of the
BDDV; checking for the presence of water, ice, and hydraulic fluid; and
re-identifying the BDDV; and related investigative and corrective
actions if necessary. We are proposing this AD to prevent damage to the
BDDV, which could lead to water ingestion in the BDDV and freezing of
the BDDV in flight, possibly resulting in loss of braking system
function after landing.
DATES: We must receive comments on this proposed AD by January 4, 2016.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
[[Page 72402]]
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email [email protected]; Internet http://www.airbus.com. You may view this referenced service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA, call
425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
4816; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-4816;
Directorate Identifier 2014-NM-238-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 http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2014-0251R1, dated December 17, 2014 (referred
to after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A319, A320, and A321 series airplanes. The MCAI states:
In 1998, an operator experienced a dual loss of braking systems.
Investigation results revealed that the cover seal of the Brake Dual
Distribution Valve (BDDV) was damaged and did not ensure the sealing
efficiency.
This condition, if not corrected, could lead to water ingestion
in the BDDV and freezing of the BDDV in flight, possibly resulting
in loss of braking system function after landing.
[The Directorate General for Civil Aviation] (DGAC) France
issued AD 2000-258-146 [http://ad.easa.europa.eu/blob/20002580tb_superseded.pdf/AD_F-2000-258-146_1] [which corresponds to
certain actions in FAA AD 2001-15-10, Amendment 39-12344 (66 FR
39413, July 31, 2001)] to require modification of the BDDV with a
new cover and installation of a draining tube with a cap.
Since that French AD was issued, following a new event, Airbus
developed a modification of the BDDV drain tube which will leave it
open, ensuring continuous drainage of any ingested water, thereby
preventing freezing of the brake system.
For the reasons described above, EASA issued [another AD] * * *,
to require modification of the BDDV drain tube.
Since that [EASA] AD was issued, comments were received that
indicated a need for correction and clarification. Consequently,
this [EASA] AD is revised to add a Note to Table 1 and to amend
paragraph (3).
The modification includes a check for the presence of water, ice,
and hydraulic fluid, and related investigative and corrective actions
if necessary. Related investigative actions include an inspection for
corrosion. Corrective actions include replacing the BDDV. You may
examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
4816.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A320-32-1415, dated September 2,
2014. The service information describes procedures for modifying the
BDDV having certain part numbers; and modifying the drain hose of the
BDDV; the modification includes a check for the presence of water, ice,
and hydraulic fluid; and re-identifying the BDDV; and related
investigative and corrective actions if necessary. 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 of this NPRM.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of these
same type designs.
Explanation of ``RC'' Procedures and Tests in Service Information
The FAA worked in conjunction with industry, under the
Airworthiness Directive Implementation Aviation Rulemaking Committee
(ARC), to enhance the AD system. One enhancement was a new process for
annotating which procedures and tests in the service information are
required for compliance with an AD. Differentiating these procedures
and tests from other tasks in the service information is expected to
improve an owner's/operator's understanding of crucial AD requirements
and help provide consistent judgment in AD compliance. The procedures
and tests identified as RC (required for compliance) in any service
information have a direct effect on detecting, preventing, resolving,
or eliminating an identified unsafe condition.
As specified in a NOTE under the Accomplishment Instructions of the
specified service information, procedures and tests that are identified
as RC in any service information must be done to comply with the
proposed AD. However, procedures and tests that are not identified as
RC are recommended. Those procedures and
[[Page 72403]]
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 alternative method of
compliance (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
will require approval of an AMOC.
Costs of Compliance
We estimate that this proposed AD affects 953 airplanes of U.S.
registry.
We also estimate that it would take about 6 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Required parts would cost about $421
per product. Based on these figures, we estimate the cost of this
proposed AD on U.S. operators to be $887,243, or $931 per product.
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.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
Airbus: Docket No. FAA-2015-4816; Directorate Identifier 2014-NM-
238-AD.
(a) Comments Due Date
We must receive comments by January 4, 2016.
(b) Affected ADs
None.
(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.
(1) Airbus Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes.
(2) Airbus Model A320-211, -212, -214, -231, -232, and -233
airplanes.
(3) Airbus 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 BDDV was damaged and did not ensure efficient
sealing. We are issuing this AD to prevent damage to the BDDV, which
could lead to water ingestion in the BDDV and freezing of the BDDV
in flight, possibly resulting in loss of braking system function
after landing.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Modification and Re-Identification
Within 24 months after the effective date of this AD, modify the
BDDV having a part number listed in the column ``Old Part Number''
in table 1 to paragraph (g) of this AD; modify the drain hose of the
affected BDDV; check for the presence of water, ice, and hydraulic
fluid; and re-identify the BDDV to the corresponding part number, as
applicable, as listed as ``New Part Number'' in table 1 to paragraph
(g) of this AD; and do all applicable related investigative and
corrective actions; in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-32-1415, dated
September 2, 2014. Do all applicable related investigative and
corrective actions before further flight.
Table 1 to Paragraph (g) of This AD--BDDV Part Number Re-Identification
------------------------------------------------------------------------
Old part number New part number
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A25434006-3.......................................... A25434006-3000.
A25434005-101........................................ A25434005-1010.
A25434005-201........................................ A25434005-2010.
A25434005-301........................................ A25434005-3010.
A25434005-401........................................ A25434005-4010.
A25434006-101........................................ A25434006-1010.
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Note 2 to table 1 to paragraph (g) of this AD: The part number
listed in table 1 to paragraph (g) of this AD can have an ``A'' or
``B'' suffix, which is an indication of the amendment level of the
BDDV. This does not affect compliance with this AD.
(h) Parts Installation Limitations
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
listed as ``Old Part Number'' in table 1 to paragraph (g) 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 listed as ``Old Part Number'' in
table 1 to paragraph (g) of this AD: After modification of the
airplane, as required by paragraph (g) of this AD.
(2) For any airplane that, on the effective date of this AD, has
a BDDV installed with a part number listed as ``New Part Number'' in
table 1 to paragraph (g) of this AD, or has a BDDV installed with a
part number not listed in table 1 to paragraph (g) of this AD: As of
the effective date of this AD.
(i) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, 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
[[Page 72404]]
Flight Standards District Office, as appropriate. If sending
information directly to the International Branch, send it to ATTN:
Sanjay Ralhan, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone 425-227-1405; fax 425-227-1149. 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. The
AMOC approval letter must specifically reference this AD.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA); or Airbus's EASA Design
Organization Approval (DOA). If approved by the DOA, the approval
must include the DOA-authorized signature.
(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.
(j) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2014-0251R1, dated December 17,
2014, for related information. This MCAI may be found in the AD
docket on the Internet at http://www.regulations.gov by searching
for and locating Docket No. FAA-2015-4816.
(2) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email [email protected]; Internet http://www.airbus.com. You may view this service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA,
call 425-227-1221.
Issued in Renton, Washington, on November 10, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-29444 Filed 11-18-15; 8:45 am]
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