Airworthiness Directives; Airbus Airplanes, 22939-22943 [2015-09288]
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Federal Register / Vol. 80, No. 79 / Friday, April 24, 2015 / Proposed Rules
On April 1, 2015, the U.S.
Department of Energy (DOE) published
in the Federal Register a notice of
proposed rulemaking and public
meeting for Energy Conservation
Program: Test Procedure for Pumps.
This document corrects terms in four
equations.
SUMMARY:
DEPARTMENT OF ENERGY
10 CFR Parts 429 and 431
[Docket No. EERE–2013–BT–TP–0055]
RIN 1905–AD50
Energy Conservation Program: Test
Procedure for Pumps; Correction
Office of Energy Efficiency and
Renewable Energy, Department of
Energy.
ACTION: Notice of proposed rulemaking
and public meeting; correction.
AGENCY:
Appendix A to Subpart Y of Part 431—
Uniform Test Method for the
Measurement of Energy Consumption of
Pumps. [Corrected]
2. On page 17645: The equation in
section II.B.1.1.1 is corrected by
DATES:
April 24, 2015.
FOR FURTHER INFORMATION CONTACT:
Ashley Armstrong, U.S. Department of
Energy, Office of Energy Efficiency and
Renewable Energy, Building
Technologies Office, EE–5B, 1000
removing ‘‘13.46’’ and adding in its
place ‘‘17.80’’. The corrected equation
reads as follows:
hpump,STD = ¥0.85 * In(Q100%)2 ¥ 0.38 *
In(NS) * In(Q100%) ¥ 11.48 * In(NS)2
+ 17.80 * In(Q100%) + 179.80 *
In(NS) ¥ (C ¥ 555.6)
[Docket No. FAA–2015–0831; Directorate
Identifier 2014–NM–061–AD]
BILLING CODE 6450–01–P
Federal Aviation Administration
14 CFR Part 39
RIN 2120–AA64
tkelley on DSK3SPTVN1PROD with PROPOSALS
3. On page 17646: The equation in
section III.D.1.2.1 is corrected by
removing ‘‘MotorH’’ and adding in its
place ‘‘MotorHP’’. The corrected
equation reads as follows:
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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We propose to adopt a new
airworthiness directive (AD) for all
Airbus Model A318, A319, A320, and
A321 series airplanes. This proposed
AD was prompted by a report of a
rupture of a main landing gear (MLG)
sliding tube axle. This proposed AD
would require an inspection to identify
the part number and serial number of
the MLG sliding tubes installed on the
airplane; and an inspection of the axle
on certain MLG sliding tubes for burned
areas, and replacement of the sliding
tube if necessary. We are proposing this
AD to detect and correct cracks in the
axle and (partial) detachment of the axle
and wheel from the sliding tube, which
could result in failure of an MLG.
SUMMARY:
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EP24AP15.002</GPH>
[FR Doc. 2015–09566 Filed 4–23–15; 8:45 am]
In the Federal Register published on
April 1, 2015, in FR Doc. 2015–06945,
make the following corrections:
1. On page 17604: Equation (6) is
corrected by removing ‘‘13.46’’ and
adding in its place ‘‘17.80’’. The
corrected equation reads as follows:
EP24AP15.001</GPH>
DEPARTMENT OF TRANSPORTATION
Corrections
adding in its place ‘‘MotorHP’’. The
corrected equation reads as follows:
Issued in Washington, DC, on April 20,
2015.
Kathleen B. Hogan,
Deputy Assistant Secretary for Energy
Efficiency, Energy Efficiency and Renewable
Energy.
Independence Avenue SW.,
Washington, DC 20585–0121.
Telephone: (202) 586–6590. Email:
ashley.armstrong@ee.doe.gov.
EP24AP15.017</GPH>
4. On page 17648: The equation in
section V.D.1.2.1 is corrected by
removing ‘‘MotorHPMotorH’’ and
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Federal Register / Vol. 80, No. 79 / Friday, April 24, 2015 / Proposed Rules
We must receive comments on
this proposed AD by June 8, 2015.
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: 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 Airbus 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
account.airworth-eas@airbus.com;
Internet https://www.airbus.com.
For Messier-Bugatti-Dowty service
information identified in this proposed
AD, contact Messier Services Americas,
Customer Support Center, 45360 Severn
Way, Sterling, VA 20166–8910; phone:
703–450–8233; fax: 703–404–1621;
Internet: https://techpubs.services/
messier-dowty.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.
tkelley on DSK3SPTVN1PROD with PROPOSALS
DATES:
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–2015–
0831; 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.
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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–2015–0831; Directorate Identifier
2014–NM–061–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.
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 2014–0058, dated March 11,
2014 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for all Airbus
Model A318, A319, A320, and A321
series airplanes. The MCAI states:
A main landing gear (MLG) sliding tube
axle rupture occurred in service.
Investigation of the affected part showed that
this failure was due to an abnormal grinding
operation during overhaul by a certain
maintenance and repair organisation located
in Singapore. A population of MLG sliding
tubes was subsequently identified whose
axles may have been subject to this grinding
operation, which may have resulted in areas
of residual stress on the axles on the MLG
sliding tubes. In addition, the MSN
[manufacturer serial number] of the
aeroplanes which are known to have had the
affected parts installed have been identified.
This condition, if not detected and
corrected, could lead to cracks in the axle
and (partial) detachment of axle and wheel
from the sliding tube, possibly resulting in
failure of a MLG with consequent damage to
the aeroplane and injury to occupants.
To address this potential unsafe condition,
Messier-Bugatti-Dowty, the MLG gear
manufacturer, issued Service Bulletin (SB)
200–32–313 and SB 201–32–62 [both dated
February 25, 2013], providing inspection
instructions and criteria for removal from
service of the affected MLG sliding tubes.
For the reasons described above, this
[EASA] AD requires a one-time Special
Detailed Inspection (SDI) of the axle on the
affected MLG sliding tubes and, depending
on findings, replacement of the MLG sliding
tube.
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The SDI includes a detailed visual
inspection of the chromium plate for
damage, and a Barkhausen noise
inspection of the sliding tube axles for
burned areas. 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–2015–0831.
Related Service Information Under 1
CFR part 51
Airbus has issued Service Bulletin
A320–32–1416, including Appendix 01,
dated March 10, 2014 (for Model A319,
A320, and A321 series airplanes). This
service bulletin describes procedures for
inspection of the MLG sliding tube
axles, and replacement if necessary.
Messier-Bugatti-Dowty has issued
Service Bulletin 200–32–313, including
Appendices A, B, and C, dated February
25, 2013 (for Model A318, A319, and
A320 series airplanes); and Service
Bulletin 201–32–62, including
Appendices A, B, and C, dated February
25, 2013 (for Model A321 series
airplanes). These service bulletins
describe procedures for inspection of
the MLG axles and brake flanges, and
replacement if necessary.
The actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI. This service information is
reasonably available; see ADDRESSES for
ways to access this service information.
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
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Federal Register / Vol. 80, No. 79 / Friday, April 24, 2015 / Proposed Rules
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
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 a
serviceable condition. Any substitutions
or changes to procedures or tests
identified as RC will require approval of
an AMOC.
tkelley on DSK3SPTVN1PROD with PROPOSALS
Costs of Compliance
We estimate that this proposed AD
affects 3 airplanes of U.S. registry.
We also estimate that it would take
about 18 work-hours per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour. Based on
these figures, we estimate the cost of
this proposed AD on U.S. operators to
be $4,590, or $1,530 per product.
In addition, we estimate that any
necessary follow-on actions would take
about 3 work-hours, for a cost of $255
per product. We have received no
definitive data that would enable us to
provide part cost estimates for the oncondition actions specified in this
proposed AD. We have no way of
determining the number of aircraft that
might need these 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.
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
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):
■
Airbus: Docket No. FAA–2015–0831;
Directorate Identifier 2014–NM–061–AD.
(a) Comments Due Date
We must receive comments by June 8,
2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes
identified in paragraphs (c)(1) through (c)(4)
of this AD, certificated in any category, all
manufacturer serial numbers.
(1) Airbus Model A318–111, –112, –121,
and –122 airplanes.
(2) Airbus Model A319–111, –112, –113,
–114, –115, –131, –132, and –133 airplanes.
(3) Airbus Model A320–211, –212, –214,
–231, –232, and –233 airplanes.
(4) 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 a report of a
rupture of a main landing gear (MLG) sliding
tube axle. We are issuing this AD to detect
and correct cracks in the axle and (partial)
detachment of the axle and wheel from the
sliding tube, which could result in failure of
an MLG.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) MLG Sliding Tube Part Number and
Serial Number Identification
Within 3 months after the effective date of
this AD: 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.
(h) Identification of Airplanes Not Affected
by the Requirements of Paragraph (i) of This
AD
An airplane with a manufacturer serial
number (MSN) not listed in figure 1 to
paragraph (h) of this AD is not affected by the
requirements of paragraph (i) 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 (h), (i),
(k)(1), (k)(2), (l)(1), and (l)(2) of this AD has
been installed on that airplane since first
flight of the airplane.
FIGURE 1 TO PARAGRAPH (h) OF THIS AD
Affected airplanes listed by MSN
0179
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Federal Register / Vol. 80, No. 79 / Friday, April 24, 2015 / Proposed Rules
FIGURE 1 TO PARAGRAPH (h) OF THIS AD—Continued
0607
0754
0909
1030
1108
0668
0771
0914
1041
1148
0704
0799
0925
1070
1294
TABLE 1 TO PARAGRAPHS (h), (i),
(k)(1), (k)(2), (l)(1), AND (l)(2) OF
THIS AD—AFFECTED MLG SLIDING
TUBES
tkelley on DSK3SPTVN1PROD with PROPOSALS
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Serial No.
78B.
1016B11.
1144B.
B4493.
B4513.
SS4359.
B4530.
B4517.
B4568.
B4498.
4490B.
B202–4598.
B165–4623.
B244–4766.
B267–4794.
B272–4813.
1108B.
B041–4871.
B045–4869.
B001–4781.
B051–4892.
B110–1952.
B054–4891.
B063–4921.
B071–4911.
B071–4917.
B080–1933.
B117–5010.
B120–4989.
B132–2023.
B114–1956.
B208–2009.
B133–1947.
B154–5037.
B89 4952.
B129–1964.
B227–2010.
B170–5031.
B182–5047.
B239–2053.
B1401–2856.
B1813–3142.
B116–5004.
B011–149.
B014–25.
B019–56.
B019–57.
B021–69.
B022–60.
B03–111.
B03–110.
B112–317.
B174–351.
B179–392.
4377B.
4393B.
B1831.
B1832.
SS4355B.
SS4400B.
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(i) Inspections
For each MLG sliding tube, identified as
required by paragraph (g) of this AD, having
a part number and serial number listed in
table 1 to paragraphs (h), (i), (k)(1), (k)(2),
(l)(1), and (l)(2) of this AD: Within 3 months
after the effective date of this AD, inspect
each affected MLG axle and brake flange by
doing a detailed visual inspection of the
chromium plate for damage, and a
Barkhausen noise inspection of the sliding
tube axles for burned areas, in accordance
with the Accomplishment Instructions of
Messier-Bugatti-Dowty Service Bulletin 200–
32–313, including Appendices A, B, and C,
dated February 25, 2013 (for Model A318,
A319, and A320 series airplanes); or MessierBugatti-Dowty Service Bulletin 201–32–62,
including Appendices A, B, and C, dated
February 25, 2013 (for Model A321 series
airplanes); or Airbus Service Bulletin A320–
32–1416, including Appendix 01, dated
March 10, 2014 (for Model A319, A320, and
A321 series airplanes).
(j) Corrective Action
If, during any inspection required by
paragraph (i) 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 Messier-Bugatti-Dowty
Service Bulletin 200–32–313, including
Appendices A, B, and C, dated February 25,
2013 (for Model A318, A319, and A320 series
airplanes); or Messier-Bugatti-Dowty Service
Bulletin 201–32–62, including Appendices
A, B, and C, dated February 25, 2013 (for
Model A321 series airplanes); or Airbus
Service Bulletin A320–32–1416, including
Appendix 01, dated March 10, 2014 (for
Model A319, A320, and A321 series
airplanes).
(k) Definition of Serviceable Sliding Tube
For the purpose of this AD, a serviceable
sliding tube is defined in paragraphs (k)(1)
and (k)(2) of this AD.
(1) A sliding tube having a part number
and serial number not listed in table 1 to
paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and
(l)(2) of this AD.
(2) A sliding tube having a part number
and serial number listed in table 1 to
paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and
(l)(2) of this AD that has passed the
inspections required by paragraph (i) of this
AD.
(l) Parts Installation Prohibitions
(1) For airplanes that have an MLG sliding
tube installed that has a part number and
serial number listed in table 1 to paragraphs
(h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this
AD: After an airplane is returned to service
following accomplishment of the actions
required by paragraphs (g), (h), and (i) of this
AD, no person may install on any airplane an
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MLG sliding tube having a part number and
serial number listed in table 1 to paragraphs
(h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this
AD.
(2) For airplanes that, as of the effective
date of this AD, do not have an MLG sliding
tube installed that has a part number and
serial number listed in table 1 to paragraphs
(h), (i), (k)(1), (k)(2), (l)(1), and (l)(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 (h), (i), (k)(1), (k)(2), (l)(1), and
(l)(2) of this AD.
(m) 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
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: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office. The AMOC approval letter
must specifically reference this AD.
(2) 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
a serviceable condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(3) 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
E:\FR\FM\24APP1.SGM
24APP1
Federal Register / Vol. 80, No. 79 / Friday, April 24, 2015 / Proposed Rules
the DOA, the approval must include the
DOA-authorized signature.
(n) Special Flight Permits
Special flight permits may be issued in
accordance with sections 21.197 and 21.199
of the Federal Aviation Regulations (14 CFR
21.197 and 21.199) to operate the airplane to
a location where the airplane can be
modified (if the operator elects to do so),
provided the MLG remains extended
throughout the flight.
(o) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) European
Aviation Safety Agency (EASA)
Airworthiness Directive 2014–0058, dated
March 11, 2014, 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–
2015–0831.
(2) For Airbus 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 account.airworth-eas@
airbus.com; Internet https://www.airbus.com.
(3) For Messier-Bugatti-Dowty service
information identified in this AD, contact
Messier Services Americas, Customer
Support Center, 45360 Severn Way, Sterling,
VA 20166 8910; phone: 703–450–8233; fax:
703–404–1621; Internet: https://
techpubs.services/messier-dowty.com.
(4) 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 April 9,
2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–09288 Filed 4–23–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–0926; Directorate
Identifier 2014–NM–121–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
tkelley on DSK3SPTVN1PROD with PROPOSALS
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 97–07–14,
for certain Airbus Model A320–111,
–211, and –231 airplanes. AD 97–07–14
SUMMARY:
VerDate Sep<11>2014
17:05 Apr 23, 2015
Jkt 235001
currently requires modification of an
area on the front spar of the wing center
section by installing shims and new
fasteners to reinforce pressure floor
fittings. Since we issued AD 97–07–14,
we have determined the need for
repetitive inspections on airplanes on
which the modification of the rib flange
on the front spar of the wing center
section has been done. This proposed
AD would continue to require
modifying the rib flange on the front
spar of the wing center section by
installing shims and new fasteners to
reinforce pressure floor fittings; and
would require repetitive high frequency
eddy current inspections for cracking of
the radius of the rib flanges and vertical
stiffener at frame 36, a rototest
inspection for cracking of the fastener
holes of the rib flanges, repair if needed,
and adding additional airplanes to the
applicability. We are proposing this AD
to prevent fatigue cracking on the rib
flange area of the front spar of the wing
center section, which can reduce the
structural integrity of fuselage frame 36
and the wing center section.
DATES: We must receive comments on
this proposed AD by June 8, 2015.
ADDRESSES: You may send comments 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: 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
account.airworth-eas@airbus.com;
Internet https://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 https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
PO 00000
Frm 00017
Fmt 4702
Sfmt 4702
22943
0926; 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–2015–0926; Directorate Identifier
2014–NM–121–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.
Discussion
On March 27, 1997, we issued AD 97–
07–14, Amendment 39–9988 (62 FR
16473, April 7, 1997). AD 97–07–14
requires modification of an area on the
front spar of the wing center section by
installing shims and new fasteners to
reinforce pressure floor fittings on
certain Airbus Model A320–111, –211
and –231 airplanes.
Since we issued AD 97–07–14,
Amendment 39–9988 (62 FR 16473,
April 7, 1997), we have determined the
need for repetitive inspections on
airplanes on which Airbus Modification
20976 (modification of the rib flange on
the front spar of the wing center section)
was done in production, or was done
using Airbus Service Bulletin A320–57–
1013, dated April 12, 1989; or Airbus
Service Bulletin A320–57–1013,
Revision 1, dated September 29, 1992.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
E:\FR\FM\24APP1.SGM
24APP1
]]>Agencies
[Federal Register Volume 80, Number 79 (Friday, April 24, 2015)]
[Proposed Rules]
[Pages 22939-22943]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-09288]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-0831; Directorate Identifier 2014-NM-061-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
Airbus Model A318, A319, A320, and A321 series airplanes. This proposed
AD was prompted by a report of a rupture of a main landing gear (MLG)
sliding tube axle. This proposed AD would require an inspection to
identify the part number and serial number of the MLG sliding tubes
installed on the airplane; and an inspection of the axle on certain MLG
sliding tubes for burned areas, and replacement of the sliding tube if
necessary. We are proposing this AD to detect and correct cracks in the
axle and (partial) detachment of the axle and wheel from the sliding
tube, which could result in failure of an MLG.
[[Page 22940]]
DATES: We must receive comments on this proposed AD by June 8, 2015.
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: 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 Airbus 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 account.airworth-eas@airbus.com; Internet
https://www.airbus.com.
For Messier-Bugatti-Dowty service information identified in this
proposed AD, contact Messier Services Americas, Customer Support
Center, 45360 Severn Way, Sterling, VA 20166-8910; phone: 703-450-8233;
fax: 703-404-1621; Internet: https://techpubs.services/messier-dowty.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 https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0831; 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-2015-0831;
Directorate Identifier 2014-NM-061-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.
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 2014-0058, dated March 11, 2014 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model
A318, A319, A320, and A321 series airplanes. The MCAI states:
A main landing gear (MLG) sliding tube axle rupture occurred in
service. Investigation of the affected part showed that this failure
was due to an abnormal grinding operation during overhaul by a
certain maintenance and repair organisation located in Singapore. A
population of MLG sliding tubes was subsequently identified whose
axles may have been subject to this grinding operation, which may
have resulted in areas of residual stress on the axles on the MLG
sliding tubes. In addition, the MSN [manufacturer serial number] of
the aeroplanes which are known to have had the affected parts
installed have been identified.
This condition, if not detected and corrected, could lead to
cracks in the axle and (partial) detachment of axle and wheel from
the sliding tube, possibly resulting in failure of a MLG with
consequent damage to the aeroplane and injury to occupants.
To address this potential unsafe condition, Messier-Bugatti-
Dowty, the MLG gear manufacturer, issued Service Bulletin (SB) 200-
32-313 and SB 201-32-62 [both dated February 25, 2013], providing
inspection instructions and criteria for removal from service of the
affected MLG sliding tubes.
For the reasons described above, this [EASA] AD requires a one-
time Special Detailed Inspection (SDI) of the axle on the affected
MLG sliding tubes and, depending on findings, replacement of the MLG
sliding tube.
The SDI includes a detailed visual inspection of the chromium plate for
damage, and a Barkhausen noise inspection of the sliding tube axles for
burned areas. 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-2015-0831.
Related Service Information Under 1 CFR part 51
Airbus has issued Service Bulletin A320-32-1416, including Appendix
01, dated March 10, 2014 (for Model A319, A320, and A321 series
airplanes). This service bulletin describes procedures for inspection
of the MLG sliding tube axles, and replacement if necessary.
Messier-Bugatti-Dowty has issued Service Bulletin 200-32-313,
including Appendices A, B, and C, dated February 25, 2013 (for Model
A318, A319, and A320 series airplanes); and Service Bulletin 201-32-62,
including Appendices A, B, and C, dated February 25, 2013 (for Model
A321 series airplanes). These service bulletins describe procedures for
inspection of the MLG axles and brake flanges, and replacement if
necessary.
The actions described in this service information are intended to
correct the unsafe condition identified in the MCAI. This service
information is reasonably available; see ADDRESSES for ways to access
this service information.
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
[[Page 22941]]
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 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 a serviceable 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 3 airplanes of U.S.
registry.
We also estimate that it would take about 18 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of this proposed AD on U.S. operators to be $4,590, or $1,530
per product.
In addition, we estimate that any necessary follow-on actions would
take about 3 work-hours, for a cost of $255 per product. We have
received no definitive data that would enable us to provide part cost
estimates for the on-condition actions specified in this proposed AD.
We have no way of determining the number of aircraft that might need
these 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.
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-2015-0831; Directorate Identifier 2014-NM-
061-AD.
(a) Comments Due Date
We must receive comments by June 8, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs
(c)(1) through (c)(4) of this AD, certificated in any category, all
manufacturer serial numbers.
(1) Airbus Model A318-111, -112, -121, and -122 airplanes.
(2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes.
(3) Airbus Model A320-211, -212, -214, -231, -232, and -233
airplanes.
(4) 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 a report of a rupture of a main landing
gear (MLG) sliding tube axle. We are issuing this AD to detect and
correct cracks in the axle and (partial) detachment of the axle and
wheel from the sliding tube, which could result in failure of an
MLG.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) MLG Sliding Tube Part Number and Serial Number Identification
Within 3 months after the effective date of this AD: 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.
(h) Identification of Airplanes Not Affected by the Requirements of
Paragraph (i) of This AD
An airplane with a manufacturer serial number (MSN) not listed
in figure 1 to paragraph (h) of this AD is not affected by the
requirements of paragraph (i) 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 (h), (i), (k)(1), (k)(2),
(l)(1), and (l)(2) of this AD has been installed on that airplane
since first flight of the airplane.
Figure 1 to Paragraph (h) of This AD
------------------------------------------------------------------------
------------
Affected airplanes listed by MSN
------------------------------------------------------------------------
0179 0214 0296 0412 0558 0604
[[Page 22942]]
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
------------------------------------------------------------------------
Table 1 to Paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of
This AD--Affected MLG Sliding Tubes
------------------------------------------------------------------------
Part No. Serial No.
------------------------------------------------------------------------
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.
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................................. B117-5010.
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................................. B1401-2856.
201371304................................. B1813-3142.
201371304................................. B116-5004.
201522353................................. B011-149.
201522350................................. B014-25.
201522350................................. B019-56.
201522350................................. B019-57.
201522350................................. B021-69.
201522350................................. B022-60.
201522353................................. B03-111.
201522353................................. B03-110.
201522353................................. B112-317.
201522353................................. B174-351.
201522353................................. B179-392.
201383350................................. 4377B.
201383350................................. 4393B.
201383350................................. B1831.
201383350................................. B1832.
201383350................................. SS4355B.
201383350................................. SS4400B.
------------------------------------------------------------------------
(i) Inspections
For each MLG sliding tube, identified as required by paragraph
(g) of this AD, having a part number and serial number listed in
table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2)
of this AD: Within 3 months after the effective date of this AD,
inspect each affected MLG axle and brake flange by doing a detailed
visual inspection of the chromium plate for damage, and a Barkhausen
noise inspection of the sliding tube axles for burned areas, in
accordance with the Accomplishment Instructions of Messier-Bugatti-
Dowty Service Bulletin 200-32-313, including Appendices A, B, and C,
dated February 25, 2013 (for Model A318, A319, and A320 series
airplanes); or Messier-Bugatti-Dowty Service Bulletin 201-32-62,
including Appendices A, B, and C, dated February 25, 2013 (for Model
A321 series airplanes); or Airbus Service Bulletin A320-32-1416,
including Appendix 01, dated March 10, 2014 (for Model A319, A320,
and A321 series airplanes).
(j) Corrective Action
If, during any inspection required by paragraph (i) 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 Messier-Bugatti-Dowty Service
Bulletin 200-32-313, including Appendices A, B, and C, dated
February 25, 2013 (for Model A318, A319, and A320 series airplanes);
or Messier-Bugatti-Dowty Service Bulletin 201-32-62, including
Appendices A, B, and C, dated February 25, 2013 (for Model A321
series airplanes); or Airbus Service Bulletin A320-32-1416,
including Appendix 01, dated March 10, 2014 (for Model A319, A320,
and A321 series airplanes).
(k) Definition of Serviceable Sliding Tube
For the purpose of this AD, a serviceable sliding tube is
defined in paragraphs (k)(1) and (k)(2) of this AD.
(1) A sliding tube having a part number and serial number not
listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1),
and (l)(2) of this AD.
(2) A sliding tube having a part number and serial number listed
in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and
(l)(2) of this AD that has passed the inspections required by
paragraph (i) of this AD.
(l) Parts Installation Prohibitions
(1) For airplanes that have an MLG sliding tube installed that
has a part number and serial number listed in table 1 to paragraphs
(h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this AD: After an
airplane is returned to service following accomplishment of the
actions required by paragraphs (g), (h), and (i) 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 (h), (i),
(k)(1), (k)(2), (l)(1), and (l)(2) of this AD.
(2) For airplanes that, as of the effective date of this AD, do
not have an MLG sliding tube installed that has a part number and
serial number listed in table 1 to paragraphs (h), (i), (k)(1),
(k)(2), (l)(1), and (l)(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 (h), (i), (k)(1), (k)(2), (l)(1),
and (l)(2) of this AD.
(m) 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 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: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office. The
AMOC approval letter must specifically reference this AD.
(2) 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 a serviceable
condition. Any substitutions or changes to procedures or tests
identified as RC require approval of an AMOC.
(3) 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
[[Page 22943]]
the DOA, the approval must include the DOA-authorized signature.
(n) Special Flight Permits
Special flight permits may be issued in accordance with sections
21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199) to operate the airplane to a location where the airplane
can be modified (if the operator elects to do so), provided the MLG
remains extended throughout the flight.
(o) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) European Aviation Safety Agency (EASA) Airworthiness
Directive 2014-0058, dated March 11, 2014, 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-
2015-0831.
(2) For Airbus 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 account.airworth-eas@airbus.com;
Internet https://www.airbus.com. (3) For Messier-Bugatti-Dowty
service information identified in this AD, contact Messier Services
Americas, Customer Support Center, 45360 Severn Way, Sterling, VA
20166 8910; phone: 703-450-8233; fax: 703-404-1621; Internet:
https://techpubs.services/messier-dowty.com.
(4) 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 April 9, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-09288 Filed 4-23-15; 8:45 am]
BILLING CODE 4910-13-P
