Airworthiness Directives; Airbus Airplanes, 8571-8575 [2015-02922]
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Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Proposed Rules
(b) Affected ADs
This AD replaces AD 2012–24–10,
Amendment 39–17280 (77 FR 73908,
December 12, 2012).
(c) Applicability
This AD applies to The Boeing Company
Model 747–400 and –400F series airplanes,
certificated in any category, as identified in
Boeing Alert Service Bulletin 747–21A2523,
Revision 2, dated June 7, 2013.
(d) Subject
Air Transport Association (ATA) of
America Code 21, Air Conditioning; 31,
Instruments.
(e) Unsafe Condition
This AD was prompted by reports of
intermittent or blank displays of a certain
integrated display unit (IDU) in the flight
deck. We are issuing this AD to prevent IDU
malfunctions, which could affect the ability
of the flightcrew to read primary displays for
airplane attitude, altitude, or airspeed, and
consequently reduce the ability of the
flightcrew to maintain control of the airplane.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Software Update
This paragraph restates the requirements of
paragraph (g) of AD 2012–24–10,
Amendment 39–17280 (77 FR 73908,
December 12, 2012), with revised service
information. Within 12 months after January
16, 2013 (the effective date of AD 2012–24–
10), except as provided by paragraph (j) of
this AD: Install integrated display system
software, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–21A2523, Revision 1,
dated October 3, 2011; or Boeing Alert
Service Bulletin 747–21A2523, Revision 2,
dated June 7, 2013. As of the effective date
of this AD, only Boeing Alert Service Bulletin
747–21A2523, Revision 2, dated June 7,
2013, may be used to accomplish the actions
required by this paragraph.
Note 1 to paragraph (g) and (j) of this AD:
Boeing Alert Service Bulletin 747–21A2523,
Revision 1, dated October 3, 2011; and
Boeing Alert Service Bulletin 747–21A2523,
Revision 2, dated June 7, 2013; refer to
Boeing Service Bulletin 747–31–2426, dated
July 29, 2010 (for airplanes with Rolls-Royce
engines); Boeing Service Bulletin 747–31–
2427, dated July 29, 2010 (for airplanes with
General Electric engines); and Boeing Service
Bulletin 747–31–2428, dated July 29, 2010
(for airplanes with Pratt & Whitney engines);
as additional sources of guidance for the
software installation specified by paragraph
(g) of this AD. Boeing Service Bulletin 747–
31–2426, dated July 29, 2010; Boeing Service
Bulletin 747–31–2427, dated July 29, 2010;
and Boeing Service Bulletin 747–31–2428,
dated July 29, 2010; are not incorporated by
reference in this AD.
(h) Retained Duct Assembly Replacement
and Wiring Changes
This paragraph restates the requirements of
paragraph (h) of AD 2012–24–10,
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Amendment 39–17280 (77 FR 73908,
December 12, 2012), with revised service
information. Within 60 months after January
16, 2013 (the effective date of AD 2012–24–
10), except as provided by paragraph (j) of
this AD: Replace the duct assembly with a
new duct assembly, do wiring changes, and
route certain wire bundles, in accordance
with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–21A2523,
Revision 1, dated October 3, 2011; or Boeing
Alert Service Bulletin 747–21A2523,
Revision 2, dated June 7, 2013. As of the
effective date of this AD, only Boeing Alert
Service Bulletin 747–21A2523, Revision 2,
dated June 7, 2013, may be used to
accomplish the actions required by this
paragraph.
(i) New Installation of Pressure Switch
Bracket and Altitude Pressure Switch
Within 60 months after the effective date
of this AD: Install a new or serviceable
pressure switch bracket and a new or
serviceable altitude pressure switch on the
forward side of the station 400 bulkhead, do
wiring changes, route certain wire bundles,
install a new hose assembly, and perform a
leak check and a functional logic test, in
accordance with the Accomplishment
Instructions of the service information
specified in paragraph (i)(1) or (i)(2) of this
AD, as applicable.
(1) For Model 747–400F series airplanes:
Boeing Alert Service Bulletin 747–21–2532,
dated February 13, 2014.
(2) For Model 747–400BCF series
airplanes: Boeing Alert Service Bulletin 747–
21–2533, dated February 13, 2014.
(j) Actions for Group 21 Airplanes
For Group 21 airplanes, as identified in
Boeing Alert Service Bulletin 747–21A2523,
Revision 2, dated June 7, 2013, do the actions
specified in paragraphs (j)(1) and (j)(2) of this
AD, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–21A2523, Revision 2, dated June 7,
2013.
(1) Within 12 months after the effective
date of this AD, install integrated display
system software.
(2) Within 60 months after the effective
date of this AD, replace the duct assembly
with a new duct assembly, do wiring
changes, and route certain wire bundles.
(k) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraphs (g) and (h) of this AD,
if those actions were performed before the
effective date of this AD using Boeing Alert
Service Bulletin 747–21A2523, Revision 1,
dated October 3, 2011.
(l) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in
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paragraph (m)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD if it is approved by
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOCs approved for AD 2012–24–10,
Amendment 39–17280 (77 FR 73908,
December 12, 2012), are approved as AMOCs
for the corresponding provisions of
paragraphs (g) and (h) of this AD.
(m) Related Information
(1) For more information about this AD,
contact Ana Martinez Hueto, Aerospace
Engineer, Cabin Safety and Environmental
Systems Branch, ANM–150S, FAA, Seattle
Aircraft Certification Office (ACO), 1601 Lind
Avenue SW., Renton, WA 98057–3356;
phone: 425–917–6592; fax: 425–917–6591;
email: ana.m.hueto@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone 206–
544–5000, extension 1; fax 206–766–5680;
Internet https://www.myboeingfleet.com. You
may view this referenced service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, Washington.
For information on the availability of this
material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on February
2, 2015.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–02925 Filed 2–17–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–0243; Directorate
Identifier 2014–NM–114–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all
SUMMARY:
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Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Proposed Rules
Airbus Model A300 series airplanes;
Model A300 B4–600, B4–600R, and F4–
600R series airplanes, and A300 C4–
605R Variant F airplanes (collectively
called Model A300–600 series
airplanes); and Model A310 series
airplanes. This proposed AD was
prompted by reports of cracked
aluminum support struts of the
trimmable horizontal stabilizer (THS)
caused by stress corrosion. This
proposed AD would require inspections
to identify the part number of each
support strut, repetitive inspections for
cracking of the THS support strut ends,
installation of reinforcing clamps on
strut ends, and replacement of support
struts, if necessary. We are proposing
this AD to detect and correct cracked
THS support struts, which could lead to
the rupture of all four support struts
making the remaining structure unable
to carry limit loads, which could result
in loss of the THS and reduced control
of the airplane.
DATES: We must receive comments on
this proposed AD by April 6, 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 service information identified in
this proposed AD, contact Airbus SAS,
Airworthiness Office—EAW, 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–
0243; or in person at the Docket
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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.
Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–2125;
fax 425–227–1149.
FOR FURTHER INFORMATION CONTACT:
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–2015–0243; Directorate Identifier
2014–NM–114–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 2014–0164, dated July 11,
2014 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for all Airbus
Model A300 series airplanes; Model
A300 B4–600, B4–600R, and F4–600R
series airplanes, and A300 C4–605R
Variant F airplanes (collectively called
Model A300–600 series airplanes); and
Model A310 series airplanes. The MCAI
states:
During scheduled maintenance, several
Trimmable Horizontal Stabilizer (THS)
support struts were found cracked at the strut
ends. The THS is supported and articulated
at frame (FR) 91 in the tail cone. Lateral
movement is prevented by four diagonal
support struts.
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Investigations revealed that the cracks were
caused by stress corrosion and propagated
from the inside to the outside of the strut.
This condition, if not detected and
corrected, could lead to the rupture of all
four THS support struts at FR91, which
would make the remaining structure unable
to carry limit loads, potentially resulting in
loss of the Horizontal Tail Plane.
To address this unsafe condition, EASA
issued [EASA] AD 2014–0121 [https://
ad.easa.europa.eu/ad/2014-0121] to require
repetitive High Frequency Eddy Current
(HFEC) inspections of the THS support strut
ends, installation of reinforcing clamps on
strut ends and, depending on findings,
replacement of damaged support struts.
Installation of reinforcing clamps on strut
ends is considered a temporary solution
pending introduction of a re-designed
support strut.
Since that [EASA] AD was issued, it was
discovered that the [EASA] AD appeared to
also require HFEC inspections of steel struts,
which are not prone to cracking. The unsafe
condition exists only on support struts made
of aluminum, which were introduced
through Airbus modification (mod) 06101,
but may also have been installed in service
as replacement parts on aeroplanes in premod 06101 configuration.
For the reason described above, this
[EASA] AD retains the requirements of EASA
AD 2014–0121, which is superseded, and
clarifies the need for an initial identification
of the support struts installed on aeroplanes
in pre-mod 06101 configuration. The related
Airbus Service Bulletins (SB) remain
unchanged.
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–
0243.
Relevant Service Information Under 1
CFR Part 51
Airbus has issued the following
service information. The actions
described in this service information are
intended to correct the unsafe condition
identified in the MCAI.
• Airbus Service Bulletin A300–53–
0394, dated February 14, 2014. This
service information describes
procedures for reinforcing the support
struts of the THS at frame 91 in the
fuselage tail section of Airbus Model
A300 series airplanes.
• Airbus Service Bulletin A300–53–
0395, dated February 14, 2014. This
service information describes
procedures for inspecting for cracking of
the support struts of the THS at frame
91 in the fuselage tail section of Airbus
Model A300 series airplanes.
• Airbus Service Bulletin A300–53–
6172, dated February 14, 2014. This
service information describes
procedures for reinforcing the support
struts of the THS at frame 91 in the
fuselage tail section of Airbus Model
A300–600 series airplanes.
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• Airbus Service Bulletin A300–53–
6174, dated February 14, 2014. This
service information describes
procedures for inspecting for cracking of
the support struts of the THS at frame
91 in the fuselage tail section of Airbus
Model A300–600 series airplanes.
• Airbus Service Bulletin A310–53–
2136, dated February 14, 2014. This
service information describes
procedures for reinforcing the support
struts of the THS at frame 91 in the
fuselage tail section of Airbus Model
A310 series airplanes.
• Airbus Service Bulletin A310–53–
2137, dated February 14, 2014. This
service information describes
procedures for inspecting for cracking of
the support struts of the THS at frame
91 in the fuselage tail section of Airbus
Model A310 series airplanes. This
service information is reasonably
available; see ADDRESSES for ways to
access this service information.
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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.
Differences Between This Proposed AD
and the MCAI or Service Information
Unlike the procedures described in
Airbus Service Bulletin A300–53–0395;
Airbus Service Bulletin A300–53–6174;
and Airbus Service Bulletin A310–53–
2137; each dated February 14, 2014; this
proposed AD would not permit further
flight if cracks are detected in the
aluminum support strut ends of the
trimmable horizontal stabilizer at frame
91. We have determined that, because of
the safety implications and
consequences associated with that
cracking, any cracked aluminum
support strut ends of the trimmable
horizontal stabilizer must be repaired or
modified before further flight. This
difference has been coordinated with
EASA and Airbus.
Costs of Compliance
We estimate that this proposed AD
affects 174 airplanes of U.S. registry.
We also estimate that it would take
about 5 work-hours per product to
comply with the basic requirements of
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this proposed AD. The average labor
rate is $85 per work-hour. Required
parts would cost about $2,100 per
product. Based on these figures, we
estimate the cost of this proposed AD on
U.S. operators to be $439,350, or $2,525
per product.
In addition, we estimate that any
necessary follow-on actions would take
about 15 work-hours and require parts
costing $10,000, for a cost of $11,275
per product. We have no way of
determining the number of aircraft that
might need these actions.
Paperwork Reduction Act
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject
to penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork
Reduction Act unless that collection of
information displays a current valid
OMB control number. The control
number for the collection of information
required by this proposed AD is 2120–
0056. The paperwork cost associated
with this proposed AD has been
detailed in the Costs of Compliance
section of this document and includes
time for reviewing instructions, as well
as completing and reviewing the
collection of information. Therefore, all
reporting associated with this proposed
AD is mandatory. Comments concerning
the accuracy of this burden and
suggestions for reducing the burden
should be directed to the FAA at 800
Independence Ave. SW., Washington,
DC 20591, ATTN: Information
Collection Clearance Officer, AES–200.
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.
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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–2015–0243;
Directorate Identifier 2014–NM–114–AD.
(a) Comments Due Date
We must receive comments by April 6,
2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes
specified in paragraphs (c)(1) through (c)(6)
of this AD, certificated in any category, all
manufacturer serial numbers.
(1) Airbus Model A300 B2–1A, B2–1C,
B2K–3C, B2–203, B4–2C, B4–103, and B4–
203 airplanes.
(2) Airbus Model A300 B4–601, B4–603,
B4–620, and B4–622 airplanes.
(3) Airbus Model A300 B4–605R and B4–
622R airplanes.
(4) Airbus Model A300 F4–605R and F4–
622R airplanes.
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(5) Airbus Model A300 C4–605R Variant F
airplanes.
(6) Airbus Model A310–203, –204, –221,
–222, –304, –322, –324, and –325 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of
cracked aluminum support struts of the
trimmable horizontal stabilizer (THS) caused
by stress corrosion. We are issuing this AD
to detect and correct cracked THS support
struts, which could lead to the rupture of all
four support struts making the remaining
structure unable to carry limit loads, which
could result in loss of the THS and reduced
control of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Inspection for Part Number
For airplanes in pre-modification 06101
configuration: Within 12 months after the
effective date of this AD, do an inspection to
identify the part number (P/N) of each
support strut installed on the trimmable
horizontal stabilizer (THS) at frame (FR) 91,
in accordance with the Accomplishment
Instructions of the applicable service bulletin
identified in paragraphs (g)(1) through (g)(3)
of this AD. A review of airplane maintenance
records is acceptable in lieu of this
inspection, provided those records can be
relied upon for that purpose and the part
number can be positively identified from that
review. If no aluminum strut(s) having P/N
R21449, R21449D, R21449G, or R21449H is
found during any inspection required by this
paragraph no further action is required by
this AD for that horizontal stabilizer, except
for paragraph (l) of this AD.
(1) For Airbus Model A300 series
airplanes: Airbus Service Bulletin A300–53–
0395, dated February 14, 2014.
(2) For Airbus Model A300 B4–600, B4–
600R, and F4–600R series airplanes, and
A300 C4–605R Variant F airplanes
(collectively called Model A300–600 series
airplanes): Airbus Service Bulletin A300–53–
6174, dated February 14, 2014.
(3) For Airbus Model A310 series
airplanes: Airbus Service Bulletin A310–53–
2137, dated February 14, 2014.
(h) Repetitive High Frequency Eddy Current
(HFEC) Inspections
For airplanes in post-modification 06101
configuration; and for airplanes in premodification 06101 configuration on which
one or more aluminum support strut(s)
having P/N R21449, P/N R21449D, P/N
R21449G, or P/N R21449H was found during
the inspection by paragraph (g) of this AD:
Within the applicable compliance times
specified in paragraphs (h)(1), (h)(2), or (h)(3)
of this AD, do an HFEC inspection for
cracking of the aluminum THS support strut
ends at FR 91, in accordance with the
Accomplishment Instructions of the
applicable service bulletin identified in
paragraphs (g)(1) through (g)(3) of this AD.
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Reinforcing clamps already installed on strut
ends must be removed before accomplishing
the HFEC inspection and re-installed after
the inspection, in accordance with the
Accomplishment Instructions of the
applicable service bulletin specified in
paragraphs (g)(1) through (g)(3) of this AD.
Repeat the inspection thereafter at intervals
not to exceed 24 months.
(1) For airplanes having manufacturer
serial number (MSN) 0499 through MSN
0747 inclusive (post-mod 06101): Within 12
months after the effective date of this AD.
(2) For airplanes having MSN 0748 through
MSN 0878 inclusive (post-mod 06101):
Within 18 months after the effective date of
this AD.
(3) For airplanes having MSN 0001 through
MSN 0498 inclusive (pre-mod 06101) having
one or more aluminum struts: Within 24
months after the effective date of this AD.
(i) Installation of Reinforcing Clamps
Concurrently with the initial HFEC
inspection required by paragraph (h) of this
AD, identify struts having P/N R21449, P/N
R21449D, P/N R21449G, or P/N R21449H
with no reinforcing clamps previously
installed, and before next flight, install
reinforcing clamps on each strut end, in
accordance with the Accomplishment
Instructions of the applicable service bulletin
specified in paragraphs (i)(1) through (i)(3) of
this AD.
(1) For Airbus Model A300 series
airplanes: Airbus Service Bulletin A300–53–
0394, dated February 14, 2014.
(2) For Airbus Model A300 B4–600, B4–
600R, and F4–600R series airplanes, and
A300 C4–605R Variant F airplanes
(collectively called Model A300–600 series
airplanes): Airbus Service Bulletin A300–53–
6172, dated February 14, 2014.
(3) For Airbus Model A310 series
airplanes: Airbus Service Bulletin A310–53–
2136, dated February 14, 2014.
(j) Corrective Actions
If, during any inspection required by
paragraph (h) of this AD, any cracking is
found, before further flight, replace the
affected THS support strut(s) with
serviceable struts and install clamps on each
strut end, in accordance with the
Accomplishment Instructions of the
applicable service bulletin identified in
paragraphs (g)(1) through (g)(3) of this AD.
(k) Clarification
Installation of reinforcing clamps as
required by paragraph (i) of this AD, and the
replacement of support struts and/or the
installation of clamps as required by
paragraph (j) of this AD, do not constitute
terminating action for the repetitive
inspections required by paragraph (h) of this
AD.
(l) Reporting
At the applicable time specified in
paragraphs (l)(1) and (l)(2) of this AD: After
accomplishment of any inspection required
by paragraphs (g) and (h) of this AD, report
all inspection results to Airbus, including no
findings, in accordance with the
Accomplishment Instructions of the
applicable service bulletins specified in
PO 00000
Frm 00014
Fmt 4702
Sfmt 4702
paragraphs (g)(1) through (g)(3) of this AD,
and paragraphs (i)(1) through (i)(3) of this
AD.
(1) If the inspection was done on or after
the effective date of this AD: Submit the
report within 30 days after the inspection.
(2) If the inspection was done before the
effective date of this AD: Submit the report
within 30 days after the effective date 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:
Dan Rodina, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–2125; 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) 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) Reporting Requirements: A federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
(n) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) European
E:\FR\FM\18FEP1.SGM
18FEP1
Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Proposed Rules
Aviation Safety Agency Airworthiness
Directive 2014–0164, dated July 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–2015–0243.
(2) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAW, 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 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 February
2, 2015.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–02922 Filed 2–17–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–0086; Directorate
Identifier 2014–NM–191–AD]
Examining the AD Docket
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all
Airbus Model A310–203 airplanes. This
proposed AD is intended to complete
certain mandated programs intended to
support the airplane reaching its limit of
validity (LOV) of the engineering data
that support the established structural
maintenance program. This proposed
AD was prompted by reports that side
link clevis bolts of the front engine
mount do not meet the Design Service
Goal (DSG) requirements on airplanes
equipped with General Electric
Company CF6–80A3 engines. This
proposed AD would require repetitive
replacement of all side link clevis
engine mount bolts. We are proposing
this AD to prevent failure of the front
engine mount, and consequent possible
departure of the engine.
DATES: We must receive comments on
this proposed AD by April 6, 2015.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
mstockstill on DSK4VPTVN1PROD with PROPOSALS
SUMMARY:
VerDate Sep<11>2014
17:51 Feb 17, 2015
Jkt 235001
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 service information identified in
this proposed AD, contact Airbus SAS,
Airworthiness Office—EAW, 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.
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
0086; 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: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton,
Washington 98057–3356; telephone
425–227–2125; 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–2015–0086; Directorate Identifier
2014–NM–191–AD’’ at the beginning of
your comments. We specifically invite
PO 00000
Frm 00015
Fmt 4702
Sfmt 4702
8575
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
As described in FAA Advisory
Circular 120 104 (https://www.faa.gov/
documentLibrary/media/Advisory_
Circular/120-104.pdf), several programs
have been developed to support
initiatives that will ensure the
continued airworthiness of aging
airplane structure. The last element of
those initiatives is the requirement to
establish a LOV of the engineering data
that support the structural maintenance
program under 14 CFR 26.21. This
proposed AD is the result of an
assessment of the previously established
programs by Airbus during the process
of establishing the LOV for Airbus
Model A310–203 airplanes. The actions
specified in this proposed AD are
necessary to complete certain programs
to ensure the continued airworthiness of
aging airplane structure and to support
an airplane reaching its LOV.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2014–0191, dated August 29,
2014 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for all Airbus
Model A310–203 airplanes. The MCAI
states:
During fatigue analysis performed in the
scope of the Extended Service Goal, taking
into account the certification loads and the
new lift-off loads, Airbus determined that
side link clevis engine mount bolts do not
meet the Design Service Goal (DSG)
requirements on aeroplanes equipped with
CF6–80A3 engines.
This condition, if not corrected, could lead
to failure of the front engine mount, possibly
resulting in-flight separation of the engine
from the aeroplane.
To address this potential unsafe condition,
Airbus issued Service Bulletin (SB) A310–
71–2038 to introduce a life limit on the side
link clevis engine mount bolts.
For the reason described above, this
[EASA] AD requires implementation of the
new life limit and replacement of all side
link clevis engine mount bolts that have
exceeded the new limit.
E:\FR\FM\18FEP1.SGM
18FEP1
]]>Agencies
[Federal Register Volume 80, Number 32 (Wednesday, February 18, 2015)]
[Proposed Rules]
[Pages 8571-8575]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-02922]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-0243; Directorate Identifier 2014-NM-114-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
[[Page 8572]]
Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4-
600R series airplanes, and A300 C4-605R Variant F airplanes
(collectively called Model A300-600 series airplanes); and Model A310
series airplanes. This proposed AD was prompted by reports of cracked
aluminum support struts of the trimmable horizontal stabilizer (THS)
caused by stress corrosion. This proposed AD would require inspections
to identify the part number of each support strut, repetitive
inspections for cracking of the THS support strut ends, installation of
reinforcing clamps on strut ends, and replacement of support struts, if
necessary. We are proposing this AD to detect and correct cracked THS
support struts, which could lead to the rupture of all four support
struts making the remaining structure unable to carry limit loads,
which could result in loss of the THS and reduced control of the
airplane.
DATES: We must receive comments on this proposed AD by April 6, 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 service information identified in this proposed AD, contact
Airbus SAS, Airworthiness Office--EAW, 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-
0243; 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: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125;
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-2015-0243;
Directorate Identifier 2014-NM-114-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 2014-0164, dated July 11, 2014 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model A300
series airplanes; Model A300 B4-600, B4-600R, and F4-600R series
airplanes, and A300 C4-605R Variant F airplanes (collectively called
Model A300-600 series airplanes); and Model A310 series airplanes. The
MCAI states:
During scheduled maintenance, several Trimmable Horizontal
Stabilizer (THS) support struts were found cracked at the strut
ends. The THS is supported and articulated at frame (FR) 91 in the
tail cone. Lateral movement is prevented by four diagonal support
struts.
Investigations revealed that the cracks were caused by stress
corrosion and propagated from the inside to the outside of the
strut.
This condition, if not detected and corrected, could lead to the
rupture of all four THS support struts at FR91, which would make the
remaining structure unable to carry limit loads, potentially
resulting in loss of the Horizontal Tail Plane.
To address this unsafe condition, EASA issued [EASA] AD 2014-
0121 [https://ad.easa.europa.eu/ad/2014-0121] to require repetitive
High Frequency Eddy Current (HFEC) inspections of the THS support
strut ends, installation of reinforcing clamps on strut ends and,
depending on findings, replacement of damaged support struts.
Installation of reinforcing clamps on strut ends is considered a
temporary solution pending introduction of a re-designed support
strut.
Since that [EASA] AD was issued, it was discovered that the
[EASA] AD appeared to also require HFEC inspections of steel struts,
which are not prone to cracking. The unsafe condition exists only on
support struts made of aluminum, which were introduced through
Airbus modification (mod) 06101, but may also have been installed in
service as replacement parts on aeroplanes in pre-mod 06101
configuration.
For the reason described above, this [EASA] AD retains the
requirements of EASA AD 2014-0121, which is superseded, and
clarifies the need for an initial identification of the support
struts installed on aeroplanes in pre-mod 06101 configuration. The
related Airbus Service Bulletins (SB) remain unchanged.
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-
0243.
Relevant Service Information Under 1 CFR Part 51
Airbus has issued the following service information. The actions
described in this service information are intended to correct the
unsafe condition identified in the MCAI.
Airbus Service Bulletin A300-53-0394, dated February 14,
2014. This service information describes procedures for reinforcing the
support struts of the THS at frame 91 in the fuselage tail section of
Airbus Model A300 series airplanes.
Airbus Service Bulletin A300-53-0395, dated February 14,
2014. This service information describes procedures for inspecting for
cracking of the support struts of the THS at frame 91 in the fuselage
tail section of Airbus Model A300 series airplanes.
Airbus Service Bulletin A300-53-6172, dated February 14,
2014. This service information describes procedures for reinforcing the
support struts of the THS at frame 91 in the fuselage tail section of
Airbus Model A300-600 series airplanes.
[[Page 8573]]
Airbus Service Bulletin A300-53-6174, dated February 14,
2014. This service information describes procedures for inspecting for
cracking of the support struts of the THS at frame 91 in the fuselage
tail section of Airbus Model A300-600 series airplanes.
Airbus Service Bulletin A310-53-2136, dated February 14,
2014. This service information describes procedures for reinforcing the
support struts of the THS at frame 91 in the fuselage tail section of
Airbus Model A310 series airplanes.
Airbus Service Bulletin A310-53-2137, dated February 14,
2014. This service information describes procedures for inspecting for
cracking of the support struts of the THS at frame 91 in the fuselage
tail section of Airbus Model A310 series airplanes. 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.
Differences Between This Proposed AD and the MCAI or Service
Information
Unlike the procedures described in Airbus Service Bulletin A300-53-
0395; Airbus Service Bulletin A300-53-6174; and Airbus Service Bulletin
A310-53-2137; each dated February 14, 2014; this proposed AD would not
permit further flight if cracks are detected in the aluminum support
strut ends of the trimmable horizontal stabilizer at frame 91. We have
determined that, because of the safety implications and consequences
associated with that cracking, any cracked aluminum support strut ends
of the trimmable horizontal stabilizer must be repaired or modified
before further flight. This difference has been coordinated with EASA
and Airbus.
Costs of Compliance
We estimate that this proposed AD affects 174 airplanes of U.S.
registry.
We also estimate that it would take about 5 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 $2,100
per product. Based on these figures, we estimate the cost of this
proposed AD on U.S. operators to be $439,350, or $2,525 per product.
In addition, we estimate that any necessary follow-on actions would
take about 15 work-hours and require parts costing $10,000, for a cost
of $11,275 per product. We have no way of determining the number of
aircraft that might need these actions.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this proposed AD
is 2120-0056. The paperwork cost associated with this proposed AD has
been detailed in the Costs of Compliance section of this document and
includes time for reviewing instructions, as well as completing and
reviewing the collection of information. Therefore, all reporting
associated with this proposed AD is mandatory. Comments concerning the
accuracy of this burden and suggestions for reducing the burden should
be directed to the FAA at 800 Independence Ave. SW., Washington, DC
20591, ATTN: Information Collection Clearance Officer, AES-200.
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-2015-0243; Directorate Identifier 2014-NM-
114-AD.
(a) Comments Due Date
We must receive comments by April 6, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes specified in paragraphs
(c)(1) through (c)(6) of this AD, certificated in any category, all
manufacturer serial numbers.
(1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-
103, and B4-203 airplanes.
(2) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622
airplanes.
(3) Airbus Model A300 B4-605R and B4-622R airplanes.
(4) Airbus Model A300 F4-605R and F4-622R airplanes.
[[Page 8574]]
(5) Airbus Model A300 C4-605R Variant F airplanes.
(6) Airbus Model A310-203, -204, -221, -222, -304, -322, -324,
and -325 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of cracked aluminum support
struts of the trimmable horizontal stabilizer (THS) caused by stress
corrosion. We are issuing this AD to detect and correct cracked THS
support struts, which could lead to the rupture of all four support
struts making the remaining structure unable to carry limit loads,
which could result in loss of the THS and reduced control of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection for Part Number
For airplanes in pre-modification 06101 configuration: Within 12
months after the effective date of this AD, do an inspection to
identify the part number (P/N) of each support strut installed on
the trimmable horizontal stabilizer (THS) at frame (FR) 91, in
accordance with the Accomplishment Instructions of the applicable
service bulletin identified in paragraphs (g)(1) through (g)(3) of
this AD. A review of airplane maintenance records is acceptable in
lieu of this inspection, provided those records can be relied upon
for that purpose and the part number can be positively identified
from that review. If no aluminum strut(s) having P/N R21449,
R21449D, R21449G, or R21449H is found during any inspection required
by this paragraph no further action is required by this AD for that
horizontal stabilizer, except for paragraph (l) of this AD.
(1) For Airbus Model A300 series airplanes: Airbus Service
Bulletin A300-53-0395, dated February 14, 2014.
(2) For Airbus Model A300 B4-600, B4-600R, and F4-600R series
airplanes, and A300 C4-605R Variant F airplanes (collectively called
Model A300-600 series airplanes): Airbus Service Bulletin A300-53-
6174, dated February 14, 2014.
(3) For Airbus Model A310 series airplanes: Airbus Service
Bulletin A310-53-2137, dated February 14, 2014.
(h) Repetitive High Frequency Eddy Current (HFEC) Inspections
For airplanes in post-modification 06101 configuration; and for
airplanes in pre-modification 06101 configuration on which one or
more aluminum support strut(s) having P/N R21449, P/N R21449D, P/N
R21449G, or P/N R21449H was found during the inspection by paragraph
(g) of this AD: Within the applicable compliance times specified in
paragraphs (h)(1), (h)(2), or (h)(3) of this AD, do an HFEC
inspection for cracking of the aluminum THS support strut ends at FR
91, in accordance with the Accomplishment Instructions of the
applicable service bulletin identified in paragraphs (g)(1) through
(g)(3) of this AD. Reinforcing clamps already installed on strut
ends must be removed before accomplishing the HFEC inspection and
re-installed after the inspection, in accordance with the
Accomplishment Instructions of the applicable service bulletin
specified in paragraphs (g)(1) through (g)(3) of this AD. Repeat the
inspection thereafter at intervals not to exceed 24 months.
(1) For airplanes having manufacturer serial number (MSN) 0499
through MSN 0747 inclusive (post-mod 06101): Within 12 months after
the effective date of this AD.
(2) For airplanes having MSN 0748 through MSN 0878 inclusive
(post-mod 06101): Within 18 months after the effective date of this
AD.
(3) For airplanes having MSN 0001 through MSN 0498 inclusive
(pre-mod 06101) having one or more aluminum struts: Within 24 months
after the effective date of this AD.
(i) Installation of Reinforcing Clamps
Concurrently with the initial HFEC inspection required by
paragraph (h) of this AD, identify struts having P/N R21449, P/N
R21449D, P/N R21449G, or P/N R21449H with no reinforcing clamps
previously installed, and before next flight, install reinforcing
clamps on each strut end, in accordance with the Accomplishment
Instructions of the applicable service bulletin specified in
paragraphs (i)(1) through (i)(3) of this AD.
(1) For Airbus Model A300 series airplanes: Airbus Service
Bulletin A300-53-0394, dated February 14, 2014.
(2) For Airbus Model A300 B4-600, B4-600R, and F4-600R series
airplanes, and A300 C4-605R Variant F airplanes (collectively called
Model A300-600 series airplanes): Airbus Service Bulletin A300-53-
6172, dated February 14, 2014.
(3) For Airbus Model A310 series airplanes: Airbus Service
Bulletin A310-53-2136, dated February 14, 2014.
(j) Corrective Actions
If, during any inspection required by paragraph (h) of this AD,
any cracking is found, before further flight, replace the affected
THS support strut(s) with serviceable struts and install clamps on
each strut end, in accordance with the Accomplishment Instructions
of the applicable service bulletin identified in paragraphs (g)(1)
through (g)(3) of this AD.
(k) Clarification
Installation of reinforcing clamps as required by paragraph (i)
of this AD, and the replacement of support struts and/or the
installation of clamps as required by paragraph (j) of this AD, do
not constitute terminating action for the repetitive inspections
required by paragraph (h) of this AD.
(l) Reporting
At the applicable time specified in paragraphs (l)(1) and (l)(2)
of this AD: After accomplishment of any inspection required by
paragraphs (g) and (h) of this AD, report all inspection results to
Airbus, including no findings, in accordance with the Accomplishment
Instructions of the applicable service bulletins specified in
paragraphs (g)(1) through (g)(3) of this AD, and paragraphs (i)(1)
through (i)(3) of this AD.
(1) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done before the effective date of this
AD: Submit the report within 30 days after the effective date 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: Dan Rodina,
Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-2125; 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) 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) Reporting Requirements: A federal agency may not conduct or
sponsor, and a person is not required to respond to, nor shall a
person be subject to a penalty for failure to comply with a
collection of information subject to the requirements of the
Paperwork Reduction Act unless that collection of information
displays a current valid OMB Control Number. The OMB Control Number
for this information collection is 2120-0056. Public reporting for
this collection of information is estimated to be approximately 5
minutes per response, including the time for reviewing instructions,
completing and reviewing the collection of information. All
responses to this collection of information are mandatory. Comments
concerning the accuracy of this burden and suggestions for reducing
the burden should be directed to the FAA at: 800 Independence Ave.
SW., Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.
(n) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) European
[[Page 8575]]
Aviation Safety Agency Airworthiness Directive 2014-0164, dated July
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-2015-0243.
(2) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAW, 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 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 February 2, 2015.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-02922 Filed 2-17-15; 8:45 am]
BILLING CODE 4910-13-P
