Airworthiness Directives; Airbus Airplanes, 26487-26490 [2015-10948]
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Federal Register / Vol. 80, No. 89 / Friday, May 8, 2015 / Proposed Rules
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
(h) Retained Restrictions on Alternative
Actions, Intervals, and/or CDCCLs, With a
New Exception
This paragraph restates the requirements of
paragraph (k) of AD 2011–21–06,
Amendment 39–16829 (76 FR 64788, October
19, 2011), with a new exception. Except as
required by paragraph (i) of this AD, after
accomplishing the revision required by
paragraph (g) of this AD, no alternative
actions (e.g., inspections), intervals, and/or
CDCCLs may be used unless the actions,
intervals, and/or CDCCLs are approved as an
alternative method of compliance (AMOC) in
accordance with the procedures specified in
paragraph (l) of this AD.
(i) New Maintenance or Inspection Program
Revision
Within 90 days after the effective date of
this AD: Revise the maintenance or
inspection program, as applicable, by
incorporating Subjects 05–10–10,
‘‘Airworthiness Limitations’’; 05–10–20,
‘‘Certification Maintenance Requirements’’;
and 05–10–30, ‘‘Critical Design Configuration
Control Limitations (CDCCL)—Fuel System’’;
of Chapter 05, ‘‘Airworthiness Limitations,’’
of the BAE Systems (Operations) Limited J41
AMM, Revision 38, dated September 15,
2013. The initial compliance times for the
tasks are at the applicable times specified in
paragraphs (i)(1), (i)(2), and (i)(3) of this AD.
Doing the actions required by this paragraph
terminates the requirements of paragraph (g)
of this AD.
(1) For replacement tasks of life limited
parts specified in Subject 05–10–10,
‘‘Airworthiness Limitations,’’ of Chapter 05,
‘‘Airworthiness Limitations,’’ of the BAE
Systems (Operations) Limited J41 AMM,
Revision 38, dated September 15, 2013: Prior
to the applicable flight cycles (landings) or
flight hours (flying hours) on the part
specified in the ‘‘Mandatory Life Limits’’
column in Subject 05–10–10, or within 90
days after the effective date of this AD,
whichever occurs later.
(2) For structurally significant item tasks
specified in Subject 05–10–10,
‘‘Airworthiness Limitations,’’ of Chapter 05,
‘‘Airworthiness Limitations,’’ of the BAE
Systems (Operations) Limited J41 AMM,
Revision 38, dated September 15, 2013: Prior
to the accumulation of the applicable flight
cycles specified in the ‘‘Initial Inspection’’
column in Subject 05–10–10, or within 90
days after the effective date of this AD,
whichever occurs later.
(3) For certification maintenance
requirements tasks specified in Subject 05–
10–20, ‘‘Certification Maintenance
Requirements,’’ of Chapter 05,
‘‘Airworthiness Limitations,’’ of the BAE
Systems (Operations) Limited J41 AMM,
Revision 38, dated September 15, 2013: Prior
to the accumulation of the applicable flight
hours specified in the ‘‘Time Between
Checks’’ column in Subject 05–10–20, or
within 90 days after the effective date of this
AD, whichever occurs later; except for tasks
that specify ‘‘first flight of the day’’ in the
‘‘Time Between Checks’’ column in Subject
05–10–20, the initial compliance time is the
first flight of the next day after doing the
revision required by paragraph (j) of this AD,
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26487
or within 90 days the effective date of this
AD, whichever occurs later.
the approval must include the DOAauthorized signature.
(j) New Restrictions on Alternative Actions,
Intervals, and/or (CDCCLs)
After the maintenance or inspection
program, as applicable, has been revised as
required by paragraph (i) of this AD, no
alternative actions (e.g., inspections),
intervals, and/or CDCCLs may be used unless
the actions, intervals, and/or CDCCLs are
approved as an AMOC in accordance with
the procedures specified in paragraph (l) of
this AD.
(m) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0043, dated
February 21, 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–2015–1279.
(2) For service information identified in
this AD, contact BAE SYSTEMS (Operations)
Limited, Customer Information Department,
Prestwick International Airport, Ayrshire,
KA9 2RW, Scotland, United Kingdom;
telephone +44 1292 675207; fax +44 1292
675704; email RApublications@
baesystems.com; Internet https://
www.baesystems.com/Businesses/
RegionalAircraft/index.htm. 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.
(k) Credit for Previous Actions
This paragraph restates the provisions of
paragraph (j) of AD 2011–21–06, Amendment
39–16829 (76 FR 64788, October 19, 2011).
This paragraph provides credit for actions
required by paragraph (g) of this AD, if those
actions were performed before November 23,
2011 (the effective date of AD 2011–21–06),
in accordance with Subjects 05–10–10,
‘‘Airworthiness Limitations’’; 05–10–20,
‘‘Certification Maintenance Requirements’’;
and 05–10–30, ‘‘Critical Design Configuration
Control Limitations (CDCCL)—Fuel System’’;
of Chapter 05, ‘‘Airworthiness Limitations,’’
of the BAE Systems (Operations) Limited
Jetstream Series 4100 AMM, Revision 33,
dated February 15, 2010; which are not
incorporated by reference in this AD.
(l) 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:
Todd Thompson, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone: 425–227–1175; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov.
(i) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
(ii) AMOCs approved previously for AD
2011–21–06, Amendment 39–16829 (76 FR
64788, October 19, 2011), are not approved
as AMOCs with this AD.
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the European Aviation Safety Agency
(EASA); or BAE Systems (Operations)
Limited’s EASA Design Organization
Approval (DOA). If approved by the DOA,
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Issued in Renton, Washington, on April 29,
2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–11023 Filed 5–7–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–1277; Directorate
Identifier 2014–NM–155–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 certain
Airbus Model A319, A320, and A321
series airplanes. This proposed AD was
prompted by fatigue testing that
determined fatigue damage could
appear on clips, shear webs, and angles
at certain rear fuselage sections and
certain frames. 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 would require replacing the clips,
the shear webs, and angles, including
doing all applicable related investigative
SUMMARY:
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Federal Register / Vol. 80, No. 89 / Friday, May 8, 2015 / Proposed Rules
actions, and repair if necessary. We are
proposing this AD to prevent fatigue
damage on the clips, shear webs, and
angles, which could affect the structural
integrity of the airplane.
DATES: We must receive comments on
this proposed AD by June 22, 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,
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.
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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–
1277; 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:
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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–2015–1277; Directorate Identifier
2014–NM–155–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
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 limit of validity (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 the DAH
during the process of establishing the
LOV for Airbus Model A319, A320, and
A321 series 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 2014–0177, dated July 25,
2014 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain Airbus
Model A319, A320, and A321 series
airplanes. The MCAI states:
During the A320 fatigue test campaign for
Extended Service Goal (ESG), it was
determined that fatigue damage could appear
on the clips, shear webs and angles at rear
fuselage section 19, on Frame (FR) 72 and
FR74.
This condition, if not detected and
corrected, could affect the structural integrity
of the aeroplane.
To address this potential unsafe condition,
Airbus developed a modification, which has
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been published through Airbus Service
Bulletin (SB) A320–53–1266 for in-service
application to allow aeroplanes to operate up
to the new ESG limit.
For the reasons described above, this
[EASA] AD requires replacement of the
affected clips, shear webs and angles at rear
fuselage section 19, FR72 and FR74
[including all applicable related investigative
actions and repair if any cracking is found].
Related investigative actions include
rotating probe testing for cracking of the
fastener holes and high frequency eddy
current inspections for cracking of the
stringers. 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–
1277.
Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A320–53–1266, Revision 01, dated June
20, 2013. This service information
describes procedures for replacing clips,
shear webs, and angles at rear fuselage
section 19, FR72 and FR74. The actions
described in this service information are
intended to correct the unsafe condition
identified in the MCAI. This service
information is reasonably available
because the interested parties have
access to it through their normal course
of business or by the means identified
in the ADDRESSES section of this NPRM.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of these same
type designs.
Costs of Compliance
We estimate that this proposed AD
affects 44 airplanes of U.S. registry.
We also estimate that it would take
about 110 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 $411,400, or $9,350 per product.
We have received no definitive data
on the costs of required parts.
According to the manufacturer, some
of the costs of this proposed AD may be
covered under warranty, thereby
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reducing the cost impact on affected
individuals. We do not control warranty
coverage for affected individuals. As a
result, we have included all costs in our
cost estimate.
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.
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
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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:
VerDate Sep<11>2014
16:19 May 07, 2015
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§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Airbus: Docket No. FAA–2015–1277;
Directorate Identifier 2014–NM–155–AD.
(a) Comments Due Date
We must receive comments by June 22,
2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the airplanes identified
in paragraphs (c)(1), (c)(2), and (c)(3) of this
AD, certificated in any category, all
manufacturer serial numbers, except those on
which Airbus Modification 30975 has been
embodied in production.
(1) Airbus Model A319–111, –112, –113,
–114, –115, –131, –132, and –133 airplanes.
(2) Airbus Model A320–211, –212, –214,
–231, –232, and –233 airplanes.
(3) Airbus Model A321–111, –112, –131,
–211, –212, –213, –231, and –232 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by fatigue testing
that determined fatigue damage could appear
on clips, shear webs, and angles at certain
rear fuselage sections and certain frames.
This 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.
We are issuing this AD to prevent fatigue
damage on the clips, shear webs, and angles,
which could affect the structural integrity of
the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Replacement
At the later of the times specified in
paragraphs (g)(1) and (g)(2) of this AD:
Replace the clips, shear webs, and angles at
rear fuselage section 19, frame (FR)72 and
FR74, and do all applicable related
investigative actions before further flight, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
53–1266, Revision 01, dated June 20, 2013.
If any crack is found during any related
investigative action required by this AD:
Before further flight, repair using a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or the European Aviation
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Sfmt 4702
26489
Safety Agency (EASA); or Airbus’s EASA
Design Organization Approval (DOA).
(1) Before exceeding 48,000 flight cycles or
96,000 flight hours, whichever occurs first
since the airplane’s first flight.
(2) Within 30 days after the effective date
of this AD.
(h) Additional Replacement for Airplanes on
Which the Replacement Required by
Paragraph (g) of This AD Is Done Before
30,000 Flight Cycles or 60,000 Flight Hours
For airplanes on which the replacement of
clips, shear webs, and angles specified in
Airbus Service Bulletin A320–53–1266 is
done before accumulating 30,000 flight
cycles or 60,000 flight hours, whichever
occurred first since the airplane’s first flight:
Within 30,000 flight cycles or 60,000 flight
hours, whichever occurs first after that
replacement, do the replacement specified in
paragraph (g) of this AD.
(i) Credit for Previous Actions
Except as required by paragraph (h) of this
AD: This paragraph provides credit for the
replacement required by paragraph (g) of this
AD, if those actions were performed before
the effective date of this AD using Airbus
Service Bulletin A320–53–1266, dated
January 11, 2013, which is not incorporated
by reference in this AD.
(j) 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) 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 EASA; or Airbus’s EASA DOA. If
approved by the DOA, the approval must
include the DOA-authorized signature.
(k) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0177, dated
July 25, 2014, for related information. This
MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov by
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searching for and locating Docket No. FAA–
2015–1277.
(2) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email 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 April 29,
2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–10948 Filed 5–7–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–0929; Directorate
Identifier 2014–NM–218–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Bombardier, Inc. Model BD–100–1A10
(Challenger 300) airplanes. This
proposed AD was prompted by multiple
reports of chafing found on an electrical
wiring harness in the aft equipment bay,
caused by contact between the wiring
harness and a neighboring hydraulic
line. This proposed AD would require
an inspection, repair if necessary, and
modification of the wiring harness
installation to ensure that the wiring
harness routing is correct and a
minimum clearance between the wire
and the hydraulic line is maintained.
We are proposing this AD to detect and
correct chafing on an electrical wiring
harness, which could cause an electrical
short circuit or lead to a malfunction of
the flight control system, the engine
indication system, or the hydraulic
power control system, and adversely
affect the continued safe operation and
landing of the airplane.
DATES: We must receive comments on
this proposed AD by June 22, 2015.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
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SUMMARY:
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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 Bombardier,
ˆ
Inc., 400 Cote Vertu Road West, Dorval,
´
Quebec H4S 1Y9, Canada; telephone:
514–855–5000; fax: 514–855–7401;
email thd.crj@aero.bombardier.com;
Internet https://www.bombardier.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–
0929; 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:
Assata Dessaline, Aerospace Engineer,
Avionics and Service Branch, ANE–172,
FAA, New York Aircraft Certification
Office, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone: 516–
228–7301; fax: 516–794–5531.
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–2015–0929; Directorate Identifier
2014–NM–218–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
PO 00000
Frm 00022
Fmt 4702
Sfmt 4702
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
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian
Airworthiness Directive CF–2014–32,
dated September 8, 2014 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Bombardier, Inc. Model BD–
100–1A10 (Challenger 300) airplanes.
The MCAI states:
There have been multiple in-service
reports of chafing found on an electrical
wiring harness in the aft equipment bay. An
investigation determined that the chafing was
attributed to contact between the wiring
harness and a neighboring hydraulic line.
This chafing could cause an electrical short
circuit or lead to a malfunction of the flight
control system, the engine indication system,
or the hydraulic power control system; which
could adversely affect the continued safe
operation and landing of the aeroplane.
This [Canadian] AD mandates the
inspection [general visual inspection],
rectification as required [repair of damage
(including wear and chafing)], and
modification of the wiring harness
installation to ensure the correct wiring
routing and a minimum clearance between
the wire and the hydraulic line is
maintained.
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–
0929.
Related Service Information Under 1
CFR Part 51
Bombardier, Inc. has issued Service
Bulletin 100–24–24, dated June 6, 2014.
The service information describes
procedures for an inspection, repair if
necessary, and modification to reroute
wiring harness installation to prevent
contact with the hydraulic line. This
service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section of
this NPRM.
E:\FR\FM\08MYP1.SGM
08MYP1
]]>Agencies
[Federal Register Volume 80, Number 89 (Friday, May 8, 2015)]
[Proposed Rules]
[Pages 26487-26490]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-10948]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-1277; Directorate Identifier 2014-NM-155-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
certain Airbus Model A319, A320, and A321 series airplanes. This
proposed AD was prompted by fatigue testing that determined fatigue
damage could appear on clips, shear webs, and angles at certain rear
fuselage sections and certain frames. 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 would require replacing the clips, the shear webs, and angles,
including doing all applicable related investigative
[[Page 26488]]
actions, and repair if necessary. We are proposing this AD to prevent
fatigue damage on the clips, shear webs, and angles, which could affect
the structural integrity of the airplane.
DATES: We must receive comments on this proposed AD by June 22, 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, 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-
1277; 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-2015-1277;
Directorate Identifier 2014-NM-155-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
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 limit of
validity (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 the DAH
during the process of establishing the LOV for Airbus Model A319, A320,
and A321 series 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 2014-0177, dated July 25, 2014 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A319, A320, and A321 series airplanes. The MCAI states:
During the A320 fatigue test campaign for Extended Service Goal
(ESG), it was determined that fatigue damage could appear on the
clips, shear webs and angles at rear fuselage section 19, on Frame
(FR) 72 and FR74.
This condition, if not detected and corrected, could affect the
structural integrity of the aeroplane.
To address this potential unsafe condition, Airbus developed a
modification, which has been published through Airbus Service
Bulletin (SB) A320-53-1266 for in-service application to allow
aeroplanes to operate up to the new ESG limit.
For the reasons described above, this [EASA] AD requires
replacement of the affected clips, shear webs and angles at rear
fuselage section 19, FR72 and FR74 [including all applicable related
investigative actions and repair if any cracking is found].
Related investigative actions include rotating probe testing for
cracking of the fastener holes and high frequency eddy current
inspections for cracking of the stringers. 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-2015-1277.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A320-53-1266, Revision 01, dated
June 20, 2013. This service information describes procedures for
replacing clips, shear webs, and angles at rear fuselage section 19,
FR72 and FR74. The actions described in this service information are
intended to correct the unsafe condition identified in the MCAI. This
service information is reasonably available because the interested
parties have access to it through their normal course of business or by
the means identified in the ADDRESSES section of this NPRM.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of these
same type designs.
Costs of Compliance
We estimate that this proposed AD affects 44 airplanes of U.S.
registry.
We also estimate that it would take about 110 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 $411,400,
or $9,350 per product.
We have received no definitive data on the costs of required parts.
According to the manufacturer, some of the costs of this proposed
AD may be covered under warranty, thereby
[[Page 26489]]
reducing the cost impact on affected individuals. We do not control
warranty coverage for affected individuals. As a result, we have
included all costs in our cost estimate.
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-2015-1277; Directorate Identifier 2014-NM-
155-AD.
(a) Comments Due Date
We must receive comments by June 22, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the airplanes identified in paragraphs
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category,
all manufacturer serial numbers, except those on which Airbus
Modification 30975 has been embodied in production.
(1) Airbus Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes.
(2) Airbus Model A320-211, -212, -214, -231, -232, and -233
airplanes.
(3) Airbus Model A321-111, -112, -131, -211, -212, -213, -231,
and -232 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by fatigue testing that determined fatigue
damage could appear on clips, shear webs, and angles at certain rear
fuselage sections and certain frames. This 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. We are
issuing this AD to prevent fatigue damage on the clips, shear webs,
and angles, which could affect the structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Replacement
At the later of the times specified in paragraphs (g)(1) and
(g)(2) of this AD: Replace the clips, shear webs, and angles at rear
fuselage section 19, frame (FR)72 and FR74, and do all applicable
related investigative actions before further flight, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A320-53-1266, Revision 01, dated June 20, 2013. If any crack is
found during any related investigative action required by this AD:
Before further flight, repair 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).
(1) Before exceeding 48,000 flight cycles or 96,000 flight
hours, whichever occurs first since the airplane's first flight.
(2) Within 30 days after the effective date of this AD.
(h) Additional Replacement for Airplanes on Which the Replacement
Required by Paragraph (g) of This AD Is Done Before 30,000 Flight
Cycles or 60,000 Flight Hours
For airplanes on which the replacement of clips, shear webs, and
angles specified in Airbus Service Bulletin A320-53-1266 is done
before accumulating 30,000 flight cycles or 60,000 flight hours,
whichever occurred first since the airplane's first flight: Within
30,000 flight cycles or 60,000 flight hours, whichever occurs first
after that replacement, do the replacement specified in paragraph
(g) of this AD.
(i) Credit for Previous Actions
Except as required by paragraph (h) of this AD: This paragraph
provides credit for the replacement required by paragraph (g) of
this AD, if those actions were performed before the effective date
of this AD using Airbus Service Bulletin A320-53-1266, dated January
11, 2013, which is not incorporated by reference in this AD.
(j) 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) 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 EASA;
or Airbus's EASA DOA. If approved by the DOA, the approval must
include the DOA-authorized signature.
(k) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2014-0177, dated July 25, 2014,
for related information. This MCAI may be found in the AD docket on
the Internet at https://www.regulations.gov by
[[Page 26490]]
searching for and locating Docket No. FAA-2015-1277.
(2) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email 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 April 29, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-10948 Filed 5-7-15; 8:45 am]
BILLING CODE 4910-13-P
