Airworthiness Directives; Airbus Airplanes, 68434-68437 [2015-27925]
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68434
Federal Register / Vol. 80, No. 214 / Thursday, November 5, 2015 / Rules and Regulations
specifies to submit certain information to the
manufacturer, this AD does not include that
requirement.
(j) Alternative Methods of Compliance
(AMOCs)
(k) Related Information
For more information about this AD, Carl
Gray, Aerospace Engineer, Airframe Branch,
ACE–117A, FAA, Atlanta ACO, 1701
Columbia Avenue, College Park, GA 30337;
phone: 404–474–5554; fax: 404–474–5605;
email: carl.w.gray@faa.gov.
(l) Material Incorporated by Reference
jstallworth on DSK7TPTVN1PROD with RULES
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Lockheed Martin Electra Service
Bulletin 88/SB–722, dated April 30, 2014.
(ii) Reserved.
(3) For Lockheed service information
identified in this AD, contact Lockheed
Martin Corporation/Lockheed Martin
Aeronautics Company, Airworthiness Office,
Dept. 6A0M, Zone 0252, Column P–58, 86 S.
Cobb Drive, Marietta, GA 30063; phone: 770–
494–5444; fax: 770–494–5445; email:
ams.portal@lmco.com; Internet https://
www.lockheedmartin.com/ams/tools/
TechPubs.html.
(4) You may view this service information
at 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.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on October
22, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
BILLING CODE 4910–13–P
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Federal Aviation Administration
14 CFR Part 39
(1) The Manager, Atlanta 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
paragraph (k) of this AD.
(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.
[FR Doc. 2015–27919 Filed 11–4–15; 8:45 am]
DEPARTMENT OF TRANSPORTATION
[Docket No. FAA–2015–0244; Directorate
Identifier 2014–NM–127–AD; Amendment
39–18313; AD 2015–22–08]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Airbus Model A318, A319, and A320
series airplanes. This AD was prompted
by a cracked upper cardan in the main
landing gear (MLG). This AD requires
revising the maintenance or inspection
program, as applicable, to reduce the
life limits for the MLG upper cardan for
certain installations. We are issuing this
AD to prevent failure of the upper
cardan in the MLG, which could result
in MLG collapse and subsequent
damage to the airplane and injury to
occupants.
DATES: This AD becomes effective
December 10, 2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of December 10, 2015.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2015-0244; or in
person at the Docket Management
Facility, U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC.
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.airwortheas@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. It is also available on the Internet
at https://www.regulations.gov by
searching for and locating Docket No.
FAA–2015–0244.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
SUMMARY:
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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:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Airbus Model A318, A319,
and A320 series airplanes. The NPRM
published in the Federal Register on
March 5, 2015 (80 FR 11964).
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2014–0141, dated June 4, 2014
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition for all Airbus Model A318,
A319, and A320 series airplanes. The
MCAI states:
During an A320–200 77T main landing
gear (MLG) fatigue test by Messier BugattiDowty (MBD), an upper cardan was found
with a crack, emanating from the grease hole/
main lug intersection. The affected upper
cardan, Part Number (P/N) 201163620, is
listed in the applicable Airworthiness
Limitations Section (ALS) Part 1 with a
demonstrated fatigue life of 60,000 landings.
This condition, if not corrected, could lead
to MLG upper cardan failure, possibly
resulting in MLG collapse and subsequent
damage to the aeroplane and injury to
occupants.
Prompted by these findings and further to
analysis, it has been decided to reduce the
life limit for certain installations of the P/N
201163620 MLG upper cardan.
For the reasons described above, this AD
requires implementation of the new life
limits, as applicable, and replacement of any
affected MLG upper cardan units that have
already exceeded the reduced limit.
The reduced life limits for the affected
MLG upper cardan are expected to be
incorporated in a next revision of the Airbus
A318/A319/A320/A321 ALS Part 1.
You may examine the MCAI in the AD
docket on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2015-02440003.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM (80 FR 11964,
March 5, 2015) and the FAA’s response
to each comment.
Request To Extend the Compliance
Time
Delta Airlines (DAL) requested that
paragraph (g) of the proposed AD (80 FR
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Federal Register / Vol. 80, No. 214 / Thursday, November 5, 2015 / Rules and Regulations
11964, March 5, 2015) be revised so the
initial compliance time for replacing the
MLG upper cardan is extended and
corresponds to that of European
Aviation Safety Agency (EASA) AD
2014–0141, dated June 4, 2014. EASA
AD 2014–0141 specifies an initial
compliance time of ‘‘within 3 months’’
after the effective date of that EASA AD
and the proposed AD specified an initial
compliance time of prior to the
applicable life limit specified in
paragraphs (g)(1) through (g)(5), or
within 30 days after the effective date of
the AD, whichever occurs later.
We agree with the commenter’s
request. In consideration of the average
utilization rate of affected U.S.
operators, the practical aspects of an
orderly modification of the U.S. fleet
during regular maintenance periods,
and the availability of required
modification parts, we have determined
that a 3 month initial compliance time
is appropriate for replacing the MLG
upper cardan. We have changed
paragraph (g) of this AD accordingly.
jstallworth on DSK7TPTVN1PROD with RULES
Request To Reference Next Higher Part
Number Assembly
Lufthansa Technik requested that the
part number for the next higher
assembly of MLG cardan part number
(P/N) 201163620 be referenced in the
NPRM (80 FR 11964, March 5, 2015).
The commenter stated that the NPRM
and corresponding EASA AD 2014–
0141, dated June 4, 2014, reference P/N
201163620, but that part number is not
identified in the aircraft illustrated parts
catalog (AIPC). The commenter is
concerned that if operators only look in
the AIPC to see if P/N 201163620 is
identified, and it is not there, they may
falsely think that their airplanes would
not be affected by the NPRM.
We do not agree with the commenter’s
request. Although MLG cardan P/N
201163620 is not included in the AIPC,
it is identified in Airbus A318/A319/
A320/A321 ALS Part 1—Safe Life
Airworthiness Limitation Items, which
is part of the approved type design for
these airplanes. Therefore, we have not
changed this AD in this regard.
Clarification of Parts Installation
Limitation
In paragraph (j) of the proposed AD
(NPRM (80 FR 11964, March 5, 2015),
we referred to applicable life limits in
paragraphs (g)(1) through (g)(5) of the
proposed AD. For airplanes other than
those identified paragraphs (g)(1)
through (g)(5) of the proposed AD, the
life limit is in Airbus A318/A319/A320/
A321 ALS Part 1—Safe Life
Airworthiness Limitation, Revision 02,
dated May 13, 2011, as specified in
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paragraph (h)(5) of this AD. In addition,
if a part is transferred between
airplanes, operators must adjust the life
limit using the method specified in
Airbus A318/A319/A320/A321 ALS
Part 1—Safe Life Airworthiness
Limitation, Revision 02, dated May 13,
2011, as specified in paragraph (h)(3) of
this AD. We have clarified paragraph (j)
of this AD by also referring to
paragraphs (h)(3) and (h)(5) of this AD.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM (80 FR
11964, March 5, 2015) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (80 FR 11964,
March 5, 2015).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Related Service Information Under 1
CFR Part 51
Airbus has issued A318/A319/A320/
A321 ALS Part 1—Safe Life
Airworthiness Limitation Items,
Revision 02, dated May 13, 2011. This
document provides revised instructions
and life limits for airworthiness
limitations items. 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 AD.
Costs of Compliance
We estimate that this AD affects 851
airplanes of U.S. registry.
We also estimate that it will take
about 1 work-hour per product to
comply with the basic requirements of
this AD. The average labor rate is $85
per work-hour. Required parts will cost
about $0 per product. Based on these
figures, we estimate the cost of this AD
on U.S. operators to be $72,335, or $85
per product.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
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68435
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 AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2015-0244; 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
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
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68436
Federal Register / Vol. 80, No. 214 / Thursday, November 5, 2015 / Rules and Regulations
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):
■
2015–22–08 Airbus: Amendment 39–18313.
Docket No. FAA–2015–0244; Directorate
Identifier 2014–NM–127–AD.
(a) Effective Date
This AD becomes effective December 10,
2015.
(b) Affected ADs
For airplanes with configurations specified
in paragraphs (g)(1) through (g)(5) of this AD:
Paragraph (g) of this AD terminates the life
limit specified in paragraph (n)(1) of AD
2014–23–15, Amendment 39–18031 (80 FR
3871, January 26, 2015), for airplanes having
a main landing gear (MLG) upper cardan part
number (P/N) 201163620.
(c) Applicability
This AD applies to the Airbus airplanes
identified in paragraphs (c)(1), (c)(2), and
(c)(3) of this AD, certificated in any category,
all manufacturer serial numbers.
(1) Model A318–111, –112, –121, and –122
airplanes.
(2) Model A319–111, –112, –113, –114,
–115, –131, –132, and –133 airplanes.
(3) Model A320–211, –212, –214, –231,
–232, and –233 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 32, Landing Gear.
(e) Reason
This AD was prompted by a cracked upper
cardan in the main landing gear (MLG). We
are issuing this AD to prevent failure of the
upper cardan in the MLG, which could result
in MLG collapse and subsequent damage to
the airplane and injury to occupants.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Revision to Maintenance or Inspection
Program
For airplanes having a MLG upper cardan
part number (P/N) 201163620: Within 30
days after the effective date of this AD, revise
the maintenance or inspection program, as
applicable, to incorporate the applicable life
limits for the MLG upper cardan P/N
201163620 specified in paragraphs (g)(1)
through (g)(5) of this AD and the life limit
clarifications specified in paragraph (h) of
this AD. The initial compliance time for
replacing the MLG upper cardan is prior to
the applicable life limit specified in
paragraphs (g)(1) through (g)(5) of this AD, or
within 3 months after the effective date of
this AD, whichever occurs later.
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Accomplishing this revision terminates the
life limit required by paragraph (n)(1) of AD
2014–23–15, Amendment 39–18031 (80 FR
3871, January 26, 2015), for the MLG upper
cardan P/N 201163620 for that airplane only.
(1) For Airbus Model A319 series
airplanes, pre-Airbus Modification 26644,
excluding corporate jets post-Airbus
Modification 28238, 28162, and 28342: The
life limit is 50,590 total flight cycles.
(2) For Airbus Model A319 series
airplanes, post-Airbus Modification 26644,
excluding corporate jets post-Airbus
Modification 28238, 28162, and 28342: The
life limit is 56,480 total flight cycles.
(3) For Airbus Model A320 series airplanes
pre-Airbus Modification 26644 having weight
variant (WV) WV011, WV012, WV016, or
WV018: The life limit is 50,590 total flight
cycles.
(4) For Airbus Model A320 series airplanes
post-Airbus Modification 26644, having
WV011, WV012, WV016, or WV018: The life
limit is 56,480 total flight cycles.
(5) For Airbus Model A320 series airplanes
post-Airbus Modification 26644, having
WV015 or WV017: The life limit is 42,140
total flight cycles.
(h) Additional Life Limit Clarifications
(1) The life limits specified in paragraphs
(g)(1) through (g)(5) of this AD are total flight
cycles accumulated by the MLG since first
installation on an airplane.
(2) The life limits specified in paragraphs
(g)(1) through (g)(5) of this AD are applicable
only for the airplane model, configuration
and WV specified in those paragraphs.
(3) If a part is transferred between airplanes
having a different life limit for the MLG unit,
adjust the life limit using the method
specified in Airbus A318/A319/A320/A321
ALS Part 1—Safe Life Airworthiness
Limitation Items, Revision 02, dated May 13,
2011.
Note 1 to paragraphs (h)(3) and (h)(5) of
this AD: Airbus A318/A319/A320/A321 ALS
Part 1—Safe Life Airworthiness Limitation
Items, Revision 02, dated May 13, 2011, is
already required by paragraph (n) of AD
2014–23–15, Amendment 39–18031 (80 FR
3871, January 26, 2015).
(4) A MLG unit on which Airbus
Modification 26644 is installed is also known
as ‘‘enhanced’’ landing gear and is identified
as P/N 201582xxx Leg and Dressing Series.
A MLG unit that does not have Airbus
Modification 26644 installed is identified as
P/N 201375xxx Leg and Dressing Series. (The
xxx designation is a placeholder for
numbers).
(5) For airplanes with configurations not
specified in paragraphs (g)(1) through (g)(5)
of this AD, the life limit for the MLG unit is
specified in Airbus A318/A319/A320/A321
ALS Part 1—Safe Life Airworthiness
Limitation Items, Revision 02, dated May 13,
2011.
(i) No Alternative Actions and Intervals
After the maintenance or inspection
program, as applicable, has been revised as
required by paragraph (g) of this AD, no
alternative actions (e.g., inspections) or
intervals may be used unless the actions or
intervals are approved as an alternative
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method of compliance (AMOC) in
accordance with the procedures specified in
paragraph (k)(1) of this AD.
(j) Parts Installation Limitation
As of the effective date of this AD, a MLG
upper cardan having P/N 201163620 may be
installed on an airplane, provided the part
life has not exceeded the applicable life limit
specified in paragraphs (g)(1) through (g)(5)
of this AD, paragraph (h)(3) of this AD, and
paragraph (h)(5) of this AD, and is replaced
with a serviceable part prior to exceeding the
applicable life limit specified in paragraphs
(g)(1) through (g)(5) of this AD, paragraph
(h)(3) of this AD, and paragraph (h)(5) of this
AD.
(k) 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 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.
(l) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2014–0141, dated
June 4, 2014, for related information. This
MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov/
#!documentDetail;D=FAA-2015-0244.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Airbus A318/A319/A320/A321 ALS Part
1—Safe Life Airworthiness Limitation Items,
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Federal Register / Vol. 80, No. 214 / Thursday, November 5, 2015 / Rules and Regulations
Revision 02, dated May 13, 2011. The
revision level of this document is identified
on only the title page and in the Record of
Revisions. The revision date is not identified
on the title page of this document.
(ii) Reserved.
(3) 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.
(4) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on October
22, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–27925 Filed 11–4–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0649; Directorate
Identifier 2014–NM–132–AD; Amendment
39–18314; AD 2015–22–09]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 787–8
airplanes. This AD was prompted by
reports of missing plugs found prior to
airplane delivery, during manufacturing
inspections, at various locations in
certain stringers of the lower lobe cargo
compartments. This AD requires drilling
a hole and installing and bonding plugs
in certain stringers of the lower lobe
cargo compartments. We are issuing this
AD to detect and correct missing or
misaligned plugs which, in the event of
a fire, could cause an increased rate of
loss of Halon in the lower cargo
compartments, and result in the
inability to extinguish a fire and
jstallworth on DSK7TPTVN1PROD with RULES
SUMMARY:
VerDate Sep<11>2014
14:34 Nov 04, 2015
Jkt 238001
consequent loss of control of the
airplane.
DATES: This AD is effective December
10, 2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of December 10, 2015.
ADDRESSES: 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, WA. For information on the
availability of this material at the FAA,
call 425–227–1221. It is also available
on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0649.
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–2014–
0649; 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 AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Francis Smith, Aerospace Engineer,
Cabin Safety and Environmental
Systems Branch, ANM–150S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–917–6596; fax:
425–917–6590; email: francis.smith@
faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain The Boeing Company
Model 787–8 airplanes. The NPRM
published in the Federal Register on
September 23, 2014 (79 FR 56682). The
NPRM was prompted by reports of
missing plugs found prior to airplane
delivery, during manufacturing
PO 00000
Frm 00017
Fmt 4700
Sfmt 4700
68437
inspections, at various locations in
certain stringers of the lower lobe cargo
compartments. The NPRM proposed to
require drilling a hole and installing and
bonding plugs in certain stringers of the
lower lobe cargo compartments. We are
issuing this AD to detect and correct
missing or misaligned plugs which, in
the event of a fire, could cause an
increased rate of loss of Halon in the
lower cargo compartments, and result in
the inability to extinguish a fire and
consequent loss of control of the
airplane.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM (79 FR 56682,
September 23, 2014) and the FAA’s
response to each comment.
Supportive Comment
United Airlines stated that it concurs
with the NPRM (79 FR 56682,
September 23, 2014), and agrees that the
detection and correction of the missing
or misaligned plugs will maintain a
higher level of safety.
Request To Delay Issuance of the NPRM
(79 FR 56682, September 23, 2014)
All Nippon Airways (ANA) asked that
we delay issuance of the NPRM (79 FR
56682, September 23, 2014) until Boeing
Alert Service Bulletin B787–81205–
SB530024–00, Issue 001, dated May 15,
2014 (referred to as the appropriate
source of service information for
accomplishing the specified actions),
can be revised. ANA noted that the
service information specifies using a
stringer plug removal/installation tool,
having tool number (T/N)
MIT140Z4372–3; however, this tool
does not work well for doing the
actions. ANA provided the following
reasons to substantiate its request:
• For the instructions specified in
Task 1 of this service information, the
connecting tube on the tool (T/N
140Z4372–8/–15) interferes with the
fasteners at the section 41/43 joint;
therefore, the tool cannot be inserted
into the stringers. The connecting tube
needs to be shortened in length and
trimmed to taper.
• For the instructions specified in
Task 3 of the service information, the
tool (T/N 140Z4372–3) cannot be
inserted at stringers 30R through 35R,
adjacent to the cargo door, because it
won’t bend at the location adjacent to
the stringer end and frame.
• For the instructions specified in
Task 3 of the service information, the
tool (T/N 140Z4372–3) is inserted into
the stringer from station (STA) 1593 to
E:\FR\FM\05NOR1.SGM
05NOR1
]]>Agencies
[Federal Register Volume 80, Number 214 (Thursday, November 5, 2015)]
[Rules and Regulations]
[Pages 68434-68437]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-27925]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-0244; Directorate Identifier 2014-NM-127-AD;
Amendment 39-18313; AD 2015-22-08]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
Airbus Model A318, A319, and A320 series airplanes. This AD was
prompted by a cracked upper cardan in the main landing gear (MLG). This
AD requires revising the maintenance or inspection program, as
applicable, to reduce the life limits for the MLG upper cardan for
certain installations. We are issuing this AD to prevent failure of the
upper cardan in the MLG, which could result in MLG collapse and
subsequent damage to the airplane and injury to occupants.
DATES: This AD becomes effective December 10, 2015.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of December 10,
2015.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2015-0244; or in person at the
Docket Management Facility, U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC.
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 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. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0244.
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:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to all Airbus Model A318,
A319, and A320 series airplanes. The NPRM published in the Federal
Register on March 5, 2015 (80 FR 11964).
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2014-0141, dated June 4, 2014 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model
A318, A319, and A320 series airplanes. The MCAI states:
During an A320-200 77T main landing gear (MLG) fatigue test by
Messier Bugatti-Dowty (MBD), an upper cardan was found with a crack,
emanating from the grease hole/main lug intersection. The affected
upper cardan, Part Number (P/N) 201163620, is listed in the
applicable Airworthiness Limitations Section (ALS) Part 1 with a
demonstrated fatigue life of 60,000 landings.
This condition, if not corrected, could lead to MLG upper cardan
failure, possibly resulting in MLG collapse and subsequent damage to
the aeroplane and injury to occupants.
Prompted by these findings and further to analysis, it has been
decided to reduce the life limit for certain installations of the P/
N 201163620 MLG upper cardan.
For the reasons described above, this AD requires implementation
of the new life limits, as applicable, and replacement of any
affected MLG upper cardan units that have already exceeded the
reduced limit.
The reduced life limits for the affected MLG upper cardan are
expected to be incorporated in a next revision of the Airbus A318/
A319/A320/A321 ALS Part 1.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2015-0244-0003.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM (80
FR 11964, March 5, 2015) and the FAA's response to each comment.
Request To Extend the Compliance Time
Delta Airlines (DAL) requested that paragraph (g) of the proposed
AD (80 FR
[[Page 68435]]
11964, March 5, 2015) be revised so the initial compliance time for
replacing the MLG upper cardan is extended and corresponds to that of
European Aviation Safety Agency (EASA) AD 2014-0141, dated June 4,
2014. EASA AD 2014-0141 specifies an initial compliance time of
``within 3 months'' after the effective date of that EASA AD and the
proposed AD specified an initial compliance time of prior to the
applicable life limit specified in paragraphs (g)(1) through (g)(5), or
within 30 days after the effective date of the AD, whichever occurs
later.
We agree with the commenter's request. In consideration of the
average utilization rate of affected U.S. operators, the practical
aspects of an orderly modification of the U.S. fleet during regular
maintenance periods, and the availability of required modification
parts, we have determined that a 3 month initial compliance time is
appropriate for replacing the MLG upper cardan. We have changed
paragraph (g) of this AD accordingly.
Request To Reference Next Higher Part Number Assembly
Lufthansa Technik requested that the part number for the next
higher assembly of MLG cardan part number (P/N) 201163620 be referenced
in the NPRM (80 FR 11964, March 5, 2015). The commenter stated that the
NPRM and corresponding EASA AD 2014-0141, dated June 4, 2014, reference
P/N 201163620, but that part number is not identified in the aircraft
illustrated parts catalog (AIPC). The commenter is concerned that if
operators only look in the AIPC to see if P/N 201163620 is identified,
and it is not there, they may falsely think that their airplanes would
not be affected by the NPRM.
We do not agree with the commenter's request. Although MLG cardan
P/N 201163620 is not included in the AIPC, it is identified in Airbus
A318/A319/A320/A321 ALS Part 1--Safe Life Airworthiness Limitation
Items, which is part of the approved type design for these airplanes.
Therefore, we have not changed this AD in this regard.
Clarification of Parts Installation Limitation
In paragraph (j) of the proposed AD (NPRM (80 FR 11964, March 5,
2015), we referred to applicable life limits in paragraphs (g)(1)
through (g)(5) of the proposed AD. For airplanes other than those
identified paragraphs (g)(1) through (g)(5) of the proposed AD, the
life limit is in Airbus A318/A319/A320/A321 ALS Part 1--Safe Life
Airworthiness Limitation, Revision 02, dated May 13, 2011, as specified
in paragraph (h)(5) of this AD. In addition, if a part is transferred
between airplanes, operators must adjust the life limit using the
method specified in Airbus A318/A319/A320/A321 ALS Part 1--Safe Life
Airworthiness Limitation, Revision 02, dated May 13, 2011, as specified
in paragraph (h)(3) of this AD. We have clarified paragraph (j) of this
AD by also referring to paragraphs (h)(3) and (h)(5) of this AD.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (80 FR 11964, March 5, 2015) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (80 FR 11964, March 5, 2015).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
Airbus has issued A318/A319/A320/A321 ALS Part 1--Safe Life
Airworthiness Limitation Items, Revision 02, dated May 13, 2011. This
document provides revised instructions and life limits for
airworthiness limitations items. 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 AD.
Costs of Compliance
We estimate that this AD affects 851 airplanes of U.S. registry.
We also estimate that it will take about 1 work-hour per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Required parts will cost about $0 per product.
Based on these figures, we estimate the cost of this AD on U.S.
operators to be $72,335, or $85 per product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2015-0244; 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 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
[[Page 68436]]
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):
2015-22-08 Airbus: Amendment 39-18313. Docket No. FAA-2015-0244;
Directorate Identifier 2014-NM-127-AD.
(a) Effective Date
This AD becomes effective December 10, 2015.
(b) Affected ADs
For airplanes with configurations specified in paragraphs (g)(1)
through (g)(5) of this AD: Paragraph (g) of this AD terminates the
life limit specified in paragraph (n)(1) of AD 2014-23-15, Amendment
39-18031 (80 FR 3871, January 26, 2015), for airplanes having a main
landing gear (MLG) upper cardan part number (P/N) 201163620.
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category,
all manufacturer serial numbers.
(1) Model A318-111, -112, -121, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes.
(3) Model A320-211, -212, -214, -231, -232, and -233 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 32, Landing
Gear.
(e) Reason
This AD was prompted by a cracked upper cardan in the main
landing gear (MLG). We are issuing this AD to prevent failure of the
upper cardan in the MLG, which could result in MLG collapse and
subsequent damage to the airplane and injury to occupants.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Revision to Maintenance or Inspection Program
For airplanes having a MLG upper cardan part number (P/N)
201163620: Within 30 days after the effective date of this AD,
revise the maintenance or inspection program, as applicable, to
incorporate the applicable life limits for the MLG upper cardan P/N
201163620 specified in paragraphs (g)(1) through (g)(5) of this AD
and the life limit clarifications specified in paragraph (h) of this
AD. The initial compliance time for replacing the MLG upper cardan
is prior to the applicable life limit specified in paragraphs (g)(1)
through (g)(5) of this AD, or within 3 months after the effective
date of this AD, whichever occurs later. Accomplishing this revision
terminates the life limit required by paragraph (n)(1) of AD 2014-
23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015), for the
MLG upper cardan P/N 201163620 for that airplane only.
(1) For Airbus Model A319 series airplanes, pre-Airbus
Modification 26644, excluding corporate jets post-Airbus
Modification 28238, 28162, and 28342: The life limit is 50,590 total
flight cycles.
(2) For Airbus Model A319 series airplanes, post-Airbus
Modification 26644, excluding corporate jets post-Airbus
Modification 28238, 28162, and 28342: The life limit is 56,480 total
flight cycles.
(3) For Airbus Model A320 series airplanes pre-Airbus
Modification 26644 having weight variant (WV) WV011, WV012, WV016,
or WV018: The life limit is 50,590 total flight cycles.
(4) For Airbus Model A320 series airplanes post-Airbus
Modification 26644, having WV011, WV012, WV016, or WV018: The life
limit is 56,480 total flight cycles.
(5) For Airbus Model A320 series airplanes post-Airbus
Modification 26644, having WV015 or WV017: The life limit is 42,140
total flight cycles.
(h) Additional Life Limit Clarifications
(1) The life limits specified in paragraphs (g)(1) through
(g)(5) of this AD are total flight cycles accumulated by the MLG
since first installation on an airplane.
(2) The life limits specified in paragraphs (g)(1) through
(g)(5) of this AD are applicable only for the airplane model,
configuration and WV specified in those paragraphs.
(3) If a part is transferred between airplanes having a
different life limit for the MLG unit, adjust the life limit using
the method specified in Airbus A318/A319/A320/A321 ALS Part 1--Safe
Life Airworthiness Limitation Items, Revision 02, dated May 13,
2011.
Note 1 to paragraphs (h)(3) and (h)(5) of this AD: Airbus A318/
A319/A320/A321 ALS Part 1--Safe Life Airworthiness Limitation Items,
Revision 02, dated May 13, 2011, is already required by paragraph
(n) of AD 2014-23-15, Amendment 39-18031 (80 FR 3871, January 26,
2015).
(4) A MLG unit on which Airbus Modification 26644 is installed
is also known as ``enhanced'' landing gear and is identified as P/N
201582xxx Leg and Dressing Series. A MLG unit that does not have
Airbus Modification 26644 installed is identified as P/N 201375xxx
Leg and Dressing Series. (The xxx designation is a placeholder for
numbers).
(5) For airplanes with configurations not specified in
paragraphs (g)(1) through (g)(5) of this AD, the life limit for the
MLG unit is specified in Airbus A318/A319/A320/A321 ALS Part 1--Safe
Life Airworthiness Limitation Items, Revision 02, dated May 13,
2011.
(i) No Alternative Actions and Intervals
After the maintenance or inspection program, as applicable, has
been revised as required by paragraph (g) of this AD, no alternative
actions (e.g., inspections) or intervals may be used unless the
actions or intervals are approved as an alternative method of
compliance (AMOC) in accordance with the procedures specified in
paragraph (k)(1) of this AD.
(j) Parts Installation Limitation
As of the effective date of this AD, a MLG upper cardan having
P/N 201163620 may be installed on an airplane, provided the part
life has not exceeded the applicable life limit specified in
paragraphs (g)(1) through (g)(5) of this AD, paragraph (h)(3) of
this AD, and paragraph (h)(5) of this AD, and is replaced with a
serviceable part prior to exceeding the applicable life limit
specified in paragraphs (g)(1) through (g)(5) of this AD, paragraph
(h)(3) of this AD, and paragraph (h)(5) of this AD.
(k) 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
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.
(l) Related Information
Refer to Mandatory Continuing Airworthiness Information (MCAI)
EASA Airworthiness Directive 2014-0141, dated June 4, 2014, for
related information. This MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2015-
0244.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Airbus A318/A319/A320/A321 ALS Part 1--Safe Life
Airworthiness Limitation Items,
[[Page 68437]]
Revision 02, dated May 13, 2011. The revision level of this document
is identified on only the title page and in the Record of Revisions.
The revision date is not identified on the title page of this
document.
(ii) Reserved.
(3) 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.
(4) You may view this service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on October 22, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-27925 Filed 11-4-15; 8:45 am]
BILLING CODE 4910-13-P
