Airworthiness Directives; Airbus Airplanes, 81792-81795 [2015-32885]
Download as PDF
<![CDATA[
81792
Federal Register / Vol. 80, No. 251 / Thursday, December 31, 2015 / Proposed Rules
52948, September 2, 2015, at the modified
area only.
(2) Accomplishing the actions specified in
paragraphs (i)(2)(i) and (i)(2)(ii) of this AD
terminates the inspections required by
paragraph (g) of AD 2014–20–10,
Amendment 39–17983 (79 FR 60331, October
7, 2014), at the modified area only, provided
the actions are accomplished concurrently, or
the actions specified in paragraph (i)(2)(ii) of
this AD are done after accomplishing the
actions specified in paragraph (i)(2)(i) of this
AD.
(i) The actions specified in paragraphs
(g)(1) through (g)(4) of this AD on the left and
right struts are done in accordance with the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 777–71–
0055, Revision 1, dated April 15, 2015; and
the revision specified in paragraph (g)(5) of
this AD is done.
(ii) A one-time general visual inspection
for hydraulic fluid contamination (including
contamination caused by hydraulic fluid in
its liquid, vapor, and/or solid (coked) form)
of the interior of the strut forward dry bay,
and all applicable related investigative and
corrective actions (including checking drain
lines for blockage due to hydraulic fluid
coking, and cleaning or replacing drain lines
to allow drainage) are done in accordance
with the Accomplishment Instructions of
Boeing Special Attention Service Bulletin
777–54–0028, Revision 1, dated December
10, 2013, except where Boeing Special
Attention Service Bulletin 777–54–0028,
Revision 1, dated December 10, 2013,
specifies to contact Boeing for repair, the
repair must be done using a method
approved in accordance with the procedures
specified in paragraph (k) of this AD.
identified in an RC step, must be done to
comply with the AD. An AMOC is required
for any deviations to RC steps, including
substeps and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(l) Related Information
(1) For more information about this AD,
contact Kevin Nguyen, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA, Seattle
Aircraft Certification Office (ACO), 1601 Lind
Avenue SW., Renton, WA 98057–3356;
phone: 425–917–6501; fax: 425–917–6590;
email: kevin.nguyen@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone 206–
544–5000, extension 1; fax 206–766–5680;
Internet https://www.myboeingfleet.com. You
may view this referenced service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on
December 21, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–32852 Filed 12–30–15; 8:45 am]
tkelley on DSK3SPTVN1PROD with PROPOSALS
(j) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraph (g) of this AD, if those
actions were performed before the effective
date of this AD using Boeing Special
Attention Service Bulletin 777–71–0055,
dated June 12, 2014, which is not
incorporated by reference in this AD.
BILLING CODE 4910–13–P
(k) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in
paragraph (l)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) For service information that contains
steps that are labeled as Required for
Compliance (RC), the provisions of
paragraphs (k)(3)(i) and (k)(3)(ii) apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
[Docket No. FAA–2015–8132; Directorate
Identifier 2015–NM–127–AD]
VerDate Sep<11>2014
16:32 Dec 30, 2015
Jkt 238001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
Examining the AD Docket
14 CFR Part 39
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 A318, A319, A320, and
A321 series airplanes. This proposed
AD was prompted by a report of cracks
found during maintenance inspections
on certain lugs of the 10VU rack side
fittings in the cockpit. This proposed
AD would require repetitive inspections
for cracking of the lugs on the 10VU
rack side fittings, and repair of any
cracking. We are proposing this AD to
SUMMARY:
PO 00000
Frm 00008
Fmt 4702
prevent loss of flight-critical
information displayed to the flightcrew
during a critical phase of flight, such as
an approach or takeoff, which could
result in loss of airplane control at an
altitude insufficient for recovery.
DATES: We must receive comments on
this proposed AD by February 16, 2016.
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.
Sfmt 4702
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
8132; 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:
E:\FR\FM\31DEP1.SGM
31DEP1
Federal Register / Vol. 80, No. 251 / Thursday, December 31, 2015 / Proposed Rules
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–2015–8132; Directorate Identifier
2015–NM–127–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
tkelley on DSK3SPTVN1PROD with PROPOSALS
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2015–0170, dated August 18,
2015 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain Airbus
Model A318, A319, A320, and A321
series airplanes. The MCAI states:
During an unscheduled maintenance
operation on an A330 aeroplane, the 10VU
rack was removed for access and cracks were
discovered on 10VU rack side fittings on lugs
1, 3, and 4. As a similar design is installed
on A320 family aeroplanes, a sampling
review was done to determine the possible
fleet impact. The result showed that several
aeroplanes had cracked or broken 10VU rack
side fittings.
This condition, if not detected and
corrected, could lead to a high vibration level
on the primary flight- and navigation
displays during critical flight phases (takeoff
and landing), possibly creating reading
difficulties for the crew.
Prompted by these findings, Airbus
developed mod 35869 to reinforce the
affected rack fitting lugs. For in-service
aeroplanes, Airbus published Service
Bulletin (SB) A320–92–1087 to provide
inspection and repair instructions.
For the reasons described above, this
[EASA] AD requires repetitive detailed
inspections (DET) of the affected 10VU rack
fitting lugs and, depending on findings,
accomplishment of a repair.
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–
8132.
VerDate Sep<11>2014
16:32 Dec 30, 2015
Jkt 238001
Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A320–92–1087, Revision 02, dated
November 25, 2014. The service
information describes procedures for
repetitive inspections for cracking of the
lugs on the 10VU rack side fittings, and
repair of any cracking. 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.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of these same
type designs.
Explanation of ‘‘RC’’ Procedures and
Tests in Service Information
The FAA worked in conjunction with
industry, under the Airworthiness
Directive Implementation Aviation
Rulemaking Committee (ARC), to
enhance the AD system. One
enhancement was a new process for
annotating which procedures and tests
in the service information are required
for compliance with an AD.
Differentiating these procedures and
tests from other tasks in the service
information is expected to improve an
owner’s/operator’s understanding of
crucial AD requirements and help
provide consistent judgment in AD
compliance. The procedures and tests
identified as RC (required for
compliance) in any service information
have a direct effect on detecting,
preventing, resolving, or eliminating an
identified unsafe condition.
As specified in a Note under the
Accomplishment Instructions of the
specified service information,
procedures and tests that are identified
as RC in any service information must
be done to comply with the proposed
AD. However, procedures and tests that
are not identified as RC are
recommended. Those procedures and
tests that are not identified as RC may
be deviated from using accepted
methods in accordance with the
operator’s maintenance or inspection
PO 00000
Frm 00009
Fmt 4702
Sfmt 4702
81793
program without obtaining approval of
an alternative method of compliance
(AMOC), provided the procedures and
tests identified as RC can be done and
the airplane can be put back in an
airworthy condition. Any substitutions
or changes to procedures or tests
identified as RC will require approval of
an AMOC.
Costs of Compliance
We estimate that this proposed AD
affects 959 airplanes of U.S. registry.
We also estimate that it would take
about 2 work-hours per product to
comply with the basic requirements of
this proposed AD, and 1 work-hour per
product to report inspection findings.
The average labor rate is $85 per workhour. Based on these figures, we
estimate the cost of this proposed AD on
U.S. operators to be $244,545, or $255
per product.
In addition, we estimate that any
necessary repair would take about 84
work-hours, for a cost of $7,140 per
product. We have received no definitive
data that would enable us to provide
part cost estimates for the on-condition
actions specified in this proposed AD.
We have no way of determining the
number of aircraft that might need these
actions.
Paperwork Reduction Act
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject
to penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork
Reduction Act unless that collection of
information displays a current valid
OMB control number. The control
number for the collection of information
required by this AD is 2120–0056. The
paperwork cost associated with this AD
has been detailed in the Costs of
Compliance section of this document
and includes time for reviewing
instructions, as well as completing and
reviewing the collection of information.
Therefore, all reporting associated with
this AD is mandatory. Comments
concerning the accuracy of this burden
and suggestions for reducing the burden
should be directed to the FAA at 800
Independence Ave. SW., Washington,
DC 20591, ATTN: Information
Collection Clearance Officer, AES–200.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
E:\FR\FM\31DEP1.SGM
31DEP1
81794
Federal Register / Vol. 80, No. 251 / Thursday, December 31, 2015 / Proposed Rules
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
tkelley on DSK3SPTVN1PROD with PROPOSALS
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Airbus: Docket No. FAA–2015–8132;
Directorate Identifier 2015–NM–127–AD.
VerDate Sep<11>2014
16:32 Dec 30, 2015
Jkt 238001
(a) Comments Due Date
We must receive comments by February
16, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes
identified in paragraphs (c)(1) through (c)(4)
of this AD, certificated in any category;
except airplanes on which Airbus
Modification 35869 has been embodied in
production.
(1) Airbus Model A318–111, –112, –121,
and –122 airplanes.
(2) Airbus Model A319–111, –112, –113,
–114, –115, –131, –132, and –133 airplanes.
(3) Airbus Model A320–211, –212, –214,
–231, –232, and –233 airplanes.
(4) Airbus Model A321–111, –112, –131,
–211, –212, –213, –231, and –232 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 25, Equipment/Furnishings.
(e) Reason
This AD was prompted by a report of
cracks found during maintenance inspections
on certain lugs of the 10VU rack side fittings
in the cockpit. We are issuing this AD to
prevent loss of flight-critical information
displayed to the flightcrew during a critical
phase of flight, such as an approach or
takeoff, which could result in loss of airplane
control at an altitude insufficient for
recovery.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections and Repair
At the later of the times specified in
paragraphs (g)(1) and (g)(2) of this AD: Do a
detailed inspection for cracking of the lugs
on the 10VU rack side fittings in the cockpit,
in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
92–1087, Revision 02, dated November 25,
2014. If any crack is found, before further
flight, repair in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–92–1087, Revision 02,
dated November 25, 2014. Repeat the
inspection thereafter at intervals not to
exceed 20,000 flight cycles or 40,000 flight
hours, whichever occurs first. Repair of the
10VU rack lugs does not terminate the
repetitive inspections required by this
paragraph.
(1) Before the accumulation of 30,000 total
flight cycles or 60,000 total flight hours,
whichever occurs first since the airplane’s
first flight.
(2) Within 24 months after the effective
date of this AD.
(h) Reporting Requirement
Submit a report of any findings (positive
and negative) of any inspection required by
paragraph (g) of this AD to Airbus at the
address specified in paragraph (j)(2) of this
AD, at the applicable time specified in
paragraph (h)(1) or (h)(2) of this AD.
PO 00000
Frm 00010
Fmt 4702
Sfmt 4702
(1) If the inspection was done on or after
the effective date of this AD: Submit the
report within 90 days after the inspection.
(2) If the inspection was done before the
effective date of this AD: Submit the report
within 90 days after the effective date of this
AD.
(i) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
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.
(3) Reporting Requirements: A federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
(4) Required for Compliance (RC): If any
service information contains procedures or
tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
E:\FR\FM\31DEP1.SGM
31DEP1
Federal Register / Vol. 80, No. 251 / Thursday, December 31, 2015 / Proposed Rules
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(j) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) European
Aviation Safety Agency (EASA)
Airworthiness Directive 2015–0170, dated
August 18, 2015, 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–2015–8132.
(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.airwortheas@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
December 18, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–32885 Filed 12–30–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–8133; Directorate
Identifier 2015–NM–101–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
The Boeing Company Model 737–600,
–700, –700C, –800, –900, and –900ER
series airplanes. This proposed AD was
prompted by reports of heavy corrosion
and chrome damage on the forward and
aft trunnion pin assemblies of the right
and left main landing gears (MLGs).
This proposed AD would require
repetitive lubrication of the forward and
aft trunnion pin assemblies of the right
and left MLGs; repetitive inspections of
tkelley on DSK3SPTVN1PROD with PROPOSALS
SUMMARY:
VerDate Sep<11>2014
16:32 Dec 30, 2015
Jkt 238001
these assemblies for corrosion and
chrome damage, and related
investigative and corrective actions if
necessary; and the installation of new or
modified trunnion pin assembly
components, which would terminate the
repetitive lubrication and repetitive
inspections. We are proposing this AD
to detect and correct heavy corrosion
and chrome damage on the forward and
aft trunnion pin assemblies of the right
and left MLGs, which could result in
cracking of these assemblies and
collapse of the MLGs.
DATES: We must receive comments on
this proposed AD by February 16, 2016.
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: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed 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–2015–
8133.
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–
8133; 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 Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
PO 00000
Frm 00011
Fmt 4702
Sfmt 4702
81795
FOR FURTHER INFORMATION CONTACT:
Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA
Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–917–6450; fax:
425–917–6590; email: alan.pohl@
faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2015–8133; Directorate Identifier 2015–
NM–101–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 because of 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
We received reports of heavy
corrosion and chrome damage of the
forward and aft trunnion pin assemblies
of the right and left main MLGs on
Boeing Model 737–600, –700, –700C,
–800, –900, and –900ER series
airplanes. Investigation revealed that the
lubrication between the forward and aft
trunnion pin assemblies and the outer
cylinder assembly bushings and the
lubrication of the aft trunnion bearing
ball was not sufficient to prevent wear
and corrosion. It was also determined
that the clearances between the forward
and aft trunnion pin cross bolt bushings
and the cross bolts could affect the rate
of wear and corrosion of the MLG
trunnion pin assemblies. Corrosion and
chrome damage of the forward and aft
trunnion pin assemblies of the right and
left main MLGs, if not corrected, could
result in cracking of these assemblies
and collapse of the MLGs.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Special
Attention Service Bulletin 737–32–
1448, Revision 1, dated May 29, 2015.
The service information describes
procedures for lubricating the forward
and aft trunnion pin assemblies on the
left and right MLGs, inspecting the
forward and aft trunnion pin assemblies
E:\FR\FM\31DEP1.SGM
31DEP1
]]>Agencies
[Federal Register Volume 80, Number 251 (Thursday, December 31, 2015)]
[Proposed Rules]
[Pages 81792-81795]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-32885]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-8132; Directorate Identifier 2015-NM-127-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 A318, A319, A320, and A321 series airplanes. This
proposed AD was prompted by a report of cracks found during maintenance
inspections on certain lugs of the 10VU rack side fittings in the
cockpit. This proposed AD would require repetitive inspections for
cracking of the lugs on the 10VU rack side fittings, and repair of any
cracking. We are proposing this AD to prevent loss of flight-critical
information displayed to the flightcrew during a critical phase of
flight, such as an approach or takeoff, which could result in loss of
airplane control at an altitude insufficient for recovery.
DATES: We must receive comments on this proposed AD by February 16,
2016.
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-
8132; 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:
[[Page 81793]]
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-2015-8132;
Directorate Identifier 2015-NM-127-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2015-0170, dated August 18, 2015 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A318, A319, A320, and A321 series airplanes. The MCAI states:
During an unscheduled maintenance operation on an A330
aeroplane, the 10VU rack was removed for access and cracks were
discovered on 10VU rack side fittings on lugs 1, 3, and 4. As a
similar design is installed on A320 family aeroplanes, a sampling
review was done to determine the possible fleet impact. The result
showed that several aeroplanes had cracked or broken 10VU rack side
fittings.
This condition, if not detected and corrected, could lead to a
high vibration level on the primary flight- and navigation displays
during critical flight phases (takeoff and landing), possibly
creating reading difficulties for the crew.
Prompted by these findings, Airbus developed mod 35869 to
reinforce the affected rack fitting lugs. For in-service aeroplanes,
Airbus published Service Bulletin (SB) A320-92-1087 to provide
inspection and repair instructions.
For the reasons described above, this [EASA] AD requires
repetitive detailed inspections (DET) of the affected 10VU rack
fitting lugs and, depending on findings, accomplishment of a repair.
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-
8132.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A320-92-1087, Revision 02, dated
November 25, 2014. The service information describes procedures for
repetitive inspections for cracking of the lugs on the 10VU rack side
fittings, and repair of any cracking. 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.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of these
same type designs.
Explanation of ``RC'' Procedures and Tests in Service Information
The FAA worked in conjunction with industry, under the
Airworthiness Directive Implementation Aviation Rulemaking Committee
(ARC), to enhance the AD system. One enhancement was a new process for
annotating which procedures and tests in the service information are
required for compliance with an AD. Differentiating these procedures
and tests from other tasks in the service information is expected to
improve an owner's/operator's understanding of crucial AD requirements
and help provide consistent judgment in AD compliance. The procedures
and tests identified as RC (required for compliance) in any service
information have a direct effect on detecting, preventing, resolving,
or eliminating an identified unsafe condition.
As specified in a Note under the Accomplishment Instructions of the
specified service information, procedures and tests that are identified
as RC in any service information must be done to comply with the
proposed AD. However, procedures and tests that are not identified as
RC are recommended. Those procedures and tests that are not identified
as RC may be deviated from using accepted methods in accordance with
the operator's maintenance or inspection program without obtaining
approval of an alternative method of compliance (AMOC), provided the
procedures and tests identified as RC can be done and the airplane can
be put back in an airworthy condition. Any substitutions or changes to
procedures or tests identified as RC will require approval of an AMOC.
Costs of Compliance
We estimate that this proposed AD affects 959 airplanes of U.S.
registry.
We also estimate that it would take about 2 work-hours per product
to comply with the basic requirements of this proposed AD, and 1 work-
hour per product to report inspection findings. 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 $244,545, or $255 per product.
In addition, we estimate that any necessary repair would take about
84 work-hours, for a cost of $7,140 per product. We have received no
definitive data that would enable us to provide part cost estimates for
the on-condition actions specified in this proposed AD. We have no way
of determining the number of aircraft that might need these actions.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this AD is mandatory. Comments concerning the accuracy of this burden
and suggestions for reducing the burden should be directed to the FAA
at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information
Collection Clearance Officer, AES-200.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more
[[Page 81794]]
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-2015-8132; Directorate Identifier 2015-NM-
127-AD.
(a) Comments Due Date
We must receive comments by February 16, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs
(c)(1) through (c)(4) of this AD, certificated in any category;
except airplanes on which Airbus Modification 35869 has been
embodied in production.
(1) Airbus Model A318-111, -112, -121, and -122 airplanes.
(2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes.
(3) Airbus Model A320-211, -212, -214, -231, -232, and -233
airplanes.
(4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231,
and -232 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 25, Equipment/
Furnishings.
(e) Reason
This AD was prompted by a report of cracks found during
maintenance inspections on certain lugs of the 10VU rack side
fittings in the cockpit. We are issuing this AD to prevent loss of
flight-critical information displayed to the flightcrew during a
critical phase of flight, such as an approach or takeoff, which
could result in loss of airplane control at an altitude insufficient
for recovery.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections and Repair
At the later of the times specified in paragraphs (g)(1) and
(g)(2) of this AD: Do a detailed inspection for cracking of the lugs
on the 10VU rack side fittings in the cockpit, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A320-92-
1087, Revision 02, dated November 25, 2014. If any crack is found,
before further flight, repair in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-92-1087, Revision 02,
dated November 25, 2014. Repeat the inspection thereafter at
intervals not to exceed 20,000 flight cycles or 40,000 flight hours,
whichever occurs first. Repair of the 10VU rack lugs does not
terminate the repetitive inspections required by this paragraph.
(1) Before the accumulation of 30,000 total flight cycles or
60,000 total flight hours, whichever occurs first since the
airplane's first flight.
(2) Within 24 months after the effective date of this AD.
(h) Reporting Requirement
Submit a report of any findings (positive and negative) of any
inspection required by paragraph (g) of this AD to Airbus at the
address specified in paragraph (j)(2) of this AD, at the applicable
time specified in paragraph (h)(1) or (h)(2) of this AD.
(1) If the inspection was done on or after the effective date of
this AD: Submit the report within 90 days after the inspection.
(2) If the inspection was done before the effective date of this
AD: Submit the report within 90 days after the effective date of
this AD.
(i) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local 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.
(3) Reporting Requirements: A federal agency may not conduct or
sponsor, and a person is not required to respond to, nor shall a
person be subject to a penalty for failure to comply with a
collection of information subject to the requirements of the
Paperwork Reduction Act unless that collection of information
displays a current valid OMB Control Number. The OMB Control Number
for this information collection is 2120-0056. Public reporting for
this collection of information is estimated to be approximately 5
minutes per response, including the time for reviewing instructions,
completing and reviewing the collection of information. All
responses to this collection of information are mandatory. Comments
concerning the accuracy of this burden and suggestions for reducing
the burden should be directed to the FAA at: 800 Independence Ave.
SW., Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.
(4) Required for Compliance (RC): If any service information
contains procedures or tests that are identified as RC, those
procedures and tests must be done to comply with this AD; any
procedures or tests that are not identified as RC are recommended.
Those procedures and tests that are not identified
[[Page 81795]]
as RC may be deviated from using accepted methods in accordance with
the operator's maintenance or inspection program without obtaining
approval of an AMOC, provided the procedures and tests identified as
RC can be done and the airplane can be put back in an airworthy
condition. Any substitutions or changes to procedures or tests
identified as RC require approval of an AMOC.
(j) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) European Aviation Safety Agency (EASA) Airworthiness
Directive 2015-0170, dated August 18, 2015, 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-
2015-8132.
(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 December 18, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-32885 Filed 12-30-15; 8:45 am]
BILLING CODE 4910-13-P
