Airworthiness Directives; Airbus Airplanes, 78944-78947 [2016-26813]
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78944
Proposed Rules
Federal Register
Vol. 81, No. 218
Thursday, November 10, 2016
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–0084; Directorate
Identifier 2014–NM–181–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Supplemental notice of
proposed rulemaking (SNPRM);
reopening of comment period.
AGENCY:
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
Examining the AD Docket
We are revising an earlier
proposed airworthiness directive (AD)
for certain Airbus Model A300 B4–2C,
B4–103, and B4–203 airplanes; and
Model A300 B4–600 and A300 B4–600R
series airplanes. This action revises the
NPRM by adding additional inspections
for cracking, and related investigative
and corrective actions if necessary, and
adding airplanes to the applicability.
We are proposing this SNPRM to detect
and correct cracking on the frame (FR)
40 forward fittings, which could result
in reduced structural integrity of the
airplane. Since these actions impose an
additional burden over those proposed
in the NPRM, we are reopening the
comment period to allow the public the
chance to comment on these proposed
changes.
DATES: The comment period for the
NPRM published in the Federal
Register on February 13, 2015 (80 FR
7992) is reopened.
We must receive comments on this
SNPRM by December 27, 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,
SUMMARY:
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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 SNPRM, contact Airbus SAS,
Airworthiness Office—EAW, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You
may view this referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221.
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
0084; 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
(telephone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–2125;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
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
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Airbus Model A300 B4–
2C, B4–103, and B4–203 airplanes; and
Model A300 B4–600 and A300 B4–600R
series airplanes. The NPRM published
in the Federal Register on February 13,
2015 (80 FR 7992) (‘‘the NPRM’’). The
NPRM was prompted by reports
indicating that, on airplanes that
received a certain repair following crack
findings, cracks can re-initiate. The
NPRM proposed to require repetitive
inspections for cracking of the FR 40
forward fittings for airplanes previously
repaired.
Actions Since the NPRM Was Issued
Comments Invited
Since we issued the NPRM, we have
determined that additional inspections
for cracking are necessary and that
additional airplanes are affected by the
identified unsafe condition.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2015–0232R1, dated December
16, 2015 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for certain Airbus
Model A300 series airplanes; and Model
A300 B4–600, B4–600R and F4–600R
series airplanes, and Model A300 C4–
605R Variant F airplanes (collectively
called Model A300–600 series
airplanes). The MCAI states:
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–2015–0084; Directorate Identifier
2014–NM–181–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
Cracks were found on the lower outboard
radius of the centre wing frame 40 forward
fitting on in-service aeroplanes.
This condition, if not detected and
corrected, could lead to reduced structural
integrity of the aeroplane.
To address this unsafe condition, Airbus
issued several inspection Service Bulletins
(SB) and repair instructions. Consequently,
EASA issued AD 2009–0094, which was later
superseded by EASA AD 2011–0163 [which
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Federal Register / Vol. 81, No. 218 / Thursday, November 10, 2016 / Proposed Rules
corresponds to FAA AD 2012–25–06,
Amendment 39–17287 (77 FR 75833,
December 26, 2012) (‘‘AD 2012–25–06’’)] and
[EASA] AD 2014–0199 [which corresponds
to the FAA NPRM], to require repetitive
inspections and corrective actions on the
affected areas.
Since those [EASA] ADs were issued,
additional in-service findings induced Airbus
to do a new fatigue analysis, using a detailed
Finite Element Model study, which resulted
in defining new inspection methods.
Prompted by these results, Airbus issued SB
A300–57–0261, SB A300–57–6117 and SB
A300–57–9034 to introduce these
inspections. These new inspection SBs
supersede and render obsolete inspection SB
A300–53–0268 and SB A300–57–6052 and
the All Operators Transmissions (AOT)
A300–53A0391, AOT A300–57A6111, AOT
A300–53W002–14 and AOT A300–57W003–
14.
For the reasons described above, EASA
issued AD 2015–0232, superseding [Direction
´ ´
Generale de l’Aviation Civile] DGAC France
AD 1998–038–010(B) R1 [which corresponds
to FAA AD 98–25–07, Amendment 39–10933
(63 FR 68167, December 10, 1998) (‘‘AD 98–
25–07’’)] and [DGAC France] AD 2003–
189(B), and EASA AD 2011–0163 and
[EASA] AD 2014–0199, to require the new
inspections of the affected areas within new
thresholds and intervals.
This [EASA] AD is revised to clarify the
compliance time(s), introducing a Note after
paragraph (1), and to alleviate the reporting
requirements of paragraph (3).
Required actions include repetitive
rototest, ultrasonic, high frequency eddy
current, special detailed, and liquid
penetrant inspections, as applicable, of
the center wing FR 40 lower outboard
radius for cracking, and related
investigative and corrective actions if
necessary. Related investigative actions
include rototest, ultrasonic, high
frequency eddy current, and liquid
penetrant inspections following repairs
of cracking.
Corrective actions include oversizing
fastener holes and installing new
fasteners, doing spotfacing, doing crackstop holes, and repairing cracking.
The compliance times vary depending
on airplane configuration. The initial
compliance times range from 3 months
to 56,300 flight cycles or 76,000 flight
hours (whichever occurs first) after
accomplishing certain actions.
Repetitive intervals range from 1,400
flight cycles or 3,000 flight hours
(whichever occurs first) to 37,500 flight
cycles or 50,600 flight hours (whichever
occurs first).
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–
0084.
Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A300–57–6117, dated May 28, 2015;
and Service Bulletin A300–57–0261,
dated June 11, 2015. The service
information describes procedures for
repetitive ultrasonic inspections,
rototest inspections, high frequency
eddy current inspections, special
detailed inspections, and liquid
penetrant inspections, and related
investigative and corrective actions.
These documents are distinct since they
apply to different airplane models. 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.
Comments
We gave the public the opportunity to
participate in developing this proposed
AD. We considered the comment
received.
Request To Suspend Activities on the
NPRM Pending New Service
Information
United Parcel Service (UPS) requested
that we suspend activities on the NPRM
78945
pending the issuance of new service
information. UPS stated that the new
service information will address
airplanes that were not identified in the
NPRM and will include new
inspections.
We acknowledge the commenter’s
request. We have reviewed the new
service information (Airbus Service
Bulletin A300–57–6117, dated May 28,
2015; and Airbus Service Bulletin
A300–57–0261, dated June 11, 2015)
and have revised this SNPRM
accordingly. We have updated
paragraph (c) of this proposed AD to
include all affected airplanes, and we
have revised paragraphs (g) and (h) of
this proposed AD to refer to the new
service information.
FAA’s Determination and Requirements
of This SNPRM
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.
Certain changes described above
expand the scope of the NPRM. As a
result, we have determined that it is
necessary to reopen the comment period
to provide additional opportunity for
the public to comment on this SNPRM.
Costs of Compliance
We estimate that this SNPRM affects
26 airplanes of U.S. registry. We
estimate the following costs to comply
with this SNPRM.
ESTIMATED COSTS
Action
Labor cost
Cost per product
Cost on U.S. operators
Inspection .........
Up to 91 work-hours × $85 per hour = $7,735 per
inspection cycle.
1 work-hour × $85 per hour = $85 ...........................
Up to $7,735 per inspection cycle
Up to $201,110 per inspection
cycle.
$2,210
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
Reporting ..........
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
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$85 ................................................
OMB control number. The control
number for the collection of information
required by this proposed AD is 2120–
0056. The paperwork cost associated
with this proposed AD has been
detailed in the Costs of Compliance
section of this document and includes
time for reviewing instructions, as well
as completing and reviewing the
collection of information. Therefore, all
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reporting associated with this proposed
AD is mandatory. Comments concerning
the accuracy of this burden and
suggestions for reducing the burden
should be directed to the FAA at 800
Independence Ave. SW., Washington,
DC 20591, ATTN: Information
Collection Clearance Officer, AES–200.
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Federal Register / Vol. 81, No. 218 / Thursday, November 10, 2016 / Proposed Rules
Authority for This Rulemaking
§ 39.13
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
■
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
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[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
Airbus: Docket No. FAA–2015–0084;
Directorate Identifier 2014–NM–181–AD.
(a) Comments Due Date
We must receive comments by December
27, 2016.
(b) Affected ADs
This AD affects AD 98–25–07, Amendment
39–10933 (63 FR 68167, December 10, 1998)
(‘‘AD 98–25–07’’); and AD 2012–25–06,
Amendment 39–17287 (77 FR 75833,
December 26, 2012) (‘‘AD 2012–25–06’’).
(c) Applicability
This AD applies to the Airbus airplanes,
certificated in any category, identified in
paragraphs (c)(1) through (c)(5) of this AD,
except airplanes on which Airbus
Modification 10221 has been embodied in
production.
(1) Model A300 B2–1A, B2–1C, B2K–3C,
B2–203, B4–2C, B4–103, and B4–203
airplanes.
(2) Model A300 B4–601, B4–603, B4–620,
and B4–622 airplanes.
(3) Model A300 B4–605R and B4–622R
airplanes.
(4) Model A300 F4–605R and F4–622R
airplanes.
(5) Model A300 C4–605R Variant F
airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Reason
This AD was prompted by reports of cracks
on the lower outboard radius of the center
wing frame (FR) 40 forward fitting. We are
issuing this AD to detect and correct cracking
on the FR 40 forward fittings, which could
result in reduced structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections
Except as provided by paragraph (i)(1) of
this AD, at the applicable times specified in
paragraph E.(2), ‘‘Compliance,’’ of Airbus
Service Bulletin A300–57–0261, dated June
11, 2015; or Airbus Service Bulletin A300–
57–6117, dated May 28, 2015; accomplish
rototest, ultrasonic, high frequency eddy
current, special detailed, and liquid
penetrant inspections, as applicable, of the
center wing FR 40 lower outboard radius for
cracking, and do all applicable related
investigative actions, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–0261, dated June
11, 2015; or Airbus Service Bulletin A300–
57–6117, dated May 28, 2015; as applicable.
Do all applicable related investigative actions
before further flight. Repeat the inspections
thereafter at the applicable times specified in
paragraph E.(2), ‘‘Compliance,’’ of Airbus
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Service Bulletin A300–57–0261, dated June
11, 2015; or Airbus Service Bulletin A300–
57–6117, dated May 28, 2015.
(h) Corrective Actions
If, during any inspection required by
paragraph (g) of this AD, any crack is found,
before next flight, accomplish the applicable
corrective actions, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–57–0261, dated June
11, 2015; or Airbus Service Bulletin A300–
57–6117, dated May 28, 2015; as applicable;
except as required by paragraph (i)(2) of this
AD.
(i) Service Information Exception
(1) Where the service information specified
in paragraph (g) of this AD specifies a
compliance time ‘‘from this service bulletin
issuance date,’’ this AD requires compliance
within the specified compliance time after
the effective date of this AD.
(2) Where the service information specified
in paragraph (h) of this AD specifies to
contact Airbus for certain conditions, before
further flight, repair using a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or the European Aviation
Safety Agency (EASA); or Airbus’ EASA
Design Organization Approval (DOA).
(j) No Terminating Action for This AD
Accomplishing a corrective action required
by paragraph (h) of this AD, or accomplishing
a preventative action specified in Airbus
Service Bulletin A300–57–0260 or A300–57–
6116, as applicable, does not terminate the
repetitive inspections required by paragraph
(g) of this AD.
(k) Terminating Action for Certain
Requirements of Other ADs
(1) Accomplishing the actions required by
paragraph (g) of this AD terminates the
actions required by paragraphs (a) and (b) of
AD 98–25–07.
(2) Accomplishing the actions required by
paragraph (g) of this AD terminates the
actions required by paragraphs (i) and (j) of
AD 2012–25–06.
(l) Reporting Requirements
Within 60 days after any inspection
required by paragraph (g) of this AD, or
within 60 days after the effective date of this
AD, whichever occurs later, report any
findings, positive or negative, to Airbus
Service Bulletin Reporting Online
Application on Airbus World (https://
w3.airbus.com/).
(m) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
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Federal Register / Vol. 81, No. 218 / Thursday, November 10, 2016 / Proposed Rules
Dan Rodina, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–2125; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the EASA; or Airbus’s EASA DOA. If
approved by the DOA, the approval must
include the DOA-authorized signature.
(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.
asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
(n) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2015–0232R1, dated
December 16, 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–2015–0084.
(2) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; Internet https://www.airbus.com.
You may view this service information at the
FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on October
31, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–26813 Filed 11–9–16; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9382; Directorate
Identifier 2016–CE–032–AD]
RIN 2120–AA64
Airworthiness Directives; Alexander
Schleicher GmbH & Co. Gliders
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for
Alexander Schleicher GmbH & Co.
Model ASK 21 gliders. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as cable slack in gliders
equipped with a rudder hand control
system leading to a short-term blockage
of the rudder control system and
reduced control. We are issuing this
proposed AD to correct the unsafe
condition on these products.
DATES: We must receive comments on
this proposed AD by December 27,
2016.
SUMMARY:
You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this proposed AD, contact Alexander
Schleicher GmbH & Co.,
Segelflugzeugbau, Germany, Alexander
Schleicher Str. 1, D–36163
Poppenhausen (Wasserkuppe),
telephone: +49 6658 89–0; fax: +49 6658
89–40; email: info@alexanderschleicher.de; Internet: https://
www.alexander-schleicher.de/en/
flugzeuge/ask-21/. You may review this
referenced service information at the
ADDRESSES:
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78947
FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106.
For information on the availability of
this material at the FAA, call (816) 329–
4148.
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–2016–
9382; 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
(telephone (800) 647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Jim
Rutherford, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4165; fax: (816)
329–4090; email: jim.rutherford@
faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2016–9382; Directorate Identifier
2016–CE–032–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://
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
Community, has issued EASA AD No.:
2016–0192, dated September 28, 2016
(referred to after this as ‘‘the MCAI’’), to
correct an unsafe condition for the
specified products. The MCAI states:
A temporary rudder control blockage was
reported, involving an ASK 21 sailplane
equipped with a rudder hand control system.
E:\FR\FM\10NOP1.SGM
10NOP1
]]>Agencies
[Federal Register Volume 81, Number 218 (Thursday, November 10, 2016)]
[Proposed Rules]
[Pages 78944-78947]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-26813]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 81, No. 218 / Thursday, November 10, 2016 /
Proposed Rules
[[Page 78944]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-0084; Directorate Identifier 2014-NM-181-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Supplemental notice of proposed rulemaking (SNPRM); reopening
of comment period.
-----------------------------------------------------------------------
SUMMARY: We are revising an earlier proposed airworthiness directive
(AD) for certain Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes;
and Model A300 B4-600 and A300 B4-600R series airplanes. This action
revises the NPRM by adding additional inspections for cracking, and
related investigative and corrective actions if necessary, and adding
airplanes to the applicability. We are proposing this SNPRM to detect
and correct cracking on the frame (FR) 40 forward fittings, which could
result in reduced structural integrity of the airplane. Since these
actions impose an additional burden over those proposed in the NPRM, we
are reopening the comment period to allow the public the chance to
comment on these proposed changes.
DATES: The comment period for the NPRM published in the Federal
Register on February 13, 2015 (80 FR 7992) is reopened.
We must receive comments on this SNPRM by December 27, 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 SNPRM, contact Airbus
SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44
51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may view this referenced service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA, call
425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0084; 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 (telephone: 800-647-5527) is in the ADDRESSES section. Comments
will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-0084;
Directorate Identifier 2014-NM-181-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
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to certain Airbus Model A300
B4-2C, B4-103, and B4-203 airplanes; and Model A300 B4-600 and A300 B4-
600R series airplanes. The NPRM published in the Federal Register on
February 13, 2015 (80 FR 7992) (``the NPRM''). The NPRM was prompted by
reports indicating that, on airplanes that received a certain repair
following crack findings, cracks can re-initiate. The NPRM proposed to
require repetitive inspections for cracking of the FR 40 forward
fittings for airplanes previously repaired.
Actions Since the NPRM Was Issued
Since we issued the NPRM, we have determined that additional
inspections for cracking are necessary and that additional airplanes
are affected by the identified unsafe condition.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2015-0232R1, dated December 16, 2015 (referred
to after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for certain Airbus Model
A300 series airplanes; and Model A300 B4-600, B4-600R and F4-600R
series airplanes, and Model A300 C4-605R Variant F airplanes
(collectively called Model A300-600 series airplanes). The MCAI states:
Cracks were found on the lower outboard radius of the centre
wing frame 40 forward fitting on in-service aeroplanes.
This condition, if not detected and corrected, could lead to
reduced structural integrity of the aeroplane.
To address this unsafe condition, Airbus issued several
inspection Service Bulletins (SB) and repair instructions.
Consequently, EASA issued AD 2009-0094, which was later superseded
by EASA AD 2011-0163 [which
[[Page 78945]]
corresponds to FAA AD 2012-25-06, Amendment 39-17287 (77 FR 75833,
December 26, 2012) (``AD 2012-25-06'')] and [EASA] AD 2014-0199
[which corresponds to the FAA NPRM], to require repetitive
inspections and corrective actions on the affected areas.
Since those [EASA] ADs were issued, additional in-service
findings induced Airbus to do a new fatigue analysis, using a
detailed Finite Element Model study, which resulted in defining new
inspection methods. Prompted by these results, Airbus issued SB
A300-57-0261, SB A300-57-6117 and SB A300-57-9034 to introduce these
inspections. These new inspection SBs supersede and render obsolete
inspection SB A300-53-0268 and SB A300-57-6052 and the All Operators
Transmissions (AOT) A300-53A0391, AOT A300-57A6111, AOT A300-53W002-
14 and AOT A300-57W003-14.
For the reasons described above, EASA issued AD 2015-0232,
superseding [Direction G[eacute]n[eacute]rale de l'Aviation Civile]
DGAC France AD 1998-038-010(B) R1 [which corresponds to FAA AD 98-
25-07, Amendment 39-10933 (63 FR 68167, December 10, 1998) (``AD 98-
25-07'')] and [DGAC France] AD 2003-189(B), and EASA AD 2011-0163
and [EASA] AD 2014-0199, to require the new inspections of the
affected areas within new thresholds and intervals.
This [EASA] AD is revised to clarify the compliance time(s),
introducing a Note after paragraph (1), and to alleviate the
reporting requirements of paragraph (3).
Required actions include repetitive rototest, ultrasonic, high
frequency eddy current, special detailed, and liquid penetrant
inspections, as applicable, of the center wing FR 40 lower outboard
radius for cracking, and related investigative and corrective actions
if necessary. Related investigative actions include rototest,
ultrasonic, high frequency eddy current, and liquid penetrant
inspections following repairs of cracking.
Corrective actions include oversizing fastener holes and installing
new fasteners, doing spotfacing, doing crack-stop holes, and repairing
cracking.
The compliance times vary depending on airplane configuration. The
initial compliance times range from 3 months to 56,300 flight cycles or
76,000 flight hours (whichever occurs first) after accomplishing
certain actions. Repetitive intervals range from 1,400 flight cycles or
3,000 flight hours (whichever occurs first) to 37,500 flight cycles or
50,600 flight hours (whichever occurs first).
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-
0084.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A300-57-6117, dated May 28,
2015; and Service Bulletin A300-57-0261, dated June 11, 2015. The
service information describes procedures for repetitive ultrasonic
inspections, rototest inspections, high frequency eddy current
inspections, special detailed inspections, and liquid penetrant
inspections, and related investigative and corrective actions. These
documents are distinct since they apply to different airplane models.
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.
Comments
We gave the public the opportunity to participate in developing
this proposed AD. We considered the comment received.
Request To Suspend Activities on the NPRM Pending New Service
Information
United Parcel Service (UPS) requested that we suspend activities on
the NPRM pending the issuance of new service information. UPS stated
that the new service information will address airplanes that were not
identified in the NPRM and will include new inspections.
We acknowledge the commenter's request. We have reviewed the new
service information (Airbus Service Bulletin A300-57-6117, dated May
28, 2015; and Airbus Service Bulletin A300-57-0261, dated June 11,
2015) and have revised this SNPRM accordingly. We have updated
paragraph (c) of this proposed AD to include all affected airplanes,
and we have revised paragraphs (g) and (h) of this proposed AD to refer
to the new service information.
FAA's Determination and Requirements of This SNPRM
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.
Certain changes described above expand the scope of the NPRM. As a
result, we have determined that it is necessary to reopen the comment
period to provide additional opportunity for the public to comment on
this SNPRM.
Costs of Compliance
We estimate that this SNPRM affects 26 airplanes of U.S. registry.
We estimate the following costs to comply with this SNPRM.
Estimated Costs
------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost product operators
------------------------------------------------------------------------
Inspection........... Up to 91 work- Up to $7,735 Up to $201,110
hours x $85 per inspection per inspection
per hour = cycle. cycle.
$7,735 per
inspection
cycle.
Reporting............ 1 work-hour x $85............ $2,210
$85 per hour =
$85.
------------------------------------------------------------------------
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this proposed AD
is 2120-0056. The paperwork cost associated with this proposed AD has
been detailed in the Costs of Compliance section of this document and
includes time for reviewing instructions, as well as completing and
reviewing the collection of information. Therefore, all reporting
associated with this proposed AD is mandatory. Comments concerning the
accuracy of this burden and suggestions for reducing the burden should
be directed to the FAA at 800 Independence Ave. SW., Washington, DC
20591, ATTN: Information Collection Clearance Officer, AES-200.
[[Page 78946]]
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
Airbus: Docket No. FAA-2015-0084; Directorate Identifier 2014-NM-
181-AD.
(a) Comments Due Date
We must receive comments by December 27, 2016.
(b) Affected ADs
This AD affects AD 98-25-07, Amendment 39-10933 (63 FR 68167,
December 10, 1998) (``AD 98-25-07''); and AD 2012-25-06, Amendment
39-17287 (77 FR 75833, December 26, 2012) (``AD 2012-25-06'').
(c) Applicability
This AD applies to the Airbus airplanes, certificated in any
category, identified in paragraphs (c)(1) through (c)(5) of this AD,
except airplanes on which Airbus Modification 10221 has been
embodied in production.
(1) Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and
B4-203 airplanes.
(2) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
(3) Model A300 B4-605R and B4-622R airplanes.
(4) Model A300 F4-605R and F4-622R airplanes.
(5) Model A300 C4-605R Variant F airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by reports of cracks on the lower outboard
radius of the center wing frame (FR) 40 forward fitting. We are
issuing this AD to detect and correct cracking on the FR 40 forward
fittings, which could result in reduced structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections
Except as provided by paragraph (i)(1) of this AD, at the
applicable times specified in paragraph E.(2), ``Compliance,'' of
Airbus Service Bulletin A300-57-0261, dated June 11, 2015; or Airbus
Service Bulletin A300-57-6117, dated May 28, 2015; accomplish
rototest, ultrasonic, high frequency eddy current, special detailed,
and liquid penetrant inspections, as applicable, of the center wing
FR 40 lower outboard radius for cracking, and do all applicable
related investigative actions, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-57-0261, dated June 11,
2015; or Airbus Service Bulletin A300-57-6117, dated May 28, 2015;
as applicable. Do all applicable related investigative actions
before further flight. Repeat the inspections thereafter at the
applicable times specified in paragraph E.(2), ``Compliance,'' of
Airbus Service Bulletin A300-57-0261, dated June 11, 2015; or Airbus
Service Bulletin A300-57-6117, dated May 28, 2015.
(h) Corrective Actions
If, during any inspection required by paragraph (g) of this AD,
any crack is found, before next flight, accomplish the applicable
corrective actions, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-57-0261, dated June 11,
2015; or Airbus Service Bulletin A300-57-6117, dated May 28, 2015;
as applicable; except as required by paragraph (i)(2) of this AD.
(i) Service Information Exception
(1) Where the service information specified in paragraph (g) of
this AD specifies a compliance time ``from this service bulletin
issuance date,'' this AD requires compliance within the specified
compliance time after the effective date of this AD.
(2) Where the service information specified in paragraph (h) of
this AD specifies to contact Airbus for certain conditions, before
further flight, repair using a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or the European Aviation Safety Agency (EASA); or Airbus' EASA
Design Organization Approval (DOA).
(j) No Terminating Action for This AD
Accomplishing a corrective action required by paragraph (h) of
this AD, or accomplishing a preventative action specified in Airbus
Service Bulletin A300-57-0260 or A300-57-6116, as applicable, does
not terminate the repetitive inspections required by paragraph (g)
of this AD.
(k) Terminating Action for Certain Requirements of Other ADs
(1) Accomplishing the actions required by paragraph (g) of this
AD terminates the actions required by paragraphs (a) and (b) of AD
98-25-07.
(2) Accomplishing the actions required by paragraph (g) of this
AD terminates the actions required by paragraphs (i) and (j) of AD
2012-25-06.
(l) Reporting Requirements
Within 60 days after any inspection required by paragraph (g) of
this AD, or within 60 days after the effective date of this AD,
whichever occurs later, report any findings, positive or negative,
to Airbus Service Bulletin Reporting Online Application on Airbus
World (https://w3.airbus.com/).
(m) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN:
[[Page 78947]]
Dan Rodina, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. Information
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA;
or Airbus's EASA DOA. If approved by the DOA, the approval must
include the DOA-authorized signature.
(3) Reporting Requirements: A federal agency may not conduct or
sponsor, and a person is not required to respond to, nor shall a
person be subject to a penalty for failure to comply with a
collection of information subject to the requirements of the
Paperwork Reduction Act unless that collection of information
displays a current valid OMB Control Number. The OMB Control Number
for this information collection is 2120-0056. Public reporting for
this collection of information is estimated to be approximately 5
minutes per response, including the time for reviewing instructions,
completing and reviewing the collection of information. All
responses to this collection of information are mandatory. Comments
concerning the accuracy of this burden and suggestions for reducing
the burden should be directed to the FAA at: 800 Independence Ave.
SW., Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.
(n) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2015-0232R1, dated December 16,
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-2015-0084.
(2) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You may view this service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on October 31, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-26813 Filed 11-9-16; 8:45 am]
BILLING CODE 4910-13-P
