Airworthiness Directives; Airbus Airplanes, 12314-12318 [2017-03953]
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are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
357/197, 358/198, 361/201, 362/202, 363/
203, 364/204, and 368/206; that are
(2) certificated in any category.
(d) Subject
Air Transport Association of America
(ATA) Code 73: Engine Fuel & Control.
(e) Reason
This AD was prompted by 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 failure of
the connecting rod bearing resulting from too
much load on the rod bearings from the
engine control unit. We are issuing this
proposed AD to prevent such failure that
could lead to an uncommanded in-flight
engine shut-down, which could result in
damage to the glider.
(f) Actions and Compliance
Unless already done, do the following
actions in paragraphs (f)(1) and (2) of this
AD:
(1) Within the next 60 days after the
effective date of this AD, modify the engine
by installing a software update for the engine
control unit (ECU) following the actions in
Solo Kleinmotoren GmbH Technische
Mitteilung (English translation: Service
Bulletin), Nr. 4600–6, Ausgabe 1 (English
translation: Issue 1), dated November 16,
2016.
(2) After the modification of an engine as
required by paragraph (f)(1) of this AD, do
not install a replacement ECU on that engine
and do not upload any software update to the
ECU of that engine unless the ECU software
version is as specified in Solo Kleinmotoren
GmbH Technische Mitteilung (English
translation: Service Bulletin), Nr. 4600–6,
Ausgabe 1 (English translation: Issue 1),
dated November 16, 2016.
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Note 1 to paragraph (f)(1) and (2) of this AD:
This service information contains German
to English translation. The EASA used the
English translation in referencing the
document. For enforceability purposes, we
will refer to the Solo Kleinmotoren service
information as it appears on the document.
(g) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Jim Rutherford, Aerospace Engineer,
901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329–4165; fax: (816)
329–4090; email: jim.rutherford@faa.gov.
Before using any approved AMOC on any
airplane to which the AMOC applies, notify
your appropriate principal inspector (PI) in
the FAA Flight Standards District Office
(FSDO), or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
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(h) Related Information
Refer to MCAI European Aviation Safety
Agency (EASA) AD No.: 2016–0254, dated
December 15, 2016, correction dated January
4, 2017, for related information. You may
examine the MCAI on the Internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2017–0158. For
service information related to this AD,
contact Solo Kleinmotoren GmbH, Postfach
600152, 71050 Sindelfingen, Germany;
telephone: +49 703 1301–0; fax: +49 703
1301–136; email: aircraft@solo-germany.com;
Internet: https://aircraft.solo-online.com. You
may review this referenced service
information at the 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.
Issued in Kansas City, Missouri, on
February 17, 2017.
Pat Mullen,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2017–03967 Filed 3–1–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9055; Directorate
Identifier 2016–NM–071–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:
We are revising an earlier
proposal for certain Airbus Model A300
B4–600R series airplanes, Model A300
C4–605R Variant F airplanes, and Model
A300 F4–600R series airplanes. This
action revises the notice of proposed
rulemaking (NPRM) by extending the
area to be inspected for cracking. This
SNPRM also proposes to require an
additional inspection for previously
inspected airplanes. We are proposing
this airworthiness directive (AD) to
address the unsafe condition on these
products. 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.
SUMMARY:
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The comment period for the
NPRM published in the Federal
Register on September 8, 2016 (81 FR
62026), is reopened.
We must receive comments on this
SNPRM by April 17, 2017.
DATES:
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.
ADDRESSES:
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–
9055; 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.
Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–2125;
fax 425–227–1149.
FOR FURTHER INFORMATION CONTACT:
SUPPLEMENTARY INFORMATION:
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Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2016–9055; Directorate Identifier
2016–NM–071–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.
pmangrum on DSK3GDR082PROD with PROPOSALS
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–
600R series airplanes, Model A300 C4–
605R Variant F airplanes, and Model
A300 F4–600R series airplanes. The
NPRM published in the Federal
Register on September 8, 2016 (81 FR
62026). The NPRM was prompted by the
results of a full stress analysis of the
lower area of frame (FR) 40 that revealed
a crack could occur in the forward
fitting lower radius of FR 40 after a
certain number of flight cycles. The
NPRM proposed to require an
inspection of the lower area of the FR
40 radius for cracking, and corrective
action if necessary.
Actions Since the NPRM Was Issued
Since we issued the NPRM, we have
determined that the area to be inspected
for cracking in the lower area of the FR
40 radius should be extended. We have
also determined that an additional
inspection is necessary for airplanes
previously inspected. In addition, the
European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, issued EASA AD 2016–0179,
dated September 12, 2016 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), which supersedes EASA AD
2016–0085, dated April 28, 2016. EASA
AD 2016–0085 was the MCAI referred to
in the NPRM.
The MCAI was issued to correct an
unsafe condition for certain Airbus
Model A300 B4–600R series airplanes,
Model A300 C4–605R Variant F
airplanes, and Model A300 F4–600R
series airplanes. The MCAI states:
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13:51 Mar 01, 2017
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Following a full stress analysis of the
Frame (FR) 40 lower area, supported by a
Finite Element Model (FEM), of the post-mod
10221 configuration, it was demonstrated
that, for the FR40 forward fitting lower
radius, a crack could occur after a certain
amount of flight cycles (FC).
This condition, if not detected and
corrected, could reduce the structural
integrity of the fuselage.
To address this potential unsafe condition,
Airbus established that crack detection could
be achieved through a special detailed
inspection (SDI) using a high frequency eddy
current (HFEC) method, and issued Alert
Operators Transmission (AOT) A57W009–16
to provide those inspection instructions.
Consequently, EASA issued AD 2016–0085
to require a one-time SDI of the FR40 lower
area and, depending on findings,
accomplishment of applicable corrective
action(s).
Since that [EASA] AD was issued, further
cracks were detected, originating from the
fastener hole, and, based on these findings,
it was determined that inspection area must
be enlarged, and Airbus AOT A57W009–16
Revision (Rev.) 01 was issued accordingly.
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2016–0085, which is superseded, extends
the area of inspection, and requires an
additional inspection for aeroplanes
previously inspected.
The one-time SDI for high cycle aeroplanes
is intended to mitigate the highest risks
within the fleet. Airbus is currently
developing instructions for repetitive
inspections that are likely to be the subject
of further [EASA] AD action.
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–2016–
9055.
Related Service Information Under 1
CFR Part 51
Airbus has issued Alert Operators
Transmission (AOT) A57W009–16, Rev
01, including Appendices 1 and 2, dated
July 13, 2016 (‘‘AOT A57W009–16, Rev
01’’). The service information describes
procedures for inspecting the forward
fitting lower radius of FR 40 for
cracking, and corrective action. 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 comments
received.
Support for the NPRM
One commenter, Joseph Luna,
supported the intent of the NPRM.
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Request To Refer to Revised MCAI and
Service Information
Airbus requested that the NPRM be
revised to specify new MCAI and
revised service information. Airbus
noted that, after the NPRM was
published, the service information and
the MCAI referred to in the NPRM were
revised. Airbus explained that Airbus
AOT A57W009–16, Rev 00, dated
February 25, 2016 (‘‘AOT A57W009–16,
Rev 00’’), was revised to extend the area
of inspection, and AOT A57W009–16,
Rev 01, was published to include that
information. Airbus also pointed out
that, after the NPRM was published,
EASA superseded EASA AD 2016–0085,
dated April 28, 2016, and issued EASA
AD 2016–0179, dated September 12,
2016, which extends the area of
inspection and requires an additional
action for airplanes previously
inspected.
We agree with the commenter’s
request. We have revised this proposed
AD to refer to AOT A57W009–16, Rev
01, as the appropriate source of service
information for completing the
proposed actions. We have also
included a one-time additional
inspection for airplanes on which the
proposed inspection in paragraph (g) of
this proposed AD was accomplished
using the procedures in AOT
A57W009–16, Rev 00. In addition, we
added credit for the proposed
inspection specified in paragraph (g) of
this proposed AD, if that action was
done before the effective date of the AD
using the procedures in AOT
A57W009–16, Rev 00, provided the
proposed inspection specified in
paragraph (h) of this proposed AD is
accomplished. In addition, we revised
the preamble and paragraph (m)(1) of
this proposed AD to refer to the current
EASA AD: AD 2016–0179, dated
September 12, 2016.
Request To Delay Issuance of Final
Rule
United Parcel Service (UPS) requested
that we delay issuance of the final rule
until Airbus issues an inspection service
bulletin that will specify the same
actions described in AOT A57W009–16,
Rev 00, and might include repetitive
inspections that are not in AOT
A57W009–16, Rev 00. UPS stated that
Airbus has committed to issue the
inspection service bulletin within the
4th quarter of 2016, and the service
bulletin will supersede AOT A57W009–
16, Rev 00. UPS suggested that, to
reduce the issuance of subsequent
alternative method of compliance
(AMOC) requests and additional
proposed rules, the final rule should be
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delayed until the Airbus inspection
service bulletin is released. UPS noted
that the areas to be inspected are
currently included in another Airbus
service bulletin and other regulations,
based on an airplane’s modification
status. UPS stated that its fleet of
airplanes affected by the NPRM is below
the initial threshold, so there would not
be an impact to the safety of its current
fleet. UPS anticipated that the first
inspection for its affected airplanes
would not take place until 2025.
We do not agree with the commenter’s
request to delay issuance of a final rule
until the Airbus inspection service
bulletin is issued. As previously
mentioned, after the issuance of the
NPRM, Airbus revised AOT A57W009–
16, Rev 00, to include an extended area
of inspection, and we have revised this
proposed AD to refer to the revised AOT
(AOT A57W009–16, Rev 01). AOT
A57W009–16, Rev 01, contains all of the
necessary information to address the
identified unsafe condition. When
repetitive inspections are developed and
related service information is available
we will consider if additional
rulemaking is necessary to mandate
those actions.
In addition, although UPS may have
time before the airplanes in its fleet are
required to be inspected, other operators
might have airplanes that have
accumulated total flight cycles that are
close to the threshold for the proposed
initial inspection.
Request To Specify Actions Required
for Compliance (‘‘RC’’)
UPS requested that paragraph (g) of
the proposed AD (in the NPRM) be
revised to specify that the required
actions are to be accomplished in
accordance with ‘‘paragraph 4.2.2’’ of
AOT A57W009–16, Rev 00, instead of
‘‘the procedures’’ in AOT A57W009–16,
Rev 00. UPS stated that, as written,
paragraph (g) of the proposed AD would
require operators to accomplish all of
the actions in AOT A57W009–16, Rev
00, but it is specifically the actions in
paragraph 4.2.2 of AOT A57W009–16,
Rev 00, that address the unsafe
condition. UPS noted that Airbus
Service Bulletin A300–57–6115
specifies the identical location, access,
and inspection procedures as AOT
A57W009–16, Rev 00, but that service
bulletin identifies which actions are
‘‘Required for Compliance’’ (‘‘RC’’). To
be in compliance with an AD, operators
must accomplish all of the actions
identified as ‘‘RC’’ in the service
information that is required by an AD.
The actions that are not identified as
‘‘RC’’ in the required service
information are classified as
recommended for compliance.
We agree with the commenter’s
request and have revised paragraphs (g)
and (h) of this proposed AD to refer to
the actions in paragraph 4.2.2 of the
Airbus AOT, which are the actions
required for compliance. As previously
mentioned, we have revised this
SNPRM to refer to AOT A57W009–16,
Rev 01, which was issued after the
NPRM was published. We note that this
AOT does not include standard ‘‘RC’’
language.
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 the same
type design.
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 proposed AD
affects 94 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
Inspection ................................
Report .....................................
3 work-hours × $85 per hour = $255 .....................................
1 work-hour × $85 per hour = $85 .........................................
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this proposed AD.
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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 AD has been detailed in the
Costs of Compliance section of this
document and includes time for
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13:51 Mar 01, 2017
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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
detail the scope of the Agency’s
authority.
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Cost per
product
Parts cost
Sfmt 4702
$0
0
$255
85
Cost on U.S.
operators
$23,970
7,990
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
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substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Airbus: Docket No. FAA–2016–9055;
Directorate Identifier 2016–NM–071–AD.
(a) Comments Due Date
We must receive comments by April 17,
2017.
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(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus airplanes,
certificated in any category, identified in
paragraphs (c)(1), (c)(2), and (c)(3) of this AD,
on which Airbus Modification 10221 was
embodied in production.
(1) Airbus Model A300 B4–605R and B4–
622R airplanes.
(2) Airbus Model A300 C4–605R Variant F
airplanes.
(3) Airbus Model A300 F4–605R and F4–
622R airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
(e) Reason
This AD was prompted by the detection of
cracking that originated from the fastener
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holes in the forward fitting lower radius of
frame (FR) 40. We are issuing this AD to
detect and correct cracking in the forward
fitting lower radius of FR 40. Such cracking
could reduce the structural integrity of the
fuselage.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Inspection
At the later of the compliance times
specified in paragraphs (g)(1) and (g)(2) of
this AD, do a high frequency eddy current
(HFEC) inspection of the lower area of the FR
40 radius for cracking, in accordance with
paragraph 4.2.2 in Airbus Alert Operators
Transmission (AOT) A57W009–16, Rev 01,
including Appendices 1 and 2, dated July 13,
2016.
(1) Prior to exceeding 19,000 total flight
cycles or 41,000 total flight hours since the
airplane’s first flight, whichever occurs first.
(2) Within 300 flight cycles or 630 flight
hours after the effective date of this AD,
whichever occurs first.
(h) Additional Inspection for Previously
Inspected Airplanes
For airplanes on which the HFEC
inspection required by paragraph (g) of this
AD was accomplished before the effective
date of this AD using the procedures in
Airbus AOT A57W009–16, Rev 00, including
Appendices 1 and 2, dated February 25,
2016: Within 300 flight cycles or 630 flight
hours after the effective date of this AD,
whichever occurs first, do a one-time
additional HFEC inspection of the lower area
of the FR 40 radius for cracking, in
accordance with paragraph 4.2.2 in Airbus
AOT A57W009–16, Rev 01, including
Appendices 1 and 2, dated July 13, 2016.
(i) Corrective Action
If any crack is found during the inspection
required by paragraph (g) or (h) of this AD:
Before further flight, do the applicable
corrective actions in accordance with the
procedures in Airbus AOT A57W009–16, Rev
01, including Appendices 1 and 2, dated July
13, 2016. Where AOT A57W009–16, Rev 01,
including Appendices 1 and 2, dated July 13,
2016, specifies to contact Airbus for
appropriate action, accomplish the corrective
actions in accordance with the procedures
specified in paragraph (l)(2) of this AD.
(j) Reporting Requirement
Submit a report of all findings (both
positive and negative) from the inspection
required by paragraph (g) of this AD to
Airbus Customer Services through
TechRequest on Airbus World (https://
w3.airbus.com/) by selecting Engineering
Domain and ATA 57–10.
(1) For airplanes on which the inspection
specified in paragraph (g) of this AD is
accomplished on or after the effective date of
this AD: Submit the report within 30 days
after performing the inspection.
(2) For airplanes on which the inspection
specified in paragraph (g) of this AD is
accomplished before the effective date of this
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AD: Submit the report within 30 days after
the effective date of this AD.
(k) Credit for Previous Actions
This paragraph provides credit for the
action required by paragraph (g) of this AD,
if that action was done before the effective
date of this AD using Airbus AOT A57W009–
16, Rev 00, including Appendices 1 and 2,
dated February 25, 2016, provided the
inspection required by paragraph (h) of this
AD is accomplished.
(l) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
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 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.
(m) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
E:\FR\FM\02MRP1.SGM
02MRP1
12318
Federal Register / Vol. 82, No. 40 / Thursday, March 2, 2017 / Proposed Rules
Airworthiness Directive 2016–0179, dated
September 12, 2016, 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–2016–9055.
(2) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; Internet https://www.airbus.com.
You may view this service information at the
FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on February
16, 2017.
Thomas Groves,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–03953 Filed 3–1–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF LABOR
Occupational Safety and Health
Administration
29 CFR Parts 1910, 1915, and 1926
[Docket No. OSHA–H005C–2006–0870]
RIN 1218–AB76
Occupational Exposure to Beryllium:
Proposed Delay of Effective Date
Occupational Safety and Health
Administration, Department of Labor.
ACTION: Proposed delay of effective date.
AGENCY:
In accordance with the
Presidential directive as expressed in
the memorandum of January 20, 2017,
from the Assistant to the President and
Chief of Staff, entitled ‘‘Regulatory
Freeze Pending Review,’’ this action
proposes, following a brief 10-day
comment period, to further temporarily
delay until May 20, 2017 the effective
date of the rule entitled Occupational
Exposure to Beryllium, published in the
Federal Register on January 9, 2017 (82
FR 2470). The current effective date is
March 21, 2017. This additional delay
will allow OSHA officials the
opportunity for further review and
consideration of the new regulations.
DATES: Written comments must be
submitted (postmarked, sent, or
received) by March 13, 2017.
ADDRESSES: Written comments. You may
submit comments, identified by Docket
No. OSHA–H005C–2006–0870, by any
of the following methods:
Electronically: You may submit
comments and attachments
pmangrum on DSK3GDR082PROD with PROPOSALS
SUMMARY:
VerDate Sep<11>2014
13:51 Mar 01, 2017
Jkt 241001
electronically at https://
www.regulations.gov, which is the
Federal e-Rulemaking Portal. Follow the
instructions on-line for making
electronic submissions. When
uploading multiple attachments into
Regulations.gov, please number all of
your attachments because
www.Regulations.gov will not
automatically number the attachments.
This will be very useful in identifying
all attachments in the beryllium rule.
For example, Attachment 1—title of
your document, Attachment 2—title of
your document, Attachment 3—title of
your document, etc. Specific
instructions on uploading all documents
are found in the Facts, Answer,
Questions portion and the commenter
check list on Regulations.gov Web page.
Fax: If your submissions, including
attachments, are not longer than 10
pages, you may fax them to the OSHA
Docket Office at (202) 693–1648.
Mail, hand delivery, express mail,
messenger, or courier service: You may
submit your comments to the OSHA
Docket Office, Docket No. OSHA–
H005C–2006–0870, Room N–3653, U.S.
Department of Labor, 200 Constitution
Avenue NW., Washington, DC 20210;
telephone (202) 693–2350 (TTY (887)
889–5627). OSHA’s Docket Office
accepts deliveries (hand deliveries,
express mail, and messenger/courier
service) from 10 a.m. to 3 p.m. e.t.,
weekdays.
Instructions: All submissions must
include the Agency name and the
docket number for this rulemaking
(Docket No. OSHA–H005C–2006–0870).
All comments, including any personal
information you provide, are placed in
the public docket without change and
may be made available online at https://
www.regulations.gov. Therefore, OSHA
cautions you about submitting personal
information such as Social Security
numbers and birthdates.
Docket: To read or download
comments and materials submitted in
response to this Federal Register
document, go to Docket No. OSHA–
H005C–2006–0870 at https://
www.regulations.gov, or to the OSHA
Docket Office at the address above. All
comments and submissions are listed in
the https://www.regulations.gov index;
however, some information (e.g.,
copyrighted material) is not publicly
available to read or download through
that Web site. All comments and
submissions are available for inspection
at the OSHA Docket Office.
Electronic copies of this Federal
Register document are available at
https://www.regulations.gov. Copies also
are available from the OSHA Office of
Publications, Room N–3101, U.S.
PO 00000
Frm 00018
Fmt 4702
Sfmt 4702
Department of Labor, 200 Constitution
Avenue NW., Washington, DC 20210;
telephone (202) 693–1888. This
document, as well as news releases and
other relevant information, is also
available at OSHA’s Web site at https://
www.osha.gov.
FOR FURTHER INFORMATION CONTACT:
Frank Meilinger, Director, Office of
Communications, Room N–3647, OSHA,
U.S. Department of Labor, 200
Constitution Avenue NW., Washington,
DC 20210; telephone (202) 693–1999;
email meilinger.francis2@dol.gov.
OSHA
published a final rule entitled
Occupational Exposure to Beryllium on
January 9, 2017 (82 FR 2470). On
February 1, 2017, OSHA published a
document in the Federal Register
delaying the effective date of this rule
from March 10, 2017 until March 21,
2017 (82 FR 8901 (February 1, 2017)).
OSHA based this extension on the
Presidential directive as expressed in
the memorandum of January 20, 2017,
from the Assistant to the President and
Chief of Staff, entitled ‘‘Regulatory
Freeze Pending Review’’ (82 FR 8346
(January 24, 2017)) (‘‘Memorandum’’).
The Memorandum directed the heads of
Executive Departments and Agencies to
temporarily postpone for sixty days
from the date of the memorandum the
effective dates of all regulations that had
been published in the Federal Register
but had not yet taken effect. The
Memorandum also noted certain
exceptions that do not apply here.
OSHA therefore delayed the effective
date for the rule entitled ‘‘Occupational
Exposure to Beryllium’’ to March 21,
2017.
The Memorandum also directed
agencies to consider further delaying the
effective date for regulations beyond
that 60-day period. After further review,
OSHA has preliminarily determined
that it is appropriate to further delay the
effective date of this rule, for the
purpose of further reviewing questions
of fact, law, and policy raised therein.
Therefore, in accordance with the
Memorandum, OSHA proposes to
further delay the effective date for the
rule entitled ‘‘Occupational Exposure to
Beryllium’’ to May 20, 2017. The
proposed extension of the effective date
will not affect the compliance dates of
the beryllium rule.
OSHA seeks comment by March 13,
2017 on its proposal to extend the
effective date by 60 days to May 20,
2017.
SUPPLEMENTARY INFORMATION:
E:\FR\FM\02MRP1.SGM
02MRP1
Agencies
[Federal Register Volume 82, Number 40 (Thursday, March 2, 2017)]
[Proposed Rules]
[Pages 12314-12318]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-03953]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9055; Directorate Identifier 2016-NM-071-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 proposal for certain Airbus Model
A300 B4-600R series airplanes, Model A300 C4-605R Variant F airplanes,
and Model A300 F4-600R series airplanes. This action revises the notice
of proposed rulemaking (NPRM) by extending the area to be inspected for
cracking. This SNPRM also proposes to require an additional inspection
for previously inspected airplanes. We are proposing this airworthiness
directive (AD) to address the unsafe condition on these products. 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 September 8, 2016 (81 FR 62026), is reopened.
We must receive comments on this SNPRM by April 17, 2017.
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-2016-
9055; 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:
[[Page 12315]]
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-2016-9055;
Directorate Identifier 2016-NM-071-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
B4-600R series airplanes, Model A300 C4-605R Variant F airplanes, and
Model A300 F4-600R series airplanes. The NPRM published in the Federal
Register on September 8, 2016 (81 FR 62026). The NPRM was prompted by
the results of a full stress analysis of the lower area of frame (FR)
40 that revealed a crack could occur in the forward fitting lower
radius of FR 40 after a certain number of flight cycles. The NPRM
proposed to require an inspection of the lower area of the FR 40 radius
for cracking, and corrective action if necessary.
Actions Since the NPRM Was Issued
Since we issued the NPRM, we have determined that the area to be
inspected for cracking in the lower area of the FR 40 radius should be
extended. We have also determined that an additional inspection is
necessary for airplanes previously inspected. In addition, the European
Aviation Safety Agency (EASA), which is the Technical Agent for the
Member States of the European Union, issued EASA AD 2016-0179, dated
September 12, 2016 (referred to after this as the Mandatory Continuing
Airworthiness Information, or ``the MCAI''), which supersedes EASA AD
2016-0085, dated April 28, 2016. EASA AD 2016-0085 was the MCAI
referred to in the NPRM.
The MCAI was issued to correct an unsafe condition for certain
Airbus Model A300 B4-600R series airplanes, Model A300 C4-605R Variant
F airplanes, and Model A300 F4-600R series airplanes. The MCAI states:
Following a full stress analysis of the Frame (FR) 40 lower
area, supported by a Finite Element Model (FEM), of the post-mod
10221 configuration, it was demonstrated that, for the FR40 forward
fitting lower radius, a crack could occur after a certain amount of
flight cycles (FC).
This condition, if not detected and corrected, could reduce the
structural integrity of the fuselage.
To address this potential unsafe condition, Airbus established
that crack detection could be achieved through a special detailed
inspection (SDI) using a high frequency eddy current (HFEC) method,
and issued Alert Operators Transmission (AOT) A57W009-16 to provide
those inspection instructions.
Consequently, EASA issued AD 2016-0085 to require a one-time SDI
of the FR40 lower area and, depending on findings, accomplishment of
applicable corrective action(s).
Since that [EASA] AD was issued, further cracks were detected,
originating from the fastener hole, and, based on these findings, it
was determined that inspection area must be enlarged, and Airbus AOT
A57W009-16 Revision (Rev.) 01 was issued accordingly.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2016-0085, which is superseded, extends the
area of inspection, and requires an additional inspection for
aeroplanes previously inspected.
The one-time SDI for high cycle aeroplanes is intended to
mitigate the highest risks within the fleet. Airbus is currently
developing instructions for repetitive inspections that are likely
to be the subject of further [EASA] AD action.
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-2016-
9055.
Related Service Information Under 1 CFR Part 51
Airbus has issued Alert Operators Transmission (AOT) A57W009-16,
Rev 01, including Appendices 1 and 2, dated July 13, 2016 (``AOT
A57W009-16, Rev 01''). The service information describes procedures for
inspecting the forward fitting lower radius of FR 40 for cracking, and
corrective action. 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 comments received.
Support for the NPRM
One commenter, Joseph Luna, supported the intent of the NPRM.
Request To Refer to Revised MCAI and Service Information
Airbus requested that the NPRM be revised to specify new MCAI and
revised service information. Airbus noted that, after the NPRM was
published, the service information and the MCAI referred to in the NPRM
were revised. Airbus explained that Airbus AOT A57W009-16, Rev 00,
dated February 25, 2016 (``AOT A57W009-16, Rev 00''), was revised to
extend the area of inspection, and AOT A57W009-16, Rev 01, was
published to include that information. Airbus also pointed out that,
after the NPRM was published, EASA superseded EASA AD 2016-0085, dated
April 28, 2016, and issued EASA AD 2016-0179, dated September 12, 2016,
which extends the area of inspection and requires an additional action
for airplanes previously inspected.
We agree with the commenter's request. We have revised this
proposed AD to refer to AOT A57W009-16, Rev 01, as the appropriate
source of service information for completing the proposed actions. We
have also included a one-time additional inspection for airplanes on
which the proposed inspection in paragraph (g) of this proposed AD was
accomplished using the procedures in AOT A57W009-16, Rev 00. In
addition, we added credit for the proposed inspection specified in
paragraph (g) of this proposed AD, if that action was done before the
effective date of the AD using the procedures in AOT A57W009-16, Rev
00, provided the proposed inspection specified in paragraph (h) of this
proposed AD is accomplished. In addition, we revised the preamble and
paragraph (m)(1) of this proposed AD to refer to the current EASA AD:
AD 2016-0179, dated September 12, 2016.
Request To Delay Issuance of Final Rule
United Parcel Service (UPS) requested that we delay issuance of the
final rule until Airbus issues an inspection service bulletin that will
specify the same actions described in AOT A57W009-16, Rev 00, and might
include repetitive inspections that are not in AOT A57W009-16, Rev 00.
UPS stated that Airbus has committed to issue the inspection service
bulletin within the 4th quarter of 2016, and the service bulletin will
supersede AOT A57W009-16, Rev 00. UPS suggested that, to reduce the
issuance of subsequent alternative method of compliance (AMOC) requests
and additional proposed rules, the final rule should be
[[Page 12316]]
delayed until the Airbus inspection service bulletin is released. UPS
noted that the areas to be inspected are currently included in another
Airbus service bulletin and other regulations, based on an airplane's
modification status. UPS stated that its fleet of airplanes affected by
the NPRM is below the initial threshold, so there would not be an
impact to the safety of its current fleet. UPS anticipated that the
first inspection for its affected airplanes would not take place until
2025.
We do not agree with the commenter's request to delay issuance of a
final rule until the Airbus inspection service bulletin is issued. As
previously mentioned, after the issuance of the NPRM, Airbus revised
AOT A57W009-16, Rev 00, to include an extended area of inspection, and
we have revised this proposed AD to refer to the revised AOT (AOT
A57W009-16, Rev 01). AOT A57W009-16, Rev 01, contains all of the
necessary information to address the identified unsafe condition. When
repetitive inspections are developed and related service information is
available we will consider if additional rulemaking is necessary to
mandate those actions.
In addition, although UPS may have time before the airplanes in its
fleet are required to be inspected, other operators might have
airplanes that have accumulated total flight cycles that are close to
the threshold for the proposed initial inspection.
Request To Specify Actions Required for Compliance (``RC'')
UPS requested that paragraph (g) of the proposed AD (in the NPRM)
be revised to specify that the required actions are to be accomplished
in accordance with ``paragraph 4.2.2'' of AOT A57W009-16, Rev 00,
instead of ``the procedures'' in AOT A57W009-16, Rev 00. UPS stated
that, as written, paragraph (g) of the proposed AD would require
operators to accomplish all of the actions in AOT A57W009-16, Rev 00,
but it is specifically the actions in paragraph 4.2.2 of AOT A57W009-
16, Rev 00, that address the unsafe condition. UPS noted that Airbus
Service Bulletin A300-57-6115 specifies the identical location, access,
and inspection procedures as AOT A57W009-16, Rev 00, but that service
bulletin identifies which actions are ``Required for Compliance''
(``RC''). To be in compliance with an AD, operators must accomplish all
of the actions identified as ``RC'' in the service information that is
required by an AD. The actions that are not identified as ``RC'' in the
required service information are classified as recommended for
compliance.
We agree with the commenter's request and have revised paragraphs
(g) and (h) of this proposed AD to refer to the actions in paragraph
4.2.2 of the Airbus AOT, which are the actions required for compliance.
As previously mentioned, we have revised this SNPRM to refer to AOT
A57W009-16, Rev 01, which was issued after the NPRM was published. We
note that this AOT does not include standard ``RC'' language.
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 the same
type design.
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 proposed AD affects 94 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Inspection......................... 3 work-hours x $85 per hour $0 $255 $23,970
= $255.
Report............................. 1 work-hour x $85 per hour 0 85 7,990
= $85.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.
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 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 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
[[Page 12317]]
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-2016-9055; Directorate Identifier 2016-NM-
071-AD.
(a) Comments Due Date
We must receive comments by April 17, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus airplanes, certificated in any
category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of
this AD, on which Airbus Modification 10221 was embodied in
production.
(1) Airbus Model A300 B4-605R and B4-622R airplanes.
(2) Airbus Model A300 C4-605R Variant F airplanes.
(3) Airbus Model A300 F4-605R and F4-622R airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by the detection of cracking that
originated from the fastener holes in the forward fitting lower
radius of frame (FR) 40. We are issuing this AD to detect and
correct cracking in the forward fitting lower radius of FR 40. Such
cracking could reduce the structural integrity of the fuselage.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspection
At the later of the compliance times specified in paragraphs
(g)(1) and (g)(2) of this AD, do a high frequency eddy current
(HFEC) inspection of the lower area of the FR 40 radius for
cracking, in accordance with paragraph 4.2.2 in Airbus Alert
Operators Transmission (AOT) A57W009-16, Rev 01, including
Appendices 1 and 2, dated July 13, 2016.
(1) Prior to exceeding 19,000 total flight cycles or 41,000
total flight hours since the airplane's first flight, whichever
occurs first.
(2) Within 300 flight cycles or 630 flight hours after the
effective date of this AD, whichever occurs first.
(h) Additional Inspection for Previously Inspected Airplanes
For airplanes on which the HFEC inspection required by paragraph
(g) of this AD was accomplished before the effective date of this AD
using the procedures in Airbus AOT A57W009-16, Rev 00, including
Appendices 1 and 2, dated February 25, 2016: Within 300 flight
cycles or 630 flight hours after the effective date of this AD,
whichever occurs first, do a one-time additional HFEC inspection of
the lower area of the FR 40 radius for cracking, in accordance with
paragraph 4.2.2 in Airbus AOT A57W009-16, Rev 01, including
Appendices 1 and 2, dated July 13, 2016.
(i) Corrective Action
If any crack is found during the inspection required by
paragraph (g) or (h) of this AD: Before further flight, do the
applicable corrective actions in accordance with the procedures in
Airbus AOT A57W009-16, Rev 01, including Appendices 1 and 2, dated
July 13, 2016. Where AOT A57W009-16, Rev 01, including Appendices 1
and 2, dated July 13, 2016, specifies to contact Airbus for
appropriate action, accomplish the corrective actions in accordance
with the procedures specified in paragraph (l)(2) of this AD.
(j) Reporting Requirement
Submit a report of all findings (both positive and negative)
from the inspection required by paragraph (g) of this AD to Airbus
Customer Services through TechRequest on Airbus World (https://w3.airbus.com/) by selecting Engineering Domain and ATA 57-10.
(1) For airplanes on which the inspection specified in paragraph
(g) of this AD is accomplished on or after the effective date of
this AD: Submit the report within 30 days after performing the
inspection.
(2) For airplanes on which the inspection specified in paragraph
(g) of this AD is accomplished before the effective date of this AD:
Submit the report within 30 days after the effective date of this
AD.
(k) Credit for Previous Actions
This paragraph provides credit for the action required by
paragraph (g) of this AD, if that action was done before the
effective date of this AD using Airbus AOT A57W009-16, Rev 00,
including Appendices 1 and 2, dated February 25, 2016, provided the
inspection required by paragraph (h) of this AD is accomplished.
(l) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: 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
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.
(m) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA
[[Page 12318]]
Airworthiness Directive 2016-0179, dated September 12, 2016, 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-2016-9055.
(2) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You may view this service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on February 16, 2017.
Thomas Groves,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-03953 Filed 3-1-17; 8:45 am]
BILLING CODE 4910-13-P