Airworthiness Directives; Airbus Airplanes, 28030-28033 [2017-12613]
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Federal Register / Vol. 82, No. 117 / Tuesday, June 20, 2017 / Proposed Rules
(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):
■
Honeywell International Inc.: Docket No.
FAA–2017–0034; Directorate Identifier
2016–NE–32–AD.
(a) Comments Due Date
We must receive comments by August 4,
2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Honeywell
International Inc. (Honeywell) AS907–1–1A
turbofan engines with second stage lowpressure turbine (LPT2) rotor blades, part
number (P/N) 3035602–1, installed.
(d) Subject
Joint Aircraft System Component (JASC)
Code 7250, Turbine Section.
asabaliauskas on DSKBBXCHB2PROD with PROPOSALS
(e) Unsafe Condition
This AD was prompted by reports of loss
of power due to failure of the LPT2 blade. We
are issuing this AD to prevent failure of the
LPT2 blades, failure of one or more engines,
and loss of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(1) For LPT2 rotor blades, P/N 3035602–1
that have more than 8,000 hours since new
on the effective date of this AD, perform a
one-time borescope inspection for wear of the
Z gap contact area at the blade tip shroud for
each of the 62 LPT2 rotor blades within 200
hours time in service after the effective date
of this AD.
(2) Use the Accomplishment Instructions,
Paragraph 3.B.(1), of Honeywell Service
Bulletin (SB) AS907–72–9067, Revision 1,
dated March 20, 2017, to do the inspection.
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(3) If the measured wear and/or fretting of
any Z gap contact area is greater than 0.005
inch, replace the LPT2 rotor assembly with
a part eligible for installation before further
flight.
(4) Do the following actions within 200
hours time in service after the effective date
of this AD:
(i) Using a borescope make a clear digital
image of the Z gap contact area at the blade
tip shroud of the 62 LPT2 rotor blades.
(ii) Identify the three Z gap contact areas
with the greatest amount of wear and/or
fretting.
(iii) Record the blade position on the LPT2
rotor assembly and the measured wear of the
three Z gap contact areas with the greatest
amount of wear and/or fretting.
(iv) Send the results to Honeywell at
engine.reliability@honeywell.com within 30
days after completing these actions.
(g) Credit for Previous Actions
You may take credit for the actions
required by paragraphs (f)(1) and (4) of this
AD, if you performed these actions before the
effective date of this AD using Honeywell SB
AS907–72–9067, Revision 0, dated December
12, 2016.
(h) Paperwork Reduction Act Burden
Statement
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.
(i) Alternative Methods of Compliance
(AMOCs)
The Manager, Los Angeles Aircraft
Certification Office, FAA, may approve
AMOCs for this AD. Use the procedures
found in 14 CFR 39.19 to make your request.
(j) Related Information
(1) For more information about this
proposed AD, contact Joseph Costa,
Aerospace Engineer, Los Angeles Aircraft
Certification Office, FAA, Transport Airplane
Directorate, 3960 Paramount Blvd.,
Lakewood, CA 90712–4137; phone: 562–627–
5246; fax: 562–627–5210; email:
joseph.costa@faa.gov.
(2) Honeywell SBs AS907–72–9067,
Revision 0, dated December 12, 2016 and
AS907–72–9067, Revision 1, dated March 20,
2017, can be obtained from Honeywell
International Inc., using the contact
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information in paragraph (j)(3) of this
proposed AD.
(3) For service information identified in
this proposed AD, contact Honeywell
International Inc., 111 S 34th Street, Phoenix,
AZ 85034–2802; phone: 800–601–3099;
Internet: https://
myaerospace.honeywell.com/wps/portal/!ut/.
(4) You may view this service information
at the FAA, Engine & Propeller Directorate,
1200 District Avenue, Burlington, MA. For
information on the availability of this
material at the FAA, call 781–238–7125.
Issued in Burlington, Massachusetts, on
June 13, 2017.
Robert J. Ganley,
Acting Manager, Engine & Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 2017–12561 Filed 6–19–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0560; Directorate
Identifier 2016–NM–172–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all
Airbus Model A310–203, –204, –221,
–222, –304, –322, –324, and –325
airplanes. This proposed AD was
prompted by reports of cracking in the
drainage holes on the lower skin panel
in the center wing box between frames
(FR) 42 and FR 46. This proposed AD
would require repetitive rotating probe
inspections for cracking of the trellis
boom drainage holes, the holes in the
stringers bottom, and the holes of the
inner pump, and corrective actions if
necessary. We are proposing this AD to
address the unsafe condition on these
products.
SUMMARY:
We must receive comments on
this proposed AD by August 4, 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
DATES:
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W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, 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.
asabaliauskas on DSKBBXCHB2PROD with PROPOSALS
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–2017–
0560; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone: 800–647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: 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–2017–0560; Directorate Identifier
2016–NM–172–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.
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Discussion
Fatigue damage can occur locally, in
small areas or structural design details,
or globally, in widespread areas.
Multiple-site damage is widespread
damage that occurs in a large structural
element such as a single rivet line of a
lap splice joining two large skin panels.
Widespread damage can also occur in
multiple elements such as adjacent
frames or stringers. Multiple-site
damage and multiple-element damage
cracks are typically too small initially to
be reliably detected with normal
inspection methods. Without
intervention, these cracks will grow,
and eventually compromise the
structural integrity of the airplane. This
condition is known as widespread
fatigue damage (WFD). It is associated
with general degradation of large areas
of structure with similar structural
details and stress levels. As an airplane
ages, WFD will likely occur, and will
certainly occur if the airplane is
operated long enough without any
intervention.
The FAA’s WFD final rule (75 FR
69746, November 15, 2010) became
effective on January 14, 2011. The WFD
rule requires certain actions to prevent
structural failure due to WFD
throughout the operational life of
certain existing transport category
airplanes and all of these airplanes that
will be certificated in the future. For
existing and future airplanes subject to
the WFD rule, the rule requires that
DAHs establish a limit of validity (LOV)
of the engineering data that support the
structural maintenance program.
Operators affected by the WFD rule may
not fly an airplane beyond its LOV,
unless an extended LOV is approved.
The WFD rule (75 FR 69746,
November 15, 2010) does not require
identifying and developing maintenance
actions if the DAHs can show that such
actions are not necessary to prevent
WFD before the airplane reaches the
LOV. Many LOVs, however, do depend
on accomplishment of future
maintenance actions. As stated in the
WFD rule, any maintenance actions
necessary to reach the LOV will be
mandated by airworthiness directives
through separate rulemaking actions.
In the context of WFD, this action is
necessary to enable DAHs to propose
LOVs that allow operators the longest
operational lives for their airplanes, and
still ensure that WFD will not occur.
This approach allows for an
implementation strategy that provides
flexibility to DAHs in determining the
timing of service information
development (with FAA approval),
while providing operators with certainty
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regarding the LOV applicable to their
airplanes.
On April 22, 2011, we issued AD
2011–10–06, Amendment 39–16687 (76
FR 27227, May 11, 2011) (‘‘AD 2011–
10–06’’), applicable to all Airbus Model
A310–203, –204, –221, –222, –304,
–322, –324, and –325 airplanes. That
AD currently requires:
• Cold working of trellis boom
drainage holes;
• Repetitive detailed or rotating probe
inspections for cracking in the drainage
holes on the lower skin panel in the
center wing box between FR 42 and FR
46, and corrective actions if necessary,
including repair; and
• Repetitive eddy current inspections
for cracking of the upper corner angle
fitting and the vertical tee fitting at left
and right FR 40, and corrective actions
if necessary, including repair and
replacement of the internal angle fitting.
AD 2011–10–06 was prompted by
European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, AD 2009–0057 to identify and
correct an unsafe condition. The
identified unsafe condition is cracking
of trellis boom drainage holes, the holes
in the stringers bottom, and the holes of
the inner pump, which could result in
reduced structural integrity of the
wings.
Since issuance of AD 2011–10–06,
EASA has issued EASA AD 2016–0196,
dated September 30, 2016 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for all Airbus Model A310–203, –204,
–221, –222, –304, –322, –324, and –325
airplanes. The MCAI states:
DGAC France issued AD F–1992–106–
132R7 to require certain inspections and
modifications which addressed JAR/FAR
[Joint Aviation Requirements/Federal
Aviation Regulations] 25–571 requirements,
related to damage-tolerance and fatigue
evaluation of structure. Following the
Extended Design Service Goal activities as
part of the Structure Task Group for the
Airbus A310 program, EASA published AD
2007–0053, which replaced DGAC France AD
F–1992–106–132R7.
After EASA issued AD 2007–0053R1, the
thresholds and the intervals of Airbus
Service Bulletins (SB) A310–57–2050 and
A310–57–2064 were updated, prompting
EASA to issue AD 2009–0057 [which
corresponds to FAA AD 2011–10–06] and
[EASA] AD 2007–0053 was revised (R2)
accordingly. EASA AD 2009–0057 also
required the accomplishment of the actions
specified in Airbus SB A310–57–2048 at
Revision 01.
After EASA issued AD 2009–0057, in the
frame of the Widespread Fatigue Damage
campaign, new analysis has indicated the
need for additional work included in
Revision 03 of Airbus SB A310–57–2050.
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Federal Register / Vol. 82, No. 117 / Tuesday, June 20, 2017 / Proposed Rules
For the reason described above, this new
[EASA] AD retains the requirements of EASA
AD 2009–0057, which is superseded, and
requires inspection and corrective actions as
specified in Airbus SB A310–57–2050
Revision 04.
Required actions include a repetitive
rotating probe inspection for cracking of
certain holes in the stringers bottom,
inner pumps, and the trellis boom; and
corrective actions, i.e., repair of holes
where cracks are discovered.
The compliance times vary depending
on airplane configuration. The earliest
initial inspection compliance time is
11,400 total flight cycles or 57,300 total
flight hours, whichever occurs first. The
latest initial compliance time is 38,700
total flight cycles or 77,500 total flight
hours, whichever occurs first. The
shortest repetitive interval is 6,200 flight
cycles or 31,200 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–2017–
0560.
Related Service Information Under 1
CFR Part 51
We reviewed Airbus Service Bulletin
A310–57–2050, Revision 04, dated
March 13, 2015. This service
information describes procedures for
repetitive rotating probe inspections for
cracking of the trellis boom drainage
holes, the holes in the stringers bottom,
and the holes of the inner pump, and
corrective actions. 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.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products the same
type design.
This proposed AD would not
supersede AD 2011–10–06. Rather, we
have determined that a stand-alone AD
would be more appropriate to address
the changes in the MCAI. This proposed
AD would require repetitive rotating
probe inspections for cracking of the
trellis boom drainage holes, the holes in
the stringers bottom, and the holes of
the inner pump, and corrective actions,
if necessary. Accomplishment of the
proposed actions would then terminate
the actions required by paragraph (h) of
AD 2011–10–06.
Costs of Compliance
We estimate that this proposed AD
affects 8 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Action
Labor cost
Inspection ...................
84 work-hours × $85 per hour = $7,140 .............................................
asabaliauskas on DSKBBXCHB2PROD with PROPOSALS
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this proposed AD.
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
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Parts cost
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:
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Cost per
product
$5,890
Cost on U.S.
operators
$13,030
$104,240
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–2017–0560;
Directorate Identifier 2016–NM–172–AD.
(a) Comments Due Date
We must receive comments by August 4,
2017.
(b) Affected ADs
This AD affects AD 2011–10–06,
Amendment 39–16687 (76 FR 27227, May 11,
2011) (‘‘AD 2011–10–06’’).
(c) Applicability
This AD applies to Airbus Model A310–
203, –204, –221, –222, –304, –322, –324, and
–325 airplanes, certificated in any category,
all serial numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
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Federal Register / Vol. 82, No. 117 / Tuesday, June 20, 2017 / Proposed Rules
(e) Reason
This AD was prompted by reports of
cracking in the drainage holes on the lower
skin panel in the center wing box between
frames (FR) 42 and FR 46. We are issuing this
AD to detect and correct cracking of trellis
boom drainage holes, the holes in the
stringers bottom, and the holes of the inner
pump, which could result in reduced
structural integrity of the wings.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Rotating Probe Inspections and
Corrective Actions
Except as provided by paragraph (h)(1) of
this AD, before exceeding the applicable
threshold or grace period, whichever occurs
later, as defined in paragraph 1.E.,
‘‘Compliance,’’ of Airbus Service Bulletin
A310–57–2050, Revision 04, dated March 13,
2015, accomplish the rotating probe
inspection for cracking of the trellis boom
drainage holes, the holes in the stringers
bottom, and the holes of the inner pump, as
applicable, and do all applicable corrective
actions, as specified in, and in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A310–57–2050,
Revision 04, dated March 13, 2015, except as
required by paragraph (h)(2) of this AD. Do
all applicable corrective actions before
further flight. Repeat the inspection
thereafter at intervals not to exceed those
defined in paragraph 1.E., ‘‘Compliance,’’ of
Airbus Service Bulletin A310–57–2050,
Revision 04, dated March 13, 2015.
(h) Exceptions to Service Information
(1) Where Airbus Service Bulletin A310–
57–2050, Revision 04, dated March 13, 2015,
specifies a grace period ‘‘after receipt of the
Service Bulletin without exceeding previous
Service Bulletin revision values,’’ this AD
requires compliance within the specified
grace period after the effective date of this
AD.
(2) Where Airbus Service Bulletin A310–
57–2050, Revision 04, dated March 13, 2015,
specifies to contact Airbus for appropriate
action, and specifies that action as ‘‘RC’’
(Required for Compliance): Before further
flight, accomplish corrective actions in
accordance with the procedures specified in
paragraph (l)(2) of this AD.
asabaliauskas on DSKBBXCHB2PROD with PROPOSALS
(i) No Terminating Action for Inspections
Accomplishing corrective actions on an
airplane as required by paragraph (g) or (h)(2)
of this AD does not constitute terminating
action for the repetitive actions required by
paragraph (g) of this AD.
(j) Terminating Action
Accomplishment of the initial inspection
required by paragraph (g) of this AD
constitutes terminating action for the actions
required by paragraph (h) of AD 2011–10–06.
(k) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraph (g) of this AD, if those
actions were performed before the effective
date of this AD using the service information
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specified in Airbus Service Bulletin A310–
57–2050, Revision 03, dated December 19,
2014.
(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 manager of the International Branch,
send it to the attention of the person
identified in paragraph (m)(2) of this AD.
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: Except as
required by paragraph (h)(2) of this AD: For
any requirement in this AD to obtain
corrective actions from a manufacturer, the
action must be accomplished using a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or the European Aviation
Safety Agency (EASA); or Airbus’s EASA
Design Organization Approval (DOA). If
approved by the DOA, the approval must
include the DOA-authorized signature.
(3) Required for Compliance (RC): Except
as required by paragraph (h)(2) of this AD: If
any service information contains procedures
or tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(m) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2016–0196, dated September 30, 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–2017–0560.
(2) For more information about this AD,
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.
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
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28033
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 June 9,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–12613 Filed 6–19–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2017–0458; Airspace
Docket No. 17–ASW–8]
Proposed Amendment of Class E
Airspace; Canadian, TX; and Wheeler,
TX
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
This action proposes to
modify Class E airspace extending
upward from 700 feet above the surface
at Hemphill County Airport, Canadian,
TX, and Wheeler Municipal Airport,
Wheeler, TX. The FAA is proposing this
action due to the decommissioning of
the Sayre co-located VHF
omnidirectional range and tactical air
navigation system (VORTAC) facility,
which provided navigation guidance for
the instrument procedures to these
airports. The VORTAC is being
decommissioned as part of the VHF
omnidirectional range (VOR) Minimum
Operational Network (MON) Program.
This action would enhance the safety
and management of instrument flight
rules (IFR) operations at these airports.
Additionally, the geographic
coordinates of the airports would be
adjusted to coincide with the FAA’s
aeronautical database.
DATES: Comments must be received on
or before August 4, 2017.
ADDRESSES: Send comments on this
proposal to the U.S. Department of
Transportation, Docket Operations, 1200
New Jersey Avenue SE., West Building
Ground Floor, Room W12–140,
Washington, DC 20590; telephone (202)
366–9826, or 1–800–647–5527. You
must identify FAA Docket No. FAA–
2017–0458; Airspace Docket No. 17–
ASW–8 at the beginning of your
SUMMARY:
E:\FR\FM\20JNP1.SGM
20JNP1
]]>Agencies
[Federal Register Volume 82, Number 117 (Tuesday, June 20, 2017)]
[Proposed Rules]
[Pages 28030-28033]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-12613]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0560; Directorate Identifier 2016-NM-172-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325
airplanes. This proposed AD was prompted by reports of cracking in the
drainage holes on the lower skin panel in the center wing box between
frames (FR) 42 and FR 46. This proposed AD would require repetitive
rotating probe inspections for cracking of the trellis boom drainage
holes, the holes in the stringers bottom, and the holes of the inner
pump, and corrective actions if necessary. We are proposing this AD to
address the unsafe condition on these products.
DATES: We must receive comments on this proposed AD by August 4, 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
[[Page 28031]]
W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, 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-2017-
0560; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone: 800-647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: 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-2017-0560;
Directorate Identifier 2016-NM-172-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
Fatigue damage can occur locally, in small areas or structural
design details, or globally, in widespread areas. Multiple-site damage
is widespread damage that occurs in a large structural element such as
a single rivet line of a lap splice joining two large skin panels.
Widespread damage can also occur in multiple elements such as adjacent
frames or stringers. Multiple-site damage and multiple-element damage
cracks are typically too small initially to be reliably detected with
normal inspection methods. Without intervention, these cracks will
grow, and eventually compromise the structural integrity of the
airplane. This condition is known as widespread fatigue damage (WFD).
It is associated with general degradation of large areas of structure
with similar structural details and stress levels. As an airplane ages,
WFD will likely occur, and will certainly occur if the airplane is
operated long enough without any intervention.
The FAA's WFD final rule (75 FR 69746, November 15, 2010) became
effective on January 14, 2011. The WFD rule requires certain actions to
prevent structural failure due to WFD throughout the operational life
of certain existing transport category airplanes and all of these
airplanes that will be certificated in the future. For existing and
future airplanes subject to the WFD rule, the rule requires that DAHs
establish a limit of validity (LOV) of the engineering data that
support the structural maintenance program. Operators affected by the
WFD rule may not fly an airplane beyond its LOV, unless an extended LOV
is approved.
The WFD rule (75 FR 69746, November 15, 2010) does not require
identifying and developing maintenance actions if the DAHs can show
that such actions are not necessary to prevent WFD before the airplane
reaches the LOV. Many LOVs, however, do depend on accomplishment of
future maintenance actions. As stated in the WFD rule, any maintenance
actions necessary to reach the LOV will be mandated by airworthiness
directives through separate rulemaking actions.
In the context of WFD, this action is necessary to enable DAHs to
propose LOVs that allow operators the longest operational lives for
their airplanes, and still ensure that WFD will not occur. This
approach allows for an implementation strategy that provides
flexibility to DAHs in determining the timing of service information
development (with FAA approval), while providing operators with
certainty regarding the LOV applicable to their airplanes.
On April 22, 2011, we issued AD 2011-10-06, Amendment 39-16687 (76
FR 27227, May 11, 2011) (``AD 2011-10-06''), applicable to all Airbus
Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes.
That AD currently requires:
Cold working of trellis boom drainage holes;
Repetitive detailed or rotating probe inspections for
cracking in the drainage holes on the lower skin panel in the center
wing box between FR 42 and FR 46, and corrective actions if necessary,
including repair; and
Repetitive eddy current inspections for cracking of the
upper corner angle fitting and the vertical tee fitting at left and
right FR 40, and corrective actions if necessary, including repair and
replacement of the internal angle fitting.
AD 2011-10-06 was prompted by European Aviation Safety Agency
(EASA), which is the Technical Agent for the Member States of the
European Union, AD 2009-0057 to identify and correct an unsafe
condition. The identified unsafe condition is cracking of trellis boom
drainage holes, the holes in the stringers bottom, and the holes of the
inner pump, which could result in reduced structural integrity of the
wings.
Since issuance of AD 2011-10-06, EASA has issued EASA AD 2016-0196,
dated September 30, 2016 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition for all Airbus Model A310-203, -204, -221, -222, -304,
-322, -324, and -325 airplanes. The MCAI states:
DGAC France issued AD F-1992-106-132R7 to require certain
inspections and modifications which addressed JAR/FAR [Joint
Aviation Requirements/Federal Aviation Regulations] 25-571
requirements, related to damage-tolerance and fatigue evaluation of
structure. Following the Extended Design Service Goal activities as
part of the Structure Task Group for the Airbus A310 program, EASA
published AD 2007-0053, which replaced DGAC France AD F-1992-106-
132R7.
After EASA issued AD 2007-0053R1, the thresholds and the
intervals of Airbus Service Bulletins (SB) A310-57-2050 and A310-57-
2064 were updated, prompting EASA to issue AD 2009-0057 [which
corresponds to FAA AD 2011-10-06] and [EASA] AD 2007-0053 was
revised (R2) accordingly. EASA AD 2009-0057 also required the
accomplishment of the actions specified in Airbus SB A310-57-2048 at
Revision 01.
After EASA issued AD 2009-0057, in the frame of the Widespread
Fatigue Damage campaign, new analysis has indicated the need for
additional work included in Revision 03 of Airbus SB A310-57-2050.
[[Page 28032]]
For the reason described above, this new [EASA] AD retains the
requirements of EASA AD 2009-0057, which is superseded, and requires
inspection and corrective actions as specified in Airbus SB A310-57-
2050 Revision 04.
Required actions include a repetitive rotating probe inspection for
cracking of certain holes in the stringers bottom, inner pumps, and the
trellis boom; and corrective actions, i.e., repair of holes where
cracks are discovered.
The compliance times vary depending on airplane configuration. The
earliest initial inspection compliance time is 11,400 total flight
cycles or 57,300 total flight hours, whichever occurs first. The latest
initial compliance time is 38,700 total flight cycles or 77,500 total
flight hours, whichever occurs first. The shortest repetitive interval
is 6,200 flight cycles or 31,200 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-2017-
0560.
Related Service Information Under 1 CFR Part 51
We reviewed Airbus Service Bulletin A310-57-2050, Revision 04,
dated March 13, 2015. This service information describes procedures for
repetitive rotating probe inspections for cracking of the trellis boom
drainage holes, the holes in the stringers bottom, and the holes of the
inner pump, and corrective actions. 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.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products the same
type design.
This proposed AD would not supersede AD 2011-10-06. Rather, we have
determined that a stand-alone AD would be more appropriate to address
the changes in the MCAI. This proposed AD would require repetitive
rotating probe inspections for cracking of the trellis boom drainage
holes, the holes in the stringers bottom, and the holes of the inner
pump, and corrective actions, if necessary. Accomplishment of the
proposed actions would then terminate the actions required by paragraph
(h) of AD 2011-10-06.
Costs of Compliance
We estimate that this proposed AD affects 8 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........................ 84 work-hours x $85 per hour $5,890 $13,030 $104,240
= $7,140.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.
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-2017-0560; Directorate Identifier 2016-NM-
172-AD.
(a) Comments Due Date
We must receive comments by August 4, 2017.
(b) Affected ADs
This AD affects AD 2011-10-06, Amendment 39-16687 (76 FR 27227,
May 11, 2011) (``AD 2011-10-06'').
(c) Applicability
This AD applies to Airbus Model A310-203, -204, -221, -222, -
304, -322, -324, and -325 airplanes, certificated in any category,
all serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
[[Page 28033]]
(e) Reason
This AD was prompted by reports of cracking in the drainage
holes on the lower skin panel in the center wing box between frames
(FR) 42 and FR 46. We are issuing this AD to detect and correct
cracking of trellis boom drainage holes, the holes in the stringers
bottom, and the holes of the inner pump, which could result in
reduced structural integrity of the wings.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Rotating Probe Inspections and Corrective Actions
Except as provided by paragraph (h)(1) of this AD, before
exceeding the applicable threshold or grace period, whichever occurs
later, as defined in paragraph 1.E., ``Compliance,'' of Airbus
Service Bulletin A310-57-2050, Revision 04, dated March 13, 2015,
accomplish the rotating probe inspection for cracking of the trellis
boom drainage holes, the holes in the stringers bottom, and the
holes of the inner pump, as applicable, and do all applicable
corrective actions, as specified in, and in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A310-57-2050,
Revision 04, dated March 13, 2015, except as required by paragraph
(h)(2) of this AD. Do all applicable corrective actions before
further flight. Repeat the inspection thereafter at intervals not to
exceed those defined in paragraph 1.E., ``Compliance,'' of Airbus
Service Bulletin A310-57-2050, Revision 04, dated March 13, 2015.
(h) Exceptions to Service Information
(1) Where Airbus Service Bulletin A310-57-2050, Revision 04,
dated March 13, 2015, specifies a grace period ``after receipt of
the Service Bulletin without exceeding previous Service Bulletin
revision values,'' this AD requires compliance within the specified
grace period after the effective date of this AD.
(2) Where Airbus Service Bulletin A310-57-2050, Revision 04,
dated March 13, 2015, specifies to contact Airbus for appropriate
action, and specifies that action as ``RC'' (Required for
Compliance): Before further flight, accomplish corrective actions in
accordance with the procedures specified in paragraph (l)(2) of this
AD.
(i) No Terminating Action for Inspections
Accomplishing corrective actions on an airplane as required by
paragraph (g) or (h)(2) of this AD does not constitute terminating
action for the repetitive actions required by paragraph (g) of this
AD.
(j) Terminating Action
Accomplishment of the initial inspection required by paragraph
(g) of this AD constitutes terminating action for the actions
required by paragraph (h) of AD 2011-10-06.
(k) Credit for Previous Actions
This paragraph provides credit for actions required by paragraph
(g) of this AD, if those actions were performed before the effective
date of this AD using the service information specified in Airbus
Service Bulletin A310-57-2050, Revision 03, dated December 19, 2014.
(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 manager of the International Branch, send it to the
attention of the person identified in paragraph (m)(2) of this AD.
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: Except as required by paragraph
(h)(2) of this AD: For any requirement in this AD to obtain
corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA); or Airbus's EASA Design
Organization Approval (DOA). If approved by the DOA, the approval
must include the DOA-authorized signature.
(3) Required for Compliance (RC): Except as required by
paragraph (h)(2) of this AD: If any service information contains
procedures or tests that are identified as RC, those procedures and
tests must be done to comply with this AD; any procedures or tests
that are not identified as RC are recommended. Those procedures and
tests that are not identified as RC may be deviated from using
accepted methods in accordance with the operator's maintenance or
inspection program without obtaining approval of an AMOC, provided
the procedures and tests identified as RC can be done and the
airplane can be put back in an airworthy condition. Any
substitutions or changes to procedures or tests identified as RC
require approval of an AMOC.
(m) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2016-0196, dated September 30, 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-2017-0560.
(2) For more information about this AD, 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.
(3) 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 June 9, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-12613 Filed 6-19-17; 8:45 am]
BILLING CODE 4910-13-P
