Airworthiness Directives; Airbus SAS Airplanes, 28431-28434 [2019-12877]
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Federal Register / Vol. 84, No. 118 / Wednesday, June 19, 2019 / Proposed Rules
The Boeing Company: Docket No. FAA–
2019–0399; Product Identifier 2018–
NM–149–AD.
(a) Comments Due Date
The FAA must receive comments by
August 5, 2019.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 737 series airplanes, certificated in
any category, except for Model 737–100,
–200, –200C, –300, –400, and –500 series
airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of
separation of lower aft wing-to-body fairing
panel 194E (‘‘fairing panel 194E’’) during
flight, due to worn or damaged nutplates on
the 193D wheel well panel and support
structure. The FAA is issuing this AD to
address separation of fairing panel 194E.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections and Corrective
Actions
(1) For airplanes with an original
airworthiness certificate or an original export
certificate of airworthiness dated on or before
the effective date of this AD: Within 24
months after the effective date of this AD, do
a general visual inspection for discrepancies
of fairing panel 194E, wheel well panel 193D,
and support structure, and do all applicable
related investigative and corrective actions,
in accordance with Part 1 and Part 2 of the
Accomplishment Instructions of Boeing
Service Bulletin 737–53–1307, dated January
12, 2012. All applicable related investigative
and corrective actions must be done before
further flight. Repeat the inspection
thereafter at intervals not to exceed 1,000
flight cycles.
(2) For airplanes having line numbers 3533
and subsequent with an original
airworthiness certificate or an original export
certificate of airworthiness dated on or before
the effective date of this AD: If the initial
inspection required by paragraph (g)(1)
shows that fairing panel 194E, wheel well
panel 193D, and the support structure have
the number and type of attachments specified
in the post-reworked configuration of Boeing
Service Bulletin 737–53–1307, dated January
12, 2012, then the repetitive inspections
required by paragraph (g)(1) of this AD are
terminated. The requirements of paragraph (i)
of this AD continue to apply.
(h) Terminating Action
For airplanes with an original
airworthiness certificate or an original export
certificate of airworthiness dated on or before
the effective date of this AD: Within 72
months after the effective date of this AD, do
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the actions required by paragraph (h)(1) or
(h)(2) of this AD, as applicable.
Accomplishing the actions in paragraph
(h)(1) or (h)(2) of this AD terminates the
repetitive inspections required by paragraph
(g)(1) of this AD. The requirements of
paragraph (i) of this AD continue to apply.
(1) Rework fairing panel 194E, wheel well
panel 193D, and the support structure,
including accomplishment of all applicable
related investigative actions and repair, in
accordance with Part 3 of the
Accomplishment Instructions of Boeing
Service Bulletin 737–53–1307, dated January
12, 2012. All applicable related investigative
actions and repairs must be done before
further flight.
(2) Verify that fairing panel 194E, wheel
well panel 193D, and the support structure
have the number and type of attachments
specified in the post-reworked configuration
of Boeing Service Bulletin 737–53–1307,
dated January 12, 2012.
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; internet https://
www.myboeingfleet.com. You may view this
service information at the FAA, Transport
Standards Branch, 2200 South 216th St., Des
Moines, WA. For information on the
availability of this material at the FAA, call
206–231–3195.
(i) Parts Installation Limitation
As of the effective date of this AD, no
person may install a fairing panel 194E on
any airplane identified in paragraph (c) of
this AD, unless fairing panel 194E, wheel
well panel 193D, and the support structure
have the number and type of attachments
specified in the post-reworked configuration
of Boeing Service Bulletin 737–53–1307,
dated January 12, 2012.
14 CFR Part 39
(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle ACO Branch,
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
certification office, send it to the attention of
the person identified in paragraph (k)(1) of
this AD. Information may be emailed to: 9ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by The Boeing Company
Organization Designation Authorization
(ODA) that has been authorized by the
Manager, Seattle ACO Branch, FAA, to make
those findings. To be approved, the repair
method, modification deviation, or alteration
deviation must meet the certification basis of
the airplane, and the approval must
specifically refer to this AD.
(k) Related Information
(1) For more information about this AD,
contact Alan Pohl, Aerospace Engineer,
Airframe Section, FAA, Seattle ACO Branch,
2200 South 216th St., Des Moines, WA
98198; phone and fax: 206–231–3527; email:
alan.pohl@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
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Issued in Des Moines, Washington, on June
14, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–13020 Filed 6–18–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
[Docket No. FAA–2019–0439; Product
Identifier 2019–NM–037–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2012–22–
18, which applies to all Airbus SAS
Model A330–243, –243F, –341, –342,
and –343 airplanes. AD 2012–22–18
requires repetitive inspections of the
three inner acoustic panels of both
engine air intake cowls to detect
disbonding, and corrective actions if
necessary. Since we issued AD 2012–
22–18, we have received additional
reports of engine air inlet cowl collapse.
This proposed AD would retain the
requirements of AD 2012–22–18 with a
reduced compliance time and reduced
repetitive inspection intervals. This
proposed AD would also provide for an
optional modification that is
terminating action for the repetitive
inspections. These actions are specified
in a European Aviation Safety Agency
(EASA) AD, which will be incorporated
by reference. We are proposing this AD
to address the unsafe condition on these
products.
DATES: We must receive comments on
this proposed AD by August 5, 2019.
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.
SUMMARY:
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Federal Register / Vol. 84, No. 118 / Wednesday, June 19, 2019 / Proposed Rules
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE, Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE, Washington, DC 20590,
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For the material identified in this
proposed AD that will be incorporated
by reference (IBR), contact the EASA,
Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; telephone +49 221
89990 1000; email ADs@easa.europa.eu;
internet www.easa.europa.eu. You may
find this IBR material on the EASA
website at https://ad.easa.europa.eu.
You may view this IBR material at the
FAA, Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available in the AD docket on
the internet at https://
www.regulations.gov.
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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–2019–
0439; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this NPRM, the
regulatory evaluation, any comments
received, and other information. The
street address for Docket Operations is
listed above. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3229.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2019–0439; Product Identifier 2019–
NM–037–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this NPRM. We will consider
all comments received by the closing
date and may amend this NPRM based
on those comments.
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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 NPRM.
Discussion
We issued AD 2012–22–18,
Amendment 39–17256 (77 FR 70366,
November 26, 2012) (‘‘AD 2012–22–
18’’), for all Airbus SAS Model A330–
243, –243F, –341, –342, and –343
airplanes. AD 2012–22–18 requires
repetitive inspections of the three inner
acoustic panels of both engine air intake
cowls to detect disbonding, and
corrective actions if necessary. AD
2012–22–18 resulted from reports of
extensive damage to engine air intake
cowls as a result of acoustic panel
detachment. We issued AD 2012–22–18
to address disbonding, which could
result in detachment of the engine air
intake cowl from the engine leading to
ingestion of parts, which could cause
failure of the engine, and possible injury
to persons on the ground.
Actions Since AD 2012–22–18 Was
Issued
Since we issued AD 2012–22–18, we
have received additional reports of
engine air inlet cowl collapse and made
a determination that there should be a
reduction of the existing compliance
time and repetitive inspection intervals
required by AD 2012–22–18.
The EASA, which is the Technical
Agent for the Member States of the
European Union, has issued EASA AD
2019–0042, dated February 27, 2019
(‘‘EASA AD 2019–0042’’) (also referred
to as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for all Airbus SAS Model A330–243,
A330–243F, A330–341, A330–342 and
A330–343 airplanes. The MCAI states:
Occurrences were reported on A330
aeroplanes fitted with Rolls-Royce Trent 700
engines, where the air inlet cowl was found
with extensive damage, as a result of acoustic
panel collapse. The technical investigation
results revealed that these occurrences were
caused by panel disbonding.
This condition, if not detected and
corrected, could lead to in-flight detachment
of an air inlet cowl acoustic panel, possibly
resulting in damage to the aeroplane, and/or
in damage to the engine by ingestion of parts,
and/or injury to persons on the ground.
To initially address this potential unsafe
condition, Airbus published the inspection
[service bulletin] SB (original issue up to
Revision 03), to provide instructions for
[special detailed inspection] SDI of the three
acoustic panels of air inlet cowl.
Consequently, EASA issued AD 2011–0173
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[which corresponds to FAA AD 2012–22–18]
to require repetitive SDI of these air inlet
cowl acoustic panels on both engines.
Since that [EASA] AD was issued, Airbus
developed mod 202395, installation of
improved inner acoustic panels, and
published the modification SB, which
constitutes an optional terminating action for
the SDI. Consequently, EASA AD 2011–0173
was revised to introduce this optional
terminating action.
Since that revised [EASA] AD was issued,
new events of Rolls-Royce Trent 700 engines
air inlet cowl collapse have been reported.
These events only occurred on pre-mod
202395 engine air inlet cowls. Prompted by
these findings, Airbus performed new
calculations of the SDI threshold/interval
values and those of the Acceptable/
Repairable Damage Limits, leading to an
amended inspection programme.
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2011–0173R1, which is superseded, and
requires the SDI of affected parts at amended
threshold(s) and interval(s), and, depending
on findings, repair or replacement of affected
parts. This [EASA] AD also allows a postmod aeroplane to be modified, either
partially or completely, to pre-mod
configuration [which terminates the need for
the repetitive inspections].
The initial compliance time for the
special detailed inspection is within 12
months after an installation or
inspection, or 6 months after the
effective date of the AD, whichever
occurs later; but not to exceed 24
months since the last inspection. The
compliance times for the corrective
action are before further flight and
before 10 flight cycles since the last
inspection, depending on the condition.
The repetitive inspection interval is 12
months.
Explanation of Retained Requirements
Although this proposed AD does not
explicitly restate the requirements of AD
2012–22–18, this proposed AD would
retain all of the requirements of AD
2012–22–18, except the existing
compliance time and repetitive
inspection intervals are reduced. Those
requirements are referenced in EASA
AD 2019–0042, which, in turn, is
referenced in paragraph (g) of this
proposed AD.
Related IBR Material Under 1 CFR Part
51
EASA AD 2019–0042 describes
procedures for repetitive inspections of
engine air inlet cowls having certain
part numbers, repair or replacement of
any engine air inlet cowl that has
disbonding, and an optional
modification that terminates the need
for the repetitive inspections. This
material is reasonably available because
the interested parties have access to it
through their normal course of business
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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 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.
Proposed Requirements of This NPRM
This proposed AD would require
accomplishing the actions specified in
EASA AD 2019–0042 described
previously, as incorporated by
reference, except for any differences
identified as exceptions in the
regulatory text of this AD.
Explanation of Required Compliance
Information
In the FAA’s ongoing efforts to
improve the efficiency of the AD
process, the FAA worked with Airbus
and EASA to develop a process to use
certain EASA ADs as the primary source
of information for compliance with
requirements for corresponding FAA
ADs. As a result, EASA AD 2019–0042
will be incorporated by reference in the
28433
FAA final rule. This proposed AD
would, therefore, require compliance
with the provisions specified in EASA
AD 2019–0042, except for any
differences identified as exceptions in
the regulatory text of this proposed AD.
Service information specified in EASA
AD 2019–0042 that is required for
compliance with EASA AD 2019–0042
will be available on the internet https://
www.regulations.gov by searching for
and locating Docket No. FAA–2019–
0439 after the FAA final rule is
published.
Costs of Compliance
We estimate that this proposed AD
affects 47 airplanes of U.S. registry. We
estimate the following costs to comply
with this proposed AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS
Action
Labor cost
Retained actions from AD 2012–22–18 .....
Up to 20 work-hours × $85 per hour = Up
to $1,700.
Cost per
product
Parts cost
$0
Cost on U.S.
operators
$1,700
Up to $79,900.
ESTIMATED COSTS FOR OPTIONAL ACTIONS
Labor cost
Cost per
product
Parts cost
Up to 154 work hours × $85 per hour = Up to $13,090 .................................................................................
(*)
Up to $13,090.*
* We have received no definitive data on the parts costs for the optional actions.
We estimate the following costs to do
any necessary on-condition action that
would be required based on the results
of any required actions. We have no way
of determining the number of aircraft
that might need this on-condition
action:
ESTIMATED COSTS OF ON-CONDITION ACTIONS
Labor cost
Cost per
product
Parts cost
Up to 34 work-hours × $85 per hour = Up to $2,890 .....................................................................................
(*)
Up to $2,890.*
* We have received no definitive data on the parts costs for the on-condition actions.
The new requirements of this
proposed AD add no additional
economic burden. However, the
optional modification, if done, would
result in additional costs as specified in
the ‘‘Estimate costs for optional actions’’
table.
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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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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.
This proposed AD is issued in
accordance with authority delegated by
the Executive Director, Aircraft
PO 00000
Frm 00005
Fmt 4702
Sfmt 4702
Certification Service, as authorized by
FAA Order 8000.51C. In accordance
with that order, issuance of ADs is
normally a function of the Compliance
and Airworthiness Division, but during
this transition period, the Executive
Director has delegated the authority to
issue ADs applicable to transport
category airplanes and associated
appliances to the Director of the System
Oversight Division.
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
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Federal Register / Vol. 84, No. 118 / Wednesday, June 19, 2019 / Proposed Rules
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
removing Airworthiness Directive (AD)
2012–22–18, Amendment 39–17256 (77
FR 70366, November 26, 2012), and
adding the following new AD:
■
Airbus SAS: Docket No. FAA–2019–0439;
Product Identifier 2019–NM–037–AD.
(a) Comments Due Date
We must receive comments by August 5,
2019.
(b) Affected ADs
This AD replaces 2012–22–18, Amendment
39–17256 (77 FR 70366, November 26, 2012)
(‘‘AD 2012–22–18’’).
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(c) Applicability
This AD applies to all Airbus SAS Model
A330–243, –243F, –341, –342, and –343
airplanes, certificated in any category.
(d) Subject
Air Transport Association (ATA) of
America Code 71, Powerplant.
(e) Reason
This AD was prompted by reports of
extensive damage to engine air intake cowls
as a result of acoustic panel collapse. We are
issuing this AD to address disbonding, which
could result in detachment of the engine air
intake cowl from the engine, leading to
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ingestion of parts, which could cause failure
of the engine, and possible injury to persons
on the ground.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Requirements
Except as specified in paragraph (h) of this
AD: Comply with all required actions and
compliance times specified in, and in
accordance with, European Aviation Safety
Agency (EASA) AD 2019–0042, dated
February 27, 2019 (‘‘EASA AD 2019–0042’’).
(h) Exceptions to EASA AD 2019–0042
(1) For purposes of determining
compliance with the requirements of this AD:
Where EASA AD 2019–0042 refers to its
effective date, this AD requires using the
effective date of this AD.
(2) The ‘‘Remarks’’ section of EASA AD
2019–0042 does not apply to this AD.
(i) No Reporting Requirement
Although the service information
referenced in EASA AD 2019–0042 specifies
to submit certain information to the
manufacturer, this AD does not include that
requirement.
(j) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Section, Transport Standards Branch, 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 Section, send it
to the attention of the person identified in
paragraph (k)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@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 instructions
from a manufacturer, the instructions must
be accomplished using a method approved
by the Manager, International Section,
Transport Standards Branch, FAA; or EASA;
or Airbus SAS’s EASA Design Organization
Approval (DOA). If approved by the DOA,
the approval must include the DOAauthorized signature.
(3) Required for Compliance (RC): For any
service information referenced in EASA AD
2019–0042 that contains RC procedures and
tests: Except as required by paragraph (j)(2)
of this AD, RC 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
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Sfmt 4702
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.
(k) Related Information
(1) For information about EASA AD 2019–
0042, contact the EASA, Konrad-AdenauerUfer 3, 50668 Cologne, Germany; telephone
+49 221 89990 6017; email ADs@
easa.europa.eu; Internet
www.easa.europa.eu. You may find this
EASA AD on the EASA website at https://
ad.easa.europa.eu. You may view this EASA
AD at the FAA, Transport Standards Branch,
2200 South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
EASA AD 2019–0042 may be found in the
AD docket on the internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2019–0439.
(2) For more information about this AD,
contact Vladimir Ulyanov, Aerospace
Engineer, International Section, Transport
Standards Branch, FAA, 2200 South 216th
St., Des Moines, WA 98198; telephone and
fax 206–231–3229.
Issued in Des Moines, Washington, on June
10, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–12877 Filed 6–18–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2019–0431; Airspace
Docket No. 19–ASO–9]
RIN 2120–AA66
Proposed Amendment of VOR Federal
Airway V–159 in the Vicinity of
Hamilton, AL
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
This action proposes to
modify VHF Omnidirectional Range
(VOR) Federal airway V–159 due to the
planned decommissioning of the
Hamilton, AL, VORTAC navigation aid
which provides navigation guidance for
a segment of the route. The Hamilton
VORTAC is being decommissioned as
part of the FAA’s VOR Minimum
Operational Network (MON) program.
DATES: Comments must be received on
or before August 5, 2019.
ADDRESSES: Send comments on this
proposal to the U.S. Department of
SUMMARY:
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]]>Agencies
[Federal Register Volume 84, Number 118 (Wednesday, June 19, 2019)]
[Proposed Rules]
[Pages 28431-28434]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-12877]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0439; Product Identifier 2019-NM-037-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2012-22-
18, which applies to all Airbus SAS Model A330-243, -243F, -341, -342,
and -343 airplanes. AD 2012-22-18 requires repetitive inspections of
the three inner acoustic panels of both engine air intake cowls to
detect disbonding, and corrective actions if necessary. Since we issued
AD 2012-22-18, we have received additional reports of engine air inlet
cowl collapse. This proposed AD would retain the requirements of AD
2012-22-18 with a reduced compliance time and reduced repetitive
inspection intervals. This proposed AD would also provide for an
optional modification that is terminating action for the repetitive
inspections. These actions are specified in a European Aviation Safety
Agency (EASA) AD, which will be incorporated by reference. We are
proposing this AD to address the unsafe condition on these products.
DATES: We must receive comments on this proposed AD by August 5, 2019.
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.
[[Page 28432]]
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For the material identified in this proposed AD that will be
incorporated by reference (IBR), contact the EASA, Konrad-Adenauer-Ufer
3, 50668 Cologne, Germany; telephone +49 221 89990 1000; email
[email protected]; internet www.easa.europa.eu. You may find this IBR
material on the EASA website at https://ad.easa.europa.eu. You may view
this IBR material at the FAA, Transport Standards Branch, 2200 South
216th St., Des Moines, WA. For information on the availability of this
material at the FAA, call 206-231-3195. It is also available in the AD
docket on the internet at https://www.regulations.gov.
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-2019-
0439; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this NPRM, the regulatory evaluation, any comments received, and other
information. The street address for Docket Operations is listed above.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; telephone and fax 206-231-3229.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2019-0439;
Product Identifier 2019-NM-037-AD'' at the beginning of your comments.
We specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this NPRM. We will consider all
comments received by the closing date and may amend this NPRM 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 NPRM.
Discussion
We issued AD 2012-22-18, Amendment 39-17256 (77 FR 70366, November
26, 2012) (``AD 2012-22-18''), for all Airbus SAS Model A330-243, -
243F, -341, -342, and -343 airplanes. AD 2012-22-18 requires repetitive
inspections of the three inner acoustic panels of both engine air
intake cowls to detect disbonding, and corrective actions if necessary.
AD 2012-22-18 resulted from reports of extensive damage to engine air
intake cowls as a result of acoustic panel detachment. We issued AD
2012-22-18 to address disbonding, which could result in detachment of
the engine air intake cowl from the engine leading to ingestion of
parts, which could cause failure of the engine, and possible injury to
persons on the ground.
Actions Since AD 2012-22-18 Was Issued
Since we issued AD 2012-22-18, we have received additional reports
of engine air inlet cowl collapse and made a determination that there
should be a reduction of the existing compliance time and repetitive
inspection intervals required by AD 2012-22-18.
The EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2019-0042, dated February 27, 2019
(``EASA AD 2019-0042'') (also referred to as the Mandatory Continuing
Airworthiness Information, or ``the MCAI''), to correct an unsafe
condition for all Airbus SAS Model A330-243, A330-243F, A330-341, A330-
342 and A330-343 airplanes. The MCAI states:
Occurrences were reported on A330 aeroplanes fitted with Rolls-
Royce Trent 700 engines, where the air inlet cowl was found with
extensive damage, as a result of acoustic panel collapse. The
technical investigation results revealed that these occurrences were
caused by panel disbonding.
This condition, if not detected and corrected, could lead to in-
flight detachment of an air inlet cowl acoustic panel, possibly
resulting in damage to the aeroplane, and/or in damage to the engine
by ingestion of parts, and/or injury to persons on the ground.
To initially address this potential unsafe condition, Airbus
published the inspection [service bulletin] SB (original issue up to
Revision 03), to provide instructions for [special detailed
inspection] SDI of the three acoustic panels of air inlet cowl.
Consequently, EASA issued AD 2011-0173 [which corresponds to FAA AD
2012-22-18] to require repetitive SDI of these air inlet cowl
acoustic panels on both engines.
Since that [EASA] AD was issued, Airbus developed mod 202395,
installation of improved inner acoustic panels, and published the
modification SB, which constitutes an optional terminating action
for the SDI. Consequently, EASA AD 2011-0173 was revised to
introduce this optional terminating action.
Since that revised [EASA] AD was issued, new events of Rolls-
Royce Trent 700 engines air inlet cowl collapse have been reported.
These events only occurred on pre-mod 202395 engine air inlet cowls.
Prompted by these findings, Airbus performed new calculations of the
SDI threshold/interval values and those of the Acceptable/Repairable
Damage Limits, leading to an amended inspection programme.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2011-0173R1, which is superseded, and
requires the SDI of affected parts at amended threshold(s) and
interval(s), and, depending on findings, repair or replacement of
affected parts. This [EASA] AD also allows a post-mod aeroplane to
be modified, either partially or completely, to pre-mod
configuration [which terminates the need for the repetitive
inspections].
The initial compliance time for the special detailed inspection is
within 12 months after an installation or inspection, or 6 months after
the effective date of the AD, whichever occurs later; but not to exceed
24 months since the last inspection. The compliance times for the
corrective action are before further flight and before 10 flight cycles
since the last inspection, depending on the condition. The repetitive
inspection interval is 12 months.
Explanation of Retained Requirements
Although this proposed AD does not explicitly restate the
requirements of AD 2012-22-18, this proposed AD would retain all of the
requirements of AD 2012-22-18, except the existing compliance time and
repetitive inspection intervals are reduced. Those requirements are
referenced in EASA AD 2019-0042, which, in turn, is referenced in
paragraph (g) of this proposed AD.
Related IBR Material Under 1 CFR Part 51
EASA AD 2019-0042 describes procedures for repetitive inspections
of engine air inlet cowls having certain part numbers, repair or
replacement of any engine air inlet cowl that has disbonding, and an
optional modification that terminates the need for the repetitive
inspections. This material is reasonably available because the
interested parties have access to it through their normal course of
business
[[Page 28433]]
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 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.
Proposed Requirements of This NPRM
This proposed AD would require accomplishing the actions specified
in EASA AD 2019-0042 described previously, as incorporated by
reference, except for any differences identified as exceptions in the
regulatory text of this AD.
Explanation of Required Compliance Information
In the FAA's ongoing efforts to improve the efficiency of the AD
process, the FAA worked with Airbus and EASA to develop a process to
use certain EASA ADs as the primary source of information for
compliance with requirements for corresponding FAA ADs. As a result,
EASA AD 2019-0042 will be incorporated by reference in the FAA final
rule. This proposed AD would, therefore, require compliance with the
provisions specified in EASA AD 2019-0042, except for any differences
identified as exceptions in the regulatory text of this proposed AD.
Service information specified in EASA AD 2019-0042 that is required for
compliance with EASA AD 2019-0042 will be available on the internet
https://www.regulations.gov by searching for and locating Docket No.
FAA-2019-0439 after the FAA final rule is published.
Costs of Compliance
We estimate that this proposed AD affects 47 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
Estimated Costs for Required Actions
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Cost per
Action Labor cost Parts cost product Cost on U.S. operators
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Retained actions from AD 2012- Up to 20 work- $0 $1,700 Up to $79,900.
22-18. hours x $85 per
hour = Up to
$1,700.
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Estimated Costs for Optional Actions
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Labor cost Parts cost Cost per product
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Up to 154 work hours x $85 (*) Up to $13,090.*
per hour = Up to $13,090.
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* We have received no definitive data on the parts costs for the
optional actions.
We estimate the following costs to do any necessary on-condition
action that would be required based on the results of any required
actions. We have no way of determining the number of aircraft that
might need this on-condition action:
Estimated Costs of On-Condition Actions
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Labor cost Parts cost Cost per product
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Up to 34 work-hours x $85 per (*) Up to $2,890.*
hour = Up to $2,890.
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* We have received no definitive data on the parts costs for the on-
condition actions.
The new requirements of this proposed AD add no additional economic
burden. However, the optional modification, if done, would result in
additional costs as specified in the ``Estimate costs for optional
actions'' table.
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.
This proposed AD is issued in accordance with authority delegated
by the Executive Director, Aircraft Certification Service, as
authorized by FAA Order 8000.51C. In accordance with that order,
issuance of ADs is normally a function of the Compliance and
Airworthiness Division, but during this transition period, the
Executive Director has delegated the authority to issue ADs applicable
to transport category airplanes and associated appliances to the
Director of the System Oversight Division.
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
[[Page 28434]]
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 removing Airworthiness Directive (AD)
2012-22-18, Amendment 39-17256 (77 FR 70366, November 26, 2012), and
adding the following new AD:
Airbus SAS: Docket No. FAA-2019-0439; Product Identifier 2019-NM-
037-AD.
(a) Comments Due Date
We must receive comments by August 5, 2019.
(b) Affected ADs
This AD replaces 2012-22-18, Amendment 39-17256 (77 FR 70366,
November 26, 2012) (``AD 2012-22-18'').
(c) Applicability
This AD applies to all Airbus SAS Model A330-243, -243F, -341, -
342, and -343 airplanes, certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 71, Powerplant.
(e) Reason
This AD was prompted by reports of extensive damage to engine
air intake cowls as a result of acoustic panel collapse. We are
issuing this AD to address disbonding, which could result in
detachment of the engine air intake cowl from the engine, leading to
ingestion of parts, which could cause failure of the engine, and
possible injury to persons on the ground.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Requirements
Except as specified in paragraph (h) of this AD: Comply with all
required actions and compliance times specified in, and in
accordance with, European Aviation Safety Agency (EASA) AD 2019-
0042, dated February 27, 2019 (``EASA AD 2019-0042'').
(h) Exceptions to EASA AD 2019-0042
(1) For purposes of determining compliance with the requirements
of this AD: Where EASA AD 2019-0042 refers to its effective date,
this AD requires using the effective date of this AD.
(2) The ``Remarks'' section of EASA AD 2019-0042 does not apply
to this AD.
(i) No Reporting Requirement
Although the service information referenced in EASA AD 2019-0042
specifies to submit certain information to the manufacturer, this AD
does not include that requirement.
(j) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Section, Transport Standards Branch, 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 Section, send it to the attention of
the person identified in paragraph (k)(2) of this AD. Information
may be emailed to: [email protected]. 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 instructions from a manufacturer, the instructions must be
accomplished using a method approved by the Manager, International
Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's
EASA Design Organization Approval (DOA). If approved by the DOA, the
approval must include the DOA-authorized signature.
(3) Required for Compliance (RC): For any service information
referenced in EASA AD 2019-0042 that contains RC procedures and
tests: Except as required by paragraph (j)(2) of this AD, RC
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.
(k) Related Information
(1) For information about EASA AD 2019-0042, contact the EASA,
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221
89990 6017; email [email protected]; Internet www.easa.europa.eu.
You may find this EASA AD on the EASA website at https://ad.easa.europa.eu. You may view this EASA AD at the FAA, Transport
Standards Branch, 2200 South 216th St., Des Moines, WA. For
information on the availability of this material at the FAA, call
206-231-3195. EASA AD 2019-0042 may be found in the AD docket on the
internet at https://www.regulations.gov by searching for and locating
Docket No. FAA-2019-0439.
(2) For more information about this AD, contact Vladimir
Ulyanov, Aerospace Engineer, International Section, Transport
Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198;
telephone and fax 206-231-3229.
Issued in Des Moines, Washington, on June 10, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-12877 Filed 6-18-19; 8:45 am]
BILLING CODE 4910-13-P
