Airworthiness Directives; Airbus SAS Airplanes, 19881-19885 [2019-09264]
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Federal Register / Vol. 84, No. 88 / Tuesday, May 7, 2019 / Proposed Rules
effective date, this AD requires using the
effective date of this AD.
(2) The ‘‘Remarks’’ section of EASA AD
2019–0081 does not apply to this AD.
Branch, FAA, 2200 South 216th St., Des
Moines, WA 98198; telephone and fax 206–
231–3223.
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(i) 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 (j)(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
2019–0081 that contains RC procedures and
tests: Except as required by paragraphs (h)(1)
and (h)(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.
(j) Related Information
(1) For information about EASA AD 2019–
0081, 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 2019–0081 may be found in the
AD docket on the internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2019–0251.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards
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Issued in Des Moines, Washington, on
April 25, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–09256 Filed 5–6–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0257; Product
Identifier 2018–NM–175–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) 2018–20–
06, which applies to certain Airbus SAS
Model A300 F4–600R series airplanes.
AD 2018–20–06 requires repetitive high
frequency eddy current (HFEC)
inspections of the aft lower deck cargo
door (LDCD) frame forks; a one-time
check of the LDCD clearances; and a
one-time detailed visual inspection of
hooks, eccentric bushes, and x-stops;
and corrective actions if necessary.
Since we issued AD 2018–20–06, we
determined certain compliance times
need to be revised, depending on frame
fork configuration. This proposed AD
would continue to require the actions of
AD 2018–20–06 and would require new
compliance times, depending on frame
fork configuration. We are proposing
this AD to address the unsafe condition
on these products.
DATES: We must receive comments on
this proposed AD by June 21, 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.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
SUMMARY:
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19881
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Airbus SAS,
Airworthiness Office—EAW, RondPoint Emile Dewoitine No: 2, 31700
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
Standards Branch, 2200 South 216th St.,
Des Moines, WA. For information on the
availability of this material at the FAA,
call 206–231–3195.
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–
0257; 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
(phone 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 Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3225.
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–
2019–0257; Product Identifier 2018–
NM–175–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
We issued AD 2018–20–06,
Amendment 39–19440 (83 FR 49265,
October 1, 2018) (‘‘AD 2018–20–06’’),
for certain Airbus SAS Model A300 F4–
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Federal Register / Vol. 84, No. 88 / Tuesday, May 7, 2019 / Proposed Rules
600R series airplanes. AD 2018–20–06
requires repetitive HFEC inspections of
the aft LDCD frame forks; a one-time
check of the LDCD clearances; and a
one-time detailed visual inspection of
hooks, eccentric bushes, and x-stops;
and corrective actions if necessary. AD
2018–20–06 resulted from a report of
two adjacent frame forks that were
found cracked on the aft LDCD of two
airplanes during scheduled
maintenance, and the introduction of
frame fork reinforcement or repair
procedures that, when done, allow an
extension of repetitive inspection
intervals. We issued AD 2018–20–06 to
address cracked or ruptured aft LDCD
frames, which could allow loads to be
transferred to the remaining structural
elements. This condition could lead to
the rupture of one or more vertical aft
LDCD frames, which could result in
reduced structural integrity of the aft
LDCD.
Actions Since AD 2018–20–06 Was
Issued
Since we issued AD 2018–20–06, we
have determined that certain
compliance times need to be reduced,
depending on the frame fork
configuration. In addition, certain
compliance times are extended.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2018–0266,
dated December 11, 2018 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Airbus SAS Model A300 F4–
600R series airplanes. The MCAI states:
During scheduled maintenance at frames
(FR) 61 and FR61A on the aft lower deck
cargo door (LDCD) of two [Airbus SAS]
A300–600F4 aeroplanes, two adjacent frame
forks were found cracked. Subsequent
analysis determined that, in case of cracked
or ruptured aft cargo door frame(s), loads will
be transferred to the remaining structural
elements. However, these secondary load
paths will be able to sustain the loads for a
limited number of flight cycles (FC) only.
This condition, if not detected and
corrected, could lead to the rupture of one or
more vertical aft cargo door frame(s),
resulting in reduced structural integrity of
the aft cargo door.
To address this unsafe condition, Airbus
issued Alert Operators Transmission (AOT)
A52W011–15 to provide inspection
instructions, and, consequently, EASA issued
AD 2015–0152 to require repetitive
inspections of the aft LDCD frame forks and,
depending on findings, the accomplishment
of applicable corrective action(s).
Subsequently, Airbus published the
modification SB [service bulletin] to provide
frame fork reinforcement instructions, and
the inspection SB to provide instructions to
inspect the cargo door for cracks, as well as
for frame fork replacement, including
provisions for extended inspection intervals.
EASA revised the AD accordingly.
Since EASA AD 2015–0152R1 [which
corresponds to FAA AD 2018–20–06] was
issued, further investigations results allowed
Airbus to define new thresholds and
inspection intervals according to the frame
fork configuration. Consequently, the
inspection SB was revised to include these
new thresholds and intervals.
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2015–0152R1, which is superseded, and
introduces new thresholds and intervals,
depending on frame fork configuration.
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–2019–
0257.
Related Service Information Under 1
CFR Part 51
This proposed AD would require
Airbus Alert Operators Transmission
A52W011–15, Revision 00, including
Appendices 1, 2, 3, and 4, dated July 23,
2015, which the Director of the Federal
Register approved for incorporation by
reference as of January 26, 2017 (81 FR
93801, December 22, 2016).
This proposed AD would also require
Airbus Service Bulletin A300–52–6085,
Revision 01, dated May 2, 2018; and
Airbus Service Bulletin A300–52–6086,
Revision 01, dated May 29, 2018; which
the Director of the Federal Register
approved for incorporation by reference
as of November 5, 2018 (83 FR 49265,
October 1, 2018).
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
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 the
relevant information and determined
the unsafe condition described
previously is likely to exist or develop
on other products of the same type
design.
Proposed Requirements of This NPRM
This proposed AD would retain the
actions of AD 2018–20–06. This
proposed AD would require
accomplishing the actions specified in
the service information described
previously.
Costs of Compliance
We estimate that this proposed AD
affects 58 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 2018–20–06 .........
17 work-hours × $85 per hour = $1,445 ........
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The new requirements of this
proposed AD add no additional
economic burden.
Cost per
product
Parts cost
We estimate the following costs to do
any necessary on-condition actions that
would be required based on the results
of any required actions. We have no way
$0
Cost on
U.S. operators
$1,445
of determining the number of aircraft
that might need these on-condition
actions:
ESTIMATED COSTS OF ON-CONDITION ACTIONS
Labor cost
Parts cost
Up to 65 work-hours × $85 per hour = $5,525 .......................................
Up to $10,000 ................................
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$83,810
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Cost per product
Up to $15,525.
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Federal Register / Vol. 84, No. 88 / Tuesday, May 7, 2019 / Proposed Rules
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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
(h) Retained Inspection Requirements and
On-Condition Actions, With Revised
Compliance Language
This paragraph restates the requirements of
paragraph (g) of AD 2018–20–06, with
revised compliance language. At the
applicable time specified in paragraph (i) of
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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.
(a) Comments Due Date
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Air Transport Association (ATA) of
America Code 52, Doors.
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)
2018–20–06, Amendment 39–19440 (83
FR 49265, October 1, 2018), and adding
the following new AD:
■
We must receive comments by June 21,
2019.
(b) Affected ADs
This AD replaces 2018–20–06, Amendment
39–19440 (83 FR 49265, October 1, 2018)
(‘‘AD 2018–20–06’’).
(c) Applicability
This AD applies to Airbus SAS Model
A300 F4–605R and F4–622R airplanes,
certificated in any category, on which Airbus
modification 12046 has been embodied in
production. Modification 12046 has been
embodied in production on manufacturer
serial numbers (MSNs) 0805 and above,
except MSNs 0836, 0837, and 0838.
(d) Subject
(e) Reason
This AD was prompted by a report of two
adjacent frame forks that were found cracked
on the aft lower deck cargo door (LDCD) of
two airplanes during scheduled maintenance,
and a determination that certain compliance
times need to be revised. We are issuing this
AD to address cracked or ruptured aft LDCD
frames, which could allow loads to be
transferred to the remaining structural
elements. This condition could lead to the
rupture of one or more vertical aft LDCD
frames, which could result in reduced
structural integrity of the aft LDCD.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) New Affected Part Definition
Airbus SAS: Docket No. FAA–2019–0257;
Product Identifier 2018–NM–175–AD.
For the purposes of this AD, an affected
part is a frame fork having a part number
identified in figure 1 to paragraph (g) of this
AD.
this AD, or before exceeding the threshold
defined in figure 2 to paragraph (h) of this
AD, whichever occurs later: Do the actions
specified in paragraphs (h)(1), (h)(2), and
(h)(3) of this AD. Repeat the high frequency
eddy current (HFEC) inspection specified in
paragraph (h)(3) of this AD at all LDCD frame
fork stations having affected parts thereafter
at intervals not to exceed the applicable
times specified in figure 2 to paragraph (h)
of this AD.
(1) A one-time check of the aft LDCD
clearances ‘‘U’’ and ‘‘V’’ between the latching
hooks and the eccentric bush at frame (FR)
60 through FR64A, in accordance with the
instructions of Airbus Alert Operators
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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.
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.
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Transmission A52W011–15, Revision 00,
dated July 23, 2015; or the Accomplishment
Instructions of Airbus Service Bulletin A300–
52–6086, Revision 01, dated May 29, 2018. If
any value outside tolerance is found, adjust
the latching hook before further flight, in
accordance with the instructions of Airbus
Alert Operators Transmission A52W011–15,
Revision 00, dated July 23, 2015; or the
Accomplishment Instructions of Airbus
Service Bulletin A300–52–6086, Revision 01,
dated May 29, 2018.
(2) A one-time detailed inspection to detect
signs of wear of the hooks, eccentric bushes,
and x-stops, in accordance with the
instructions of Airbus Alert Operators
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Transmission A52W011–15, Revision 00,
dated July 23, 2015. If any wear is found, do
all applicable corrective actions before
further flight, in accordance with the
instructions of Airbus Alert Operators
Transmission A52W011–15, Revision 00,
dated July 23, 2015.
(3) An HFEC inspection to detect cracking
at all frame fork stations of the aft LDCD, in
accordance with the instructions of Airbus
Alert Operators Transmission A52W011–15,
Revision 00, dated July 23, 2015; or the
Accomplishment Instructions of Airbus
Service Bulletin A300–52–6086, Revision 01,
dated May 29, 2018. If any crack is found,
before further flight, replace the cracked
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frame fork, in accordance with the
instructions of Airbus Alert Operators
Transmission A52W011–15, Revision 00,
dated July 23, 2015; repair the cracked frame
fork, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–52–6086, Revision 01,
dated May 29, 2018; or modify (reinforce) the
cracked frame fork, including doing all
applicable related investigative and
corrective actions, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–52–6085, Revision 01,
dated May 2, 2018, except as required by
paragraph (j) of this AD.
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(i) Retained Compliance Times, With No
Changes
At the later of the times specified in
paragraphs (i)(1) and (i)(2) of this AD, do the
actions required by paragraph (h) of this AD.
(1) Before the accumulation of 4,500 total
flight cycles.
(2) At the applicable time specified by
paragraph (i)(2)(i) or (i)(2)(ii) of this AD.
(i) For airplanes that have accumulated
8,000 or more total flight cycles as of January
26, 2017 (the effective date of AD 2016–25–
03, Amendment 39–18729 (81 FR 93801,
December 22, 2016) (‘‘AD 2016–25–03’’)):
Within 100 flight cycles after January 26,
2017.
(ii) For airplanes that have accumulated
fewer than 8,000 total flight cycles as of
January 26, 2017 (the effective date of AD
2016–25–03): Within 400 flight cycles after
January 26, 2017.
(j) Service Information Exception
Where Airbus Service Bulletin A300–52–
6085, Revision 01, dated May 2, 2018,
specifies to contact Airbus for appropriate
action: Before further flight, accomplish
corrective actions in accordance with the
procedures specified in paragraph (n)(2) of
this AD.
(k) No Terminating Action
Accomplishment of corrective actions on
an airplane as required by paragraph (h)(1) or
(h)(2) of this AD, or repair, modification, or
replacement of a frame fork as required by
paragraph (h)(3) of this AD, on the aft LDCD
of an airplane does not constitute terminating
action for the repetitive HFEC inspections
required by paragraph (h)(3) of this AD for
that airplane.
(l) No Reporting
Although the Accomplishment Instructions
of Airbus Alert Operators Transmission
A52W011–15, Revision 00, dated July 23,
2015; and Airbus Service Bulletin A300–52–
6086, Revision 01, dated May 29, 2018;
specify to submit certain information to the
manufacturer, this AD does not include that
requirement.
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(m) Credit for Previous Actions
(1) This paragraph provides credit for
actions required by paragraphs (h)(1) and
(h)(3) of this AD, if those actions were
performed before the effective date of this AD
using Airbus Service Bulletin A300–52–6086,
Revision 00, dated December 25, 2016.
(2) This paragraph provides credit for
actions required by paragraph (h)(3) of this
AD, if those actions were performed before
the effective date of this AD using Airbus
Service Bulletin A300–52–6085, Revision 00,
dated December 22, 2016.
(n) Other FAA AD Provisions
(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
VerDate Sep<11>2014
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Jkt 247001
directly to the International Section, send it
to the attention of the person identified in
paragraph (o)(2) of this AD. Information may
be emailed to 9-ANM-116-AMOCREQUESTS@faa.gov.
(i) 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.
(ii) AMOCs approved previously for AD
2018–20–06 are approved as AMOCs for the
corresponding provisions of this AD.
(2) Contacting the Manufacturer: As of the
effective date 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 Section, Transport
Standards Branch, FAA; or the European
Aviation Safety Agency (EASA); or Airbus
SAS’s EASA Design Organization Approval
(DOA). If approved by the DOA, the approval
must include the DOA-authorized signature.
(o) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2018–0266, dated December 11, 2018, 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–2019–0257.
(2) For more information about this AD,
contact Dan Rodina, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des
Moines, WA 98198; telephone and fax 206–
231–3225.
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAW, Rond-Point Emile Dewoitine
No: 2, 31700 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 Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
Issued in Des Moines, Washington, on
April 25, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–09264 Filed 5–6–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0258; Product
Identifier 2018–NM–134–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), DOT.
AGENCY:
PO 00000
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19885
Notice of proposed rulemaking
(NPRM).
ACTION:
We propose to supersede
Airworthiness Directive (AD) 96–25–04,
which applies to certain Airbus SAS
Model A320 series airplanes. AD 96–
25–04 requires repetitive inspections to
detect chafing of the wire looms
(bundles) in the wing and the horizontal
stabilizer and in certain areas of the
main landing gear (MLG) bays; repair or
replacement, protection, and
realignment, if necessary; installation of
protective sleeves around the wire
bundles; and realignment of bundles
that are not guided centrally into the
conduit end fittings. Since we issued
AD 96–25–04, investigations identified
issues with the previously installed
protective sleeves. This proposed AD
would partially retain the requirements
of AD 96–25–04 and would require
modification of the wing electrical
installation, as specified in an 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 June 21, 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.
• 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 incorporation by reference
(IBR) material described in the ‘‘Related
IBR material under 1 CFR part 51’’
section in SUPPLEMENTARY INFORMATION,
contact 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
SUMMARY:
E:\FR\FM\07MYP1.SGM
07MYP1
Agencies
[Federal Register Volume 84, Number 88 (Tuesday, May 7, 2019)]
[Proposed Rules]
[Pages 19881-19885]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-09264]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0257; Product Identifier 2018-NM-175-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2018-20-
06, which applies to certain Airbus SAS Model A300 F4-600R series
airplanes. AD 2018-20-06 requires repetitive high frequency eddy
current (HFEC) inspections of the aft lower deck cargo door (LDCD)
frame forks; a one-time check of the LDCD clearances; and a one-time
detailed visual inspection of hooks, eccentric bushes, and x-stops; and
corrective actions if necessary. Since we issued AD 2018-20-06, we
determined certain compliance times need to be revised, depending on
frame fork configuration. This proposed AD would continue to require
the actions of AD 2018-20-06 and would require new compliance times,
depending on frame fork configuration. We are proposing this AD to
address the unsafe condition on these products.
DATES: We must receive comments on this proposed AD by June 21, 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.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact Airbus
SAS, Airworthiness Office--EAW, Rond-Point Emile Dewoitine No: 2, 31700
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44
51; email [email protected]; internet https://www.airbus.com. You may view this referenced 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.
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-
0257; 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 (phone 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 Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; telephone and fax 206-231-3225.
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-2019-0257;
Product Identifier 2018-NM-175-AD'' at the beginning of your comments.
We specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this proposed AD. We will consider
all comments received by the closing date and may amend this proposed
AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We issued AD 2018-20-06, Amendment 39-19440 (83 FR 49265, October
1, 2018) (``AD 2018-20-06''), for certain Airbus SAS Model A300 F4-
[[Page 19882]]
600R series airplanes. AD 2018-20-06 requires repetitive HFEC
inspections of the aft LDCD frame forks; a one-time check of the LDCD
clearances; and a one-time detailed visual inspection of hooks,
eccentric bushes, and x-stops; and corrective actions if necessary. AD
2018-20-06 resulted from a report of two adjacent frame forks that were
found cracked on the aft LDCD of two airplanes during scheduled
maintenance, and the introduction of frame fork reinforcement or repair
procedures that, when done, allow an extension of repetitive inspection
intervals. We issued AD 2018-20-06 to address cracked or ruptured aft
LDCD frames, which could allow loads to be transferred to the remaining
structural elements. This condition could lead to the rupture of one or
more vertical aft LDCD frames, which could result in reduced structural
integrity of the aft LDCD.
Actions Since AD 2018-20-06 Was Issued
Since we issued AD 2018-20-06, we have determined that certain
compliance times need to be reduced, depending on the frame fork
configuration. In addition, certain compliance times are extended.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2018-0266, dated December 11, 2018 (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to
correct an unsafe condition for certain Airbus SAS Model A300 F4-600R
series airplanes. The MCAI states:
During scheduled maintenance at frames (FR) 61 and FR61A on the
aft lower deck cargo door (LDCD) of two [Airbus SAS] A300-600F4
aeroplanes, two adjacent frame forks were found cracked. Subsequent
analysis determined that, in case of cracked or ruptured aft cargo
door frame(s), loads will be transferred to the remaining structural
elements. However, these secondary load paths will be able to
sustain the loads for a limited number of flight cycles (FC) only.
This condition, if not detected and corrected, could lead to the
rupture of one or more vertical aft cargo door frame(s), resulting
in reduced structural integrity of the aft cargo door.
To address this unsafe condition, Airbus issued Alert Operators
Transmission (AOT) A52W011-15 to provide inspection instructions,
and, consequently, EASA issued AD 2015-0152 to require repetitive
inspections of the aft LDCD frame forks and, depending on findings,
the accomplishment of applicable corrective action(s). Subsequently,
Airbus published the modification SB [service bulletin] to provide
frame fork reinforcement instructions, and the inspection SB to
provide instructions to inspect the cargo door for cracks, as well
as for frame fork replacement, including provisions for extended
inspection intervals. EASA revised the AD accordingly.
Since EASA AD 2015-0152R1 [which corresponds to FAA AD 2018-20-
06] was issued, further investigations results allowed Airbus to
define new thresholds and inspection intervals according to the
frame fork configuration. Consequently, the inspection SB was
revised to include these new thresholds and intervals.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2015-0152R1, which is superseded, and
introduces new thresholds and intervals, depending on frame fork
configuration.
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-2019-
0257.
Related Service Information Under 1 CFR Part 51
This proposed AD would require Airbus Alert Operators Transmission
A52W011-15, Revision 00, including Appendices 1, 2, 3, and 4, dated
July 23, 2015, which the Director of the Federal Register approved for
incorporation by reference as of January 26, 2017 (81 FR 93801,
December 22, 2016).
This proposed AD would also require Airbus Service Bulletin A300-
52-6085, Revision 01, dated May 2, 2018; and Airbus Service Bulletin
A300-52-6086, Revision 01, dated May 29, 2018; which the Director of
the Federal Register approved for incorporation by reference as of
November 5, 2018 (83 FR 49265, October 1, 2018).
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
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 the relevant information and determined the unsafe
condition described previously is likely to exist or develop on other
products of the same type design.
Proposed Requirements of This NPRM
This proposed AD would retain the actions of AD 2018-20-06. This
proposed AD would require accomplishing the actions specified in the
service information described previously.
Costs of Compliance
We estimate that this proposed AD affects 58 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2018-20-06... 17 work-hours x $85 per $0 $1,445 $83,810
hour = $1,445.
----------------------------------------------------------------------------------------------------------------
The new requirements of this proposed AD add no additional economic
burden.
We estimate the following costs to do any necessary on-condition
actions 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 these on-condition actions:
Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
Labor cost Parts cost Cost per product
------------------------------------------------------------------------
Up to 65 work-hours x $85 per Up to $10,000..... Up to $15,525.
hour = $5,525.
------------------------------------------------------------------------
[[Page 19883]]
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 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)
2018-20-06, Amendment 39-19440 (83 FR 49265, October 1, 2018), and
adding the following new AD:
Airbus SAS: Docket No. FAA-2019-0257; Product Identifier 2018-NM-
175-AD.
(a) Comments Due Date
We must receive comments by June 21, 2019.
(b) Affected ADs
This AD replaces 2018-20-06, Amendment 39-19440 (83 FR 49265,
October 1, 2018) (``AD 2018-20-06'').
(c) Applicability
This AD applies to Airbus SAS Model A300 F4-605R and F4-622R
airplanes, certificated in any category, on which Airbus
modification 12046 has been embodied in production. Modification
12046 has been embodied in production on manufacturer serial numbers
(MSNs) 0805 and above, except MSNs 0836, 0837, and 0838.
(d) Subject
Air Transport Association (ATA) of America Code 52, Doors.
(e) Reason
This AD was prompted by a report of two adjacent frame forks
that were found cracked on the aft lower deck cargo door (LDCD) of
two airplanes during scheduled maintenance, and a determination that
certain compliance times need to be revised. We are issuing this AD
to address cracked or ruptured aft LDCD frames, which could allow
loads to be transferred to the remaining structural elements. This
condition could lead to the rupture of one or more vertical aft LDCD
frames, which could result in reduced structural integrity of the
aft LDCD.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) New Affected Part Definition
For the purposes of this AD, an affected part is a frame fork
having a part number identified in figure 1 to paragraph (g) of this
AD.
[GRAPHIC] [TIFF OMITTED] TP07MY19.000
(h) Retained Inspection Requirements and On-Condition Actions, With
Revised Compliance Language
This paragraph restates the requirements of paragraph (g) of AD
2018-20-06, with revised compliance language. At the applicable time
specified in paragraph (i) of this AD, or before exceeding the
threshold defined in figure 2 to paragraph (h) of this AD, whichever
occurs later: Do the actions specified in paragraphs (h)(1), (h)(2),
and (h)(3) of this AD. Repeat the high frequency eddy current (HFEC)
inspection specified in paragraph (h)(3) of this AD at all LDCD
frame fork stations having affected parts thereafter at intervals
not to exceed the applicable times specified in figure 2 to
paragraph (h) of this AD.
(1) A one-time check of the aft LDCD clearances ``U'' and ``V''
between the latching hooks and the eccentric bush at frame (FR) 60
through FR64A, in accordance with the instructions of Airbus Alert
Operators
[[Page 19884]]
Transmission A52W011-15, Revision 00, dated July 23, 2015; or the
Accomplishment Instructions of Airbus Service Bulletin A300-52-6086,
Revision 01, dated May 29, 2018. If any value outside tolerance is
found, adjust the latching hook before further flight, in accordance
with the instructions of Airbus Alert Operators Transmission
A52W011-15, Revision 00, dated July 23, 2015; or the Accomplishment
Instructions of Airbus Service Bulletin A300-52-6086, Revision 01,
dated May 29, 2018.
(2) A one-time detailed inspection to detect signs of wear of
the hooks, eccentric bushes, and x-stops, in accordance with the
instructions of Airbus Alert Operators Transmission A52W011-15,
Revision 00, dated July 23, 2015. If any wear is found, do all
applicable corrective actions before further flight, in accordance
with the instructions of Airbus Alert Operators Transmission
A52W011-15, Revision 00, dated July 23, 2015.
(3) An HFEC inspection to detect cracking at all frame fork
stations of the aft LDCD, in accordance with the instructions of
Airbus Alert Operators Transmission A52W011-15, Revision 00, dated
July 23, 2015; or the Accomplishment Instructions of Airbus Service
Bulletin A300-52-6086, Revision 01, dated May 29, 2018. If any crack
is found, before further flight, replace the cracked frame fork, in
accordance with the instructions of Airbus Alert Operators
Transmission A52W011-15, Revision 00, dated July 23, 2015; repair
the cracked frame fork, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-52-6086, Revision 01,
dated May 29, 2018; or modify (reinforce) the cracked frame fork,
including doing all applicable related investigative and corrective
actions, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A300-52-6085, Revision 01, dated May 2,
2018, except as required by paragraph (j) of this AD.
[GRAPHIC] [TIFF OMITTED] TP07MY19.001
[[Page 19885]]
(i) Retained Compliance Times, With No Changes
At the later of the times specified in paragraphs (i)(1) and
(i)(2) of this AD, do the actions required by paragraph (h) of this
AD.
(1) Before the accumulation of 4,500 total flight cycles.
(2) At the applicable time specified by paragraph (i)(2)(i) or
(i)(2)(ii) of this AD.
(i) For airplanes that have accumulated 8,000 or more total
flight cycles as of January 26, 2017 (the effective date of AD 2016-
25-03, Amendment 39-18729 (81 FR 93801, December 22, 2016) (``AD
2016-25-03'')): Within 100 flight cycles after January 26, 2017.
(ii) For airplanes that have accumulated fewer than 8,000 total
flight cycles as of January 26, 2017 (the effective date of AD 2016-
25-03): Within 400 flight cycles after January 26, 2017.
(j) Service Information Exception
Where Airbus Service Bulletin A300-52-6085, Revision 01, dated
May 2, 2018, specifies to contact Airbus for appropriate action:
Before further flight, accomplish corrective actions in accordance
with the procedures specified in paragraph (n)(2) of this AD.
(k) No Terminating Action
Accomplishment of corrective actions on an airplane as required
by paragraph (h)(1) or (h)(2) of this AD, or repair, modification,
or replacement of a frame fork as required by paragraph (h)(3) of
this AD, on the aft LDCD of an airplane does not constitute
terminating action for the repetitive HFEC inspections required by
paragraph (h)(3) of this AD for that airplane.
(l) No Reporting
Although the Accomplishment Instructions of Airbus Alert
Operators Transmission A52W011-15, Revision 00, dated July 23, 2015;
and Airbus Service Bulletin A300-52-6086, Revision 01, dated May 29,
2018; specify to submit certain information to the manufacturer,
this AD does not include that requirement.
(m) Credit for Previous Actions
(1) This paragraph provides credit for actions required by
paragraphs (h)(1) and (h)(3) of this AD, if those actions were
performed before the effective date of this AD using Airbus Service
Bulletin A300-52-6086, Revision 00, dated December 25, 2016.
(2) This paragraph provides credit for actions required by
paragraph (h)(3) of this AD, if those actions were performed before
the effective date of this AD using Airbus Service Bulletin A300-52-
6085, Revision 00, dated December 22, 2016.
(n) Other FAA AD Provisions
(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 (o)(2) of this AD. Information
may be emailed to [email protected].
(i) 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.
(ii) AMOCs approved previously for AD 2018-20-06 are approved as
AMOCs for the corresponding provisions of this AD.
(2) Contacting the Manufacturer: As of the effective date 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 Section, Transport Standards
Branch, FAA; or the European Aviation Safety Agency (EASA); or
Airbus SAS's EASA Design Organization Approval (DOA). If approved by
the DOA, the approval must include the DOA-authorized signature.
(o) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2018-0266, dated December 11, 2018, 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-2019-0257.
(2) For more information about this AD, contact Dan Rodina,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone
and fax 206-231-3225.
(3) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EAW, Rond-Point Emile Dewoitine
No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax
+33 5 61 93 44 51; email [email protected]; internet
https://www.airbus.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.
Issued in Des Moines, Washington, on April 25, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-09264 Filed 5-6-19; 8:45 am]
BILLING CODE 4910-13-P