[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]
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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).
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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 http://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 http://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 http://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 http://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 http://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
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Retained actions from AD 2018-20-06... 17 work-hours x $85 per $0 $1,445 $83,810
hour = $1,445.
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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
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Labor cost Parts cost Cost per product
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Up to 65 work-hours x $85 per Up to $10,000..... Up to $15,525.
hour = $5,525.
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[[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 http://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
http://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