[Federal Register Volume 84, Number 116 (Monday, June 17, 2019)]
[Proposed Rules]
[Pages 27990-27994]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-12664]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2019-0441; Product Identifier 2019-NM-036-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
[[Page 27991]]
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2000-03-
20 R1, which applies to all Airbus SAS Model A300 B4-601, B4-603, and
B4-620, Model A300 B4-600R series, and Model A300 F4-605R airplanes. AD
2000-03-20 R1 requires repetitive ultrasonic inspections to detect
cracks on the forward fittings in the radius of a certain frame,
adjacent to the tension bolts in the center section of the wings, and
various follow-on actions. Since we issued AD 2000-03-20 R1, we have
determined that the existing compliance times must be reduced. This
proposed AD would retain the requirements of AD 2000-03-20 R1, add new
airplanes to the applicability, and introduce new compliance times for
the required inspections as 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 1, 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: 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 http://www.regulations.gov.
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-
0441; 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: 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-2019-0441;
Product Identifier 2019-NM-036-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 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 NPRM.
Discussion
We issued AD 2000-03-20 R1, Amendment 39-12298 (66 FR 34530, June
29, 2001) (``AD 2000-03-20 R1''), for all Airbus SAS Model A300 B4-601,
B4-603, and B4-620, Model A300 B4-600R series, and Model A300 F4-605R
airplanes. AD 2000-03-20 R1 requires repetitive ultrasonic inspections
to detect cracks on the forward fittings in the radius of frame 40,
adjacent to the tension bolts in the center section of the wings, and
various follow-on actions. AD 2000-03-20 R1 resulted from reports of
cracking due to fatigue-related stress in the radius of frame 40
adjacent to the tension bolts at the center/outer wing junction. We
issued AD 2000-03-20 R1 to address fatigue cracking on the forward
fittings in the radius of frame 40 adjacent to the tension bolts in the
center section of the wings, which could result in reduced structural
integrity of the wings.
Actions Since AD 2000-03-20 R1 Was Issued
Since we issued AD 2000-03-20 R1, we have determined that the
existing compliance times must be reduced.
The EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2019-0044, dated March 7, 2019
(``EASA AD 2019-0044'') (also referred to as the Mandatory Continuing
Airworthiness Information, or ``the MCAI''), to correct an unsafe
condition for certain Airbus SAS Model A300 B4-600 series, Model A300
B4-600R series, Model A300 F4-605R, and Model A300 C4-605R Variant F
airplanes. The MCAI states:
During sampling inspection on A300 fleet, cracks were reported
in the radius of frame (FR) 40, adjacent to the tension bolts at the
centre wing/outer wing.
This condition, if not detected and corrected, could lead to a
reduction of the residual strength of the structure and lead to
extensive repairs.
Prompted by these findings and to address this potential unsafe
condition on A300-600 fleet, Airbus issued [service bulletin] SB
A300-57-6062 to provide inspection instructions. Consequently,
[Direction Generale de l'Aviation Civile] DGAC France published AD
95-063-177 [which corresponds to FAA AD 2000-03-20 R1] for A300-600
aeroplanes (except A300F4-622R), followed by AD 98-040-012 for A300-
600ST aeroplanes (both ADs later revised) to require initial and
repetitive ultrasonic test (UT) and high-frequency eddy current
(HFEC) inspections and, depending on findings, accomplishment of
applicable corrective action(s). Depending on a crack finding,
Airbus SB A300-57-6062 instructs to accomplish a repair per SB A300-
57-6084 to restore FR40 strength capability. That SB does not apply
to A300-600ST aeroplanes.
Since DGAC France AD 1998-040-012(B) R1 and AD F-1995-063-177 R5
(EASA approval 2003-662) were issued, material data used in the
frame of fatigue and damage tolerance analysis have been changed. It
was determined that the existing threshold and interval values must
be reduced. Consequently, Airbus revised SB A300-57-6062 to Revision
05 to take into account the new thresholds and intervals. Airbus
also issued SB A300-57-9036, specifically for A300-600ST aeroplanes.
For the reasons described above, this [EASA] AD retains the
requirements of DGAC France AD 1998-040-012(B) R1 and AD F-1995-063-
177 R5, which are superseded, and introduces new thresholds and
intervals for the required inspections [and adds Model A300 B4-622
and A300 C4-605 R Variant F airplanes to the applicability].
The initial compliance time for airplanes on which Airbus Service
Bulletin A300-57-6048 has not been embodied is before 7,600 total
flight
[[Page 27992]]
cycles. The initial compliance time for airplanes on which Airbus
Service Bulletin A300-57-6048 has been embodied is before 11,100 total
flight cycles.
Explanation of Retained Requirements
Although this proposed AD does not explicitly restate the
requirements of AD 2000-03-20 R1, this proposed AD would retain all of
the requirements of AD 2000-03-20 R1. Those requirements are referenced
in EASA AD 2019-0044, which, in turn, is referenced in paragraph (g) of
this proposed AD.
Explanation of Change to Credit Service Information
Note 2 of AD 2000-03-20 R1 provides credit for inspections
accomplished using Airbus Service Bulletin A300-57-6062, Revision 1,
dated July 23, 1995. However, EASA AD 2019-0044 does not include credit
for Airbus Service Bulletin A300-57-6062, Revision 1, dated July 23,
1995. Therefore, this proposed AD would not include that credit.
Related IBR Material Under 1 CFR Part 51
EASA AD 2019-0044 describes procedures for initial and repetitive
UT and HFEC inspections and applicable corrective actions. Corrective
actions include reworking the fuselage lateral panel at frame 40,
blending out around cracks, and repair. This material is reasonably
available because the interested parties have access to it through
their normal course of business or by the means identified in the
ADDRESSES section.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI 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 2019-0044 described previously, as incorporated by
reference, except for any differences identified as exceptions in the
regulatory text of this AD. This proposed AD also adds Model A300 B4-
622 and A300 C4-605 R Variant F airplanes to the applicability. This
proposed AD also would require sending the inspection results to
Airbus.
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 2019-0044 will be incorporated by reference in the FAA final
rule. This proposed AD would, therefore, require compliance with the
provisions specified in EASA AD 2019-0044, except for any differences
identified as exceptions in the regulatory text of this proposed AD.
Service information specified in EASA AD 2019-0044 that is required for
compliance with EASA AD 2019-0044 will be available on the internet
http://www.regulations.gov by searching for and locating Docket No.
FAA-2019-0441 after the FAA final rule is published.
Costs of Compliance
We estimate that this proposed AD affects 65 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 2000-03-20 2 work-hours x $85 per hour $0 $170 $11,050
R1. = $170.
New proposed actions............... 161 work-hours x $85 per 0 13,685 889,525
hour = $13,685.
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* Table does not include estimated costs for reporting.
We estimate that it would take about 1 work-hour per product to
comply with the proposed reporting requirement in this proposed AD. The
average labor rate is $85 per hour. Based on these figures, we estimate
the cost of reporting the inspection results on U.S. operators to be
$5,525, or $85 per product.
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
AD.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this NPRM is 2120-
0056. The paperwork cost associated with this NPRM has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this NPRM is mandatory. Comments concerning the accuracy of this burden
and suggestions for reducing the burden should be directed to the FAA
at 800 Independence Ave. SW, Washington, DC 20591, ATTN: Information
Collection Clearance Officer, AES-200.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
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
[[Page 27993]]
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. Will not affect intrastate aviation in Alaska; and
3. 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)
2000-03-20 R1, Amendment 39-12298 (66 FR 34530, June 29, 2001), and
adding the following new AD:
Airbus SAS: Docket No. FAA-2019-0441; Product Identifier 2019-NM-
036-AD.
(a) Comments Due Date
We must receive comments by August 1, 2019.
(b) Affected ADs
This AD replaces AD 2000-03-20 R1, Amendment 39-12298 (66 FR
34530, June 29, 2001) (``AD 2000-03-20 R1'').
(c) Applicability
This AD applies to Airbus SAS airplanes identified in paragraphs
(c)(1), (c)(2), (c)(3), and (c)(4) of this AD, certificated in any
category, as identified in European Aviation Safety Agency (EASA)
2019-0044, dated March 7, 2019 (``EASA AD 2019-0044'').
(1) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
(2) Model A300 B4-605R and B4-622R airplanes.
(3) Model A300 F4-605R airplanes.
(4) Model A300 C4-605R Variant F airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by reports of cracking due to fatigue-
related stress in the radius of frame 40, adjacent to the tension
bolts at the center/outer wing junction. We are issuing this AD to
address fatigue cracking on the forward fittings in the radius of
frame 40, adjacent to the tension bolts in the center section of the
wings, which could result in reduced structural integrity of the
wings.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Requirements
Except as specified in paragraph (h) of this AD: Comply with all
required actions and compliance times specified in, and in
accordance with, EASA AD 2019-0044.
(h) Exceptions to EASA AD 2019-0044
(1) For purposes of determining compliance with the requirements
of this AD: Where EASA AD 2019-0044 refers to its effective date,
this AD requires using the effective date of this AD.
(2) The ``Remarks'' section of EASA AD 2019-0044 does not apply
to this AD.
(3) Paragraph (5) of EASA AD 2019-0044 specifies to report all
inspection results to Airbus. For this AD, report all inspection
results to Airbus Service Bulletin Reporting Online Application on
Airbus World (https://w3.airbus.com/) at the applicable time
specified in paragraph (h)(3)(i) or (h)(3)(ii) of this AD.
(i) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(ii) If the inspection was done before the effective date of
this AD: Submit the report within 30 days after the effective date
of this AD.
(4) For Model A300 B4-622 and A300 C4-605 R Variant F airplanes:
The initial compliance time for the inspections required by EASA AD
2019-0044 is at the applicable time specified in EASA AD 2019-0044,
or within 12 months after the effective date of this AD, whichever
occurs later.
(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: [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 2000-03-20 R1 are approved
as AMOCs for the corresponding provisions of EASA AD 2019-0044 that
are required by paragraph (g) of this AD.
(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 2019-0044 that contains RC procedures and
tests: Except as required by paragraph (i)(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.
(4) Paperwork Reduction Act Burden Statement: A federal agency
may not conduct or sponsor, and a person is not required to respond
to, nor shall a person be subject to a penalty for failure to comply
with a collection of information subject to the requirements of the
Paperwork Reduction Act unless that collection of information
displays a current valid OMB Control Number. The OMB Control Number
for this information collection is 2120-0056. Public reporting for
this collection of information is estimated to be approximately 1
hour per response, including the time for reviewing instructions,
completing and reviewing the collection of information. All
responses to this collection of information are mandatory. Comments
concerning the accuracy of this burden and suggestions for reducing
the burden should be directed to the FAA at: 800 Independence Ave.
SW, Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.
[[Page 27994]]
(j) Related Information
(1) For information about EASA AD 2019-0044, 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 2019-0044 may be found in the AD docket on the
internet at http://www.regulations.gov by searching for and locating
Docket No. FAA-2019-0441.
(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.
Issued in Des Moines, Washington, on June 10, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-12664 Filed 6-14-19; 8:45 am]
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