[Federal Register Volume 83, Number 74 (Tuesday, April 17, 2018)]
[Proposed Rules]
[Pages 16787-16792]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-07626]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 83, No. 74 / Tuesday, April 17, 2018 /
Proposed Rules
[[Page 16787]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0277; Product Identifier 2017-NM-124-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus 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) 2017-15-
17, which applies to certain Airbus Model A300 B4-600R series
airplanes, Model A300 C4-605R Variant F airplanes, and Model A300 F4-
600R series airplanes. AD 2017-15-17 requires an inspection of the
lower area of a certain frame radius for cracking, and corrective
action if necessary. Since we issued AD 2017-15-17, we have determined
that repetitive inspections and applicable corrective actions are
necessary. This proposed AD would add new repetitive inspections of the
lower area of a certain frame radius for cracking, and corrective
actions if necessary. We are proposing this AD to address the unsafe
condition on these products.
DATES: We must receive comments on this proposed AD by June 1, 2018.
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, 1 Rond Point Maurice Bellonte, 31707
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-2018-
0277; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International 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 proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2018-0277;
Product Identifier 2017-NM-124-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 2017-15-17, Amendment 39-18977 (82 FR 35644, August 1,
2017) (``AD 2017-15-17''), for certain Airbus Model A300 B4-600R series
airplanes, Model A300 C4-605R Variant F airplanes, and Model A300 F4-
600R series airplanes. AD 2017-15-17 was prompted by the detection of
cracking that originated from the fastener holes in the forward fitting
lower radius of frame (FR) 40. AD 2017-15-17 requires an inspection of
the lower area of a certain frame radius for cracking, and corrective
action if necessary. We issued AD 2017-15-17 to detect and correct
cracking in the forward fitting lower radius of FR 40. Such cracking
could reduce the structural integrity of the fuselage.
Since we issued AD 2017-15-17, we have determined that new
repetitive inspections of the lower area of a certain frame radius for
cracking, and corrective actions are necessary.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2017-0158, dated August 25, 2017 (referred to after this as the
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to
correct an unsafe condition for certain Airbus Model A300 B4-600R
series airplanes, Model A300 C4-605R Variant F airplanes, and Model
A300 F4-600R series airplanes. The MCAI states:
Following a full stress analysis of the Frame (FR) 40 lower
area, supported by a Finite Element Model (FEM), of the post-mod
[modification] 10221 configuration, it was demonstrated that, for
the FR40 forward fitting lower radius, a crack could occur after a
certain number of flight cycles (FC).
This condition, if not detected and corrected, could reduce the
structural integrity of the fuselage.
To address this potential unsafe condition, Airbus established
that crack detection could be achieved through a special detailed
inspection (SDI) using a high frequency eddy current (HFEC) method,
and issued Alert Operators Transmission (AOT) A57W009-16 to provide
those inspection instructions.
Consequently, EASA issued AD 2016-0085 to require a one-time SDI
of the FR40 lower area and, depending on findings, accomplishment of
applicable corrective action(s). After that [EASA] AD was issued,
further cracks were detected, originating from
[[Page 16788]]
the fastener hole, and, based on these findings, it was determined
that the inspection area must be enlarged, and Airbus issued AOT
A57W009-16 Revision (Rev.) 01 accordingly. Consequently, EASA issued
AD 2016-0179 [which corresponds to FAA AD 2017-15-17], retaining the
requirements of EASA AD 2016-0085, which was superseded, to extend
the area of inspection, and to require an additional inspection for
aeroplanes that were previously inspected.
The one-time SDI for high cycle A300-600 aeroplanes was intended
to mitigate the highest risks within the fleet, pending development
of instructions for repetitive inspections.
Since EASA AD 2016-0179 was issued, Airbus published SB A300-57-
6120 * * * [for] the inspection programme for A300-600 * * * post-
mod 10221 * * * [airplanes]. The AOT one-time inspection is
superseded by these repetitive inspection SBs. These SBs include
alternative inspection methods and repair solutions in case of
findings together with the associated inspection programme.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2016-0179, which is superseded, * * * and
defines new inspections methods with new compliance times, including
repetitive inspections, depending on the aeroplane inspection
status.
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-2018-
0277.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A300-57-6120, including
Appendices 1 through 7, dated April 28, 2017. This service information
describes procedures for repetitive inspections of the forward fitting
lower radius of FR 40 for cracking, and corrective action. This service
information is reasonably available because the interested parties have
access to it through their normal course of business or by the means
identified in the ADDRESSES section.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Costs of Compliance
We estimate that this proposed AD affects 94 airplanes of U.S.
registry.
The actions required by AD 2017-15-17, and retained in this
proposed AD, take about 4 work-hours per product, at an average labor
rate of $85 per work-hour. Based on these figures, the estimated cost
of the actions that are required by AD 2017-15-17 is $340 per product.
We also estimate that it would take about 4 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of this proposed AD on U.S. operators to be $31,960, or $340
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 AD is 2120-
0056. The paperwork cost associated with this AD 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 AD 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 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 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)
2017-15-17, Amendment 39-18977 (82
[[Page 16789]]
FR 35644, August 1, 2017), and adding the following new AD:
Airbus: Docket No. FAA-2018-0277; Product Identifier 2017-NM-124-AD.
(a) Comments Due Date
We must receive comments by June 1, 2018.
(b) Affected ADs
This AD replaces AD 2017-15-17, Amendment 39-18977 (82 FR 35644,
August 1, 2017) (``AD 2017-15-17'').
(c) Applicability
This AD applies to Airbus airplanes, certificated in any
category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of
this AD, on which Airbus Modification 10221 was embodied in
production.
(1) Airbus Model A300 B4-605R and B4-622R airplanes.
(2) Airbus Model A300 C4-605R Variant F airplanes.
(3) Airbus Model A300 F4-605R and F4-622R airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by the detection of cracking that
originated from the fastener holes in the forward fitting lower
radius of frame (FR) 40. We are issuing this AD to detect and
correct cracking in the forward fitting lower radius of FR 40. Such
cracking could reduce the structural integrity of the fuselage.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Definitions
(1) For the purpose of this AD, the average flight time (AFT)
can be established by dividing the flight hours (FHs) by the flight
cycles (FCs) counted:
(i) From first flight, for selecting the inspection threshold of
the non-repaired area,
(ii) From repair, for selecting the inspection threshold of the
repaired area,
(iii) From the last inspection, for selecting the inspection
interval.
(2) For the purpose of this AD, Group 1 airplanes are those
airplanes already inspected in accordance with paragraph 4.2.2 in
Alert Operators Transmission (AOT) A57W009-16, Revision 01, dated
July 13, 2016, before the effective date of this AD. Group 2
airplanes are those airplanes not inspected in accordance with
paragraph 4.2.2 in AOT A57W009-16, Revision 01, dated July 13, 2016,
as of the effective date of this AD.
(3) For the purpose of this AD, inspection method A is a high
frequency (HFEC) inspection of the radius and fastener area.
Inspection method B is a HFEC inspection of the radius and fastener
area and a rototest of the fastener hole. Both are defined as a
special detailed inspection (SDI) in this AD.
(h) Repetitive Inspections for Non-Repaired Areas
Within the compliance time specified in table 1 to paragraph (h)
of this AD (Group 1 airplanes) or table 2 to paragraph (h) of this
AD (Group 2 airplanes), as applicable, and, thereafter, at intervals
not exceeding the values specified in table 3 to paragraph (h) of
this AD, do a SDI for cracking of any non-repaired radius, fastener
areas, and fastener holes, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A300-57-6120, including
Appendices 1 through 7, dated April 28, 2017; except where Airbus
Service Bulletin A300-57-6120, including Appendices 1 through 7,
dated April 28, 2017, specifies contacting Airbus for appropriate
action, before further flight, obtain instructions using the
procedures specified in paragraph (l) of this AD and accomplish
those instructions.
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(i) Repetitive Inspections for Repaired Areas
Within the compliance time values as specified in table 4 to
paragraph (i) of this AD, and, thereafter, at intervals not
exceeding those same values, do a SDI for cracking of the repaired
radius, fastener areas, and fastener holes, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A300-57-6120,
including Appendices 1 through 7, dated April 28, 2017; except where
Airbus Service Bulletin A300-57-6120, including Appendices 1 through
7, dated April 28, 2017, specifies contacting Airbus for appropriate
action, before further flight, obtain instructions using the
procedures specified in paragraph (l) of this AD and accomplish
those instructions.
[GRAPHIC] [TIFF OMITTED] TP17AP18.011
(j) Corrective Action
If any crack is found during any inspection required by
paragraph (h) or (i) of this AD: Before further flight, repair in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A300-57-6120, including Appendices 1 through 7, dated April
28, 2017.
(k) Reporting
Submit a report of the findings (both positive and negative) of
each inspection required by paragraph (h) and (i) of this AD to
Airbus, in accordance with the instructions of Airbus Service
Bulletin A300-57-6120, including Appendices 1 through 7, dated April
28, 2017, at the applicable time specified in paragraph (k)(1) or
(k)(2) of this AD.
(1) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(2) 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.
(l) 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 (m)(2) of this AD. Information
may be emailed to: [email protected]. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office.
(2) Contacting the Manufacturer: 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's EASA Design Organization Approval (DOA). If approved by the
DOA, the approval must include the DOA-authorized signature.
(3) Required for Compliance (RC): Except as required by
paragraphs (g) and (h) of this AD: If any service information
contains procedures or tests that are identified as RC, those
procedures and tests must be done to comply with this AD; any
procedures or tests that are not identified as RC are recommended.
Those procedures and tests that are not identified as RC may be
deviated from using accepted methods in accordance with the
operator's maintenance or inspection program without obtaining
approval of an AMOC, provided the procedures and tests identified as
RC can be done and the airplane can be put back in an airworthy
condition. Any substitutions or changes to procedures or tests
identified as RC require approval of an AMOC.
(m) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2017-0158, dated August 25,
2017, for related information. This MCAI may be found in the AD
docket
[[Page 16792]]
on the internet at http://www.regulations.gov by searching for and
locating Docket No. FAA-2018-0277.
(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, 1 Rond Point Maurice
Bellonte, 31707 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 March 30, 2018.
Chris Spangenberg,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-07626 Filed 4-16-18; 8:45 am]
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