Airworthiness Directives; Airbus Airplanes, 16787-16792 [2018-07626]
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16787
Proposed Rules
Federal Register
Vol. 83, No. 74
Tuesday, April 17, 2018
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.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0277; Product
Identifier 2017–NM–124–AD]
RIN 2120–AA64
Examining the AD Docket
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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
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
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SUMMARY:
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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
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.
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You may examine the AD docket on
the internet at https://
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 https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
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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
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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 https://
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.
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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.
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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 workhour. 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.
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.
Authority for This Rulemaking
The Proposed Amendment
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
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
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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)
2017–15–17, Amendment 39–18977 (82
■
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Federal Register / Vol. 83, No. 74 / Tuesday, April 17, 2018 / Proposed Rules
Airbus: Docket No. FAA–2018–0277; Product
Identifier 2017–NM–124–AD.
(a) Comments Due Date
We must receive comments by June 1,
2018.
(f) Compliance
(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
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This AD was prompted by the detection of
cracking that originated from the fastener
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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.
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
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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 nonrepaired 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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FR 35644, August 1, 2017), and adding
the following new AD:
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Federal Register / Vol. 83, No. 74 / Tuesday, April 17, 2018 / Proposed Rules
Table 2 to Paragraph (h) of this AD- Group 2 Inspection Thresholds- Non-repaired
Areas
AFT
Compliance Time (whichever occurs later,
A orB)
A: Before exceeding 14,700 FC or 31,900
FH since first flight of the airplane,
whichever occurs first.
B: Within 12 months after the effective
Greater than 1. 5
date of this AD, without exceeding
(whichever occurs later):
- 19,000 FC or 41,000 FH, whichever
occurs first since airplane first flight.
- 300 FC or 630 FH, whichever occurs first
after September 5, 2017 (the effective date
of AD 2017-15-17).
A: Before exceeding 15,900 FC or 23,900
FH since first flight of the airplane,
whichever occurs first.
1.5 or less
B: Within 12 months after the effective
date of this AD, without exceeding
(whichever occurs later):
- 19,000 FC or 41,000 FH, whichever
occurs first since airplane first flight.
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- 300 FC or 630 FH, whichever occurs first
after September 5, 2017 (the effective date
of AD 2017-15-17).
Federal Register / Vol. 83, No. 74 / Tuesday, April 17, 2018 / Proposed Rules
(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.
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(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.
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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.
(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: 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: 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.
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(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
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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
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on the internet at https://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 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
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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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0271; Product
Identifier 2017–NM–111–AD]
RIN 2120–AA64
Examining the AD Docket
Airworthiness Directives; Saab AB,
Saab Aeronautics (Formerly Known as
Saab AB, Saab Aerosystems)
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2016–13–
06, which applies to certain Saab AB,
Saab Aeronautics Model 340A (SAAB/
SF340A) and SAAB 340B airplanes. AD
2016–13–06 requires a revision of the
applicable airplane flight manual
(AFM), repetitive inspections of the
horizontal stabilizer de-icing boots, and
applicable corrective actions. Since we
issued AD 2016–13–06, the
manufacturer has developed an
improved de-icing boot. This proposed
AD would continue to require a revision
of the applicable AFM, repetitive
inspections of the horizontal stabilizer
de-icing boots, and applicable corrective
actions. This proposed AD would also
require replacement of single stitched
de-icing boots with improved double
stitched boots, and re-identification of
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SUMMARY:
VerDate Sep<11>2014
17:36 Apr 16, 2018
the modified horizontal stabilizer
leading edge. 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
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 Saab AB, Saab
¨
Aeronautics, SE–581 88, Linkoping,
Sweden; telephone: +46 13 18 5591; fax:
+46 13 18 4874; email:
saab340techsupport@saabgroup.com;
internet: https://www.saabgroup.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.
Jkt 244001
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0271; 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:
Shahram Daneshmandi, Aerospace
Engineer, International Section,
Transport Standards Branch, FAA, 2200
South 216th St., Des Moines, WA 98198;
telephone and fax: 206–231–3220.
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–
PO 00000
Frm 00006
Fmt 4702
Sfmt 4702
2018–0271; Product Identifier 2017–
NM–111–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 2016–13–06,
Amendment 39–18570 (81 FR 41432,
June 27, 2016) (‘‘AD 2016–13–06’’), for
certain Saab AB, Saab Aeronautics
Model 340A (SAAB/SF340A) and SAAB
340B airplanes. AD 2016–13–06 was
prompted by reports of ruptured
horizontal stabilizer de-icing boots. AD
2016–13–06 requires a revision of the
applicable AFM, repetitive inspections
of the horizontal stabilizer de-icing
boots, and applicable corrective actions.
We issued AD 2016–13–06 to detect and
correct damage of the de-icing boot;
such damage could lead to a ruptured
boot, severe vibrations, and possible
reduced control of the airplane.
Since we issued AD 2016–13–06, the
manufacturer has developed an
improved de-icing boot, reinforced
through double stitch lines.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2017–0144,
dated August 9, 2017 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Saab AB, Saab Aeronautics
Model 340A (SAAB/SF340A) and SAAB
340B airplanes. The MCAI states:
Several occurrences were reported of
rupture of the horizontal stabilizer de-icing
boot in flight. In some of the reported events,
the de-icing boot had formed a large open
scoop.
This condition, if not detected and
corrected, could lead to complete loss of the
de-icing function within its associated zone
and severe vibrations, possibly resulting in
reduced control of the aeroplane.
To address this potential unsafe condition,
Saab AB, Aeronautics (hereafter referred to as
‘‘Saab’’ in this [EASA] AD) issued Alert
Operations Bulletin (AOB) No. 12 and AOB
No. 23 as temporary measures,
recommending to select Flaps 0 for landing
in the event of a suspected rupture of the deicing boot on the horizontal stabilizer. In
addition, Saab issued SB [Service Bulletin]
340–30–094 providing instructions for
inspection of de-icing boots.
E:\FR\FM\17APP1.SGM
17APP1
]]>Agencies
[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]
========================================================================
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.
========================================================================
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).
-----------------------------------------------------------------------
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 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, 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 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-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 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 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 https://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.
BILLING CODE 4910-13-P
[GRAPHIC] [TIFF OMITTED] TP17AP18.008
[[Page 16790]]
[GRAPHIC] [TIFF OMITTED] TP17AP18.009
[[Page 16791]]
[GRAPHIC] [TIFF OMITTED] TP17AP18.010
BILLING CODE 4910-13-C
(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 https://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 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 March 30, 2018.
Chris Spangenberg,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-07626 Filed 4-16-18; 8:45 am]
BILLING CODE 4910-13-P
