Airworthiness Directives; Airbus Airplanes, 39520-39523 [2017-17203]
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39520
Federal Register / Vol. 82, No. 160 / Monday, August 21, 2017 / Rules and Regulations
Airframe and Mechanical Systems Section,
FAA, New York ACO Branch, 1600 Stewart
Avenue, Suite 410, Westbury, NY 11590;
telephone 516–228–7318; fax 516–794–5531.
(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (k)(3) and (k)(4) of this AD.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Bombardier Service Bulletin 605–35–
003, Revision 02, dated April 18, 2016.
(ii) Reserved.
(3) For service information identified in
ˆ
this AD, contact Bombardier, Inc., 400 Cote´
Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; Widebody Customer Response
Center North America toll-free telephone 1–
866–538–1247 or direct-dial telephone 1–
514–855–2999; fax 514–855–7401; email
ac.yul@aero.bombardier.com; Internet https://
www.bombardier.com.
(4) You may view this service information
at the FAA, Transport Standards Branch,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on August
4, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft
Certification Service.
[FR Doc. 2017–17086 Filed 8–18–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0520; Product
Identifier 2016–NM–143–AD; Amendment
39–18995; AD 2017–17–05]
RIN 2120–AA64
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Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Airbus Model A300 series airplanes;
SUMMARY:
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16:12 Aug 18, 2017
Jkt 241001
and Model A300 B4–600, B4–600R, and
F4–600R series airplanes, and Model
A300 C4–605R Variant F airplanes
(collectively called Model A300–600
series airplanes). This AD was prompted
by reports of cracks initiating at the
upper radius of a certain frame and a
determination that the current
inspection procedure is not reliable in
detecting certain cracking of the forward
fitting of the frame. This AD requires
repetitive inspections to detect cracking
of the upper radius of the forward fitting
of a certain frame, and related
investigative actions and corrective
actions if necessary. We are issuing this
AD to address the unsafe condition on
these products.
DATES: This AD is effective September
25, 2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of September 25, 2017.
ADDRESSES: For service information
identified in this final rule, 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.airwortheas@airbus.com; Internet: https://
www.airbus.com. You may view this
referenced service information at the
FAA, Transport Standards Branch, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
It is also available on the Internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2017–
0520.
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–2017–
0520; 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 AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (telephone 800–647–
5527) is Docket Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Dan
Rodina, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
PO 00000
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telephone: 425–227–2125; fax: 425–
227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Airbus Model A300
series airplanes; and Model A300 B4–
600, B4–600R, and F4–600R series
airplanes, and Model A300 C4–605R
Variant F airplanes (collectively called
Model A300–600 series airplanes). The
NPRM published in the Federal
Register on May 31, 2017 (82 FR 24903)
(‘‘the NPRM’’). The NPRM was
prompted by reports of cracks initiating
at the upper radius of frame (FR) 47 and
a determination that the current
inspection procedure is not reliable in
detecting certain cracking of the forward
fitting of FR 47. The NPRM proposed to
require repetitive inspections to detect
cracking of the upper radius of the
forward fitting of FR 47, and related
investigative actions and corrective
actions if necessary. We are issuing this
AD to detect and correct fatigue
cracking of the FR 47 forward fitting
upper radius on the left-hand and righthand sides of the fuselage, which could
propagate and result in reduced
structural integrity of the airplane.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2016–0150,
dated July 25, 2016 (referred to after this
as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
on all. The MCAI states:
During scheduled maintenance inspections
on the fuselage, cracks initiating at the upper
radius of frame (FR) 47 have been reported
on several aeroplanes. Similar damage was
also discovered on the A300 fatigue test
fuselage.
This condition, if not detected and
corrected, could reduce the structural
integrity of the fuselage.
Prompted by these findings, Airbus issued
Service Bulletin (SB) A300–53–0246, SB
A300–53–6029 and SB A300–53–9014 to
provide inspection instructions and,
consequently, DGAC France issued AD F–
2006–016 to require repetitive inspections
and corrective action.
Since that [French] AD was issued, further
investigation led to the conclusion that the
current ultrasonic inspection performed in
accordance with Airbus SB A300–53–0246
Revision 06, or SB A300–53–6029 Revision
08, or SB A300–53–9014 Revision 01, as
applicable, was not reliable to detect deep
crack going downward.
Consequently, to ensure the crack depth is
correctly measured whatever the crack
direction, Airbus developed a new
nondestructive testing method [eddy current]
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Federal Register / Vol. 82, No. 160 / Monday, August 21, 2017 / Rules and Regulations
for this special detailed inspection (SDI) and
revised the affected SBs accordingly.
For the reasons described above, this
[EASA] AD retains the requirements of DGAC
France AD F–2006–016, which is
superseded, but requires the accomplishment
of repetitive SDI to replace the previously
required ultrasonic inspections [and related
investigative and corrective actions if
necessary].
Related investigative actions include an
ultrasonic inspection for cracking on the
forward face of the forward fitting and
a detailed inspection for cracking of the
aft fitting around the fasteners.
Corrective actions include crack repairs,
and modification of the sealing fittings
and sealing shims. This AD requires
reporting of the inspection results to
Airbus. 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–2017–
0520.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Conclusion
We reviewed the relevant data and
determined that air safety and the
public interest require adopting this AD
as proposed except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Related Service Information Under 1
CFR Part 51
Airbus has issued Airbus Service
Bulletin A300–53–0246, Revision 08,
39521
including Appendix 1, dated April 13,
2016 (for Model A300 series airplanes);
and Airbus Service Bulletin A300–53–
6029, Revision 12, including Appendix
1, dated April 13, 2016 (for Model
A300–600 series airplanes). The service
information describes procedures for
doing an SDI for cracking of the FR 47
forward fitting upper radius on the lefthand and right-hand sides of the
fuselage, and related investigative and
corrective actions. 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.
Costs of Compliance
We estimate that this AD will affect
132 airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Inspection ............
19 work-hours × $85 per hour =
$1,615.
1 work-hour × $85 per hour = $85
Reporting .............
Parts cost
We estimate the following costs to do
any necessary related investigative and
corrective actions that would be
Cost per product
Cost on U.S. operators
$0
$1,615 per inspection cycle .........
$213,180 per inspection cycle.
$0
$85 per inspection cycle ..............
$11,220 per inspection cycle.
required based on the results of the
inspection. We have no way of
determining the number of aircraft that
might need these repairs:
ON-CONDITION COSTS
Action
Labor cost
Related investigative and Corrective actions ...............
21 work-hours × $85 per hour = $1,785 ......................
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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
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16:12 Aug 18, 2017
Jkt 241001
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
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Parts cost
$1,835
Cost per
product
$3,620
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.
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Federal Register / Vol. 82, No. 160 / Monday, August 21, 2017 / Rules and Regulations
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
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 that this AD:
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.
(3) Model A300 B4–605R and B4–622R
airplanes.
(4) Model A300 F4–605R and F4–622R
airplanes.
(5) Model A300 C4–605R Variant F
airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of cracks
initiating at the upper radius of frame (FR)
47 and a determination that the current
inspection procedure is not reliable in
detecting certain cracking of the forward
fitting of FR 47. We are issuing this AD to
detect and correct fatigue cracking of the FR
47 forward fitting upper radius on the lefthand and right-hand sides of the fuselage,
which could propagate and result in reduced
structural integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
Except as required by paragraph (h) of this
AD: Before exceeding 10,000 flight cycles
since first flight of the airplane or within 30
days after the effective date of this AD,
whichever occurs later, do a special detailed
inspection (SDI) for cracking of the FR 47
forward fitting upper radius on the left-hand
and right-hand sides of the fuselage, in
accordance with the Accomplishment
Instructions of the applicable Airbus service
information specified in paragraphs (g)(1)
and (g)(2) of this AD. Repeat the inspection
thereafter at intervals not to exceed 4,150
flight cycles, except as required by paragraph
(j) of this AD.
(1) Airbus Service Bulletin A300–53–0246,
Revision 08, including Appendix 1, dated
April 13, 2016.
(2) Airbus Service Bulletin A300–53–6029,
Revision 12, including Appendix 1, dated
April 13, 2016.
2017–17–05 Airbus: Amendment 39–18995;
Docket No. FAA–2017–0520; Product
Identifier 2016–NM–143–AD.
(h) Initial Inspection for Airplanes
Previously Inspected
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
■
(a) Effective Date
This AD is effective September 25, 2017.
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(b) Affected ADs
This AD affects AD 2007–26–14,
Amendment 39–15316 (73 FR 2803, January
16, 2008) (‘‘AD 2007–26–14’’).
(c) Applicability
This AD applies to the Airbus airplanes
identified in paragraphs (c)(1) through (c)(5)
of this AD, certificated in any category,
except airplanes that have been repaired as
specified in Airbus Service Bulletin A300–
53–0370; or Airbus Service Bulletin A300–
53–6144, as applicable.
(1) Model A300 B2–1A, B2–1C, B2K–3C,
B2–203, B4–2C, B4–103, and B4–203
airplanes.
(2) Model A300 B4–601, B4–603, B4–620,
and B4–622 airplanes.
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For airplanes previously inspected as
specified in the applicable Airbus service
information specified in paragraphs (h)(1)
through (h)(6) of this AD and on which no
cracking was found: Within 4,150 flight
cycles after the most recent inspection, do
the inspection for cracking of the FR 47
forward fitting upper radius required by
paragraph (g) of this AD.
(1) Airbus Service Bulletin A300–53–0246,
Revision 06, dated October 19, 2005.
(2) Airbus Service Bulletin A300–53–0246,
Revision 07, dated September 9, 2008.
(3) Airbus Service Bulletin A300–53–6029,
Revision 08, dated October 19, 2005.
(4) Airbus Service Bulletin A300–53–6029,
Revision 09, dated September 9, 2008.
(5) Airbus Service Bulletin A300–53–6029,
Revision 10, dated July 9, 2009.
(6) Airbus Service Bulletin A300–53–6029,
Revision 11, dated September 28, 2009.
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(i) Inspections for Airplanes With Abnormal
Load Events
For airplanes on which any crack was
found during any inspection done as
specified in Airbus Service Bulletin A300–
53–0246 or Airbus Service Bulletin A300–
53–6029, as applicable, and on which any
abnormal load event, such as hard landing or
flight in excessive turbulence, occurred
within 3 months before the effective date of
this AD or occurs on or after the effective
date of this AD: Within 3 months after each
event, accomplish an SDI for cracking of the
FR 47 forward fitting upper radius, left-hand
and right-hand sides of the fuselage, in
accordance with the applicable
Accomplishment Instructions of the Airbus
service information specified in paragraphs
(g)(1) or (g)(2) of this AD. If, during this 3month period, another abnormal load event
occurs, and if no SDI has yet been
accomplished, before further flight after the
second event, obtain corrective action
instructions from the Manager, International
Section, Transport Standards Branch, FAA;
or the European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (DOA), and
accomplish those instructions accordingly.
(j) Corrective Actions for Airplanes With
Cracks
If, during any SDI as required by paragraph
(g), (h), or (i) of this AD, any crack is found:
Before further flight, do the applicable
related investigative and corrective actions,
in accordance with the Accomplishment
Instructions of the applicable Airbus service
information specified in paragraph (g)(1) or
(g)(2) of this AD, and obtain additional
corrective action instructions from the
Manager, International Section, Transport
Standards Branch, FAA; or EASA; or
Airbus’s EASA DOA, and accomplish those
instructions accordingly before further flight.
(k) Reporting
Submit a report of the findings (both
positive and negative) of each SDI inspection
required by paragraphs (g), (h), and (i) of this
AD to Airbus Service Bulletin Reporting
Online Application on Airbus World (https://
w3.airbus.com/), 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) Terminating Action for AD 2007–26–14
Accomplishing any inspection required by
paragraph (g) or (h) of this AD terminates all
requirements of AD 2007–26–14 for the
inspected airplane.
(m) 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
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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 (n)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Section,
Transport Standards Branch, FAA; or EASA;
or Airbus’s EASA DOA. If approved by the
DOA, the approval must include the DOAauthorized signature.
(3) Reporting Requirements: 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 5 minutes 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.
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2016–0150, dated July 25, 2016, for related
information. This MCAI may be found in the
AD docket on the Internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2017–0520.
(2) For more information about this AD,
contact Dan Rodina, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW.,
Renton, WA 98057–3356; telephone: 425–
227–2125; fax: 425–227–1149.
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(o) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A300–53–0246,
Revision 08, including Appendix 1, dated
April 13, 2016.
16:12 Aug 18, 2017
Issued in Renton, Washington, on August
8, 2017.
Dionne Palermo,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2017–17203 Filed 8–18–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0270; Product
Identifier 2016–SW–032–AD; Amendment
39–18993; AD 2017–17–03]
RIN 2120–AA64
Airworthiness Directives; MD
Helicopters, Inc., Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
(n) Related Information
VerDate Sep<11>2014
(ii) Airbus Service Bulletin A300–53–6029,
Revision 12, including Appendix 1, dated
April 13, 2016.
(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.
(4) You may view this service information
at the FAA, Transport Standards Branch,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Jkt 241001
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Helicopters, Inc., Attn: Customer
Support Division, 4555 E. McDowell
Rd., Mail Stop M615, Mesa, AZ 85215–
9734; telephone 1–800–388–3378; fax
480–346–6813; or at https://
www.mdhelicopters.com. You may
review the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
10101 Hillwood Pkwy, Room 6N–321,
Fort Worth, TX 76177. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0270.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov in Docket No.
FAA–2017–0270; 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 AD, any
incorporated-by-reference information,
the economic evaluation, any comments
received, and other information. The
address for the Docket Office (phone:
800–647–5527) is Document
Management Facility, U.S. Department
of Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Eric
Schrieber, Aviation Safety Engineer, Los
Angeles ACO Branch, Compliance and
Airworthiness Division, FAA, 3960
Paramount Blvd., Lakewood, California
90712; telephone (562) 627–5348; email
eric.schrieber@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We are superseding
Airworthiness Directive (AD) 2014–16–
01 for MD Helicopters, Inc. (MDHI),
Model MD900 helicopters. AD 2014–
16–01 required an eddy current
inspection of the main rotor upper hub
assembly (upper hub) for a crack. This
AD requires additional inspections and
replacing the fillet seal. This AD was
prompted by three additional reports of
upper hub cracks. The actions of this
AD are intended to prevent an unsafe
condition on these products.
DATES: This AD is effective September
25, 2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of September 25, 2017.
ADDRESSES: For service information
identified in this final rule, contact MD
SUMMARY:
39523
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to remove AD 2014–16–01,
Amendment 39–17925 (79 FR 45322,
August 5, 2014) and add a new AD. AD
2014–16–01 applied to MDHI Model
MD900 helicopters, serial numbers 900–
00008 through 900–00140, with an
upper hub part number (P/N)
900R2101006–105, –107, –109, or –111
installed. AD 2014–16–01 required eddy
current inspecting the upper hub and
replacing it if there is a crack. The
NPRM published in the Federal
Register on April 3, 2017 (82 FR 16138).
The NPRM was prompted by reports
of three additional cracks found in the
MD900 fleet. These cracks were not
discovered by the one-time eddy current
inspection required by AD 2014–16–01,
but were found during regular
maintenance of the upper hub. The
NPRM proposed to require for MDHI
E:\FR\FM\21AUR1.SGM
21AUR1
Agencies
[Federal Register Volume 82, Number 160 (Monday, August 21, 2017)]
[Rules and Regulations]
[Pages 39520-39523]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-17203]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0520; Product Identifier 2016-NM-143-AD; Amendment
39-18995; AD 2017-17-05]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Airbus Model A300 series airplanes; and Model A300 B4-600, B4-600R, and
F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes
(collectively called Model A300-600 series airplanes). This AD was
prompted by reports of cracks initiating at the upper radius of a
certain frame and a determination that the current inspection procedure
is not reliable in detecting certain cracking of the forward fitting of
the frame. This AD requires repetitive inspections to detect cracking
of the upper radius of the forward fitting of a certain frame, and
related investigative actions and corrective actions if necessary. We
are issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective September 25, 2017.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of September 25,
2017.
ADDRESSES: For service information identified in this final rule,
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, 1601 Lind Avenue
SW., Renton, WA. For information on the availability of this material
at the FAA, call 425-227-1221. It is also available on the Internet at
https://www.regulations.gov by searching for and locating Docket No.
FAA-2017-0520.
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-2017-
0520; 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 AD, the regulatory evaluation, any comments received, and
other information. The street address for the Docket Office (telephone
800-647-5527) is Docket Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 1601 Lind
Avenue SW., Renton, WA 98057-3356; telephone: 425-227-2125; fax: 425-
227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to certain Airbus Model A300
series airplanes; and Model A300 B4-600, B4-600R, and F4-600R series
airplanes, and Model A300 C4-605R Variant F airplanes (collectively
called Model A300-600 series airplanes). The NPRM published in the
Federal Register on May 31, 2017 (82 FR 24903) (``the NPRM''). The NPRM
was prompted by reports of cracks initiating at the upper radius of
frame (FR) 47 and a determination that the current inspection procedure
is not reliable in detecting certain cracking of the forward fitting of
FR 47. The NPRM proposed to require repetitive inspections to detect
cracking of the upper radius of the forward fitting of FR 47, and
related investigative actions and corrective actions if necessary. We
are issuing this AD to detect and correct fatigue cracking of the FR 47
forward fitting upper radius on the left-hand and right-hand sides of
the fuselage, which could propagate and result in reduced structural
integrity of the airplane.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2016-0150, dated July 25, 2016 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition on all. The MCAI states:
During scheduled maintenance inspections on the fuselage, cracks
initiating at the upper radius of frame (FR) 47 have been reported
on several aeroplanes. Similar damage was also discovered on the
A300 fatigue test fuselage.
This condition, if not detected and corrected, could reduce the
structural integrity of the fuselage.
Prompted by these findings, Airbus issued Service Bulletin (SB)
A300-53-0246, SB A300-53-6029 and SB A300-53-9014 to provide
inspection instructions and, consequently, DGAC France issued AD F-
2006-016 to require repetitive inspections and corrective action.
Since that [French] AD was issued, further investigation led to
the conclusion that the current ultrasonic inspection performed in
accordance with Airbus SB A300-53-0246 Revision 06, or SB A300-53-
6029 Revision 08, or SB A300-53-9014 Revision 01, as applicable, was
not reliable to detect deep crack going downward.
Consequently, to ensure the crack depth is correctly measured
whatever the crack direction, Airbus developed a new nondestructive
testing method [eddy current]
[[Page 39521]]
for this special detailed inspection (SDI) and revised the affected
SBs accordingly.
For the reasons described above, this [EASA] AD retains the
requirements of DGAC France AD F-2006-016, which is superseded, but
requires the accomplishment of repetitive SDI to replace the
previously required ultrasonic inspections [and related
investigative and corrective actions if necessary].
Related investigative actions include an ultrasonic inspection for
cracking on the forward face of the forward fitting and a detailed
inspection for cracking of the aft fitting around the fasteners.
Corrective actions include crack repairs, and modification of the
sealing fittings and sealing shims. This AD requires reporting of the
inspection results to Airbus. 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-2017-0520.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
We reviewed the relevant data and determined that air safety and
the public interest require adopting this AD as proposed except for
minor editorial changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
Airbus has issued Airbus Service Bulletin A300-53-0246, Revision
08, including Appendix 1, dated April 13, 2016 (for Model A300 series
airplanes); and Airbus Service Bulletin A300-53-6029, Revision 12,
including Appendix 1, dated April 13, 2016 (for Model A300-600 series
airplanes). The service information describes procedures for doing an
SDI for cracking of the FR 47 forward fitting upper radius on the left-
hand and right-hand sides of the fuselage, and related investigative
and corrective actions. 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.
Costs of Compliance
We estimate that this AD will affect 132 airplanes of U.S.
registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection................... 19 work-hours x $85 $0 $1,615 per $213,180 per
per hour = $1,615. inspection cycle. inspection cycle.
Reporting.................... 1 work-hour x $85 per $0 $85 per inspection $11,220 per
hour = $85. cycle. inspection cycle.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary related
investigative and corrective actions that would be required based on
the results of the inspection. We have no way of determining the number
of aircraft that might need these repairs:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Related investigative and Corrective 21 work-hours x $85 per hour = $1,835 $3,620
actions. $1,785.
----------------------------------------------------------------------------------------------------------------
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.
[[Page 39522]]
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will 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 that this AD:
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.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 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 adding the following new airworthiness
directive (AD):
2017-17-05 Airbus: Amendment 39-18995; Docket No. FAA-2017-0520;
Product Identifier 2016-NM-143-AD.
(a) Effective Date
This AD is effective September 25, 2017.
(b) Affected ADs
This AD affects AD 2007-26-14, Amendment 39-15316 (73 FR 2803,
January 16, 2008) (``AD 2007-26-14'').
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs
(c)(1) through (c)(5) of this AD, certificated in any category,
except airplanes that have been repaired as specified in Airbus
Service Bulletin A300-53-0370; or Airbus Service Bulletin A300-53-
6144, as applicable.
(1) Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and
B4-203 airplanes.
(2) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
(3) Model A300 B4-605R and B4-622R airplanes.
(4) Model A300 F4-605R and F4-622R airplanes.
(5) Model A300 C4-605R Variant F airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of cracks initiating at the
upper radius of frame (FR) 47 and a determination that the current
inspection procedure is not reliable in detecting certain cracking
of the forward fitting of FR 47. We are issuing this AD to detect
and correct fatigue cracking of the FR 47 forward fitting upper
radius on the left-hand and right-hand sides of the fuselage, which
could propagate and result in reduced structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections
Except as required by paragraph (h) of this AD: Before exceeding
10,000 flight cycles since first flight of the airplane or within 30
days after the effective date of this AD, whichever occurs later, do
a special detailed inspection (SDI) for cracking of the FR 47
forward fitting upper radius on the left-hand and right-hand sides
of the fuselage, in accordance with the Accomplishment Instructions
of the applicable Airbus service information specified in paragraphs
(g)(1) and (g)(2) of this AD. Repeat the inspection thereafter at
intervals not to exceed 4,150 flight cycles, except as required by
paragraph (j) of this AD.
(1) Airbus Service Bulletin A300-53-0246, Revision 08, including
Appendix 1, dated April 13, 2016.
(2) Airbus Service Bulletin A300-53-6029, Revision 12, including
Appendix 1, dated April 13, 2016.
(h) Initial Inspection for Airplanes Previously Inspected
For airplanes previously inspected as specified in the
applicable Airbus service information specified in paragraphs (h)(1)
through (h)(6) of this AD and on which no cracking was found: Within
4,150 flight cycles after the most recent inspection, do the
inspection for cracking of the FR 47 forward fitting upper radius
required by paragraph (g) of this AD.
(1) Airbus Service Bulletin A300-53-0246, Revision 06, dated
October 19, 2005.
(2) Airbus Service Bulletin A300-53-0246, Revision 07, dated
September 9, 2008.
(3) Airbus Service Bulletin A300-53-6029, Revision 08, dated
October 19, 2005.
(4) Airbus Service Bulletin A300-53-6029, Revision 09, dated
September 9, 2008.
(5) Airbus Service Bulletin A300-53-6029, Revision 10, dated
July 9, 2009.
(6) Airbus Service Bulletin A300-53-6029, Revision 11, dated
September 28, 2009.
(i) Inspections for Airplanes With Abnormal Load Events
For airplanes on which any crack was found during any inspection
done as specified in Airbus Service Bulletin A300-53-0246 or Airbus
Service Bulletin A300-53-6029, as applicable, and on which any
abnormal load event, such as hard landing or flight in excessive
turbulence, occurred within 3 months before the effective date of
this AD or occurs on or after the effective date of this AD: Within
3 months after each event, accomplish an SDI for cracking of the FR
47 forward fitting upper radius, left-hand and right-hand sides of
the fuselage, in accordance with the applicable Accomplishment
Instructions of the Airbus service information specified in
paragraphs (g)(1) or (g)(2) of this AD. If, during this 3-month
period, another abnormal load event occurs, and if no SDI has yet
been accomplished, before further flight after the second event,
obtain corrective action instructions from the Manager,
International Section, Transport Standards Branch, FAA; or the
European Aviation Safety Agency (EASA); or Airbus's EASA Design
Organization Approval (DOA), and accomplish those instructions
accordingly.
(j) Corrective Actions for Airplanes With Cracks
If, during any SDI as required by paragraph (g), (h), or (i) of
this AD, any crack is found: Before further flight, do the
applicable related investigative and corrective actions, in
accordance with the Accomplishment Instructions of the applicable
Airbus service information specified in paragraph (g)(1) or (g)(2)
of this AD, and obtain additional corrective action instructions
from the Manager, International Section, Transport Standards Branch,
FAA; or EASA; or Airbus's EASA DOA, and accomplish those
instructions accordingly before further flight.
(k) Reporting
Submit a report of the findings (both positive and negative) of
each SDI inspection required by paragraphs (g), (h), and (i) of this
AD to Airbus Service Bulletin Reporting Online Application on Airbus
World (https://w3.airbus.com/), 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) Terminating Action for AD 2007-26-14
Accomplishing any inspection required by paragraph (g) or (h) of
this AD terminates all requirements of AD 2007-26-14 for the
inspected airplane.
(m) 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
[[Page 39523]]
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 (n)(2) of
this AD. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your
appropriate principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office/
certificate holding district office.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA
DOA. If approved by the DOA, the approval must include the DOA-
authorized signature.
(3) Reporting Requirements: 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 5
minutes 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.
(n) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2016-0150, dated July 25, 2016, for related
information. This MCAI may be found in the AD docket on the Internet
at https://www.regulations.gov by searching for and locating Docket
No. FAA-2017-0520.
(2) For more information about this AD, contact Dan Rodina,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone:
425-227-2125; fax: 425-227-1149.
(o) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A300-53-0246, Revision 08, including
Appendix 1, dated April 13, 2016.
(ii) Airbus Service Bulletin A300-53-6029, Revision 12,
including Appendix 1, dated April 13, 2016.
(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.
(4) You may view this service information at the FAA, Transport
Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information
on the availability of this material at the FAA, call 425-227-1221.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on August 8, 2017.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2017-17203 Filed 8-18-17; 8:45 am]
BILLING CODE 4910-13-P