Airworthiness Directives; Airbus Airplanes, 5362-5365 [2017-00408]
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5362
Federal Register / Vol. 82, No. 11 / Wednesday, January 18, 2017 / Rules and Regulations
www.archives.gov/federal-register/cfr/ibrlocations.html.
and locating Docket No. FAA–2015–
0831.
Issued in Kansas City, Missouri, on January
6, 2017.
Melvin Johnson,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
Examining the AD Docket
[FR Doc. 2017–00502 Filed 1–17–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–0831; Directorate
Identifier 2014–NM–061–AD; Amendment
39–18778; AD 2017–01–11]
RIN 2120–AA64
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 all
Airbus Model A318 and A319 series
airplanes, Model A320–211, –212, –214,
–231, –232, and –233 airplanes, and
Model A321 series airplanes. This AD
was prompted by a report of a rupture
of a main landing gear (MLG) sliding
tube axle. This AD requires
identification of the part number and
serial number of the MLG sliding tubes;
inspection of affected chromium plates
and sliding tube axles for damage; and
replacement of the sliding tube if
necessary. We are issuing this AD to
address the unsafe condition on these
products.
DATES: This AD is effective February 22,
2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of February 22, 2017.
ADDRESSES: For service information
identified in this final rule, contact
Airbus, Airworthiness Office—EIAS, 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
Airplane Directorate, 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
mstockstill on DSK3G9T082PROD with RULES
SUMMARY:
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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–2015–
0831; 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:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1405;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of
proposed rulemaking (SNPRM) to
amend 14 CFR part 39 by adding an AD
that would apply to all Airbus Model
A318 and A319 series airplanes, Model
A320–211, –212, –214, –231, –232, and
–233 airplanes, and Model A321 series
airplanes. The SNPRM published in the
Federal Register on June 28, 2016 (81
FR 41886) (‘‘the SNPRM’’). We preceded
the SNPRM with a notice of proposed
rulemaking (NPRM) that published in
the Federal Register on April 24, 2015
(80 FR 22939) (‘‘the NPRM’’). The
NPRM proposed to require an
inspection to identify the part number
and serial number of the MLG sliding
tubes installed on the airplane; an
inspection of the axle on certain MLG
sliding tubes for damage; and
replacement of the sliding tube if
necessary. The NPRM was prompted by
a report of a rupture of a MLG sliding
tube axle. The SNPRM proposed to
remove certain service information that
does not adequately address the
identified unsafe condition and revise
the compliance method. We are issuing
this AD to detect and correct cracks in
the axle and (partial) detachment of the
axle and wheel from the sliding tube,
which could result in failure of an MLG.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
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Directive 2014–0058, dated March 11,
2014 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for all Airbus
Model A318 and A319 series airplanes,
Model A320–211, –212, –214, –231,
–232, and –233 airplanes, and Model
A321 series airplanes. The MCAI states:
A main landing gear (MLG) sliding tube
axle rupture occurred in service.
Investigation of the affected part showed that
this failure was due to an abnormal grinding
operation during overhaul by a certain
maintenance and repair organization located
in Singapore. A population of MLG sliding
tubes was subsequently identified whose
axles may have been subject to this grinding
operation, which may have resulted in areas
of residual stress on the axles on the MLG
sliding tubes. In addition, the MSN
[manufacturer serial number] of the
aeroplanes which are known to have had the
affected parts installed have been identified.
This condition, if not detected and
corrected, could lead to cracks in the axle
and (partial) detachment of axle and wheel
from the sliding tube, possibly resulting in
failure of a MLG with consequent damage to
the aeroplane and injury to occupants.
To address this potential unsafe condition,
Messier-Bugatti-Dowty, the MLG gear
manufacturer, issued Service Bulletin (SB)
200–32–313 and SB 201–32–62 [both dated
February 25, 2013], providing inspection
instructions and criteria for removal from
service of the affected MLG sliding tubes.
For the reasons described above, this
[EASA] AD requires a one-time Special
Detailed Inspection (SDI) of the axle on the
affected MLG sliding tubes and, depending
on findings, replacement of the MLG sliding
tube.
The SDI includes a detailed visual
inspection of the chromium plate for
damage, and a Barkhausen noise
inspection of the sliding tube axles for
damage.
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–2015–
0831.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the SNPRM 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 SNPRM for
correcting the unsafe condition; and
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Federal Register / Vol. 82, No. 11 / Wednesday, January 18, 2017 / Rules and Regulations
• Do not add any additional burden
upon the public than was already
proposed in the SNPRM.
Related Service Information Under 1
CFR Part 51
Airbus has issued Service Bulletin
A320–32–1416, including Appendix 01,
dated March 10, 2014. This service
information describes procedures for
inspecting MLG axles and brake flanges
by doing a detailed visual inspection of
the chromium plates for damage, a
Barkhausen noise inspection of the
sliding tube axles for damage, and
replacement of affected parts if
necessary. 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 affects 3
airplanes of U.S. registry.
We also estimate that it would take
about 18 work-hours per product to
comply with the basic requirements of
this AD. The average labor rate is $85
per work-hour. Based on these figures,
we estimate the cost of this AD on U.S.
operators to be $4,590, or $1,530 per
product.
In addition, we estimate that any
necessary on-condition actions will take
about 3 work-hours, for a cost of $255
per product. We have received no
definitive data that would enable us to
provide part cost estimates for the oncondition actions specified in this AD.
We have no way of determining the
number of aircraft that might need these
actions.
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.
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
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 adding
the following new airworthiness
directive (AD):
■
2017–01–11 Airbus: Amendment 39–18778;
Docket No. FAA–2015–0831; Directorate
Identifier 2014–NM–061–AD.
(a) Effective Date
This AD is effective February 22, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes
identified in paragraphs (c)(1) through (c)(4)
of this AD, certificated in any category, all
manufacturer serial numbers.
(1) Airbus Model A318–111, –112, –121,
and –122 airplanes.
(2) Airbus Model A319–111, –112, –113,
–114, –115, –131, –132, and –133 airplanes.
(3) Airbus Model A320–211, –212, –214,
–231, –232, and –233 airplanes.
(4) Airbus Model A321–111, –112, –131,
–211, –212, –213, –231, and –232 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 32, Landing gear.
(e) Reason
This AD was prompted by a report of a
rupture of a main landing gear (MLG) sliding
tube axle. We are issuing this AD to detect
and correct cracks in the axle and (partial)
detachment of the axle and wheel from the
sliding tube, which could result in failure of
an MLG.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) MLG Sliding Tube Part Number and
Serial Number Identification
Within 3 months after the effective date of
this AD: Do an inspection to identify the part
number and serial number of the MLG
sliding tubes installed on the airplane. A
review of airplane maintenance records is
acceptable in lieu of this inspection if the
part number and serial number of the MLG
sliding tubes can be conclusively determined
from that review.
(h) Identification of Airplanes Not Affected
by the Requirements of Paragraph (i) of this
AD
An airplane with a manufacturer serial
number (MSN) not listed in figure 1 to
paragraph (h) of this AD is not affected by the
requirements of paragraph (i) of this AD,
provided it can be determined that no MLG
sliding tube having a part number and serial
number listed in table 1 to paragraphs (h), (i),
(k)(1), (k)(2), (l)(1), and (l)(2) of this AD has
been installed on that airplane since first
flight of the airplane.
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FIGURE 1 TO PARAGRAPH (H) OF THIS AD
Affected Airplanes Listed by MSN
0179
0607
0754
0909
1030
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0668
0771
0914
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0296
0704
0799
0925
1070
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0720
0828
0939
1083
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0726
0841
0986
1093
18JAR1
0604
0731
0855
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Federal Register / Vol. 82, No. 11 / Wednesday, January 18, 2017 / Rules and Regulations
FIGURE 1 TO PARAGRAPH (H) OF THIS AD—Continued
1108
1148
1294
TABLE 1 TO PARAGRAPHS (h), (i),
(k)(1), (k)(2), (l)(1), AND (l)(2) OF
THIS AD—AFFECTED MLG SLIDING
TUBES
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Part No.
201160302
201160302
201160302
201371302
201371302
201371302
201371302
201371302
201371302
201371302
201371302
201371302
201371302
201371302
201371302
201371302
201160302
201371304
201371304
201371304
201371304
201371304
201371304
201371304
201371304
201371304
201371304
201371304
201371304
201371304
201371304
201371304
201371304
201371304
201371304
201371304
201371304
201371304
201371304
201371304
201371304
201371304
201371304
201522353
201522350
201522350
201522350
201522350
201522350
201522353
201522353
201522353
201522353
201522353
201383350
201383350
201383350
201383350
201383350
201383350
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Serial No.
78B
1016B11
1144B
B4493
B4513
SS4359
B4530
B4517
B4568
B4498
4490B
B202–4598
B165–4623
B244–4766
B267–4794
B272–4813
1108B
B041–4871
B045–4869
B001–4781
B051–4892
B110–1952
B054–4891
B063–4921
B071–4911
B071–4917
B080–1933
B117–5010
B120–4989
B132–2023
B114–1956
B208–2009
B133–1947
B154–5037
B89 4952
B129–1964
B227–2010
B170–5031
B182–5047
B239–2053
B1401–2856
B1813–3142
B116–5004
B011–149
B014–25
B019–56
B019–57
B021–69
B022–60
B03–111
B03–110
B112–317
B174–351
B179–392
4377B
4393B
B1831
B1832
SS4355B
SS4400B
(i) Inspections
For each MLG sliding tube identified as
required by paragraph (g) of this AD, having
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1356
a part number and serial number listed in
table 1 to paragraphs (h), (i), (k)(1), (k)(2),
(l)(1), and (l)(2) of this AD: Within 3 months
after the effective date of this AD, inspect
affected MLG axles and brake flanges by
doing a detailed visual inspection of the
chromium plates for damage, and a
Barkhausen noise inspection of the sliding
tube axles for damage, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–32–1416, including
Appendix 01, dated March 10, 2014. For
Model A318 series airplanes, use the
procedures specified for Model A319 series
airplanes in Airbus Service Bulletin A320–
32–1416, including Appendix 01, dated
March 10, 2014.
(j) Corrective Action
If, during any inspection required by
paragraph (i) of this AD, any damage is
detected: Before further flight, replace the
MLG sliding tube with a serviceable tube, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
32–1416, including Appendix 01, dated
March 10, 2014. For Model A318 series
airplanes, use the procedures specified for
Model A319 series airplanes in Airbus
Service Bulletin A320–32–1416, including
Appendix 01, dated March 10, 2014.
(k) Definition of Serviceable Sliding Tube
For the purpose of this AD, a serviceable
sliding tube is defined as a sliding tube that
meets the criterion in either paragraph (k)(1)
or (k)(2) of this AD.
(1) A sliding tube having a part number
and serial number not listed in table 1 to
paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and
(l)(2) of this AD.
(2) A sliding tube having a part number
and serial number listed in table 1 to
paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and
(l)(2) of this AD that has passed the
inspections required by paragraph (i) of this
AD.
(l) Parts Installation Prohibitions
(1) For airplanes that have an MLG sliding
tube installed that has a part number and
serial number listed in table 1 to paragraphs
(h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this
AD: After an airplane is returned to service
following accomplishment of the actions
required by paragraphs (g), (h), and (i) of this
AD, no person may install on any airplane an
MLG sliding tube having a part number and
serial number listed in table 1 to paragraphs
(h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this
AD unless that sliding tube has passed the
inspection required by paragraph (i) of this
AD.
(2) For airplanes that, as of the effective
date of this AD, do not have an MLG sliding
tube installed that has a part number and
serial number listed in table 1 to paragraphs
(h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this
AD: No person may install on any airplane
an MLG sliding tube having a part number
and serial number listed in table 1 to
paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and
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2713
2831
(l)(2) of this AD unless that sliding tube has
passed the inspection required by paragraph
(i) of this AD.
(m) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, 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 Branch, send it to ATTN:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–1149.
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. The AMOC approval letter
must specifically reference this AD.
(2) Required for Compliance (RC): 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.
(3) 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 Branch, ANM–
116, Transport Airplane Directorate, 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.
(n) Special Flight Permits
Special flight permits may be issued in
accordance with sections 21.197 and 21.199
of the Federal Aviation Regulations (14 CFR
21.197 and 21.199) to operate the airplane to
a location where the airplane can be
modified (if the operator elects to do so),
provided the MLG remains extended
throughout the flight.
(o) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
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Federal Register / Vol. 82, No. 11 / Wednesday, January 18, 2017 / Rules and Regulations
Airworthiness Directive 2014–0058, dated
March 11, 2014, 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–
2015–0831.
(p) 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 A320–32–1416,
including Appendix 01, dated March 10,
2014.
(ii) Reserved.
(3) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 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 Airplane Directorate,
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 January
4, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–00408 Filed 1–17–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9058; Directorate
Identifier 2016–NM–024–AD; Amendment
39–18771; AD 2017–01–04]
RIN 2120–AA64
Airworthiness Directives; Fokker
Services B.V. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
mstockstill on DSK3G9T082PROD with RULES
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Fokker Services B.V. Model F28 Mark
0100 airplanes. This AD was prompted
by an analysis which determined that,
SUMMARY:
VerDate Sep<11>2014
16:39 Jan 17, 2017
Jkt 241001
for certain areas of the fuselage, the
current threshold of an Airworthiness
Limitations Section inspection is
insufficient to detect early crack
development. This AD requires one time
high and low frequency eddy current
inspections of the affected fuselage skin
for cracks, and repair if necessary. We
are issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective February 22,
2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of February 22, 2017.
ADDRESSES: For service information
identified in this final rule, contact
Fokker Services B.V., Technical
Services Dept., P.O. Box 1357, 2130 EL
Hoofddorp, the Netherlands; telephone:
+31 (0)88–6280–350; fax: +31 (0)88–
6280–111; email: technicalservices@
fokker.com; Internet https://
www.myfokkerfleet.com. You may view
this referenced service information at
the FAA, Transport Airplane
Directorate, 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–2016–
9058.
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–2016–
9058; 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: Tom
Rodriguez, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1137;
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
PO 00000
Frm 00031
Fmt 4700
Sfmt 4700
5365
apply to certain Fokker Services B.V.
Model F28 Mark 0100 airplanes. The
NPRM published in the Federal
Register on September 8, 2016 (81 FR
62029) (‘‘the NPRM’’). The NPRM was
prompted by an analysis which
determined that, for certain areas of the
fuselage, the current threshold of an
Airworthiness Limitations Section
inspection is insufficient to detect early
crack development. The NPRM
proposed to require one time high and
low frequency eddy current inspections
of the affected fuselage skin for cracks,
and repair if necessary. We are issuing
this AD to detect and correct cracks in
the fuselage skin; such cracking could
result in reduced structural integrity of
the fuselage.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive Airworthiness Directive 2016–
0029R1, dated November 17, 2016
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition for certain Fokker Services
B.V. Model F28 Mark 0100 airplanes.
The MCAI states:
A complementary fatigue and damage
tolerance analysis was accomplished by the
design approval holder on the traffic
collision avoidance system (TCAS) antenna
installation on the top of the fuselage
between station (STA) 6805 and STA7305.
Based on the results, it was determined that
for the affected area, the current 58 000 flight
cycles (FC) threshold of Airworthiness
Limitations Section (ALS) inspection task
533001–00–20 and 533028–00–20 (special
detailed inspection of longitudinal lap joints)
is insufficient to timely detect possible crack
development.
This condition, if not detected and
corrected, could affect the structural integrity
of the fuselage in this area.
To address this potential unsafe condition,
Fokker Services published Service Bulletin
(SB) SBF100–53–130 to provide inspection
instructions.
Consequently, EASA issued AD 2016–0029
to require a one-time inspection of the
fuselage skin around the largest TCAS
antenna external doubler and of the
longitudinal lap joint at stringer (STR) 37
between fuselage STA6805 and STA7305.
Since that [EASA] AD was issued, it was
discovered that another ALS inspection task,
533028–00–20, is also related to this subject.
This [EASA] AD is revised to clarify that the
inspection threshold of both ALS inspection
tasks has been re-assessed. It is expected that
a repetitive inspection task will be included
in the ALS, which will cover only the area
close to the TCAS antenna installation. For
the remainder of the affected lap joint, no
change is anticipated and this will therefore
continue to be inspected in accordance with
the existing ALS tasks.
This [EASA] AD is still considered to be
an interim action and further [EASA] AD
E:\FR\FM\18JAR1.SGM
18JAR1
Agencies
[Federal Register Volume 82, Number 11 (Wednesday, January 18, 2017)]
[Rules and Regulations]
[Pages 5362-5365]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-00408]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-0831; Directorate Identifier 2014-NM-061-AD;
Amendment 39-18778; AD 2017-01-11]
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 all
Airbus Model A318 and A319 series airplanes, Model A320-211, -212, -
214, -231, -232, and -233 airplanes, and Model A321 series airplanes.
This AD was prompted by a report of a rupture of a main landing gear
(MLG) sliding tube axle. This AD requires identification of the part
number and serial number of the MLG sliding tubes; inspection of
affected chromium plates and sliding tube axles for damage; and
replacement of the sliding tube if necessary. We are issuing this AD to
address the unsafe condition on these products.
DATES: This AD is effective February 22, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of February 22,
2017.
ADDRESSES: For service information identified in this final rule,
contact Airbus, Airworthiness Office--EIAS, 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 Airplane Directorate, 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-2015-
0831.
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-2015-
0831; 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: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of proposed rulemaking (SNPRM) to
amend 14 CFR part 39 by adding an AD that would apply to all Airbus
Model A318 and A319 series airplanes, Model A320-211, -212, -214, -231,
-232, and -233 airplanes, and Model A321 series airplanes. The SNPRM
published in the Federal Register on June 28, 2016 (81 FR 41886) (``the
SNPRM''). We preceded the SNPRM with a notice of proposed rulemaking
(NPRM) that published in the Federal Register on April 24, 2015 (80 FR
22939) (``the NPRM''). The NPRM proposed to require an inspection to
identify the part number and serial number of the MLG sliding tubes
installed on the airplane; an inspection of the axle on certain MLG
sliding tubes for damage; and replacement of the sliding tube if
necessary. The NPRM was prompted by a report of a rupture of a MLG
sliding tube axle. The SNPRM proposed to remove certain service
information that does not adequately address the identified unsafe
condition and revise the compliance method. We are issuing this AD to
detect and correct cracks in the axle and (partial) detachment of the
axle and wheel from the sliding tube, which could result in failure of
an MLG.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2014-0058, dated March 11, 2014 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model A318
and A319 series airplanes, Model A320-211, -212, -214, -231, -232, and
-233 airplanes, and Model A321 series airplanes. The MCAI states:
A main landing gear (MLG) sliding tube axle rupture occurred in
service. Investigation of the affected part showed that this failure
was due to an abnormal grinding operation during overhaul by a
certain maintenance and repair organization located in Singapore. A
population of MLG sliding tubes was subsequently identified whose
axles may have been subject to this grinding operation, which may
have resulted in areas of residual stress on the axles on the MLG
sliding tubes. In addition, the MSN [manufacturer serial number] of
the aeroplanes which are known to have had the affected parts
installed have been identified.
This condition, if not detected and corrected, could lead to
cracks in the axle and (partial) detachment of axle and wheel from
the sliding tube, possibly resulting in failure of a MLG with
consequent damage to the aeroplane and injury to occupants.
To address this potential unsafe condition, Messier-Bugatti-
Dowty, the MLG gear manufacturer, issued Service Bulletin (SB) 200-
32-313 and SB 201-32-62 [both dated February 25, 2013], providing
inspection instructions and criteria for removal from service of the
affected MLG sliding tubes.
For the reasons described above, this [EASA] AD requires a one-
time Special Detailed Inspection (SDI) of the axle on the affected
MLG sliding tubes and, depending on findings, replacement of the MLG
sliding tube.
The SDI includes a detailed visual inspection of the chromium plate
for damage, and a Barkhausen noise inspection of the sliding tube axles
for damage.
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-2015-
0831.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the SNPRM 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
SNPRM for correcting the unsafe condition; and
[[Page 5363]]
Do not add any additional burden upon the public than was
already proposed in the SNPRM.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A320-32-1416, including Appendix
01, dated March 10, 2014. This service information describes procedures
for inspecting MLG axles and brake flanges by doing a detailed visual
inspection of the chromium plates for damage, a Barkhausen noise
inspection of the sliding tube axles for damage, and replacement of
affected parts if necessary. 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 affects 3 airplanes of U.S. registry.
We also estimate that it would take about 18 work-hours per product
to comply with the basic requirements of this AD. The average labor
rate is $85 per work-hour. Based on these figures, we estimate the cost
of this AD on U.S. operators to be $4,590, or $1,530 per product.
In addition, we estimate that any necessary on-condition actions
will take about 3 work-hours, for a cost of $255 per product. We have
received no definitive data that would enable us to provide part cost
estimates for the on-condition actions specified in this AD. We have no
way of determining the number of aircraft that might need these
actions.
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.
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):
2017-01-11 Airbus: Amendment 39-18778; Docket No. FAA-2015-0831;
Directorate Identifier 2014-NM-061-AD.
(a) Effective Date
This AD is effective February 22, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs
(c)(1) through (c)(4) of this AD, certificated in any category, all
manufacturer serial numbers.
(1) Airbus Model A318-111, -112, -121, and -122 airplanes.
(2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes.
(3) Airbus Model A320-211, -212, -214, -231, -232, and -233
airplanes.
(4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231,
and -232 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 32, Landing
gear.
(e) Reason
This AD was prompted by a report of a rupture of a main landing
gear (MLG) sliding tube axle. We are issuing this AD to detect and
correct cracks in the axle and (partial) detachment of the axle and
wheel from the sliding tube, which could result in failure of an
MLG.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) MLG Sliding Tube Part Number and Serial Number Identification
Within 3 months after the effective date of this AD: Do an
inspection to identify the part number and serial number of the MLG
sliding tubes installed on the airplane. A review of airplane
maintenance records is acceptable in lieu of this inspection if the
part number and serial number of the MLG sliding tubes can be
conclusively determined from that review.
(h) Identification of Airplanes Not Affected by the Requirements of
Paragraph (i) of this AD
An airplane with a manufacturer serial number (MSN) not listed
in figure 1 to paragraph (h) of this AD is not affected by the
requirements of paragraph (i) of this AD, provided it can be
determined that no MLG sliding tube having a part number and serial
number listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2),
(l)(1), and (l)(2) of this AD has been installed on that airplane
since first flight of the airplane.
Figure 1 to Paragraph (h) of This AD
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
Affected Airplanes Listed by MSN
----------------------------------------------------------------------------------------------------------------
0179 0214 0296 0412 0558 0604
0607 0668 0704 0720 0726 0731
0754 0771 0799 0828 0841 0855
0909 0914 0925 0939 0986 1028
1030 1041 1070 1083 1093 1098
[[Page 5364]]
1108 1148 1294 1356 2713 2831
----------------------------------------------------------------------------------------------------------------
Table 1 to Paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of
this AD--Affected MLG Sliding Tubes
------------------------------------------------------------------------
Part No. Serial No.
------------------------------------------------------------------------
201160302............................................... 78B
201160302............................................... 1016B11
201160302............................................... 1144B
201371302............................................... B4493
201371302............................................... B4513
201371302............................................... SS4359
201371302............................................... B4530
201371302............................................... B4517
201371302............................................... B4568
201371302............................................... B4498
201371302............................................... 4490B
201371302............................................... B202-4598
201371302............................................... B165-4623
201371302............................................... B244-4766
201371302............................................... B267-4794
201371302............................................... B272-4813
201160302............................................... 1108B
201371304............................................... B041-4871
201371304............................................... B045-4869
201371304............................................... B001-4781
201371304............................................... B051-4892
201371304............................................... B110-1952
201371304............................................... B054-4891
201371304............................................... B063-4921
201371304............................................... B071-4911
201371304............................................... B071-4917
201371304............................................... B080-1933
201371304............................................... B117-5010
201371304............................................... B120-4989
201371304............................................... B132-2023
201371304............................................... B114-1956
201371304............................................... B208-2009
201371304............................................... B133-1947
201371304............................................... B154-5037
201371304............................................... B89 4952
201371304............................................... B129-1964
201371304............................................... B227-2010
201371304............................................... B170-5031
201371304............................................... B182-5047
201371304............................................... B239-2053
201371304............................................... B1401-2856
201371304............................................... B1813-3142
201371304............................................... B116-5004
201522353............................................... B011-149
201522350............................................... B014-25
201522350............................................... B019-56
201522350............................................... B019-57
201522350............................................... B021-69
201522350............................................... B022-60
201522353............................................... B03-111
201522353............................................... B03-110
201522353............................................... B112-317
201522353............................................... B174-351
201522353............................................... B179-392
201383350............................................... 4377B
201383350............................................... 4393B
201383350............................................... B1831
201383350............................................... B1832
201383350............................................... SS4355B
201383350............................................... SS4400B
------------------------------------------------------------------------
(i) Inspections
For each MLG sliding tube identified as required by paragraph
(g) of this AD, having a part number and serial number listed in
table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2)
of this AD: Within 3 months after the effective date of this AD,
inspect affected MLG axles and brake flanges by doing a detailed
visual inspection of the chromium plates for damage, and a
Barkhausen noise inspection of the sliding tube axles for damage, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-32-1416, including Appendix 01, dated March 10, 2014.
For Model A318 series airplanes, use the procedures specified for
Model A319 series airplanes in Airbus Service Bulletin A320-32-1416,
including Appendix 01, dated March 10, 2014.
(j) Corrective Action
If, during any inspection required by paragraph (i) of this AD,
any damage is detected: Before further flight, replace the MLG
sliding tube with a serviceable tube, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-32-1416,
including Appendix 01, dated March 10, 2014. For Model A318 series
airplanes, use the procedures specified for Model A319 series
airplanes in Airbus Service Bulletin A320-32-1416, including
Appendix 01, dated March 10, 2014.
(k) Definition of Serviceable Sliding Tube
For the purpose of this AD, a serviceable sliding tube is
defined as a sliding tube that meets the criterion in either
paragraph (k)(1) or (k)(2) of this AD.
(1) A sliding tube having a part number and serial number not
listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1),
and (l)(2) of this AD.
(2) A sliding tube having a part number and serial number listed
in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and
(l)(2) of this AD that has passed the inspections required by
paragraph (i) of this AD.
(l) Parts Installation Prohibitions
(1) For airplanes that have an MLG sliding tube installed that
has a part number and serial number listed in table 1 to paragraphs
(h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this AD: After an
airplane is returned to service following accomplishment of the
actions required by paragraphs (g), (h), and (i) of this AD, no
person may install on any airplane an MLG sliding tube having a part
number and serial number listed in table 1 to paragraphs (h), (i),
(k)(1), (k)(2), (l)(1), and (l)(2) of this AD unless that sliding
tube has passed the inspection required by paragraph (i) of this AD.
(2) For airplanes that, as of the effective date of this AD, do
not have an MLG sliding tube installed that has a part number and
serial number listed in table 1 to paragraphs (h), (i), (k)(1),
(k)(2), (l)(1), and (l)(2) of this AD: No person may install on any
airplane an MLG sliding tube having a part number and serial number
listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1),
and (l)(2) of this AD unless that sliding tube has passed the
inspection required by paragraph (i) of this AD.
(m) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, 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 Branch, send it to ATTN: Sanjay
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-1149. 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. The
AMOC approval letter must specifically reference this AD.
(2) Required for Compliance (RC): 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.
(3) 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
Branch, ANM-116, Transport Airplane Directorate, 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.
(n) Special Flight Permits
Special flight permits may be issued in accordance with sections
21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199) to operate the airplane to a location where the airplane
can be modified (if the operator elects to do so), provided the MLG
remains extended throughout the flight.
(o) Related Information
Refer to Mandatory Continuing Airworthiness Information (MCAI)
EASA
[[Page 5365]]
Airworthiness Directive 2014-0058, dated March 11, 2014, 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-2015-0831.
(p) 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 A320-32-1416, including Appendix 01,
dated March 10, 2014.
(ii) Reserved.
(3) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 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
Airplane Directorate, 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 January 4, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-00408 Filed 1-17-17; 8:45 am]
BILLING CODE 4910-13-P