Airworthiness Directives; Airbus Airplanes, 47696-47699 [2016-17014]
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Federal Register / Vol. 81, No. 141 / Friday, July 22, 2016 / Rules and Regulations
correct the unsafe condition on these
products.
(f) Compliance
Comply with paragraphs (g)(1) through (2)
of this AD using the following service
bulletins within the compliance times
specified below, unless already done:
(1) For Models SA26–T and SA26–AT: M7
Aerospace LLC Service Bulletin (SB) 26–27–
002, dated October 8, 2015;
(2) For Models SA226–AT, SA226–T,
SA226–T(B), and SA226–TC: M7 Aerospace
LLC SB 226–27–078, dated October 8, 2015;
(3) For Models SA227–AC(C–26A), SA227–
AT, SA227–BC(C–26A), and SA227–TT: M7
Aerospace LLC SB 227–27–058, dated
October 8, 2015; or
(4) For Models SA227–CC and SA227–DC
(C–26B): M7 Aerospace LLC SB CC7–27–030,
dated October 8, 2015.
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(g) Actions
(1) For all airplanes: Within the next 2,000
hours time-in-service (TIS) after [insert date
35 days after date of publication in the
Federal Register] (the effective date of this
AD) or no later than when the airplane
accumulates 20,000 hours TIS, whichever
occurs later, do an initial inspection of the
cockpit control column horizontal tube for
cracks following the Accomplishment
Instructions in section 2. of the service
bulletins identified in paragraphs (f)(1), (2),
(3), or (4) of this AD, as applicable; and
repetitively inspect as follows:
(i) For airplanes with less than 35,000
hours TIS as of [insert date 35 days after date
of publication in the Federal Register] (the
effective date of this AD): Repetitively
inspect the cockpit control column
horizontal tube for cracks every 5,000 hours
TIS until the airplane reaches 35,000 hours
TIS at which time do the inspection within
2,000 hours TIS from the last inspection or
within the next 100 hours TIS, whichever
occurs later, and then thereafter at intervals
not to exceed 2,000 hours TIS.
(ii) For airplanes with 35,000 hours TIS or
more as of [insert date 35 days after date of
publication in the Federal Register] (the
effective date of this AD): Repetitively
inspect the cockpit control column
horizontal tube for cracks every 2,000 hours
TIS.
(2) For all airplanes: If any cracks are
found following the inspections required in
paragraphs (g)(1), (g)(1)(i), or (ii), as
applicable, before further flight, repair the
control column following the
Accomplishment Instructions in section 2. of
the service bulletins identified in paragraphs
(f)(1), (2), (3), or (4), as applicable, of this AD.
Note to paragraph (g)(1) through (2) of this
AD: The reporting of information requested
in paragraph 2.H. of the Accomplishment
Instructions in the service bulletins
identified in paragraphs (f)(1), (2), (3), and (4)
of this AD is not a required action of this AD.
(h) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Fort Worth Airplane
Certification Office, 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
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request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in
paragraph (j) of this AD.
(2) 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.
DEPARTMENT OF TRANSPORTATION
(i) Related Information
Airworthiness Directives; Airbus
Airplanes
For more information about this AD,
contact Andrew McAnaul, Aerospace
Engineer, FAA, ASW–143 (c/o San Antonio
MIDO), 10100 Reunion Place, Suite 650, San
Antonio, Texas 78216; phone: (210) 308–
3365; fax: (210) 308–3370; email:
andrew.mcanaul@faa.gov.
(j) 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 the AD specifies otherwise.
(i) M7 Aerospace LLC Service Bulletin (SB)
26–27–002, dated October 8, 2015;
(ii) M7 Aerospace LLC SB 226–27–078,
dated October 8, 2015;
(iii) M7 Aerospace LLC SB 227–27–058,
dated October 8, 2015; or
(iv) M7 Aerospace LLC SB CC7–27–030,
dated October 8, 2015.
(3) For service information identified in
this AD, contact M7 Aerospace LLC, 10823
NE Entrance Road, San Antonio, Texas
78216; phone: (210) 824–9421; fax: (210)
804–7766; Internet: https://www.elbitsystemsus.com; email: MetroTech@
M7Aerospace.com.
(4) You may view this referenced service
information at the FAA, Small Airplane
Directorate, 901 Locust, Kansas City,
Missouri 64106. For information on the
availability of this material at the FAA, call
816–329–4148.
(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 Kansas City, Missouri, on July 13,
2016.
Pat Mullen,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2016–17039 Filed 7–21–16; 8:45 am]
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–3993; Directorate
Identifier 2015–NM–065–AD; Amendment
39–18592; AD 2016–15–01]
RIN 2120–AA64
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Airbus Model A300 series airplanes;
Model A300 B4–600, B4–600R, F4–600R
series airplanes, and Model A300 C4–
605R Variant F airplanes (collectively
called Model A300–600 series
airplanes); and Model A310 series
airplanes. This AD was prompted by
reports of partial loss of no-back brake
(NBB) efficiency on the trimmable
horizontal stabilizer actuator (THSA).
This AD requires an inspection to
determine THSA part numbers, serial
numbers, and flight cycles on certain
THSAs; and repetitive replacement of
certain THSAs. We are issuing this AD
to prevent loss of THSA NBB efficiency,
which, in conjunction with the inability
of the power gear to keep the ball screw
in its last commanded position, could
lead to an uncommanded movement of
the horizontal stabilizer, possibly
resulting in loss of control of the
airplane.
SUMMARY:
This AD is effective August 26,
2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of August 26, 2016.
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 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–2016–3993.
DATES:
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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–
3993; 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 Branch, ANM–116,
Transport Airplane Directorate, 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 all Airbus Model A300 series
airplanes; Model A300 B4–600, B4–
600R, F4–600R series airplanes, and
Model A300 C4–605R Variant F
airplanes (collectively called Model
A300–600 series airplanes); and Model
A310 series airplanes. The NPRM
published in the Federal Register on
March 7, 2016 (81 FR 11690) (‘‘the
NPRM’’). The NPRM was prompted by
reports of partial loss of NBB efficiency
on the THSA. The NPRM proposed to
require an inspection to determine
THSA part numbers, serial numbers,
and flight cycles on certain THSAs; and
repetitive replacement for certain
THSAs. We are issuing this AD to
prevent loss of THSA NBB efficiency,
which, in conjunction with the inability
of the power gear to keep the ball screw
in its last commanded position, could
lead to an uncommanded movement of
the horizontal stabilizer, possibly
resulting in loss of control 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 2015–0081,
dated May 7, 2015 (referred to after this
as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
on all Airbus Model A300 series
airplanes; Model A300 B4–600, B4–
600R, F4–600R series airplanes, and
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Model A300 C4–605R Variant F
airplanes (collectively called Model
A300–600 series airplanes); and Model
A310 series airplanes. The MCAI states:
During endurance qualification tests on a
Trimmable Horizontal Stabilizer Actuator
(THSA) concerning another aeroplane type, a
partial loss of the no-back brake (NBB)
efficiency was experienced. Investigation
results concluded that this partial loss of
braking efficiency in some specific
aerodynamic load conditions was due to
polishing and auto-contamination of the NBB
carbon friction disks.
Due to design similarity on the A300–600,
A300–600ST and A310 fleet, the same tests
were initiated by the THSA manufacturer on
certain type THSA, sampled from the field.
Subject tests confirmed that THSA Part
Number (P/N) 47142 series, as installed on
the A300–600, A300–600ST and A310 fleet,
are also affected by this partial loss of NBB
efficiency.
This condition, if not detected and
corrected, and in conjunction with the power
gear not able to keep the ball screw in its last
commanded position, could potentially lead
to an uncommanded movement of the
Horizontal Stabilizer, possibly resulting in
loss of control of the aeroplane.
For the reasons described above, this
[EASA] AD requires the removal from service
of each affected THSA, with the intent of inshop NBB carbon disk replacement.
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–2016–
3993.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Support for the NPRM
The Airline Pilots Association
International stated that it fully supports
the intent of the NPRM.
Requests To Revise Compliance Date
Airbus, FedEx Express, and United
Parcel Service requested that we revise
the compliance date in paragraph (j)(3)
of the proposed AD from February 1,
2018, to February 1, 2019. The
commenters stated that this revision
would match the MCAI.
We agree with the commenters’
request. This was a typographical error.
Our intent was to match the MCAI. We
have revised paragraph (j)(3) of this AD
accordingly.
Request To Allow Maintenance Records
Review
FedEx Express requested that we
allow a review of the operator’s
maintenance records to determine the
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47697
part number and serial number of the
THSA specified in paragraph (h)(1) of
the proposed AD. FedEx Express stated
that this review would accomplish the
same intent as a physical inspection of
the THSA.
We agree with the commenter’s
request. We have revised paragraph
(h)(1) of this AD to allow doing a review
of airplane maintenance records in lieu
of the THSA inspection if the part
number and serial number of the THSA
can be conclusively determined from
that review.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and 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.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Related Service Information Under 1
CFR Part 51
Airbus has issued Airbus Service
Bulletin A300–27–6070, dated February
17, 2015; and Airbus Service Bulletin
A310–27–2106, dated February 17,
2015. This service information describes
procedures for inspection and
replacement of the THSA.
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 152
airplanes of U.S. registry.
We also estimate that it would take
about 27 work-hours per product to
comply with the basic requirements of
this AD. The average labor rate is $85
per work-hour. Required parts would
cost about $590,000 per product. Based
on these figures, we estimate the cost of
this AD on U.S. operators to be
$90,028,840, or $592,295 per product.
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
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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.
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§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2016–15–01 Airbus: Amendment 39–18592.
Docket No. FAA–2016–3993; Directorate
Identifier 2015–NM–065–AD.
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(a) Effective Date
This AD is effective August 26, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes
identified in paragraphs (c)(1) through (c)(6)
of this AD, certificated in any category, all
manufacturer serial numbers.
(1) Airbus Model A300 B2–1A, B2–1C,
B2K–3C, B2–203, B4–2C, B4–103, and B4–
203 airplanes.
(2) Airbus Model A300 B4–601, B4–603,
B4–620, and B4–622 airplanes.
(3) Airbus Model A300 B4–605R and B4–
622R airplanes.
(4) Airbus Model A300 F4–605R and F4–
622R airplanes.
(5) Airbus Model A300 C4–605R Variant F
airplanes.
(6) Airbus Model A310–203, –204, –221,
–222, –304, –322, –324, and –325 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight controls.
(e) Reason
This AD was prompted by reports of partial
loss of no-back brake (NBB) efficiency on the
trimmable horizontal stabilizer actuator
(THSA). We are issuing this AD to prevent
loss of THSA NBB efficiency, which, in
conjunction with the inability of the power
gear to keep the ball screw in its last
commanded position, could lead to an
uncommanded movement of the horizontal
stabilizer, possibly resulting in loss of control
of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Affected THSAs
THSAs affected by the requirements of this
AD have part numbers (P/Ns) 47142–403,
47142–413, 47142–414, and 47142–423.
Note 1 to paragraph (g) of this AD: FAA
AD 2011–15–08, Amendment 39–16755 (76
FR 42029, July 18, 2011), requires installation
of three secondary retention plates for the
gimbal bearings on the THSA upper primary
attachment, which involved a THSA part
number change from the –300 series to the
–400 series.
Note 2 to paragraph (g) of this AD: The life
limits specified in Part 4 of the airworthiness
limitations section are still relevant for the
affected THSA. This AD addresses a
replacement limit for the NBB disks installed
on the THSA, not the life limit for the THSA
itself.
(h) Inspection for Affected THSAs, Flight
Cycles, and THSA Replacement
Before each date and before exceeding the
corresponding THSA flight-cycle limits
specified in paragraphs (j)(1), (j)(2), and (j)(3)
of this AD, do the actions specified in
paragraphs (h)(1) and (h)(2) of this AD; and
before exceeding the flight-cycle limit
corresponding to each date as specified in
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paragraphs (j)(1), (j)(2), and (j)(3) of this AD,
do the actions specified in paragraph (i) of
this AD.
(1) Do an inspection of the THSA to
determine the part number and serial
number. A review of airplane maintenance
records is acceptable in lieu of this
inspection if the part number and serial
number of the THSA can be conclusively
determined from that review.
(2) Do an inspection of the airplane
maintenance records to determine the flight
cycles accumulated on each affected THSA
since first installation on an airplane, or
since last NBB replacement, whichever is
later. If no maintenance records conclusively
identifying the last NBB disk replacement are
available, the flight cycles accumulated since
first installation of the THSA on an airplane
apply.
(i) THSA Replacement
By each date specified in paragraphs (j)(1),
(j)(2), and (j)(3) of this AD, for those affected
THSAs having reached or exceeded the
corresponding number of flight cycles
specified in paragraphs (j)(1), (j)(2), and (j)(3)
of this AD, replace the THSA with a
serviceable unit, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–27–6070, dated
February 17, 2015; or Airbus Service Bulletin
A310–27–2106, dated February 17, 2015, as
applicable.
(j) Compliance Dates and THSA Flight-Cycle
Limits
Paragraphs (j)(1), (j)(2), and (j)(3) of this AD
specify compliance dates and THSA flightcycle limits for accomplishing the actions
required by paragraphs (h) and (i) of this AD.
(1) As of 30 days after the effective date of
this AD: The affected THSA flight-cycle limit
is 30,000 flight cycles since first installation
of the THSA on an airplane, or since last
NBB replacement, whichever is later.
(2) As of February 1, 2017: The affected
THSA flight-cycle limit is 20,000 flight cycles
since first installation of the THSA on an
airplane, or since last NBB replacement,
whichever is later.
(3) As of February 1, 2019: The affected
THSA flight-cycle limit is 14,600 flight cycles
since first installation of the THSA on an
airplane, or since last NBB replacement,
whichever is later.
(k) Serviceable THSA Definition
For the purpose of this AD, a serviceable
THSA is a unit identified in paragraph (k)(1)
or (k)(2) of this AD.
(1) A THSA identified in paragraph (g) of
this AD that, as of each date specified in
paragraphs (j)(1), (j)(2), and (j)(3) of this AD,
has not exceeded the flight-cycle limits
specified in paragraphs (j)(1), (j)(2), and (j)(3)
of this AD since first installation of the THSA
on an airplane, or since the last NBB disk
replacement, whichever is later.
(2) A THSA with a different part number
(e.g., a THSA that is not identified in
paragraph (g) of this AD) that is not affected
by the requirements of this AD.
(l) THSA Replacements
As of each date and before exceeding the
flight-cycle limit corresponding to each date
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specified in paragraphs (j)(1), (j)(2), and (j)(3)
of this AD: Replace each affected THSA with
a serviceable unit, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A300–27–6070, dated
February 17, 2015; or Airbus Service Bulletin
A310–27–2106, dated February 17, 2015.
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(m) Parts Installation Limitation
Before each date specified in paragraphs
(j)(1), (j)(2), and (j)(3) of this AD, an operator
may install an affected THSA on an airplane,
provided that the unit has not exceeded the
corresponding number of flight cycles
specified in paragraphs (j)(1), (j)(2), and (j)(3)
of this AD, since first installation on an
airplane, or since last NBB replacement,
whichever is later.
(n) 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 Dan
Rodina, Aerospace Engineer, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, 1601 Lind Avenue SW.,
Renton, WA 98057–3356; telephone: 425–
227–2125; fax: 425–227–1149. 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. The AMOC approval letter
must specifically reference this AD.
(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 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.
(3) 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.
(o) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
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2015–0081, dated May 7, 2015, 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–2016–3993.
(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 A300–27–6070,
dated February 17, 2015.
(ii) Airbus Service Bulletin A310–27–2106,
dated February 17, 2015.
(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 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 July 11,
2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–17014 Filed 7–21–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 91
[Docket No.: FAA–2014–0225; Amdt. No.
91–331C]
RIN 2120–AK78
Extension of the Prohibition Against
Certain Flights in the Simferopol
(UKFV) and Dnipropetrovsk (UKDV)
Flight Information Regions (FIRs);
Technical Amendment
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; technical
amendment.
AGENCY:
On October 27, 2015, the
Federal Aviation Administration (FAA)
published a final rule extending the
SUMMARY:
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
47699
prohibition against certain flight
operations in the Simferopol (UKFV)
and Dnipropetrovsk (UKDV) flight
information regions (FIRs) by all United
States (U.S.) air carriers; U.S.
commercial operators; persons
exercising the privileges of a U.S.
airman certificate, except when such
persons are operating a U.S.-registered
aircraft for a foreign air carrier; and
operators of U.S.-registered civil aircraft,
except when such operators are foreign
air carriers. The State Aviation
Administration of Ukraine conducted
and completed an airspace restructuring
that altered the Simferopol (UKFV) and
Dnipropetrovsk (UKDV) Flight
Information Region (FIR) altitude
structure specified in the final rule. To
address the Ukraine airspace
restructuring and provide additional
clarity, this technical amendment
specifically identifies the prohibited
airspace in which Special Federal
Aviation Regulation (SFAR) 113,
applies, with inclusive altitudes and
lateral limitations (latitude and
longitude coordinates).
DATES: This final rule is effective on July
21, 2016.
FOR FURTHER INFORMATION CONTACT:
Michael Filippell, Air Transportation
Division, AFS–220, Flight Standards
Service, Federal Aviation
Administration, 800 Independence
Avenue SW., Washington, DC 20591;
telephone: 202–267–8166; email:
michael.e.filippell@faa.gov.
SUPPLEMENTARY INFORMATION:
I. Good Cause for Immediate Adoption
Section 553(b)(3)(B) of the
Administrative Procedure Act (APA) (5
U.S.C.) authorizes agencies to dispense
with notice and comment procedures
for rules when the agency for ‘‘good
cause’’ finds that those procedures are
‘‘impracticable, unnecessary, or contrary
to the public interest.’’ Under this
section, an agency, upon finding good
cause, may issue a final rule without
seeking comment prior to the
rulemaking.
The FAA finds that good cause exists
under APA section 553(b)(3)(B) for this
technical amendment to published
without public notice and comment
because this amendment is limited to
providing additional clarity concerning
specific airspace subject to the existing
SFAR restriction, by adding latitude and
longitude coordinates in lieu of the
names for the FIRs.
In addition, section 553(d)(3) of the
Administrative Procedure Act requires
publication of a substantive rule must
be made not less than 30 days before the
effective date except when the agency
E:\FR\FM\22JYR1.SGM
22JYR1
]]>Agencies
[Federal Register Volume 81, Number 141 (Friday, July 22, 2016)]
[Rules and Regulations]
[Pages 47696-47699]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-17014]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-3993; Directorate Identifier 2015-NM-065-AD;
Amendment 39-18592; AD 2016-15-01]
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 A300 series airplanes; Model A300 B4-600, B4-600R, F4-600R
series airplanes, and Model A300 C4-605R Variant F airplanes
(collectively called Model A300-600 series airplanes); and Model A310
series airplanes. This AD was prompted by reports of partial loss of
no-back brake (NBB) efficiency on the trimmable horizontal stabilizer
actuator (THSA). This AD requires an inspection to determine THSA part
numbers, serial numbers, and flight cycles on certain THSAs; and
repetitive replacement of certain THSAs. We are issuing this AD to
prevent loss of THSA NBB efficiency, which, in conjunction with the
inability of the power gear to keep the ball screw in its last
commanded position, could lead to an uncommanded movement of the
horizontal stabilizer, possibly resulting in loss of control of the
airplane.
DATES: This AD is effective August 26, 2016.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of August 26,
2016.
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 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-2016-3993.
[[Page 47697]]
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-
3993; 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 Branch, ANM-116, Transport Airplane Directorate, 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 all Airbus Model A300
series airplanes; Model A300 B4-600, B4-600R, F4-600R series airplanes,
and Model A300 C4-605R Variant F airplanes (collectively called Model
A300-600 series airplanes); and Model A310 series airplanes. The NPRM
published in the Federal Register on March 7, 2016 (81 FR 11690) (``the
NPRM''). The NPRM was prompted by reports of partial loss of NBB
efficiency on the THSA. The NPRM proposed to require an inspection to
determine THSA part numbers, serial numbers, and flight cycles on
certain THSAs; and repetitive replacement for certain THSAs. We are
issuing this AD to prevent loss of THSA NBB efficiency, which, in
conjunction with the inability of the power gear to keep the ball screw
in its last commanded position, could lead to an uncommanded movement
of the horizontal stabilizer, possibly resulting in loss of control 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
2015-0081, dated May 7, 2015 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition on all Airbus Model A300 series airplanes; Model A300
B4-600, B4-600R, F4-600R series airplanes, and Model A300 C4-605R
Variant F airplanes (collectively called Model A300-600 series
airplanes); and Model A310 series airplanes. The MCAI states:
During endurance qualification tests on a Trimmable Horizontal
Stabilizer Actuator (THSA) concerning another aeroplane type, a
partial loss of the no-back brake (NBB) efficiency was experienced.
Investigation results concluded that this partial loss of braking
efficiency in some specific aerodynamic load conditions was due to
polishing and auto-contamination of the NBB carbon friction disks.
Due to design similarity on the A300-600, A300-600ST and A310
fleet, the same tests were initiated by the THSA manufacturer on
certain type THSA, sampled from the field. Subject tests confirmed
that THSA Part Number (P/N) 47142 series, as installed on the A300-
600, A300-600ST and A310 fleet, are also affected by this partial
loss of NBB efficiency.
This condition, if not detected and corrected, and in
conjunction with the power gear not able to keep the ball screw in
its last commanded position, could potentially lead to an
uncommanded movement of the Horizontal Stabilizer, possibly
resulting in loss of control of the aeroplane.
For the reasons described above, this [EASA] AD requires the
removal from service of each affected THSA, with the intent of in-
shop NBB carbon disk replacement.
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-2016-
3993.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response to each comment.
Support for the NPRM
The Airline Pilots Association International stated that it fully
supports the intent of the NPRM.
Requests To Revise Compliance Date
Airbus, FedEx Express, and United Parcel Service requested that we
revise the compliance date in paragraph (j)(3) of the proposed AD from
February 1, 2018, to February 1, 2019. The commenters stated that this
revision would match the MCAI.
We agree with the commenters' request. This was a typographical
error. Our intent was to match the MCAI. We have revised paragraph
(j)(3) of this AD accordingly.
Request To Allow Maintenance Records Review
FedEx Express requested that we allow a review of the operator's
maintenance records to determine the part number and serial number of
the THSA specified in paragraph (h)(1) of the proposed AD. FedEx
Express stated that this review would accomplish the same intent as a
physical inspection of the THSA.
We agree with the commenter's request. We have revised paragraph
(h)(1) of this AD to allow doing a review of airplane maintenance
records in lieu of the THSA inspection if the part number and serial
number of the THSA can be conclusively determined from that review.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and 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.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
Airbus has issued Airbus Service Bulletin A300-27-6070, dated
February 17, 2015; and Airbus Service Bulletin A310-27-2106, dated
February 17, 2015. This service information describes procedures for
inspection and replacement of the THSA.
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 152 airplanes of U.S. registry.
We also estimate that it would take about 27 work-hours per product
to comply with the basic requirements of this AD. The average labor
rate is $85 per work-hour. Required parts would cost about $590,000 per
product. Based on these figures, we estimate the cost of this AD on
U.S. operators to be $90,028,840, or $592,295 per product.
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
[[Page 47698]]
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):
2016-15-01 Airbus: Amendment 39-18592. Docket No. FAA-2016-3993;
Directorate Identifier 2015-NM-065-AD.
(a) Effective Date
This AD is effective August 26, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs
(c)(1) through (c)(6) of this AD, certificated in any category, all
manufacturer serial numbers.
(1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-
103, and B4-203 airplanes.
(2) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622
airplanes.
(3) Airbus Model A300 B4-605R and B4-622R airplanes.
(4) Airbus Model A300 F4-605R and F4-622R airplanes.
(5) Airbus Model A300 C4-605R Variant F airplanes.
(6) Airbus Model A310-203, -204, -221, -222, -304, -322, -324,
and -325 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
controls.
(e) Reason
This AD was prompted by reports of partial loss of no-back brake
(NBB) efficiency on the trimmable horizontal stabilizer actuator
(THSA). We are issuing this AD to prevent loss of THSA NBB
efficiency, which, in conjunction with the inability of the power
gear to keep the ball screw in its last commanded position, could
lead to an uncommanded movement of the horizontal stabilizer,
possibly resulting in loss of control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Affected THSAs
THSAs affected by the requirements of this AD have part numbers
(P/Ns) 47142-403, 47142-413, 47142-414, and 47142-423.
Note 1 to paragraph (g) of this AD: FAA AD 2011-15-08,
Amendment 39-16755 (76 FR 42029, July 18, 2011), requires
installation of three secondary retention plates for the gimbal
bearings on the THSA upper primary attachment, which involved a THSA
part number change from the -300 series to the -400 series.
Note 2 to paragraph (g) of this AD: The life limits specified
in Part 4 of the airworthiness limitations section are still
relevant for the affected THSA. This AD addresses a replacement
limit for the NBB disks installed on the THSA, not the life limit
for the THSA itself.
(h) Inspection for Affected THSAs, Flight Cycles, and THSA Replacement
Before each date and before exceeding the corresponding THSA
flight-cycle limits specified in paragraphs (j)(1), (j)(2), and
(j)(3) of this AD, do the actions specified in paragraphs (h)(1) and
(h)(2) of this AD; and before exceeding the flight-cycle limit
corresponding to each date as specified in paragraphs (j)(1),
(j)(2), and (j)(3) of this AD, do the actions specified in paragraph
(i) of this AD.
(1) Do an inspection of the THSA to determine the part number
and serial number. A review of airplane maintenance records is
acceptable in lieu of this inspection if the part number and serial
number of the THSA can be conclusively determined from that review.
(2) Do an inspection of the airplane maintenance records to
determine the flight cycles accumulated on each affected THSA since
first installation on an airplane, or since last NBB replacement,
whichever is later. If no maintenance records conclusively
identifying the last NBB disk replacement are available, the flight
cycles accumulated since first installation of the THSA on an
airplane apply.
(i) THSA Replacement
By each date specified in paragraphs (j)(1), (j)(2), and (j)(3)
of this AD, for those affected THSAs having reached or exceeded the
corresponding number of flight cycles specified in paragraphs
(j)(1), (j)(2), and (j)(3) of this AD, replace the THSA with a
serviceable unit, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A300-27-6070, dated February 17, 2015; or
Airbus Service Bulletin A310-27-2106, dated February 17, 2015, as
applicable.
(j) Compliance Dates and THSA Flight-Cycle Limits
Paragraphs (j)(1), (j)(2), and (j)(3) of this AD specify
compliance dates and THSA flight-cycle limits for accomplishing the
actions required by paragraphs (h) and (i) of this AD.
(1) As of 30 days after the effective date of this AD: The
affected THSA flight-cycle limit is 30,000 flight cycles since first
installation of the THSA on an airplane, or since last NBB
replacement, whichever is later.
(2) As of February 1, 2017: The affected THSA flight-cycle limit
is 20,000 flight cycles since first installation of the THSA on an
airplane, or since last NBB replacement, whichever is later.
(3) As of February 1, 2019: The affected THSA flight-cycle limit
is 14,600 flight cycles since first installation of the THSA on an
airplane, or since last NBB replacement, whichever is later.
(k) Serviceable THSA Definition
For the purpose of this AD, a serviceable THSA is a unit
identified in paragraph (k)(1) or (k)(2) of this AD.
(1) A THSA identified in paragraph (g) of this AD that, as of
each date specified in paragraphs (j)(1), (j)(2), and (j)(3) of this
AD, has not exceeded the flight-cycle limits specified in paragraphs
(j)(1), (j)(2), and (j)(3) of this AD since first installation of
the THSA on an airplane, or since the last NBB disk replacement,
whichever is later.
(2) A THSA with a different part number (e.g., a THSA that is
not identified in paragraph (g) of this AD) that is not affected by
the requirements of this AD.
(l) THSA Replacements
As of each date and before exceeding the flight-cycle limit
corresponding to each date
[[Page 47699]]
specified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD:
Replace each affected THSA with a serviceable unit, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A300-27-6070, dated February 17, 2015; or Airbus Service Bulletin
A310-27-2106, dated February 17, 2015.
(m) Parts Installation Limitation
Before each date specified in paragraphs (j)(1), (j)(2), and
(j)(3) of this AD, an operator may install an affected THSA on an
airplane, provided that the unit has not exceeded the corresponding
number of flight cycles specified in paragraphs (j)(1), (j)(2), and
(j)(3) of this AD, since first installation on an airplane, or since
last NBB replacement, whichever is later.
(n) 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 Dan Rodina,
Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone: 425-227-2125; 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) 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.
(3) 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.
(o) Related Information
Refer to Mandatory Continuing Airworthiness Information (MCAI)
EASA AD 2015-0081, dated May 7, 2015, 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-
2016-3993.
(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 A300-27-6070, dated February 17,
2015.
(ii) Airbus Service Bulletin A310-27-2106, dated February 17,
2015.
(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
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 July 11, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-17014 Filed 7-21-16; 8:45 am]
BILLING CODE 4910-13-P
