Airworthiness Directives; Airbus Airplanes, 51083-51088 [2014-19708]
Download as PDF
<![CDATA[
Federal Register / Vol. 79, No. 166 / Wednesday, August 27, 2014 / Rules and Regulations
(3) Task 55–21–27–960–802 of the
Canadair Regional Jet Model CL–600–2B19
Aircraft Maintenance Manual, CSP A–001,
Revision 49, dated May 10, 2014.
(j) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York Aircraft
Certification Office (ACO), ANE–170, 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 ACO, send it to ATTN:
Program Manager, Continuing Operational
Safety, FAA, New York ACO, 1600 Stewart
Avenue, Suite 410, Westbury, NY 11590;
telephone 516–228–7300; fax 516–794–5531.
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, New York ACO, ANE–170,
Engine and Propeller Directorate, FAA; or
Transport Canada Civil Aviation (TCCA); or
Bombardier, Inc.’s TCCA Design Approval
Organization (DAO). If approved by the DAO,
the approval must include the DAOauthorized signature.
mstockstill on DSK4VPTVN1PROD with RULES
(k) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
Airworthiness Directive CF–2014–04, dated
January 13, 2014, for related information.
This MCAI may be found in the AD docket
on the Internet at https://www.regulations.
gov/#!documentDetail;D=FAA-2014-01750002.
(2) Service information identified in this
AD that is not incorporated by reference may
be viewed at the addresses specified in
paragraphs (l)(3) and (l)(4) of this AD.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Bombardier Service Bulletin 601R–55–
008, Revision B, dated March 12, 2014.
(ii) Reserved.
(3) For service information identified in
ˆ
this AD, contact Bombardier, Inc., 400 Cote´
Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; telephone 514–855–5000; fax 514–
855–7401; email thd.crj@
aero.bombardier.com; Internet https://
www.bombardier.com.
(4) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
VerDate Mar<15>2010
17:33 Aug 26, 2014
Jkt 232001
information on the availability of this
material at the FAA, call 425–227–1221.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://www.archives.
gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on August
15, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2014–19976 Filed 8–26–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0236; Directorate
Identifier 2013–NM–184–AD; Amendment
39–17937; AD 2014–16–13]
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 A300 series airplanes.
This AD was prompted by our
determination of the need to incorporate
new life limits for the main landing gear
(MLG) barrel assembly, retraction
actuator assembly linkage, and flange
duct. This AD requires revising the
maintenance or inspection program, as
applicable, to include the new life
limits. We are issuing this AD to prevent
reduced structural integrity of the
airplane and possible loss of
controllability of the airplane.
DATES: This AD becomes effective
October 1, 2014.
ADDRESSES: You may examine the AD
docket on the Internet at https://www.
regulations.gov/#!docketDetail;D=FAA2014-0236 or in person at the 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.
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;
SUMMARY:
PO 00000
Frm 00017
Fmt 4700
Sfmt 4700
51083
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.
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. The NPRM published in the
Federal Register on April 17, 2014 (79
FR 21651).
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2013–0210,
dated September 11, 2013 (referred to
after this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
all Airbus Model A300 series airplanes.
The MCAI states:
Some life limits previously defined in
Revision 00 of A300 ALS [airworthiness
limitations section] Part 1 have been removed
[from] that document at Revision 01 and
should normally be included in an ALS Part
4.
At this time, there are no plans to issue an
ALS Part 4 for A300 aeroplanes.
Nevertheless, failure to comply with these
life limits could result in an unsafe
condition.
For the reasons described above, it has
been decided to require the application of
these life limits through a separate [EASA]
AD. Consequently, this [EASA] AD requires
application of life limits applicable to Main
Landing Gear (MLG) barrel assembly,
retraction actuator assembly linkage
assembly and flanged duct which were
previously contained in Airbus ALS Part 1
Revision 00.
EASA AD 2007–0293 [which corresponds
with FAA AD 2009–18–15, Amendment 39–
16011 (74 FR 48143, September 22, 2009)],
which required compliance with the actions
specified in ALS Part 1, will be superseded
by a new [EASA] AD, requiring compliance
with ALS Part 1 at Revision 1.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov/#!documentDetail;
D=FAA-2014-0236-0002.
Comments
We gave the public the opportunity to
participate in developing this AD. We
E:\FR\FM\27AUR1.SGM
27AUR1
51084
Federal Register / Vol. 79, No. 166 / Wednesday, August 27, 2014 / Rules and Regulations
mstockstill on DSK4VPTVN1PROD with RULES
received no comments on the NPRM (79
FR 21651, April 17, 2014) or on the
determination of the cost to the public.
‘‘Contacting the Manufacturer’’
Paragraph in This AD
Since late 2006, we have included a
standard paragraph titled ‘‘Airworthy
Product’’ in all MCAI ADs in which the
FAA develops an AD based on a foreign
authority’s AD.
We have become aware that some
operators have misunderstood or
misinterpreted the Airworthy Product
paragraph to allow the owner/operator
to use messages provided by the
manufacturer as approval of deviations
during the accomplishment of an ADmandated action. The Airworthy
Product paragraph does not approve
messages or other information provided
by the manufacturer for deviations to
the requirements of the AD-mandated
actions. The Airworthy Product
paragraph only addresses the
requirement to contact the manufacturer
for corrective actions for the identified
unsafe condition and does not cover
deviations from other AD requirements.
However, deviations to AD-required
actions are addressed in 14 CFR 39.17,
and anyone may request the approval
for an alternative method of compliance
to the AD-required actions using the
procedures found in 14 CFR 39.19.
To address this misunderstanding and
misinterpretation of the Airworthy
Product paragraph, we have changed the
paragraph and retitled it ‘‘Contacting the
Manufacturer.’’ This paragraph now
clarifies that for any requirement in this
AD to obtain corrective actions from a
manufacturer, the actions must be
accomplished using a method approved
by the FAA, the European Aviation
Safety Agency (EASA), or Airbus’s
EASA Design Organization Approval
(DOA).
The Contacting the Manufacturer
paragraph also clarifies that, if approved
by the DOA, the approval must include
the DOA-authorized signature. The DOA
signature indicates that the data and
information contained in the document
are EASA-approved, which is also FAAapproved. Messages and other
information provided by the
manufacturer that do not contain the
DOA-authorized signature approval are
not EASA-approved, unless EASA
directly approves the manufacturer’s
message or other information.
This clarification does not remove
flexibility previously afforded by the
Airworthy Product paragraph.
Consistent with long-standing FAA
policy, such flexibility was never
intended for required actions. This is
also consistent with the
VerDate Mar<15>2010
17:33 Aug 26, 2014
Jkt 232001
recommendation of the Airworthiness
Directive Implementation Aviation
Rulemaking Committee to increase
flexibility in complying with ADs by
identifying those actions in
manufacturers’ service instructions that
are ‘‘Required for Compliance’’ with
ADs. We continue to work with
manufacturers to implement this
recommendation. But once we
determine that an action is required, any
deviation from the requirement must be
approved as an alternative method of
compliance.
We also have decided not to include
a generic reference to either the
‘‘delegated agent’’ or ‘‘design approval
holder (DAH) with State of Design
Authority design organization
approval,’’ but instead we have
provided the specific delegation
approval granted by the State of Design
Authority for the DAH throughout this
AD.
Conclusion
We reviewed the relevant data 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 (79 FR
21651, April 17, 2014) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (79 FR 21651,
April 17, 2014).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Costs of Compliance
We estimate that this AD affects 7
airplanes of U.S. registry.
We also estimate that it takes about 1
work-hour 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
$595, or $85 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
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
PO 00000
Frm 00018
Fmt 4700
Sfmt 4700
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.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://www.regulations.
gov/#!docketDetail;D=FAA-2014-0236;
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 Operations office (telephone
800–647–5527) is in the ADDRESSES
section.
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.
E:\FR\FM\27AUR1.SGM
27AUR1
Federal Register / Vol. 79, No. 166 / Wednesday, August 27, 2014 / Rules and Regulations
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2014–16–13 Airbus: Amendment 39–17937.
Docket No. FAA–2014–0236; Directorate
Identifier 2013–NM–184–AD.
(a) Effective Date
This AD becomes effective October 1, 2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Airbus Model A300
B2–1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–
103, and B4–203 airplanes, certificated in
any category.
(d) Subject
Air Transport Association (ATA) of
America Code 32, Landing Gear; and 36,
Pneumatic.
(e) Reason
This AD was prompted by our
determination of the need to incorporate new
life limits for the main landing gear (MLG)
barrel assembly, retraction actuator assembly
linkage, and flange duct. We are issuing this
AD to prevent reduced structural integrity of
the airplane and possible loss of
controllability of the airplane.
mstockstill on DSK4VPTVN1PROD with RULES
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
VerDate Mar<15>2010
17:33 Aug 26, 2014
Jkt 232001
(g) Revise the Maintenance or Inspection
Program
Within 90 days after the effective date of
this AD, revise the maintenance or inspection
program, as applicable, to incorporate the life
limits specified in Appendix 1 of this AD
into the Airbus A300 Airworthiness
Limitations Section (ALS) Part 1. The initial
compliance time for the replacement is
identified in Appendix 1 of this AD and is
prior to the applicable life limits specified in
Appendix 1 of this AD, or within 90 days
after the effective date of this AD, whichever
occurs later.
(h) No Alternative Actions and Intervals
After accomplishing the revision required
by paragraph (g) of this AD, no alternative
actions (e.g., inspections) or intervals may be
used unless the actions or intervals are
approved as an alternative method of
compliance (AMOC) in accordance with the
procedures specified in paragraph (i)(1) of
this AD.
(i) 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:
PO 00000
Frm 00019
Fmt 4700
Sfmt 4700
51085
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-116AMOC-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.
(j) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) European
Aviation Safety Agency Airworthiness
Directive 2013–0210, dated September 11,
2013, for related information. This MCAI
may be found in the AD docket on the
Internet at https://www.regulations.gov/#
!documentDetailD=FAA-2014-0236-0002.
(k) Material Incorporated by Reference
None.
E:\FR\FM\27AUR1.SGM
27AUR1
mstockstill on DSK4VPTVN1PROD with RULES
51086
VerDate Mar<15>2010
Linkage, and Flange Duct
Jkt 232001
(*) Whichever occurs first.
Notes are located under the assy title.
LIFE LIMITS (*)
LIFE LIMITS APPLICABILITY
PO 00000
Frm 00020
82-320
B4-2C
B4-1xx
B4-2xx
C4-203
F4-203
N/A
X
X
X
X
76600
N/A
X
X
X
X
76600
N/A
X
X
X
X
FH
LOG
Cal.
C66277-10
N/A
66600
C66277-12
N/A
C66277-14
N/A
Part Number
B2-1A
B2-1C
B2K-3C
B2-20x
ATA32-10-00 MAIN LANDING GEAR
BARREL ASSEMBLY
Stirrup
Fmt 4700
058303-1
Stirrup pin
N/A
76600
N/A
X
X
X
X
C66457
N/A
76600
N/A
X
X
X
X
Sfmt 4725
048939
N/A
76600
N/A
X
X
X
X
048939-1
N/A
76600
N/A
X
X
X
X
E:\FR\FM\27AUR1.SGM
058314-1
N/A
76600
N/A
X
X
X
X
C66279
N/A
76600
N/A
X
X
X
X
C66279-2
N/A
76600
N/A
X
X
X
X
C66279-6
Universal joint
N/A
76600
N/A
X
X
X
X
X
X
X
X
N/A
X
X
N/A
76600
N/A
X
X
'
N/A
76600
N/A
N/A
53300
N/A
X
X
.
C61638-10
X
X
N/A
53300
N/A
C61638-20
ER27AU14.000</GPH>
N/A
76600
C61637-12
Tie rod
76600
N/A
C61637-11
Plate (Rear head end)
N/A
C61637-10
C61638-11
27AUR1
058313-1
Plate (Upper end)
N/A
76600
N/A
X
X
X
X
C68523-3
N/A
76600
N/A
X
X
Federal Register / Vol. 79, No. 166 / Wednesday, August 27, 2014 / Rules and Regulations
17:33 Aug 26, 2014
Appendix 1 to this AD- New Life Limits for the Main Landing Gear Barrel Assembly, Retraction Actuator Assembly
mstockstill on DSK4VPTVN1PROD with RULES
VerDate Mar<15>2010
Linkage, and Flange Duct (continued)
Jkt 232001
(*) Whichever occurs first.
Notes are located under the assy title.
PO 00000
Part Number
LIFE LIMITS (*)
FH
LDG
LIFE LIMITS APPLICABILITY
Frm 00021
Cal.
B2-1A
B2-1C
B2K-3C
B2-20x
N/A
X
X
X
82-320
B4-2C
B4-1xx
B4-2xx
C4-203
F4-203
X
RETRACTION ACTUATOR ASSEMBLY
(1)
When SB A300-32-0123 embodied before SB A300-32-0113.
(2)
When SB A300-32-0123 embodied after SB A300-32-0113.
Sliding rod
C69028-1
N/A
34 000
Fmt 4700
34 000
N/A
32 000
N/A
X
X
X
X
N/A
32 000
N/A
X
X
X
X
C69029-3
N/A
32 000
N/A
X
X
X
X
C69029-4 (2)
N/A
22 000
N/A
X
X
X
X
E:\FR\FM\27AUR1.SGM
End fitting
27AUR1
Upper multiple link pin
(Multiple link/Upper
link)
N/A
N/A
C69029-2
Sfmt 4725
C69028-4
C69029-1 (1)
C67078
N/A
33 000
N/A
X
X
X
X
C67078-1
N/A
33 000
N/A
X
X
X
X
C61342-4
N/A
36 700
N/A
C66510-4
N/A
32 000
N/A
X
X
X
X
C61505
Piston
N/A
76 600
N/A
X
X
X
X
X
LINKAGE ASSEMBLY
X
C61505-1
N/A
76 600
N/A
X
X
C61505-20
N/A
76 600
N/A
X
X
ATA36-11-05 PNEUMATIC
(1)
"xx" at the end of the P/N stands for any number between 00 and 99.
Duct flanged ( 1)
A2127 4063000xx
N/A
24 000
N/A
X
Federal Register / Vol. 79, No. 166 / Wednesday, August 27, 2014 / Rules and Regulations
17:33 Aug 26, 2014
Appendix 1 to this AD- New Life Limits for the Main Landing Gear Barrel Assembly, Retraction Actuator Assembly
51087
ER27AU14.001</GPH>
51088
Federal Register / Vol. 79, No. 166 / Wednesday, August 27, 2014 / Rules and Regulations
Issued in Renton, Washington, on August
4, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2014–19708 Filed 8–26–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0616; Directorate
Identifier 2014–CE–018–AD; Amendment
39–17954; AD 2014–17–01]
Examining the AD Docket
RIN 2120–AA64
Airworthiness Directives; Viking Air
Limited Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for Viking
Air Limited Model DHC–3 airplanes.
This AD results from mandatory
continuing airworthiness information
(MCAI) issued by the aviation authority
of another country to identify and
correct an unsafe condition on an
aviation product. The MCAI describes
the unsafe condition as looseness of the
horizontal stabilizer actuator mounting
block in the forward-aft and side-to-side
directions. We are issuing this AD to
require actions to address the unsafe
condition on these products.
DATES: This AD is effective September
16, 2014.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of September 16, 2014.
We must receive comments on this
AD by October 14, 2014.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
mstockstill on DSK4VPTVN1PROD with RULES
SUMMARY:
VerDate Mar<15>2010
17:33 Aug 26, 2014
Jkt 232001
For service information identified in
this AD, contact Viking Air Limited
Technical Support, 1959 De Havilland
Way, Sidney, British Columbia, Canada,
V8L 5V5; Fax: 250–656–0673;
telephone: (North America) 1–800–663–
8444; email: technical.support@
vikingair.com; Internet: https://www.
vikingair.com/content.aspx?id=358. 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.
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0616; 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 in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Cesar Gomez, Aerospace Safety Enginer,
FAA, New York Aircraft Certification
Office, 1600 Steward Avenue, Suite 410,
Westbury, New York 11590; telephone:
(516) 228–7318; fax: (516) 794–5531;
email: cesar.gomez@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
Transport Canada, which is the
aviation authority for Canada, has
issued AD No. CF–2014–14, dated June
5, 2014 (referred to after this as ‘‘the
MCAI’’), to correct an unsafe condition
for Viking Air Limited Model DHC–3
airplanes. The MCAI states:
A horizontal stabilizer actuator (trim jack)
mounting block, part number C3FS79–5, was
found loose in the forward-aft and side-toside directions. The trim jack mounting block
fastens the stabilizer actuator (trim jack)
which allows the angle of incidence of the
stabilizer to be varied. The stabilizer actuator
(trim jack) also functions as the rear
mounting point for the stabilizer.
Failure of the mounting block through
breakage or detachment may cause loss of
control of the horizontal stabilizer and
subsequent loss of control of the aeroplane.
Therefore, this AD mandates a one-time
inspection of the stabilizer actuator (trim
jack) mounting block.
You may examine the MCAI on the
Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2014–0616.
PO 00000
Frm 00022
Fmt 4700
Sfmt 4700
Relevant Service Information
Viking Air Limited has issued Viking
Service Bulletin No. V3/0005, Revision
‘A’, dated May 27, 2014. The actions
described in this service information are
intended to correct the unsafe condition
identified in the MCAI.
FAA’s Determination and Requirements
of the AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with this State of
Design Authority, they have notified us
of the unsafe condition described in the
MCAI and service information
referenced above. We are issuing this
AD because we evaluated all
information provided by the State of
Design Authority and determined the
unsafe condition exists and is likely to
exist or develop on other products of the
same type design.
Interim Action
We consider this AD interim action.
After the State of Design reviews and
evaluates the reporting data, we may
take further rulemaking action in the
future.
FAA’s Determination of the Effective
Date
An unsafe condition exists that
requires the immediate adoption of this
AD. The FAA has found that the risk to
the flying public justifies waiving notice
and comment prior to adoption of this
rule because failure of the mounting
block through breakage or detachment
may cause loss of control of horizontal
stabilizer and subsequent loss of
control. Therefore, we determined that
notice and opportunity for public
comment before issuing this AD are
impracticable and that good cause exists
for making this amendment effective in
fewer than 30 days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not precede it by notice and
opportunity for public comment. We
invite you to send any written relevant
data, views, or arguments about this AD.
Send your comments to an address
listed under the ADDRESSES section.
Include ‘‘Docket No. FAA–2014–0616;
Directorate Identifier 2014–CE–018–
AD’’ at the beginning of your comments.
We specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this AD. We will consider all comments
received by the closing date and may
E:\FR\FM\27AUR1.SGM
27AUR1
]]>Agencies
[Federal Register Volume 79, Number 166 (Wednesday, August 27, 2014)]
[Rules and Regulations]
[Pages 51083-51088]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-19708]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0236; Directorate Identifier 2013-NM-184-AD;
Amendment 39-17937; AD 2014-16-13]
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. This AD was prompted by our
determination of the need to incorporate new life limits for the main
landing gear (MLG) barrel assembly, retraction actuator assembly
linkage, and flange duct. This AD requires revising the maintenance or
inspection program, as applicable, to include the new life limits. We
are issuing this AD to prevent reduced structural integrity of the
airplane and possible loss of controllability of the airplane.
DATES: This AD becomes effective October 1, 2014.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0236 or in person at the
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.
For service information identified in this AD, contact Airbus SAS,
Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51;
email account.airworth-eas@airbus.com; Internet https://www.airbus.com.
You may view this 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.
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. The NPRM published in the Federal Register on April
17, 2014 (79 FR 21651).
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2013-0210, dated September 11, 2013 (referred
to after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition all Airbus Model A300
series airplanes. The MCAI states:
Some life limits previously defined in Revision 00 of A300 ALS
[airworthiness limitations section] Part 1 have been removed [from]
that document at Revision 01 and should normally be included in an
ALS Part 4.
At this time, there are no plans to issue an ALS Part 4 for A300
aeroplanes.
Nevertheless, failure to comply with these life limits could
result in an unsafe condition.
For the reasons described above, it has been decided to require
the application of these life limits through a separate [EASA] AD.
Consequently, this [EASA] AD requires application of life limits
applicable to Main Landing Gear (MLG) barrel assembly, retraction
actuator assembly linkage assembly and flanged duct which were
previously contained in Airbus ALS Part 1 Revision 00.
EASA AD 2007-0293 [which corresponds with FAA AD 2009-18-15,
Amendment 39-16011 (74 FR 48143, September 22, 2009)], which
required compliance with the actions specified in ALS Part 1, will
be superseded by a new [EASA] AD, requiring compliance with ALS Part
1 at Revision 1.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0236-0002.
Comments
We gave the public the opportunity to participate in developing
this AD. We
[[Page 51084]]
received no comments on the NPRM (79 FR 21651, April 17, 2014) or on
the determination of the cost to the public.
``Contacting the Manufacturer'' Paragraph in This AD
Since late 2006, we have included a standard paragraph titled
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD
based on a foreign authority's AD.
We have become aware that some operators have misunderstood or
misinterpreted the Airworthy Product paragraph to allow the owner/
operator to use messages provided by the manufacturer as approval of
deviations during the accomplishment of an AD-mandated action. The
Airworthy Product paragraph does not approve messages or other
information provided by the manufacturer for deviations to the
requirements of the AD-mandated actions. The Airworthy Product
paragraph only addresses the requirement to contact the manufacturer
for corrective actions for the identified unsafe condition and does not
cover deviations from other AD requirements. However, deviations to AD-
required actions are addressed in 14 CFR 39.17, and anyone may request
the approval for an alternative method of compliance to the AD-required
actions using the procedures found in 14 CFR 39.19.
To address this misunderstanding and misinterpretation of the
Airworthy Product paragraph, we have changed the paragraph and retitled
it ``Contacting the Manufacturer.'' This paragraph now clarifies that
for any requirement in this AD to obtain corrective actions from a
manufacturer, the actions must be accomplished using a method approved
by the FAA, the European Aviation Safety Agency (EASA), or Airbus's
EASA Design Organization Approval (DOA).
The Contacting the Manufacturer paragraph also clarifies that, if
approved by the DOA, the approval must include the DOA-authorized
signature. The DOA signature indicates that the data and information
contained in the document are EASA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer
that do not contain the DOA-authorized signature approval are not EASA-
approved, unless EASA directly approves the manufacturer's message or
other information.
This clarification does not remove flexibility previously afforded
by the Airworthy Product paragraph. Consistent with long-standing FAA
policy, such flexibility was never intended for required actions. This
is also consistent with the recommendation of the Airworthiness
Directive Implementation Aviation Rulemaking Committee to increase
flexibility in complying with ADs by identifying those actions in
manufacturers' service instructions that are ``Required for
Compliance'' with ADs. We continue to work with manufacturers to
implement this recommendation. But once we determine that an action is
required, any deviation from the requirement must be approved as an
alternative method of compliance.
We also have decided not to include a generic reference to either
the ``delegated agent'' or ``design approval holder (DAH) with State of
Design Authority design organization approval,'' but instead we have
provided the specific delegation approval granted by the State of
Design Authority for the DAH throughout this AD.
Conclusion
We reviewed the relevant data 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 (79 FR 21651, April 17, 2014) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (79 FR 21651, April 17, 2014).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Costs of Compliance
We estimate that this AD affects 7 airplanes of U.S. registry.
We also estimate that it takes about 1 work-hour 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 $595, or $85 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 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.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0236; 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 Operations office (telephone 800-647-
5527) is in the ADDRESSES section.
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.
[[Page 51085]]
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2014-16-13 Airbus: Amendment 39-17937. Docket No. FAA-2014-0236;
Directorate Identifier 2013-NM-184-AD.
(a) Effective Date
This AD becomes effective October 1, 2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Airbus Model A300 B2-1A, B2-1C, B2K-3C,
B2-203, B4-2C, B4-103, and B4-203 airplanes, certificated in any
category.
(d) Subject
Air Transport Association (ATA) of America Code 32, Landing
Gear; and 36, Pneumatic.
(e) Reason
This AD was prompted by our determination of the need to
incorporate new life limits for the main landing gear (MLG) barrel
assembly, retraction actuator assembly linkage, and flange duct. We
are issuing this AD to prevent reduced structural integrity of the
airplane and possible loss of controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Revise the Maintenance or Inspection Program
Within 90 days after the effective date of this AD, revise the
maintenance or inspection program, as applicable, to incorporate the
life limits specified in Appendix 1 of this AD into the Airbus A300
Airworthiness Limitations Section (ALS) Part 1. The initial
compliance time for the replacement is identified in Appendix 1 of
this AD and is prior to the applicable life limits specified in
Appendix 1 of this AD, or within 90 days after the effective date of
this AD, whichever occurs later.
(h) No Alternative Actions and Intervals
After accomplishing the revision required by paragraph (g) of
this AD, no alternative actions (e.g., inspections) or intervals may
be used unless the actions or intervals are approved as an
alternative method of compliance (AMOC) in accordance with the
procedures specified in paragraph (i)(1) of this AD.
(i) 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: 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.
(j) Related Information
Refer to Mandatory Continuing Airworthiness Information (MCAI)
European Aviation Safety Agency Airworthiness Directive 2013-0210,
dated September 11, 2013, for related information. This MCAI may be
found in the AD docket on the Internet at https://www.regulations.gov/#!documentDetailD=FAA-2014-0236-0002.
(k) Material Incorporated by Reference
None.
[[Page 51086]]
[GRAPHIC] [TIFF OMITTED] TR27AU14.000
[[Page 51087]]
[GRAPHIC] [TIFF OMITTED] TR27AU14.001
[[Page 51088]]
Issued in Renton, Washington, on August 4, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-19708 Filed 8-26-14; 8:45 am]
BILLING CODE 4910-13-P
