Airworthiness Directives; Airbus Airplanes, 52174-52177 [2014-20259]
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52174
Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Rules and Regulations
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 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 to the extent that it justifies
making a regulatory distinction, 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
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
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■
2014–17–08 Pratt & Whitney Canada Corp.:
Amendment 39–17961; Docket No.
FAA–2013–0766; Directorate Identifier
2013–NE–26–AD.
(a) Effective Date
This AD becomes effective October 8, 2014.
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This AD applies to all Pratt & Whitney
Canada Corp. (P&WC) PT6A–114 and PT6A–
114A turboprop engines.
(d) Unsafe Condition
This AD was prompted by several
incidents of compressor turbine (CT) blade
failure, causing power loss, and engine
failure. We are issuing this AD to prevent
failure of CT blades, which could lead to
damage to the engine and damage to the
airplane.
(e) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(1) For engines that have CT blades
installed other than P&WC single crystal CT
blades, part numbers (P/Ns) 3072791–01 or
3072791–02, perform the following actions:
(i) Within 150 operating hours after the
effective date of this AD, perform a borescope
inspection (BSI) of CT blades for engines
with 500 or more hours time-since-new that
have not been previously inspected or timesince-last-inspection (TSLI).
(ii) Thereafter, repeat the inspection in
paragraph (e)(1)(i) of this AD within 500
flight hours TSLI.
(iii) During the next hot section inspection
(HSI) after the effective date of this AD, and
each HSI thereafter, replace the complete set
of CT blades with any of the following:
(A) New CT blades;
(B) CT blades that have passed a two-blade
metallurgical examination in accordance
with paragraph 3.B., Accomplishment
Instructions, of P&WC Service Bulletin (SB)
No. PT6A–72–1669, Revision 9, dated June
28, 2013; or
(C) P&WC single crystal CT blades, P/Ns
3072791–01 or 3072791–02.
(2) Reserved.
(i) Related Information
(1) For more information about this AD,
contact Robert Morlath, Aerospace Engineer,
Engine Certification Office, FAA, Engine &
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
phone: 781–238–7154; fax: 781–238–7199;
email: robert.c.morlath@faa.gov.
(2) Refer to Transport Canada Civil
Aviation AD CF–2013–21R1, dated
November 13, 2013, for more information.
You may examine the MCAI in the AD
docket on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2013-0766-0008.
(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) Pratt & Whitney Canada Service Bulletin
No. PT6A–72–1669, Revision 9, dated June
28, 2013.
(ii) Reserved.
(3) For P&WC service information
identified in this AD, contact Pratt & Whitney
Canada Corp., 1000 Marie-Victorin,
Longueuil, Quebec, Canada, J4G 1A1; phone:
800–268–8000; fax: 450–647–2888; Internet:
www.pwc.ca.
(4) You may view this service information
at FAA, Engine & Propeller Directorate, 12
New England Executive Park, Burlington,
MA. For information on the availability of
this material at the FAA, call 781–238–7125.
(5) You may view this service information
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 Burlington, Massachusetts, on
August18, 2014.
Richard P. Warren,
Acting Assistant Directorate Manager, Engine
& Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2014–20453 Filed 9–2–14; 8:45 am]
BILLING CODE 4910–13–P
(g) Credit for Previous Action
■
14:42 Sep 02, 2014
(c) Applicability
Within 36 months after the effective date
of this AD, replace the complete set of CT
blades with P&WC single crystal CT blades,
P/Ns 3072791–01 or 3072791–02.
PART 39—AIRWORTHINESS
DIRECTIVES
VerDate Mar<15>2010
None.
(f) Mandatory Terminating Action
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
§ 39.13
(b) Affected ADs
If you performed a metallurgical
examination of single crystal CT blades
before the effective date of this AD in
accordance with P&WC SB No. PT6A–72–
1669, Revision 8, dated January 17, 2013, or
earlier versions, all of which are not
incorporated by reference, you have met the
initial inspection requirements of paragraph
(e)(1)(i) of this AD. However, you must still
comply with the repetitive BSI requirement
of paragraph (e)(1)(ii) of this AD.
(h) Alternative Methods of Compliance
(AMOCs)
The Manager, Engine Certification Office,
FAA, may approve AMOCs to this AD. Use
the procedures found in 14 CFR 39.19 to
make your request.
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0137; Directorate
Identifier 2013–NM–135–AD; Amendment
39–17960; AD 2014–17–07]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
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Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Rules and Regulations
ACTION:
Final rule.
We are adopting a new
airworthiness directive (AD) for all
Airbus Model A300 series airplanes;
Model A300 B4–600, B4–600R, and F4–
600R series airplanes; 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 rupture of the uplock springs
of the nose landing gear (NLG) and main
landing gear (MLG) doors and legs. This
AD requires repetitive inspections of the
uplock springs of the NLG and MLG
doors and legs for broken and damaged
springs, and corrective actions if
necessary. We are issuing this AD to
detect and correct improper free fall
extension of the MLG or NLG, which
could lead to possible loss of control of
the airplane on the ground, and
consequent damage to the airplane and
injury to occupants.
DATES: This AD becomes effective
October 8, 2014.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of October 8, 2014.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2014-0137; 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:
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SUMMARY:
apply to all Airbus Model A300 series
airplanes; Model A300 B4–600, B4–
600R, and F4–600R series airplanes;
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, 2014 (79 FR 13003).
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2013–0150,
dated July 16, 2013 (referred to after this
as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for all Airbus Model A300 series
airplanes; Model A300 B4–600, B4–
600R, and F4–600R series airplanes;
Model A300 C4–605R Variant F
airplanes (collectively called Model
A300–600 series airplanes); and Model
A310 series airplanes. The MCAI states:
Some cases of Nose Landing Gear (NLG) and
Main Landing Gear (MLG) Door and Leg
Uplock spring ruptures on A300, A310 or
A300–600 aeroplanes have been reported in
service.
Springs within the uplock are used to
either lock the gear or the door in the up
position, or to participate in emergency
mechanical unlocking.
The springs are positioned in pairs, and in
case of rupture of one spring the other one
remains to fulfill the function, whereas the
rupture of both springs will disable the
locking function or the emergency unlocking
function.
This condition, if not detected and
corrected, could prevent proper free fall
extension of the MLG or NLG, possibly
leading to loss of control of the aeroplane on
the ground, consequently resulting in damage
to the aeroplane and injury to occupants.
For the reason described above, this
[EASA] AD requires [repetitive] detailed
visual inspection[s] of the NLG and MLG
Door and Leg Uplock springs [for broken and
damaged springs] and, depending of findings,
their replacement.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2014-01370002.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM (79
FR 13003, March 7, 2014) or on the
determination of the cost to the public.
Discussion
‘‘Contacting the Manufacturer’’
Paragraph in This AD
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
Since late 2006, we have included a
standard paragraph titled ‘‘Airworthy
Product’’ in all MCAI ADs in which the
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14:42 Sep 02, 2014
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52175
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
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
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Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Rules and Regulations
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
13003, March 7, 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 13003,
March 7, 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 156
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Parts cost
Cost per product
Cost on U.S. operators
Repetitive inspections ...
1 work-hour × $85 per hour = $85 per inspection.
$0
$85 per inspection .......
$13,260 per inspection.
In addition, we estimate that any
necessary replacement would take about
9 work-hours for a cost of $765 per
product. The cost of parts is minimal.
We have no way of determining the
number of aircraft that might need this
action.
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.
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Regulatory Findings
14:42 Sep 02, 2014
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You may examine the AD docket on
the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2014-0137; 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.
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):
■
2014–17–07 Airbus: Amendment 39–17960.
Docket No. FAA–2014–0137; Directorate
Identifier 2013–NM–135–AD.
(a) Effective Date
This AD becomes effective October 8, 2014.
(b) Affected ADs
None.
Examining the AD Docket
Adoption of the Amendment
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:
VerDate Mar<15>2010
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.
(c) Applicability
This AD applies to the Airbus airplanes
specified in paragraphs (c)(1), (c)(2), (c)(3),
(c)(4), (c)(5), and (c)(6) of this AD; certificated
in any category; all serial numbers.
(1) Model A300 B2–1A, B2–1C, B2K–3C,
B2–203, B4–2C, B4–103, and B4–203
airplanes.
(2) Model A300 B4–601, B4–603, B4–620,
and B4–622 airplanes.
(3) Model A300 B4–605R and B4–622R
airplanes.
(4) Model A300 F4–605R and F4–622R
airplanes.
(5) Model A300 C4–605R Variant F
airplanes.
(6) Model A310–203, –204, –221, –222,
–304, –322, –324, and –325 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 32, Landing Gear.
(e) Reason
This AD was prompted by reports of
rupture of the uplock springs of the nose
landing gear (NLG) and main landing gear
(MLG) doors and legs. We are issuing this AD
to detect and correct improper free fall
extension of the MLG or NLG, which could
lead to possible loss of control of the airplane
on the ground, and consequent damage to the
airplane and injury to occupants.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Repetitive Inspections
Within 18 months after the effective date
of this AD: Perform a detailed inspection of
the uplock springs of the MLG and NLG legs
and doors for broken and damaged springs,
in accordance with the Accomplishment
Instructions of the applicable service
information identified in paragraph (g)(1),
(g)(2), or (g)(3) of this AD. Repeat the
inspection thereafter at intervals not to
exceed 18 months.
(1) Airbus Service Bulletin A300–32–0465,
Revision 01, dated April 25, 2013 (for Model
A300 series airplanes).
(2) Airbus Service Bulletin A300–32–6111,
Revision 01, dated April 25, 2013 (for Model
A300–600 series airplanes).
(3) Airbus Service Bulletin A310–32–2147,
Revision 01, dated April 25, 2013 (for Model
A310 series airplanes).
(h) Corrective Actions
The corrective actions required by
paragraphs (h)(1), (h)(2), and (h)(3) of this AD
do not constitute terminating actions for the
repetitive inspections required by paragraph
(g) of this AD.
(1) If, during any inspection required by
paragraph (g) of this AD, one spring on the
MLG or NLG door uplock is found broken or
damaged, within 2 months after the
inspection, replace the affected MLG or NLG
door uplock, as applicable, with a serviceable
part, in accordance with the
Accomplishment Instructions of the
applicable service bulletin identified in
paragraph (g)(1), (g)(2), or (g)(3) of this AD.
(2) If, during any inspection required by
paragraph (g) of this AD, one spring on the
MLG or NLG leg uplock is found broken or
damaged, repeat the inspection required by
paragraph (g) of this AD thereafter at
intervals not to exceed 50 flight cycles.
Replacement of any affected leg uplock, as
required by paragraph (h)(2)(i) or (h)(2)(ii) of
this AD, as applicable, constitutes
terminating action for the repetitive
inspections required by paragraph (h)(2) of
this AD.
(i) If, during any inspection required by
paragraph (h)(2) of this AD, the second free
fall spring on the MLG or NLG leg uplock is
found broken or damaged, before further
flight, replace the affected MLG or NLG leg
uplock, as applicable, with a serviceable part,
in accordance with the Accomplishment
Instructions of the applicable service bulletin
identified in paragraph (g)(1), (g)(2), or (g)(3)
of this AD.
(ii) Within 1,000 flight cycles after doing
the inspection required by paragraph (g) of
this AD during which the spring has been
found broken, replace the affected MLG or
NLG leg uplock, as applicable, with a
serviceable part, in accordance with the
Accomplishment Instructions of the
applicable service bulletin identified in
paragraph (g)(1), (g)(2), or (g)(3) of this AD.
(3) If, during any inspection required by
paragraph (g) of this AD, two free fall springs
on the same MLG or NLG leg uplock are
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14:42 Sep 02, 2014
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found broken or damaged, before further
flight, replace the affected MLG or NLG leg
uplock, as applicable, with a serviceable part,
in accordance with the Accomplishment
Instructions of the applicable service bulletin
identified in paragraph (g)(1), (g)(2), or (g)(3)
of this AD.
(i) Credit for Previous Actions
This paragraph provides credit for the
applicable actions required by paragraphs (g)
and (h) of this AD, if those actions were
performed before the effective date of this AD
using the applicable service information
identified in paragraph (i)(1), (i)(2), or (i)(3)
of this AD.
(1) Airbus Service Bulletin A300–32–0465,
dated July 20, 2012, which is not
incorporated by reference in this AD.
(2) Airbus Service Bulletin A300–32–6111,
dated July 20, 2012, which is not
incorporated by reference in this AD.
(3) Airbus Service Bulletin A310–32–2147,
dated July 20, 2012, which is not
incorporated by reference in this AD.
(j) 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-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.
(k) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2013–0150, dated
July 16, 2013, for related information. This
MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov/
#!documentDetail;D=FAA-2014-0137-0002.
(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.
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52177
(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) Airbus Service Bulletin A300–32–0465,
Revision 01, dated April 25, 2013.
(ii) Airbus Service Bulletin A300–32–6111,
Revision 01, dated April 25, 2013.
(iii) Airbus Service Bulletin A310–32–
2147, Revision 01, dated April 25, 2013.
(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 August
15, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2014–20259 Filed 9–2–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0617; Directorate
Identifier 2014–CE–019–AD; Amendment
39–17962; AD 2014–17–09
RIN 2120–AA64
Airworthiness Directives; Various de
Havilland Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Harry E. Williams de Havilland Model
DH 82A airplanes, all Cliff Robertson de
Havilland Model DH 82A airplanes, and
all de Havilland Model DH 83 airplanes.
This AD requires inspecting the aircraft
maintenance records and/or the
installed lateral fuselage tie rods and
SUMMARY:
E:\FR\FM\03SER1.SGM
03SER1
Agencies
[Federal Register Volume 79, Number 170 (Wednesday, September 3, 2014)]
[Rules and Regulations]
[Pages 52174-52177]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-20259]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0137; Directorate Identifier 2013-NM-135-AD;
Amendment 39-17960; AD 2014-17-07]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
[[Page 52175]]
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, and F4-
600R series airplanes; 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 rupture of the
uplock springs of the nose landing gear (NLG) and main landing gear
(MLG) doors and legs. This AD requires repetitive inspections of the
uplock springs of the NLG and MLG doors and legs for broken and damaged
springs, and corrective actions if necessary. We are issuing this AD to
detect and correct improper free fall extension of the MLG or NLG,
which could lead to possible loss of control of the airplane on the
ground, and consequent damage to the airplane and injury to occupants.
DATES: This AD becomes effective October 8, 2014.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of October 8,
2014.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0137; 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; Model A300 B4-600, B4-600R, and F4-600R series
airplanes; 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, 2014 (79 FR 13003).
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2013-0150, dated July 16, 2013 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model A300
series airplanes; Model A300 B4-600, B4-600R, and F4-600R series
airplanes; Model A300 C4-605R Variant F airplanes (collectively called
Model A300-600 series airplanes); and Model A310 series airplanes. The
MCAI states:
Some cases of Nose Landing Gear (NLG) and Main Landing Gear (MLG)
Door and Leg Uplock spring ruptures on A300, A310 or A300-600
aeroplanes have been reported in service.
Springs within the uplock are used to either lock the gear or
the door in the up position, or to participate in emergency
mechanical unlocking.
The springs are positioned in pairs, and in case of rupture of
one spring the other one remains to fulfill the function, whereas
the rupture of both springs will disable the locking function or the
emergency unlocking function.
This condition, if not detected and corrected, could prevent
proper free fall extension of the MLG or NLG, possibly leading to
loss of control of the aeroplane on the ground, consequently
resulting in damage to the aeroplane and injury to occupants.
For the reason described above, this [EASA] AD requires
[repetitive] detailed visual inspection[s] of the NLG and MLG Door
and Leg Uplock springs [for broken and damaged springs] and,
depending of findings, their replacement.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0137-0002.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (79 FR 13003, March 7,
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
[[Page 52176]]
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 13003, March 7, 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 13003, March 7, 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 156 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Repetitive inspections......... 1 work-hour x $85 per $0 $85 per inspection $13,260 per
hour = $85 per inspection.
inspection.
----------------------------------------------------------------------------------------------------------------
In addition, we estimate that any necessary replacement would take
about 9 work-hours for a cost of $765 per product. The cost of parts is
minimal. We have no way of determining the number of aircraft that
might need this action.
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-2014-0137; 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.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2014-17-07 Airbus: Amendment 39-17960. Docket No. FAA-2014-0137;
Directorate Identifier 2013-NM-135-AD.
(a) Effective Date
This AD becomes effective October 8, 2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes specified in paragraphs
(c)(1), (c)(2), (c)(3), (c)(4), (c)(5), and (c)(6) of this AD;
certificated in any category; all serial numbers.
(1) Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and
B4-203 airplanes.
(2) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
(3) Model A300 B4-605R and B4-622R airplanes.
(4) Model A300 F4-605R and F4-622R airplanes.
(5) Model A300 C4-605R Variant F airplanes.
(6) Model A310-203, -204, -221, -222, -304, -322, -324, and -325
airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 32, Landing
Gear.
(e) Reason
This AD was prompted by reports of rupture of the uplock springs
of the nose landing gear (NLG) and main landing gear (MLG) doors and
legs. We are issuing this AD to detect and correct improper free
fall extension of the MLG or NLG, which could lead to possible loss
of control of the airplane on the ground, and consequent damage to
the airplane and injury to occupants.
[[Page 52177]]
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections
Within 18 months after the effective date of this AD: Perform a
detailed inspection of the uplock springs of the MLG and NLG legs
and doors for broken and damaged springs, in accordance with the
Accomplishment Instructions of the applicable service information
identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. Repeat
the inspection thereafter at intervals not to exceed 18 months.
(1) Airbus Service Bulletin A300-32-0465, Revision 01, dated
April 25, 2013 (for Model A300 series airplanes).
(2) Airbus Service Bulletin A300-32-6111, Revision 01, dated
April 25, 2013 (for Model A300-600 series airplanes).
(3) Airbus Service Bulletin A310-32-2147, Revision 01, dated
April 25, 2013 (for Model A310 series airplanes).
(h) Corrective Actions
The corrective actions required by paragraphs (h)(1), (h)(2),
and (h)(3) of this AD do not constitute terminating actions for the
repetitive inspections required by paragraph (g) of this AD.
(1) If, during any inspection required by paragraph (g) of this
AD, one spring on the MLG or NLG door uplock is found broken or
damaged, within 2 months after the inspection, replace the affected
MLG or NLG door uplock, as applicable, with a serviceable part, in
accordance with the Accomplishment Instructions of the applicable
service bulletin identified in paragraph (g)(1), (g)(2), or (g)(3)
of this AD.
(2) If, during any inspection required by paragraph (g) of this
AD, one spring on the MLG or NLG leg uplock is found broken or
damaged, repeat the inspection required by paragraph (g) of this AD
thereafter at intervals not to exceed 50 flight cycles. Replacement
of any affected leg uplock, as required by paragraph (h)(2)(i) or
(h)(2)(ii) of this AD, as applicable, constitutes terminating action
for the repetitive inspections required by paragraph (h)(2) of this
AD.
(i) If, during any inspection required by paragraph (h)(2) of
this AD, the second free fall spring on the MLG or NLG leg uplock is
found broken or damaged, before further flight, replace the affected
MLG or NLG leg uplock, as applicable, with a serviceable part, in
accordance with the Accomplishment Instructions of the applicable
service bulletin identified in paragraph (g)(1), (g)(2), or (g)(3)
of this AD.
(ii) Within 1,000 flight cycles after doing the inspection
required by paragraph (g) of this AD during which the spring has
been found broken, replace the affected MLG or NLG leg uplock, as
applicable, with a serviceable part, in accordance with the
Accomplishment Instructions of the applicable service bulletin
identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD.
(3) If, during any inspection required by paragraph (g) of this
AD, two free fall springs on the same MLG or NLG leg uplock are
found broken or damaged, before further flight, replace the affected
MLG or NLG leg uplock, as applicable, with a serviceable part, in
accordance with the Accomplishment Instructions of the applicable
service bulletin identified in paragraph (g)(1), (g)(2), or (g)(3)
of this AD.
(i) Credit for Previous Actions
This paragraph provides credit for the applicable actions
required by paragraphs (g) and (h) of this AD, if those actions were
performed before the effective date of this AD using the applicable
service information identified in paragraph (i)(1), (i)(2), or
(i)(3) of this AD.
(1) Airbus Service Bulletin A300-32-0465, dated July 20, 2012,
which is not incorporated by reference in this AD.
(2) Airbus Service Bulletin A300-32-6111, dated July 20, 2012,
which is not incorporated by reference in this AD.
(3) Airbus Service Bulletin A310-32-2147, dated July 20, 2012,
which is not incorporated by reference in this AD.
(j) 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.
(k) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2013-0150, dated July 16, 2013,
for related information. This MCAI may be found in the AD docket on
the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-
2014-0137-0002.
(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) Airbus Service Bulletin A300-32-0465, Revision 01, dated
April 25, 2013.
(ii) Airbus Service Bulletin A300-32-6111, Revision 01, dated
April 25, 2013.
(iii) Airbus Service Bulletin A310-32-2147, Revision 01, dated
April 25, 2013.
(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 August 15, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-20259 Filed 9-2-14; 8:45 am]
BILLING CODE 4910-13-P