Airworthiness Directives; PILATUS Aircraft Ltd. Airplanes, 3868-3871 [2015-00010]
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Federal Register / Vol. 80, No. 16 / Monday, January 26, 2015 / Rules and Regulations
Airworthiness Limitations Section ALS Part
3—Certification Maintenance Requirements,
Revision 04, dated August 27, 2013, except
as provided by paragraph (k)(2) of this AD,
accomplish all applicable maintenance tasks.
Accomplishing these actions terminates the
requirements of paragraphs (g), (h), (i), and (j)
of this AD.
(2) Where paragraph 3 of the ‘‘Record of
Revisions’’ section of Airbus A330
Airworthiness Limitations Section ALS Part
3—Certification Maintenance Requirements,
Revision 04, dated August 27, 2013, specifies
accomplishing the actions ‘‘from 27 August
2013,’’ this AD requires compliance within
the specified compliance time after the
effective date of this AD.
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(l) No Alternative Inspections or Intervals
After accomplishing the action required by
paragraph (k)(1) of this AD, no alternative
inspections or inspection intervals may be
used, other than those specified in Airbus
A330 Airworthiness Limitations Section ALS
Part 3—Certification Maintenance
Requirements, Revision 04, dated August 27,
2013, except as provided by paragraph (k)(2)
of this AD, unless the inspections or intervals
are approved as an AMOC in accordance
with the procedures specified in paragraph
(m) of this AD.
(m) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425)227–1138; 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: As of the
effective date of this AD, 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.
may examine the MCAI in the AD docket on
the Internet at https://www.regulations.gov/
#!documentDetail;D=FAA-2014-0587-0002.
(o) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(3) The following service information was
approved for IBR on March 2, 2015.
(i) Airbus A330 Airworthiness Limitations
Section ALS Part 3—Certification
Maintenance Requirements, Revision 04,
dated August 27, 2013. The revision level of
this document is identified on only the title
page and in the Record of Revisions. The
revision date is not identified on the title
page of this document.
(ii) Reserved.
(4) The following service information was
approved for IBR on August 1, 2011 (76 FR
37255, June 27, 2011).
(i) Airbus A330 ALS Part 3—Certification
Maintenance Requirements, Revision 03,
dated July 29, 2010. The revision level of this
document is identified on only the title page
and in the Record of Revisions. The revision
date is not identified on the title page of this
document.
(ii) Reserved.
(5) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330@airbus.com; Internet
https://www.airbus.com.
(6) 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.
(7) 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
December 19, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2014–30918 Filed 1–23–15; 8:45 am]
BILLING CODE 4910–13–P
(n) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2013–0245, dated
October 2, 2013, for related information. You
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0770; Directorate
Identifier 2014–CE–024–AD; Amendment
39–18064; AD 2015–01–03]
RIN 2120–AA64
Airworthiness Directives; PILATUS
Aircraft Ltd. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for Pilatus
Aircraft Ltd. Model PC–7 airplanes. This
AD results from mandatory continuing
airworthiness information (MCAI)
issued by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as possible cracking from
stress corrosion on various parts of the
airplane structure made of aluminum
alloy AA2024–T351. We are issuing this
AD to require actions to address the
unsafe condition on these products.
DATES: This AD is effective March 2,
2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of March 2, 2015.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0770; or in person at Document
Management Facility, U.S. Department
of Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
For service information identified in
this AD, contact Pilatus Aircraft LTD.,
Customer Technical Support (MCC),
P.O. Box 992, CH–6371 Stans,
Switzerland; phone: +41 (0)41 619 67
74; fax: +41 (0)41 619 67 73; email:
Techsupport@pilatus-aircraft.com;
internet: https://www.pilatusaircraft.com. You may review 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.
FOR FURTHER INFORMATION CONTACT:
Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Directorate, 901
Locust, Room 301, Kansas City,
SUMMARY:
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Federal Register / Vol. 80, No. 16 / Monday, January 26, 2015 / Rules and Regulations
Missouri 64106; telephone: (816) 329–
4059; fax: (816) 329–4090; email:
doug.rudolph@faa.gov.
SUPPLEMENTARY INFORMATION:
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Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to add an AD that would apply
to Pilatus Aircraft Ltd. Model PC–7
airplanes. The NPRM was published in
the Federal Register on October 7, 2014
(79 FR 60389). The NPRM proposed to
correct an unsafe condition for the
specified products and was based on
mandatory continuing airworthiness
information (MCAI) originated by an
aviation authority of another country.
Since the NPRM was issued, the MCAI
was revised based on revised service
information. The NPRM we issued
already referenced the revised service
information. The revised MCAI states:
This Airworthiness Directive (AD) is
prompted due to the possibility of cracks in
some critical parts. It is possible that stress
corrosion cracks may occur on various parts
of the aircraft structure initially made of
aluminium alloy AA2024–T351 which is
susceptible to Stress Corrosion Cracking
(SCC). Later in production, the material
specification was changed to aluminium
alloy AA2124–T851 to decrease the risk of
stress corrosion. The Part Number (P/N) of
the affected structural parts are not always
changed when the new material was
introduced.
Such a condition, if left uncorrected, could
lead to failure of critical parts on the aircraft
structure and will prejudice the structural
integrity of the aircraft.
To address this potential unsafe condition
Pilatus Aircraft Ltd. issued PILATUS PC–7
Service Bulletin (SB) No. 51–001 and FOCA
Switzerland issued AD HB–2014–001 to
require a one-time check to identify the
material specification and inspect the
affected areas of the airframe that are made
of aluminium alloy AA2024–T351. Any
structural parts of the aircraft structure found
to be cracked must be reported to Pilatus
prior to further flight.
In the meantime Pilatus Aircraft Ltd.
issued PILATUS PC–7 SB No. 51–001
Revision 1 to correct paragraphs (§ ) 1.C.(3)
and § 1.D. to update Part Number (P/N)
references of the AA2024–T351 material and
to add a clarification that an inspection can
be carried out if an elevator center controlrod P/N 116.35.07.345 is installed. It also
clarifies which center tank support bracket is
covered by SB 51–001.
For the reasons described above, this AD
retains the requirements of FOCA
Switzerland AD HB–2014–001, which is
revised and clarifies that an inspection of the
elevator center control-rod can be carried out
if P/N 116.35.07.345 is installed and corrects
some paragraphs and clarifies the
information which center tank support
bracket is affected.
The MCAI also requires replacement of
the elevator center control-rod, P/N
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116.35.07.271 or 116.35.07.345; and
shackle, P/N 116.35.07.183. The MCAI
can be found in the AD docket on the
Internet at: https://www.regulations.gov/
#!docketBrowser;rpp=25;
po=0;dct=PR%252BSR;D=FAA-20140770.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comment
received on the proposal and the FAA’s
response to the comment.
Request Revision of Paragraph (f)(3)
Tom Langen of Pilatus commented
that the NPRM (79 FR 60389, October 7,
2014) referred to MCAI AD HB–2014–
001, dated July 25, 2014. Since issuance
of the NPRM, the MCAI was revised to
AD HB–2014–001R1, dated October 22,
2014. The revised MCAI clarified P/N
116.35.07.271 needed to be replaced
where the other P/N 116.35.07.345
should be inspected and not
automatically replaced. Tom Langen
requested we revise paragraph (f)(3) of
the AD to read like the revised MCAI.
We agree. We revised this AD as
requested.
Conclusion
We reviewed the relevant data,
considered the comment received, and
determined that air safety and the
public interest require adopting the AD
with the change 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
60389, October 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 60389,
October 7, 2014).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of the AD.
Relevant Service Information
Pilatus Aircraft Ltd. has issued Pilatus
PC–7 Service Bulletin No: 51–001,
Revision No. 1, dated August 26, 2014.
The actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI. The service bulletin describes
procedures for inspecting for stress
corrosion and replacing various parts of
the airplane structure made of
aluminum alloy AA2024–T351. You can
find this service information on the
Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2014–0770.
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3869
Costs of Compliance
We estimate that this AD will affect
10 products of U.S. registry. We also
estimate that it would take about 30
work-hours per product to comply with
the basic requirements of this AD. The
average labor rate is $85 per work-hour.
Required parts would cost about $4,700
per product.
Based on these figures, we estimate
the cost of the AD on U.S. operators to
be $72,500, or $7,250 per product.
In addition, we estimate that any
necessary follow-on actions would take
about 14 work-hours and require parts
costing $10,000, for a cost of $11,190
per product. We have no way of
determining the number of products
that may need these actions.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify 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
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Federal Register / Vol. 80, No. 16 / Monday, January 26, 2015 / Rules and Regulations
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 by searching for
and locating Docket No. FAA–2014–
0770; 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 the NPRM, 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
2015–01–03 Pilatus Aircraft Ltd:
Amendment 39–18064; Docket No.
FAA–2014–0770; Directorate Identifier
2014–CE–024–AD.
(a) Effective Date
This airworthiness directive (AD) becomes
effective March 2, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Pilatus Aircraft Ltd.
Model PC–7 airplanes, manufacturer serial
numbers (MSN) 101 through MSN 618,
certificated in any category.
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(d) Subject
Air Transport Association of America
(ATA) Code 51: Standard Practices/
Structures.
(e) Reason
This AD was prompted by mandatory
continuing airworthiness information (MCAI)
originated by an aviation authority of another
country to identify and correct an unsafe
condition on an aviation product. The MCAI
describes the unsafe condition as possible
cracking from stress corrosion on various
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17:58 Jan 23, 2015
Jkt 235001
parts of the airplane structure made of
aluminum alloy AA2024–T351. We are
issuing this AD to detect and correct stress
corrosion cracks that may occur on various
parts of the airplane structure initially made
of aluminum alloy AA2024–T351, which is
susceptible to stress corrosion cracking
(SCC). Such a condition, if left uncorrected,
could lead to failure of critical parts on the
airplane structure and weaken the structural
integrity of the airplane.
(f) Actions and Compliance
Unless already done, within the next 12
months after March 2, 2015 (the effective
date of this AD), perform a one-time
conductivity test of items 6 through 9 and 11
through 13 as listed in paragraph 1.A.(2) of
Pilatus PC–7 Service Bulletin No: 51–001,
Revision No. 1, dated August 26, 2014, to
check the material of the parts—determine
whether they are made of aluminum alloy
AA2124–T851 or aluminum alloy AA2024–
T351. Do not install any item unless it has
been inspected following the applicable
paragraph of Pilatus PC–7 Service Bulletin
No: 51–001, Revision No. 1, dated August 26,
2014.
(1) For airplanes with any parts made of
aluminum alloy AA2124–T851: Within 12
months after March 2, 2015 (the effective
date of this AD), make an entry in the
airplane logbook as required by paragraph
3.D.(3) of Pilatus PC–7 Service Bulletin No:
51–001, Revision No. 1, dated August 26,
2014. The only other actions of this AD that
apply to airplanes with all parts made of
aluminum alloy AA2124–T851 are the
actions in paragraphs (f)(3), (f)(4), and (f)(5)
of this AD.
(2) For airplanes with any parts made of
aluminum alloy AA2024–T351: Within 12
months after March 2, 2015 (the effective
date of this AD), do the actions in paragraphs
(f)(2)(i) through (f)(2)(iii) as applicable,
including all subparagraphs:
(i) For items 7 through 9 and 11 through
13 as listed in paragraph 1.A.(2) of Pilatus
PC–7 Service Bulletin No: 51–001, Revision
No. 1, dated August 26, 2014, within 12
months after March 2, 2015 (the effective
date of this AD), do a one-time inspection for
cracks. If any cracks are found as a result of
the inspection, before further flight, you must
contact Pilatus Aircraft Ltd. to obtain FAAapproved repair instructions approved
specifically for compliance with this AD and
incorporate those instructions. Use the
contact information found in paragraph (h) of
this AD.
(ii) For item 6 as listed in paragraph 1.A.(2)
of Pilatus PC–7 Service Bulletin No: 51–001,
Revision No. 1, dated August 26, 2014,
within 12 months after March 2, 2015 (the
effective date of this AD), replace with a part
made of aluminum alloy AA2124–T851.
(iii) For Items 1, 2, 4, 5, and 10 as listed
in paragraph 1.A.(2) of Pilatus PC–7 Service
Bulletin No: 51–001, Revision No. 1, dated
August 26, 2014, within 12 months after
March 2, 2015 (the effective date of this AD),
do the following actions in paragraphs
(f)(2)(iii)(A) and (f)(2)(iii)(B), as applicable.
(A) For items 1, 2, 4, and 10 as listed in
paragraph 1.A.(2) of Pilatus PC–7 Service
Bulletin No: 51–001, Revision No. 1, dated
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August 26, 2014, do a one-time inspection for
cracks. If any cracks are found, before further
flight, you must contact Pilatus Aircraft Ltd.
to obtain FAA-approved repair instructions
approved specifically for compliance with
this AD and incorporate those instructions.
Use the contact information found in
paragraph (i)(3) of this AD.
(B) For item 5 as listed in paragraph 1.A.(2)
of Pilatus PC–7 Service Bulletin No: 51–001,
Revision No. 1, dated August 26, 2014,
replace with a part made of aluminum alloy
AA2124–T851.
(3) For all airplanes: For item 3 as listed
in paragraph 1.A.(2) of Pilatus PC–7 Service
Bulletin No: 51–001, Revision No. 1, dated
August 26, 2014, within 12 months after
March 2, 2015 (the effective date of this AD),
replace elevator center control-rods with
P/N 116.35.07.271 (item 3 as listed in
paragraph 1.A.(2) of Pilatus PC–7 Service
Bulletin No: 51–001, Revision No. 1, dated
August 26, 2014), because the inspection for
cracks on this type of control-rods is difficult.
If elevator center control-rods P/N
116.35.07.345 (Item 3 as listed in paragraph
1.A.(2) of Pilatus PC–7 Service Bulletin No:
51–001, Revision No. 1, dated August 26,
2014), are installed, these type of control rods
will be inspected.
(4) For all airplanes: As of 12 months after
March 2, 2015 (the effective date of this AD),
do not install the parts listed in items 1 and
2, 4, and 7 through 13 of paragraph 1.A.(2)
of Pilatus PC–7 Service Bulletin No: 51–001,
Revision No. 1, dated August 26, 2014, that
are made of aluminum alloy AA2024–T351
unless they have been inspected and found
free of cracks.
(5) For all airplanes: As of 12 months after
March 2, 2015 (the effective date of this AD),
do not install the parts listed in items 3, 5,
and 6 of paragraph 1.A.(2) of Pilatus PC–7
Service Bulletin No: 51–001, Revision No. 1,
dated August 26, 2014, that are made of
aluminum alloy AA2024–T351.
(g) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4059; fax: (816) 329–
4090; email: doug.rudolph@faa.gov. Before
using any approved AMOC on any airplane
to which the AMOC applies, notify your
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, a federal
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Federal Register / Vol. 80, No. 16 / Monday, January 26, 2015 / Rules and Regulations
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
(h) Related Information
Refer to MCAI Federal Office of Civil
Aviation (FOCA) AD HB–2014–001, dated
July 25, 2014; and AD HB–2014–001R1,
dated November 5, 2014 for related
information. The MCAI can be found in the
AD docket on the Internet at: https://
www.regulations.gov/
#!docketBrowser;rpp=25;po=0;dct=PR%25
2BSR;D=FAA-2014-0770.
tkelley on DSK3SPTVN1PROD with RULES
(i) 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) Pilatus Aircraft Ltd. Pilatus PC–7
Service Bulletin No: 51–001, Revision No. 1,
dated August 26, 2014.
(ii) Reserved.
(3) For Pilatus Aircraft Ltd. service
information identified in this AD, contact
Pilatus Aircraft Ltd., Customer Technical
Support (MCC), P.O. Box 992, CH–6371
Stans, Switzerland; phone: +41 (0)41 619 67
74; fax: +41 (0)41 619 67 73; email:
Techsupport@pilatus-aircraft.com; internet:
https://www.pilatus-aircraft.com.
(4) You may view this service information
at the FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call (816) 329–4148.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Kansas City, Missouri, on
December 31, 2014.
Robert Busto,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–00010 Filed 1–23–15; 8:45 am]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0692; Directorate
Identifier 2012–NM–024–AD; Amendment
39–18031; AD 2014–23–15]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) AD 2011–
14–06 for all Airbus Model A318, A319,
A320, and A321 series airplanes. AD
2011–14–06 required revising the
maintenance program. This new AD
requires revising the maintenance
program to incorporate new, more
restrictive limitations. This AD was
prompted by the determination that
more restrictive limitations are
necessary. We are issuing this AD to
prevent fatigue cracking, accidental
damage, or corrosion in principal
structural elements, and possible failure
of certain life limited parts, which could
result in reduced structural integrity of
the airplane.
DATES: This AD becomes effective
March 2, 2015.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of March 2, 2015.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of August 22, 2011 (76 FR
42024, July 18, 2011).
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of November 7, 2007 (72 FR
56262, October 3, 2007).
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2013-0692; 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, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email account.airworthSUMMARY:
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
3871
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:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1405;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of
proposed rulemaking (SNPRM) to
amend 14 CFR part 39 to supersede AD
2011–14–06, Amendment 39–16741 (76
FR 42024, July 18, 2011). AD 2011–14–
06 applied to Airbus Model A318, A319,
A320, and A321 series airplanes. The
SNPRM published in the Federal
Register on May 28, 2014 (79 FR 30492).
We preceded the SNPRM with a notice
of proposed rulemaking (NPRM) that
published in the Federal Register on
August 13, 2013 (78 FR 49213).
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2013–0147,
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 A318, A319, A320,
and A321 series airplanes. The MCAI
states:
The airworthiness limitations for Airbus
A320 family aeroplanes are currently
included in Airbus A318/A319/A320/A321
Airworthiness Limitations Section (ALS)
document. The airworthiness limitations
applicable to the Damage Tolerant
Airworthiness Limitation Items (DT ALI) are
currently given in Airbus ALS Part 2, which
is approved by EASA.
Previously, EASA issued AD 2010–0071R1
[https://ad.easa.europa.eu/blob/easa_ad_
2010_0071_R1.pdf/AD_2010–0071R1_1]
[associated with FAA AD 2011–14–06,
Amendment 39–16741 (76 FR 42024, July 18,
2011)], which required the implementation of
the DT ALI maintenance instructions as
specified in Airbus A318/A319/A320/A321
ALI Document ref. AI/SE–M4/95A.0252/96
issue 10 and Airbus A319 Corporate Jet ALI
Document ref. AI/SE–M2/95A.1038/99.
The new Airbus A318/A319/A320/A321
ALS Part 2 Revision 02, which includes also
Airbus A319 Corporate Jet, introduces more
restrictive DT ALI maintenance instructions.
Failure to comply with these instructions
could result in an unsafe condition.
Application of new DT ALI tasks 531129–
02–2 and 531129–02–3 introduces initial and
E:\FR\FM\26JAR1.SGM
26JAR1
]]>Agencies
[Federal Register Volume 80, Number 16 (Monday, January 26, 2015)]
[Rules and Regulations]
[Pages 3868-3871]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-00010]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0770; Directorate Identifier 2014-CE-024-AD;
Amendment 39-18064; AD 2015-01-03]
RIN 2120-AA64
Airworthiness Directives; PILATUS Aircraft Ltd. Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for Pilatus
Aircraft Ltd. Model PC-7 airplanes. This AD results from mandatory
continuing airworthiness information (MCAI) issued by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as possible cracking from stress corrosion on various parts
of the airplane structure made of aluminum alloy AA2024-T351. We are
issuing this AD to require actions to address the unsafe condition on
these products.
DATES: This AD is effective March 2, 2015.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of March 2,
2015.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0770; or in person at Document Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
For service information identified in this AD, contact Pilatus
Aircraft LTD., Customer Technical Support (MCC), P.O. Box 992, CH-6371
Stans, Switzerland; phone: +41 (0)41 619 67 74; fax: +41 (0)41 619 67
73; email: aircraft.com">Techsupport@pilatus-aircraft.com; internet: https://
www.pilatus-aircraft.com. You may review 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.
FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
[[Page 3869]]
Missouri 64106; telephone: (816) 329-4059; fax: (816) 329-4090; email:
doug.rudolph@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to add an AD that would apply to Pilatus Aircraft Ltd. Model
PC-7 airplanes. The NPRM was published in the Federal Register on
October 7, 2014 (79 FR 60389). The NPRM proposed to correct an unsafe
condition for the specified products and was based on mandatory
continuing airworthiness information (MCAI) originated by an aviation
authority of another country. Since the NPRM was issued, the MCAI was
revised based on revised service information. The NPRM we issued
already referenced the revised service information. The revised MCAI
states:
This Airworthiness Directive (AD) is prompted due to the
possibility of cracks in some critical parts. It is possible that
stress corrosion cracks may occur on various parts of the aircraft
structure initially made of aluminium alloy AA2024-T351 which is
susceptible to Stress Corrosion Cracking (SCC). Later in production,
the material specification was changed to aluminium alloy AA2124-
T851 to decrease the risk of stress corrosion. The Part Number (P/N)
of the affected structural parts are not always changed when the new
material was introduced.
Such a condition, if left uncorrected, could lead to failure of
critical parts on the aircraft structure and will prejudice the
structural integrity of the aircraft.
To address this potential unsafe condition Pilatus Aircraft Ltd.
issued PILATUS PC-7 Service Bulletin (SB) No. 51-001 and FOCA
Switzerland issued AD HB-2014-001 to require a one-time check to
identify the material specification and inspect the affected areas
of the airframe that are made of aluminium alloy AA2024-T351. Any
structural parts of the aircraft structure found to be cracked must
be reported to Pilatus prior to further flight.
In the meantime Pilatus Aircraft Ltd. issued PILATUS PC-7 SB No.
51-001 Revision 1 to correct paragraphs (Sec. ) 1.C.(3) and Sec.
1.D. to update Part Number (P/N) references of the AA2024-T351
material and to add a clarification that an inspection can be
carried out if an elevator center control-rod P/N 116.35.07.345 is
installed. It also clarifies which center tank support bracket is
covered by SB 51-001.
For the reasons described above, this AD retains the
requirements of FOCA Switzerland AD HB-2014-001, which is revised
and clarifies that an inspection of the elevator center control-rod
can be carried out if P/N 116.35.07.345 is installed and corrects
some paragraphs and clarifies the information which center tank
support bracket is affected.
The MCAI also requires replacement of the elevator center control-rod,
P/N 116.35.07.271 or 116.35.07.345; and shackle, P/N 116.35.07.183. The
MCAI can be found in the AD docket on the Internet at: https://www.regulations.gov/#!docketBrowser;rpp=25;po=0;dct=PR%252BSR;D=FAA-
2014-0770.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comment received on the proposal
and the FAA's response to the comment.
Request Revision of Paragraph (f)(3)
Tom Langen of Pilatus commented that the NPRM (79 FR 60389, October
7, 2014) referred to MCAI AD HB-2014-001, dated July 25, 2014. Since
issuance of the NPRM, the MCAI was revised to AD HB-2014-001R1, dated
October 22, 2014. The revised MCAI clarified P/N 116.35.07.271 needed
to be replaced where the other P/N 116.35.07.345 should be inspected
and not automatically replaced. Tom Langen requested we revise
paragraph (f)(3) of the AD to read like the revised MCAI.
We agree. We revised this AD as requested.
Conclusion
We reviewed the relevant data, considered the comment received, and
determined that air safety and the public interest require adopting the
AD with the change 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 60389, October 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 60389, October 7, 2014).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of the AD.
Relevant Service Information
Pilatus Aircraft Ltd. has issued Pilatus PC-7 Service Bulletin No:
51-001, Revision No. 1, dated August 26, 2014. The actions described in
this service information are intended to correct the unsafe condition
identified in the MCAI. The service bulletin describes procedures for
inspecting for stress corrosion and replacing various parts of the
airplane structure made of aluminum alloy AA2024-T351. You can find
this service information on the Internet at https://www.regulations.gov
by searching for and locating Docket No. FAA-2014-0770.
Costs of Compliance
We estimate that this AD will affect 10 products of U.S. registry.
We also estimate that it would take about 30 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Required parts would cost about $4,700 per
product.
Based on these figures, we estimate the cost of the AD on U.S.
operators to be $72,500, or $7,250 per product.
In addition, we estimate that any necessary follow-on actions would
take about 14 work-hours and require parts costing $10,000, for a cost
of $11,190 per product. We have no way of determining the number of
products that may need these actions.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify 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
[[Page 3870]]
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 by searching for and locating Docket No. FAA-2014-
0770; 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 the NPRM, 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.
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 AD:
2015-01-03 Pilatus Aircraft Ltd: Amendment 39-18064; Docket No. FAA-
2014-0770; Directorate Identifier 2014-CE-024-AD.
(a) Effective Date
This airworthiness directive (AD) becomes effective March 2,
2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Pilatus Aircraft Ltd. Model PC-7 airplanes,
manufacturer serial numbers (MSN) 101 through MSN 618, certificated
in any category.
(d) Subject
Air Transport Association of America (ATA) Code 51: Standard
Practices/Structures.
(e) Reason
This AD was prompted by mandatory continuing airworthiness
information (MCAI) originated by an aviation authority of another
country to identify and correct an unsafe condition on an aviation
product. The MCAI describes the unsafe condition as possible
cracking from stress corrosion on various parts of the airplane
structure made of aluminum alloy AA2024-T351. We are issuing this AD
to detect and correct stress corrosion cracks that may occur on
various parts of the airplane structure initially made of aluminum
alloy AA2024-T351, which is susceptible to stress corrosion cracking
(SCC). Such a condition, if left uncorrected, could lead to failure
of critical parts on the airplane structure and weaken the
structural integrity of the airplane.
(f) Actions and Compliance
Unless already done, within the next 12 months after March 2,
2015 (the effective date of this AD), perform a one-time
conductivity test of items 6 through 9 and 11 through 13 as listed
in paragraph 1.A.(2) of Pilatus PC-7 Service Bulletin No: 51-001,
Revision No. 1, dated August 26, 2014, to check the material of the
parts--determine whether they are made of aluminum alloy AA2124-T851
or aluminum alloy AA2024-T351. Do not install any item unless it has
been inspected following the applicable paragraph of Pilatus PC-7
Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014.
(1) For airplanes with any parts made of aluminum alloy AA2124-
T851: Within 12 months after March 2, 2015 (the effective date of
this AD), make an entry in the airplane logbook as required by
paragraph 3.D.(3) of Pilatus PC-7 Service Bulletin No: 51-001,
Revision No. 1, dated August 26, 2014. The only other actions of
this AD that apply to airplanes with all parts made of aluminum
alloy AA2124-T851 are the actions in paragraphs (f)(3), (f)(4), and
(f)(5) of this AD.
(2) For airplanes with any parts made of aluminum alloy AA2024-
T351: Within 12 months after March 2, 2015 (the effective date of
this AD), do the actions in paragraphs (f)(2)(i) through (f)(2)(iii)
as applicable, including all subparagraphs:
(i) For items 7 through 9 and 11 through 13 as listed in
paragraph 1.A.(2) of Pilatus PC-7 Service Bulletin No: 51-001,
Revision No. 1, dated August 26, 2014, within 12 months after March
2, 2015 (the effective date of this AD), do a one-time inspection
for cracks. If any cracks are found as a result of the inspection,
before further flight, you must contact Pilatus Aircraft Ltd. to
obtain FAA-approved repair instructions approved specifically for
compliance with this AD and incorporate those instructions. Use the
contact information found in paragraph (h) of this AD.
(ii) For item 6 as listed in paragraph 1.A.(2) of Pilatus PC-7
Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014,
within 12 months after March 2, 2015 (the effective date of this
AD), replace with a part made of aluminum alloy AA2124-T851.
(iii) For Items 1, 2, 4, 5, and 10 as listed in paragraph
1.A.(2) of Pilatus PC-7 Service Bulletin No: 51-001, Revision No. 1,
dated August 26, 2014, within 12 months after March 2, 2015 (the
effective date of this AD), do the following actions in paragraphs
(f)(2)(iii)(A) and (f)(2)(iii)(B), as applicable.
(A) For items 1, 2, 4, and 10 as listed in paragraph 1.A.(2) of
Pilatus PC-7 Service Bulletin No: 51-001, Revision No. 1, dated
August 26, 2014, do a one-time inspection for cracks. If any cracks
are found, before further flight, you must contact Pilatus Aircraft
Ltd. to obtain FAA-approved repair instructions approved
specifically for compliance with this AD and incorporate those
instructions. Use the contact information found in paragraph (i)(3)
of this AD.
(B) For item 5 as listed in paragraph 1.A.(2) of Pilatus PC-7
Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014,
replace with a part made of aluminum alloy AA2124-T851.
(3) For all airplanes: For item 3 as listed in paragraph 1.A.(2)
of Pilatus PC-7 Service Bulletin No: 51-001, Revision No. 1, dated
August 26, 2014, within 12 months after March 2, 2015 (the effective
date of this AD), replace elevator center control-rods with P/N
116.35.07.271 (item 3 as listed in paragraph 1.A.(2) of Pilatus PC-7
Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014),
because the inspection for cracks on this type of control-rods is
difficult. If elevator center control-rods P/N 116.35.07.345 (Item 3
as listed in paragraph 1.A.(2) of Pilatus PC-7 Service Bulletin No:
51-001, Revision No. 1, dated August 26, 2014), are installed, these
type of control rods will be inspected.
(4) For all airplanes: As of 12 months after March 2, 2015 (the
effective date of this AD), do not install the parts listed in items
1 and 2, 4, and 7 through 13 of paragraph 1.A.(2) of Pilatus PC-7
Service Bulletin No: 51-001, Revision No. 1, dated August 26, 2014,
that are made of aluminum alloy AA2024-T351 unless they have been
inspected and found free of cracks.
(5) For all airplanes: As of 12 months after March 2, 2015 (the
effective date of this AD), do not install the parts listed in items
3, 5, and 6 of paragraph 1.A.(2) of Pilatus PC-7 Service Bulletin
No: 51-001, Revision No. 1, dated August 26, 2014, that are made of
aluminum alloy AA2024-T351.
(g) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
Standards Office, FAA, has the authority to approve AMOCs for this
AD, if requested using the procedures found in 14 CFR 39.19. Send
information to ATTN: Doug Rudolph, Aerospace Engineer, FAA, Small
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329-4059; fax: (816) 329-4090; email:
doug.rudolph@faa.gov. Before using any approved AMOC on any airplane
to which the AMOC applies, notify your appropriate principal
inspector (PI) in the FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, a federal
[[Page 3871]]
agency may not conduct or sponsor, and a person is not required to
respond to, nor shall a person be subject to a penalty for failure
to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection
of information displays a current valid OMB Control Number. The OMB
Control Number for this information collection is 2120-0056. Public
reporting for this collection of information is estimated to be
approximately 5 minutes per response, including the time for
reviewing instructions, completing and reviewing the collection of
information. All responses to this collection of information are
mandatory. Comments concerning the accuracy of this burden and
suggestions for reducing the burden should be directed to the FAA
at: 800 Independence Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer, AES-200.
(h) Related Information
Refer to MCAI Federal Office of Civil Aviation (FOCA) AD HB-
2014-001, dated July 25, 2014; and AD HB-2014-001R1, dated November
5, 2014 for related information. The MCAI can be found in the AD
docket on the Internet at: https://www.regulations.gov/#!docketBrowser;rpp=25;po=0;dct=PR%252BSR;D=FAA-2014-0770.
(i) 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) Pilatus Aircraft Ltd. Pilatus PC-7 Service Bulletin No: 51-
001, Revision No. 1, dated August 26, 2014.
(ii) Reserved.
(3) For Pilatus Aircraft Ltd. service information identified in
this AD, contact Pilatus Aircraft Ltd., Customer Technical Support
(MCC), P.O. Box 992, CH-6371 Stans, Switzerland; phone: +41 (0)41
619 67 74; fax: +41 (0)41 619 67 73; email: aircraft.com">Techsupport@pilatus-aircraft.com; internet: https://www.pilatus-aircraft.com.
(4) You may view this service information at the FAA, Small
Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For
information on the availability of this material at the FAA, call
(816) 329-4148.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Kansas City, Missouri, on December 31, 2014.
Robert Busto,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-00010 Filed 1-23-15; 8:45 am]
BILLING CODE 4910-13-P
