(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: With-
in 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 re-
quested 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; tele-
phone: (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 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: http://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: http://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: http://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.
FOR FURTHER INFORMATION CONTACT: 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.
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.
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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 http://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: http://
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,
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: http://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 http://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
under the criteria of the Regulatory Flexibility Act.
Examining the AD Docket
You may examine the AD docket on the Internet at http://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.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new AD:
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