AD 2015-01-03

[Federal Register Volume 80, Number 16 (Monday, January 26, 2015)]
[Rules and Regulations]
[Pages 3868-3871]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2015-00010]


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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

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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> 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: <a href="/cdn-cgi/l/email-protection#93c7f6f0fbe0e6e3e3fce1e7d3e3fafff2e7e6e0beaff2b3fbe1f6f5ae" http: aircraft.com">aircraft.com</a>">Techsupport@pilatus-<a href="http://aircraft.com">aircraft.com</a></a>; internet: http://
www.pilatus-<a href="http://aircraft.com">aircraft.com</a>. 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: 
<a href="/cdn-cgi/l/email-protection#462229332168343322292a362e0620272768212930"><span class="__cf_email__" data-cfemail="dfbbb0aab8f1adaabbb0b3afb79fb9bebef1b8b0a9">[email&#160;protected]</span></a>.

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: <a href="http://www.regulations.gov/#!docketBrowser">http://www.regulations.gov/#!docketBrowser</a>;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:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM (79 FR 60389, October 7, 2014) for correcting the unsafe 
condition; and
    <bullet> 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> 
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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> 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: 
<a href="/cdn-cgi/l/email-protection#2a4e455f4d04585f4e45465a426a4c4b4b044d455c"><span class="__cf_email__" data-cfemail="3f5b504a58114d4a5b50534f577f595e5e11585049">[email&#160;protected]</span></a>. 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: <a href="http://www.regulations.gov/#!docketBrowser">http://www.regulations.gov/#!docketBrowser</a>;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: <a href="/cdn-cgi/l/email-protection#3c68595f544f494c4c534e487c4c55505d48494f11005d1c544e595a01" http: aircraft.com">aircraft.com</a>">Techsupport@pilatus-<a href="http://aircraft.com">aircraft.com</a></a>; internet: http://www.pilatus-<a href="http://aircraft.com">aircraft.com</a>.
    (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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.


    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