82 FR 10859 - Airworthiness Directives; PILATUS AIRCRAFT LTD. Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 82, Issue 31 (February 16, 2017)

The FAA is correcting an airworthiness directive (AD) that published in the Federal Register. That AD applies to all PILATUS AIRCRAFT LTD. Models PC-12, PC-12/45, PC-12/47, and PC-12/47E airplanes. The second reference to the main landing gear (MLG) in paragraph (f)(6) is incorrect. This document corrects that error. In all other respects, the original document remains the same; however we are publishing the entire rule in the Federal Register.

[Federal Register Volume 82, Number 31 (Thursday, February 16, 2017)]
[Rules and Regulations]
[Pages 10859-10860]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2017-02772]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-7003; Directorate Identifier 2016-CE-015-AD; 
Amendment 39-18766; AD 2016-26-08]
RIN 2120-AA64


Airworthiness Directives; PILATUS AIRCRAFT LTD. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; correction.

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SUMMARY: The FAA is correcting an airworthiness directive (AD) that 
published in the Federal Register. That AD applies to all PILATUS 
AIRCRAFT LTD. Models PC-12, PC-12/45, PC-12/47, and PC-12/47E 
airplanes. The second reference to the main landing gear (MLG) in 
paragraph (f)(6) is incorrect. This document corrects that error. In 
all other respects, the original document remains the same; however we 
are publishing the entire rule in the Federal Register.

DATES: This final rule is effective February 16, 2017. The effective 
date of AD 2016-26-08 remains February 9, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of February 9, 
2017 (82 FR 1172, January 5, 2017).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
7003; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (phone: 800-647-
5527) is 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 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: 
[email protected].

SUPPLEMENTARY INFORMATION: Airworthiness Directive 2016-26-08, 
Amendment 39-18766 (82 FR 1172, January 5, 2017), requires 
incorporating new revisions into the Limitations section, Chapter 4, of 
the FAA-approved maintenance program (e.g., maintenance manual). The 
limitations were revised to include repetitive inspections of the main 
landing gear (MLG) attachment bolts.
    As published, in paragraph (f)(6) there is a typographical error to 
the second reference of the MLG. The published reference is MLB and it 
is should be MLG.
    Although no other part of the preamble or regulatory information 
has been corrected, we are publishing the entire rule in the Federal 
Register.
    The effective date of this AD remains February 9, 2017.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Correction

    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   [Corrected]

0
2. The FAA amends Sec.  39.13 by removing 39-18005 (79 FR 67343, 
November 13, 2014) and adding the following new AD:

2016-26-08 PILATUS AIRCRAFT LTD.: Amendment 39-18766; Docket No. 
FAA-2016-7003; Directorate Identifier 2016-CE-015-AD.

[[Page 10860]]

(a) Effective Date

    This airworthiness directive (AD) is effective February 9, 2017.

(b) Affected ADs

    This AD replaces AD 2014-22-01, 39-18005 (79 FR 67343, November 
13, 2014).

(c) Applicability

    This AD applies to PILATUS AIRCRAFT LTD. Models PC-12, PC-12/45, 
PC-12/47, and PC-12/47E airplanes, all manufacturer serial numbers 
(MSNs), certificated in any category.

(d) Subject

    Air Transport Association of America (ATA) Code 5: Time Limits.

(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 a need to 
incorporate new revisions into the Limitations section, Chapter 4, 
of the FAA-approved maintenance program (e.g., maintenance manual). 
The limitations were revised to include repetitive inspections of 
the main landing gear (MLG) attachment bolts. These actions are 
required to ensure the continued operational safety of the affected 
airplanes.

(f) Actions and Compliance

    Unless already done, do the actions in paragraphs (f)(1) through 
(6) of this AD:
    (1) Before further flight after February 9, 2017 (the effective 
date of this AD), insert the following revisions into the 
Limitations section of the FAA-approved maintenance program (e.g., 
maintenance manual). Compliance with an electronic version of the 
Limitations section is acceptable provided the specifically 
referenced sections are followed even though there may be 
differences with the pagination:
    (i) STRUCTURAL, COMPONENT AND MISCELLANEOUS--AIRWORTHINESS 
LIMITATIONS, Data module code 12-A-04-00-00-00A-000A-A, dated July 
12, 2016, of the Pilatus Model type--PC-12, PC-12/45, PC-12/47 MSN-
101-888, Aircraft Maintenance Manual (AMM), Document No. 02049, 12-
A-AM-00-00-00-I, revision 32, dated July 18, 2016; and
    (ii) STRUCTURAL AND COMPONENT LIMITATIONS--AIRWORTHINESS 
LIMITATIONS, Data module code 12-B-04-00-00-00A-000A-A, dated July 
19, 2016, of the Pilatus Model type--PC-12/47E MSN-1001-UP, Aircraft 
Maintenance Manual (AMM), Document No. 02300, 12-B-AM-00-00-00-I, 
revision 15, dated July 30, 2016.
    (2) The new limitations section revisions listed in paragraphs 
(f)(1)(i) and (ii) of this AD specify the following:
    (i) Establish inspections of the MLG attachment bolts,
    (ii) Specify replacement of components before or upon reaching 
the applicable life limit, and
    (iii) Specify accomplishment of all applicable maintenance tasks 
within certain thresholds and intervals.
    (3) Only authorized Pilatus Service Centers can do the 
Supplemental Structural Inspection Document (SSID) as required by 
the documents in paragraphs (f)(1)(i) and (ii) of this AD because 
deviations from the type design in critical locations could make the 
airplane ineligible for this life extension.
    (4) If no compliance time is specified in the documents listed 
in paragraphs (f)(1)(i) and (ii) of this AD when doing any 
corrective actions where discrepancies are found as required in 
paragraph (f)(2)(iii) of this AD, do these corrective actions before 
further flight after doing the applicable maintenance task.
    (5) During the accomplishment of the actions required in 
paragraph (f)(2) of this AD, including all subparagraphs, if a 
discrepancy is found that is not identified in the documents listed 
in paragraphs (f)(1)(i) and (ii) of this AD, before further flight 
after finding the discrepancy, contact PILATUS AIRCRAFT LTD. at the 
address specified in paragraph (h) of this AD for a repair scheme 
and incorporate that repair scheme.
    (6) Before or upon accumulating 6 years time-in-service (TIS) on 
the MLG attachment bolts or within the next 3 months TIS after 
February 9, 2017 (the effective date of this AD), whichever occurs 
later, inspect the MLG attachment bolts for cracks and corrosion and 
before further flight take all necessary corrective actions.

(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: 
[email protected].
    (i) 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.
    (ii) AMOCs approved for AD 2014-22-01, 39-18005 (79 FR 67343, 
November 13, 2014) are not approved as AMOCs for this AD.
    (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.

(h) Related Information

    Refer to MCAI European Aviation Safety Agency (EASA) AD No. 
2016-0083, dated April 28, 2016, for related information. You may 
examine the MCAI on the Internet at https://www.regulations.gov/document?D=FAA-2016-7003-0002.

(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) STRUCTURAL, COMPONENT AND MISCELLANEOUS--AIRWORTHINESS 
LIMITATIONS, Data module code 12-A-04-00-00-00A-000A-A, dated July 
12, 2016, of the Pilatus Model type--PC-12, PC-12/45, PC-12/47 MSN-
101-888, Aircraft Maintenance Manual (AMM), Document No. 02049, 12-
A-AM-00-00-00-I, revision 32, dated July 18, 2016.
    (ii) STRUCTURAL AND COMPONENT LIMITATIONS--AIRWORTHINESS 
LIMITATIONS, Data module code 12-B-04-00-00-00A-000A-A, dated July 
19, 2016, of the Pilatus Model type--PC-12/47E MSN-1001-UP, Aircraft 
Maintenance Manual (AMM), Document No. 02300, 12-B-AM-00-00-00-I, 
revision 15, dated July 30, 2016.
    (3) For PILATUS AIRCRAFT LTD. service information identified in 
this AD, contact PILATUS AIRCRAFT LTD., Customer Service Manager, 
CH-6371 STANS, Switzerland; telephone: +41 (0) 41 619 33 33; fax: 
+41 (0) 41 619 73 11; Internet: http://www.pilatus-aircraft.com or 
email: aircraft.com">SupportPC12@pilatus-aircraft.com.
    (4) You may view this service information at FAA, 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. In addition, you can access this service information 
on the Internet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2016-7003.
    (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 January 24, 2017.
Melvin Johnson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-02772 Filed 2-15-17; 8:45 am]
BILLING CODE 4910-13-P