Quiero saber acerca de...

30158

Federal Register / Vol. 86, No. 107 / Monday, June 7, 2021 / Rules and Regulations
the existing maintenance manual or ICA for your airplane as follows:
i Replace the ALS with the Airworthiness Limitations Section of Pilatus PC6
Airworthiness Limitations Document No.
02334, Revision 10, dated October 30, 2020.
ii Add or replace, if applicable Appendix K, Fuselage Wing Fittings Inspection/Check, of Pilatus PC6
Airworthiness Limitations Document No.
02334, Revision 10, dated October 30, 2020.
iii Add Appendix L, Wing to Fuselage FittingsInspection/Check, of Pilatus PC6
Airworthiness Limitations Document No.
02334, Revision 9, dated March 6, 2020.
3 For all airplanes specified in paragraph c of this AD, after revising the ALS as required by paragraphs f1 and 2 of this AD, remove from service each part that has reached or exceeded its new life limit.
g Inspections and Replacement 1 For airplanes with a bush part number P/N 6100.0020.01 that has been bonded as specified in Section 530001, Fuselage Wing FittingsInspection/Check, of Pilatus PC6 Aircraft Maintenance Manual Document No. 01975, Revision 29, dated February 28, 2020; or Appendix K, Fuselage Wing FittingsInspection/Check, of Pilatus PC6 Airworthiness Limitations Document No. 02334, Revision 9, dated March 6, 2020:
Within 50 hours time-in-service TIS after the effective date of this AD, perform a visual and eddy current inspection of each fuselage wing fitting on fuselage Frame 3, remove bush P/N 6100.0020.01 from service, and install a new zero hours TIS bush P/N
6100.0020.01 into Frame 3 with grease by using the procedures specified in paragraph f1ii or f2ii of this AD, as applicable to your airplane.
2 Unless already done, within 1,100
hours TIS after the effective date of this AD
or within 12 months after the effective date of this AD, whichever occurs first, perform an eddy current inspection of each fuselage wing fitting and each wing-to-fuselage fitting using the procedures specified in paragraphs f1ii and iii of this AD, or paragraphs f2ii and iii of this AD, as applicable to your airplane. Thereafter, repeat the eddy current inspection of each fuselage wing fitting and each wing-to-fuselage fitting at the intervals specified in the ALS identified in paragraph f1i or f2i, as applicable to your airplane.

khammond on DSKJM1Z7X2PROD with RULES

h No Alternative Actions or Intervals After the ALS has been revised as required by paragraph f of this AD, no alternative inspection intervals or procedures may be approved, except as provided in paragraph i of this AD.
i Other FAA AD Provisions Alternative Methods of Compliance AMOCs: The Manager, International Validation Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19.
Send your request to the person identified in Related Information. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspection, the manager of the local Flight Standards District Office.

VerDate Sep<11>2014

16:24 Jun 04, 2021

Jkt 253001

j Related Information 1 Refer to Mandatory Continuing Airworthiness Information MCAI European Union Aviation Safety Agency EASA AD
20200120, dated May 27, 2020, and EASA
AD 20200278, dated December 14, 2020, for related information. This MCAI may be found in the AD docket at https
www.regulations.gov by searching for and locating Docket No. FAA20200857.
2 For more information about this AD, contact Doug Rudolph, Aviation Safety Engineer, FAA, General Aviation & Rotorcraft Section, International Validation Branch, 901
Locust, Room 301, Kansas City, MO 64106;
telephone: 816 3294059; fax: 816 329
4090; email: doug.rudolph@faa.gov.
k 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. 552a and 1 CFR
part 51.
2 You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise.
i Pilatus PC6 Aircraft Maintenance Manual Document No. 01975, Revision 29, dated February 28, 2020.
A Section 570003, Wing to Fuselage FittingsInspection/Check.
B Reserved ii Pilatus PC6 Aircraft Maintenance Manual Document No. 01975, Revision 30, dated October 30, 2020.
A Section 040000, Airworthiness Limitations, of Chapter 04, Airworthiness Limitations.
B Section 530001, Fuselage Wing FittingsInspection/Check.
iii Pilatus PC6 Airworthiness Limitations Document No. 02334, Revision 9, dated March 6, 2020.
A Appendix L, Wing to Fuselage FittingsInspection/Check.
B Reserved iv Pilatus PC6 Airworthiness Limitations Document No. 02334, Revision 10, dated October 30, 2020.
A Airworthiness Limitations Section.
B Appendix K, Fuselage Wing Fittings Inspection/Check.
3 For service information identified in this AD, contact Pilatus Aircraft Ltd., Customer Support General Aviation, CH
6371 Stans, Switzerland; telephone: +41 848
24 7 365; email: Techsupport@
pilatusaircraft.com; website: https
www.pilatusaircraft.com/en.
4 You may view this service information at the FAA, Airworthiness Products Section, Operational Safety Branch, 901 Locust, Kansas City, MO 64106. For information on the availability of this material at the FAA, call 816 3294148.
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, email: fedreg.legal@nara.gov, or go to:
https www.archives.gov/federal-register/cfr/
ibr-locations.html.

PO 00000

Frm 00008

Fmt 4700

Sfmt 4700

Issued on May 15, 2021.
Gaetano A. Sciortino, Deputy Director for Strategic Initiatives, Compliance & Airworthiness Division, Aircraft Certification Service.
FR Doc. 202111812 Filed 6421; 8:45 am BILLING CODE 491013P

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration 14 CFR Part 39
Docket No. FAA20210378; Project Identifier 2017SW122AD; Amendment 3921576; AD 20211114
RIN 2120AA64

Airworthiness Directives; Leonardo S.p.a. Helicopters Federal Aviation Administration FAA, DOT.
ACTION: Final rule; request for comments.
AGENCY:

The FAA is adopting a new airworthiness directive AD for certain Leonardo S.p.a. Model AW169
helicopters. This AD was prompted by reports of failed nose landing gear NLG
retraction actuators during the acceptance test procedures on the ground on the final assembly line. This AD requires depending on the helicopter configuration, various modifications, installation checks, inspections of the NLG and main landing gear MLG retraction actuators and of the plungers of the NLG and MLG up down lock actuators, and corrective actions if necessary. The FAA
is issuing this AD to address the unsafe condition on these products.
DATES: This AD becomes effective June 22, 2021.
The Director of the Federal Register approved the incorporation by reference of a certain document listed in this AD
as of June 22, 2021.
The FAA must receive comments on this AD by July 22, 2021.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202 4932251.
Mail: U.S. Department of Transportation, Docket Operations, M30, West Building Ground Floor, Room W12140, 1200 New Jersey Avenue SE, Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9 a.m. and 5
SUMMARY:

E:FRFM07JNR1.SGM

07JNR1