81 FR 76845 - Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 214 (November 4, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 214 (November 4, 2016)
| Page Range | 76845-76848 | |
| FR Document | 2016-26431 |
[Federal Register Volume 81, Number 214 (Friday, November 4, 2016)] [Rules and Regulations] [Pages 76845-76848] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-26431] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-9356; Directorate Identifier 2016-CE-033-AD; Amendment 39-18701; AD 2016-22-12] RIN 2120-AA64 Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for all Pilatus Aircraft Ltd. Models PC-6, PC-6-H1, PC-6-H2, PC-6/350, PC-6/ 350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1- H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as wear and cracks on the stabilizer-trim attachment and structural components. We are issuing this AD to require actions to address the unsafe condition on these products. [[Page 76846]] DATES: This AD is effective November 4, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 4, 2016. We must receive comments on this AD by December 19, 2016. ADDRESSES: You may send comments by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: (202) 493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 STANS, Switzerland; telephone: +41 41 619 3333; fax: +41 41 619 7311; Internet: http://www.pilatus-aircraft.com. You may view 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. It is also available on the Internet at http://www.regulations.gov by searching for locating Docket No. FAA-2016-9356. 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-2016- 9356; 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 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. 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: Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued Emergency AD No. 2016-0202-E, dated October 7, 2016 (referred to after this as ``the MCAI''), to correct an unsafe condition for the specified products. The MCAI states: Wear and cracks on the stabilizer-trim attachment and relevant structural components have been reported on aeroplanes having accomplished Pilatus Service Bulletin (SB) 53-001 Revision 1, as previously required by FOCA AD HB-2005-263. Subsequent investigation identified that slightly asymmetric installation and/or operational conditions may result in strong stabilizer vibration, causing crack initiation in the stabilizer- trim attachment fitting or connecting piece. This condition, if not detected and corrected, may lead to a failure of the fitting or connecting piece, possibly resulting in disconnection of the horizontal stabilizer rear attachment, with consequent loss of control of the aeroplane. To address this potential unsafe condition, Pilatus issued SB No. 53-003 (hereafter referred to as `the SB' in this AD) to provide inspection instructions. For the reason described above, this AD requires visual and non destructive inspections of the affected stabilizer-trim attachment components and the related parts and structure to detect cracks, and, depending on findings, the replacement of the affected parts. This AD also provides additional requirements for installation of these parts. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-9356. Related Service Information Under 1 CFR Part 51 Pilatus Aircraft Ltd. has issued PC-6 Service Bulletin No. 53-003, Revision 1, dated October 13, 2016. The service information describes procedures for inspecting the stabilizer-trim attachment components and the related parts and structure to detect cracks and replacing all cracked parts. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this AD. FAA's Determination and Requirements of This AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with this State of Design Authority, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are issuing this AD because we evaluated all information provided by the State of Design Authority and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. FAA's Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because failure of the stabilizer control system fitting or connecting piece could result in disconnection of the horizontal stabilizer rear attachment, with consequent loss of control. Therefore, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2016-9356; Directorate Identifier 2016-CE-033-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. Costs of Compliance We estimate that this AD will affect 30 products of U.S. registry. We also estimate that it will take about 5 work-hours per product to comply with the basic inspection requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $12,750, or $425 per product. In addition, we estimate that any necessary follow-on replacement actions will take about 6 work-hours and [[Page 76847]] require parts costing $2,000, for a cost of $2,510 per product. We have no way of determining the number of products that may need these actions. Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to 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 control number for the collection of information required by this AD is 2120- 0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is 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. 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 that 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. 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: 2016-22-12 Pilatus Aircraft Ltd.: Amendment 39-18701; Docket No. FAA-2016-9356; Directorate Identifier 2016-CE-033-AD. (a) Effective Date This airworthiness directive (AD) becomes effective November 4, 2016. (b) Affected ADs None. (c) Applicability (1) This AD applies to PILATUS Models PC-6, PC-6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC- 6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/ C1-H2 airplanes, all manufacturer serial numbers, including MSN 2001 through 2092 (see Note 1 of paragraph c), certificated in any category. Note 1 of paragraph (c): For MSN 2001-2092, these airplanes are also identified as Fairchild Republic Company PC-6 airplanes, Fairchild Industries PC-6 airplanes, Fairchild Heli Porter PC-6 airplanes, or Fairchild-Hiller Corporation PC-6 airplanes. (2) For the purpose of this AD, an ``affected part'' is any stabilizer-trim attachment component and the related parts and structure, as identified in Pilatus Aircraft Ltd. (Pilatus) PC-6 Service Bulletin (SB) No. 53-003, Revision 1, dated October 13, 2016. (d) Subject Air Transport Association of America (ATA) Code 53: Fuselage. (e) Reason This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as wear and cracks on the stabilizer-trim attachment and structural components. This condition, if not corrected, could cause failure of the stabilizer control system fitting or connecting piece, which could result in disconnection of the horizontal stabilizer rear attachment with consequent loss of control. (f) Actions and Compliance Unless already done, do the following actions. (1) For MSN 337 through 1005 and 2001 through 2092: Before further flight after November 4, 2016 (the effective date of this AD), do a visual inspection of the affected stabilizer-trim attachment and structural components following the Accomplishment Instructions in Pilatus PC-6 SB No. 53-003, Revision 1, dated October 13, 2016. (2) For MSN 337 through 1005 and 2001 through 2092: Within the next 100 hours time-in-service after November 4, 2016 (the effective date of this AD), do a visual inspection and dye-penetrant or eddy current inspection of the affected stabilizer-trim attachment and structural components following the Accomplishment Instructions in Pilatus PC-6 SB No. 53-003, Revision 1, dated October 13, 2016. (3) For MSN 337 through 1005 and 2001 through 2092: If any crack is found during any inspection required by paragraphs (f)(1) and (2) of this AD, before further flight, replace the affected part with a serviceable part following the Accomplishment Instructions in Pilatus PC-6 SB No. 53-003, Revision 1, dated October 13, 2016. For the purpose of this AD, a ``serviceable part'' is an affected part that is new, or has passed an inspection before installation following the Accomplishment Instructions in Pilatus PC-6 SB No. 53- 003, Revision 1, dated October 13, 2016. (4) For MSN 337 through 1005 and 2001 through 2092: Within 10 days after the inspections required by paragraphs (f)(1) and (2) of this AD or within the next 10 days after the effective date of this AD, whichever occurs later, report the results to Pilatus at the address in paragraph (j)(3) of this AD using the Report Form in Pilatus PC-6 SB No. 53-003, Revision 1, dated October 13, 2016. (5) For all affected MSNs: As of November 4, 2016 (the effective date of this AD), an affected part listed in Pilatus PC-6 SB No. 53- 003, Revision 1, dated October 13, 2016, may be installed provided it is a serviceable part. For the purpose of this AD, a ``serviceable part'' is an affected part that is new, or has passed an inspection before installation following the Accomplishment Instructions in Pilatus PC-6 SB No. 53-003, Revision 1, dated October 13, 2016. (g) Credit for Actions Done Following Previous Service Information This AD allows credit for the visual inspection required in paragraph (f)(1) of this [[Page 76848]] AD if done before November 4, 2016 (the effective date of this AD), following Pilatus PC-6 SB No. 53-003, dated October 4, 2016. The dye-penetrant or eddy current inspection must still be done following Pilatus PC-6 SB No. 53-003, Revision 1, dated October 13, 2016. (h) 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]. 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. (i) Related Information Refer to MCAI European Aviation Safety Agency (EASA) AD No. 2016-0202-E, dated October 7, 2016, and Pilatus Aircraft Ltd. PC-6 Service Bulletin No. 53-003, dated October 4, 2016. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-9356. (j) 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. (i) Pilatus Aircraft Ltd. PC-6 Service Bulletin No. 53-003, Revision 1, dated October 13, 2016. (ii) Reserved. (3) For Pilatus Aircraft Ltd. service information identified in this AD, contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 STANS, Switzerland; telephone: +41 41 619 3333; fax: +41 41 619 7311; Internet: http://www.pilatus-aircraft.com. (4) You may view this service information at the 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. It is also available on the Internet at http://www.regulations.gov by searching for locating Docket No. FAA-2016- 9356. (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 October 27, 2016. Pat Mullen, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-26431 Filed 11-3-16; 8:45 am] BILLING CODE 4910-13-P
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(d) Subject installed: Modify the stall warning and (iv) Saab Service Bulletin 340–27–121,
Air Transport Association (ATA) of identification system, in accordance with the dated July 11, 2014.
America Code 27, Flight Controls. Accomplishment Instructions of Saab Service (v) Saab Service Bulletin 340–27–122,
Bulletin 340–27–109, dated April 14, 2014. dated July 11, 2014.
(e) Reason (3) For service information identified in
(j) Parts Installation Prohibitions
This AD was prompted by a determination this AD, contact Saab AB, Saab Aeronautics,
that airplanes with certain modifications After the replacement required by SE–581 88, Linköping, Sweden; telephone
were excluded from the applicability in AD paragraph (h) of this AD, no person may +46 13 18 5591; fax +46 13 18 4874; email
2012–24–06, and are affected by the install any SWC having P/N 0020AK, saab340.techsupport@saabgroup.com;
identified unsafe condition; and the stall 0020AK1, 0020AK2, 0020AK4, 0020AK6, Internet http://www.saabgroup.com.
warning computer (SWC) required by AD 0020AK7, or 0020AK3 MOD 1, on any (4) You may view this service information
airplane. at the FAA, Transport Airplane Directorate,
2012–24–06 contained erroneous logic. We
are issuing this AD to prevent natural stall (k) Other FAA AD Provisions 1601 Lind Avenue SW., Renton, WA. For
events during operation in icing conditions, information on the availability of this
The following provisions also apply to this material at the FAA, call 425–227–1221.
which could result in loss of control of the AD:
airplane. (5) You may view this service information
(1) Alternative Methods of Compliance that is incorporated by reference at the
(f) Compliance (AMOCs): The Manager, International National Archives and Records
Branch, ANM–116, Transport Airplane Administration (NARA). For information on
Comply with this AD within the
Directorate, FAA, has the authority to the availability of this material at NARA, call
compliance times specified, unless already
approve AMOCs for this AD, if requested 202–741–6030, or go to: http://
done.
using the procedures found in 14 CFR 39.19. www.archives.gov/federal-register/cfr/ibr-
(g) Deactivation of Stall Speed Curves In accordance with 14 CFR 39.19, send your locations.html.
request to your principal inspector or local
For airplanes identified in paragraphs
Flight Standards District Office, as Issued in Renton, Washington, on October
(g)(1) and (g)(2) of this AD: Within 30 days
appropriate. If sending information directly 25, 2016.
after the effective date of this AD, do the
to the International Branch, send it to ATTN:
deactivation specified in paragraph (g)(1) or Dionne Palermo,
Shahram Daneshmandi, Aerospace Engineer,
(g)(2) of this AD, as applicable to airplane Acting Manager, Transport Airplane
International Branch, ANM–116, Transport
configuration, in accordance with the Directorate, Aircraft Certification Service.
Airplane Directorate, FAA, 1601 Lind
Accomplishment Instructions of Saab Service
Avenue SW., Renton, WA 98057–3356; [FR Doc. 2016–26327 Filed 11–3–16; 8:45 am]
Bulletin 340–27–116, dated October 18, 2013. telephone 425–227–1112; fax 425–227–1149.
(1) For airplanes with a basic wing tip that BILLING CODE 4910–13–P
Information may be emailed to: 9-ANM-116-
has been modified using Saab Service AMOC-REQUESTS@faa.gov. Before using
Bulletin 340–27–098: Deactivate the stall any approved AMOC, notify your appropriate
speed curves in the SWC having part number principal inspector, or lacking a principal
DEPARTMENT OF TRANSPORTATION
(P/N) 0020AK6. inspector, the manager of the local flight
(2) For airplanes with an extended wing tip standards district office/certificate holding
Federal Aviation Administration
that has been modified using Saab Service district office. The AMOC approval letter
Bulletin 340–27–099: Deactivate the stall must specifically reference this AD. 14 CFR Part 39
speed curves in the SWC having P/N (2) Contacting the Manufacturer: For any
0020AK7. requirement in this AD to obtain corrective [Docket No. FAA–2016–9356; Directorate
(h) Replacement of SWCs actions from a manufacturer, the action must Identifier 2016–CE–033–AD; Amendment
be accomplished using a method approved 39–18701; AD 2016–22–12]
Within 3 months after the effective date of by the Manager, International Branch, ANM–
this AD: Do the replacement specified in 116, Transport Airplane Directorate, FAA; or RIN 2120–AA64
paragraph (h)(1) or (h)(2) of this AD, as the European Aviation Safety Agency
applicable. (EASA); or Saab AB, Saab Aeronautics’ EASA
(1) For airplanes with basic wing tips:
Airworthiness Directives; Pilatus
Design Organization Approval (DOA). If Aircraft Ltd. Airplanes
Replace all SWCs with new, improved SWCs approved by the DOA, the approval must
having P/N 0020AK6–1, in accordance with include the DOA-authorized signature. AGENCY: Federal Aviation
the Accomplishment Instructions of Saab
Service Bulletin 340–27–121, dated July 11, (l) Related Information Administration (FAA), DOT.
2014. Refer to Mandatory Continuing ACTION: Final rule; request for
(2) For airplanes with extended wing tips: Airworthiness Information (MCAI) EASA comments.
Replace all SWCs with new, improved SWCs Airworthiness Directive 2014–0218, dated
having P/N 0020AK7–1, in accordance with September 29, 2014, for related information. SUMMARY: We are adopting a new
the Accomplishment Instructions of Saab This MCAI may be found in the AD docket airworthiness directive (AD) for all
Service Bulletin 340–27–122, dated July 11, on the Internet at http://www.regulations.gov Pilatus Aircraft Ltd. Models PC–6, PC–
2014. by searching for and locating Docket No. 6–H1, PC–6–H2, PC–6/350, PC–6/350–
(i) Concurrent Modification FAA–2015–6544. H1, PC–6/350–H2, PC–6/A, PC–6/A–H1,
Before or concurrently with the (m) Material Incorporated by Reference PC–6/A–H2, PC–6/B–H2, PC–6/B1–H2,
accomplishment of the applicable (1) The Director of the Federal Register PC–6/B2–H2, PC–6/B2–H4, PC–6/C–H2,
requirements of paragraph (h) of this AD, do approved the incorporation by reference and PC–6/C1–H2 airplanes. This AD
the actions specified in paragraph (i)(1) or (IBR) of the service information listed in this results from mandatory continuing
(i)(2) of this AD, as applicable to airplane paragraph under 5 U.S.C. 552(a) and 1 CFR airworthiness information (MCAI)
configuration. part 51. issued by the aviation authority of
(1) For airplanes on which either Saab AB (2) You must use this service information another country to identify and correct
Modification 2650 or Modification 2859 is as applicable to do the actions required by an unsafe condition on an aviation
rmajette on DSK2TPTVN1PROD with RULES
not installed: Modify the stall warning and this AD, unless this AD specifies otherwise. product. The MCAI describes the unsafe
identification system, in accordance with the (i) Saab Service Bulletin 340–27–109,
Accomplishment Instructions of Saab Service dated April 14, 2014. condition as wear and cracks on the
Bulletin 340–27–120, dated July 11, 2014. (ii) Saab Service Bulletin 340–27–116, stabilizer-trim attachment and structural
(2) For airplanes on which either Saab AB dated October 18, 2013. components. We are issuing this AD to
Modification 2650 or Modification 2859 is (iii) Saab Service Bulletin 340–27–120, require actions to address the unsafe
installed, or on which both modifications are dated July 11, 2014. condition on these products.
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require parts costing $2,000, for a cost (1) Is not a ‘‘significant regulatory (e) Reason
of $2,510 per product. We have no way action’’ under Executive Order 12866, This AD results from mandatory
of determining the number of products (2) Is not a ‘‘significant rule’’ under continuing airworthiness information (MCAI)
that may need these actions. the DOT Regulatory Policies and issued by the aviation authority of another
Procedures (44 FR 11034, February 26, country to identify and correct an unsafe
Paperwork Reduction Act condition on an aviation product. The MCAI
1979),
A federal agency may not conduct or (3) Will not affect intrastate aviation describes the unsafe condition as wear and
sponsor, and a person is not required to cracks on the stabilizer-trim attachment and
in Alaska, and
structural components. This condition, if not
respond to, nor shall a person be subject (4) Will not have a significant corrected, could cause failure of the stabilizer
to penalty for failure to comply with a economic impact, positive or negative, control system fitting or connecting piece,
collection of information subject to the on a substantial number of small entities which could result in disconnection of the
requirements of the Paperwork under the criteria of the Regulatory horizontal stabilizer rear attachment with
Reduction Act unless that collection of Flexibility Act. consequent loss of control.
information displays a current valid (f) Actions and Compliance
List of Subjects in 14 CFR Part 39
OMB control number. The control
Air transportation, Aircraft, Aviation Unless already done, do the following
number for the collection of information
safety, Incorporation by reference, actions.
required by this AD is 2120–0056. The (1) For MSN 337 through 1005 and 2001
paperwork cost associated with this AD Safety.
through 2092: Before further flight after
has been detailed in the Costs of Adoption of the Amendment November 4, 2016 (the effective date of this
Compliance section of this document AD), do a visual inspection of the affected
and includes time for reviewing Accordingly, under the authority stabilizer-trim attachment and structural
instructions, as well as completing and delegated to me by the Administrator, components following the Accomplishment
reviewing the collection of information. the FAA amends 14 CFR part 39 as Instructions in Pilatus PC–6 SB No. 53–003,
Therefore, all reporting associated with follows: Revision 1, dated October 13, 2016.
(2) For MSN 337 through 1005 and 2001
this AD is mandatory. Comments PART 39—AIRWORTHINESS through 2092: Within the next 100 hours
concerning the accuracy of this burden DIRECTIVES time-in-service after November 4, 2016 (the
and suggestions for reducing the burden effective date of this AD), do a visual
should be directed to the FAA at 800 ■ 1. The authority citation for part 39 inspection and dye-penetrant or eddy current
Independence Ave., SW., Washington, continues to read as follows: inspection of the affected stabilizer-trim
DC 20591. ATTN: Information attachment and structural components
Authority: 49 U.S.C. 106(g), 40113, 44701. following the Accomplishment Instructions
Collection Clearance Officer, AES–200.
§ 39.13 [Amended] in Pilatus PC–6 SB No. 53–003, Revision 1,
Authority for This Rulemaking dated October 13, 2016.
■ 2. The FAA amends § 39.13 by adding (3) For MSN 337 through 1005 and 2001
Title 49 of the United States Code
the following new AD: through 2092: If any crack is found during
specifies the FAA’s authority to issue any inspection required by paragraphs (f)(1)
rules on aviation safety. Subtitle I, 2016–22–12 Pilatus Aircraft Ltd.:
Amendment 39–18701; Docket No. and (2) of this AD, before further flight,
section 106, describes the authority of replace the affected part with a serviceable
FAA–2016–9356; Directorate Identifier
the FAA Administrator. ‘‘Subtitle VII: 2016–CE–033–AD. part following the Accomplishment
Aviation Programs,’’ describes in more Instructions in Pilatus PC–6 SB No. 53–003,
detail the scope of the Agency’s (a) Effective Date Revision 1, dated October 13, 2016. For the
authority. This airworthiness directive (AD) becomes purpose of this AD, a ‘‘serviceable part’’ is an
We are issuing this rulemaking under effective November 4, 2016. affected part that is new, or has passed an
the authority described in ‘‘Subtitle VII, inspection before installation following the
(b) Affected ADs Accomplishment Instructions in Pilatus PC–
Part A, Subpart III, section 44701:
None. 6 SB No. 53–003, Revision 1, dated October
General requirements.’’ Under that 13, 2016.
section, Congress charges the FAA with (c) Applicability
(4) For MSN 337 through 1005 and 2001
promoting safe flight of civil aircraft in (1) This AD applies to PILATUS Models through 2092: Within 10 days after the
air commerce by prescribing regulations PC–6, PC–6–H1, PC–6–H2, PC–6/350, PC–6/ inspections required by paragraphs (f)(1) and
for practices, methods, and procedures 350–H1, PC–6/350–H2, PC–6/A, PC–6/A–H1, (2) of this AD or within the next 10 days after
the Administrator finds necessary for PC–6/A–H2, PC–6/B–H2, PC–6/B1–H2, PC– the effective date of this AD, whichever
safety in air commerce. This regulation 6/B2–H2, PC–6/B2–H4, PC–6/C–H2, and PC– occurs later, report the results to Pilatus at
6/C1–H2 airplanes, all manufacturer serial the address in paragraph (j)(3) of this AD
is within the scope of that authority numbers, including MSN 2001 through 2092
because it addresses an unsafe condition using the Report Form in Pilatus PC–6 SB
(see Note 1 of paragraph c), certificated in No. 53–003, Revision 1, dated October 13,
that is likely to exist or develop on any category. 2016.
products identified in this rulemaking Note 1 of paragraph (c): For MSN 2001– (5) For all affected MSNs: As of November
action. 2092, these airplanes are also identified as 4, 2016 (the effective date of this AD), an
Fairchild Republic Company PC–6 airplanes, affected part listed in Pilatus PC–6 SB No.
Regulatory Findings Fairchild Industries PC–6 airplanes, 53–003, Revision 1, dated October 13, 2016,
We determined that this AD will not Fairchild Heli Porter PC–6 airplanes, or may be installed provided it is a serviceable
have federalism implications under Fairchild-Hiller Corporation PC–6 airplanes. part. For the purpose of this AD, a
Executive Order 13132. This AD will (2) For the purpose of this AD, an ‘‘affected ‘‘serviceable part’’ is an affected part that is
not have a substantial direct effect on part’’ is any stabilizer-trim attachment new, or has passed an inspection before
component and the related parts and installation following the Accomplishment
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the States, on the relationship between
the national government and the States, structure, as identified in Pilatus Aircraft Ltd. Instructions in Pilatus PC–6 SB No. 53–003,
(Pilatus) PC–6 Service Bulletin (SB) No. 53– Revision 1, dated October 13, 2016.
or on the distribution of power and 003, Revision 1, dated October 13, 2016.
responsibilities among the various (g) Credit for Actions Done Following
levels of government. (d) Subject Previous Service Information
For the reasons discussed above, I Air Transport Association of America This AD allows credit for the visual
certify that this AD: (ATA) Code 53: Fuselage. inspection required in paragraph (f)(1) of this
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![76848 Federal Register / Vol. 81, No. 214 / Friday, November 4, 2016 / Rules and Regulations
AD if done before November 4, 2016 (the (2) You must use this service information are issuing this AD to detect and correct
effective date of this AD), following Pilatus as applicable to do the actions required by cracking in the bulkhead, which could
PC–6 SB No. 53–003, dated October 4, 2016. this AD, unless this AD specifies otherwise. result in reduced structural integrity of
The dye-penetrant or eddy current inspection (i) Pilatus Aircraft Ltd. PC–6 Service
the airplane.
must still be done following Pilatus PC–6 SB Bulletin No. 53–003, Revision 1, dated
No. 53–003, Revision 1, dated October 13, October 13, 2016. DATES: This AD is effective November
2016. (ii) Reserved. 21, 2016.
(3) For Pilatus Aircraft Ltd. service The Director of the Federal Register
(h) Other FAA AD Provisions information identified in this AD, contact approved the incorporation by reference
The following provisions also apply to this Pilatus Aircraft Ltd., Customer Liaison of a certain publication listed in this AD
AD: Manager, CH–6371 STANS, Switzerland; as of November 21, 2016.
(1) Alternative Methods of Compliance telephone: +41 41 619 3333; fax: +41 41 619
We must receive comments on this
(AMOCs): The Manager, Standards Office, 7311; Internet: http://www.pilatus-
aircraft.com. AD by December 19, 2016.
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures (4) You may view this service information ADDRESSES: You may send comments,
found in 14 CFR 39.19. Send information to at the FAA, FAA, Small Airplane Directorate, using the procedures found in 14 CFR
ATTN: Doug Rudolph, Aerospace Engineer, 901 Locust, Kansas City, Missouri 64106. For 11.43 and 11.45, by any of the following
FAA, Small Airplane Directorate, 901 Locust, information on the availability of this methods:
Room 301, Kansas City, Missouri 64106; material at the FAA, call (816) 329–4148. It • Federal eRulemaking Portal: Go to
telephone: (816) 329–4059; fax: (816) 329– is also available on the Internet at http:// http://www.regulations.gov. Follow the
4090; email: doug.rudolph@faa.gov. Before www.regulations.gov by searching for
locating Docket No. FAA–2016–9356.
instructions for submitting comments.
using any approved AMOC on any airplane
(5) You may view this service information • Fax: 202–493–2251.
to which the AMOC applies, notify your
appropriate principal inspector (PI) in the that is incorporated by reference at the • Mail: U.S. Department of
FAA Flight Standards District Office (FSDO), National Archives and Records Transportation, Docket Operations, M–
or lacking a PI, your local FSDO. Administration (NARA). For information on 30, West Building Ground Floor, Room
(2) Airworthy Product: For any requirement the availability of this material at NARA, call W12–140, 1200 New Jersey Avenue SE.,
in this AD to obtain corrective actions from 202–741–6030, or go to: http:// Washington, DC 20590.
a manufacturer or other source, use these www.archives.gov/federal-register/cfr/ibr- • Hand Delivery: Deliver to Mail
actions if they are FAA-approved. Corrective locations.html. address above between 9 a.m. and 5
actions are considered FAA-approved if they p.m., Monday through Friday, except
are approved by the State of Design Authority Issued in Kansas City, Missouri on October
27, 2016. Federal holidays.
(or their delegated agent). You are required
For service information identified in
to assure the product is airworthy before it Pat Mullen,
is returned to service. this final rule, contact Boeing
Acting Manager, Small Airplane Directorate,
(3) Reporting Requirements: For any Commercial Airplanes, Attention:
Aircraft Certification Service.
reporting requirement in this AD, a federal Contractual & Data Services (C&DS),
[FR Doc. 2016–26431 Filed 11–3–16; 8:45 am]
agency may not conduct or sponsor, and a 2600 Westminster Blvd., MC 110–SK57,
BILLING CODE 4910–13–P
person is not required to respond to, nor Seal Beach, CA 90740–5600; telephone
shall a person be subject to a penalty for 562–797–1717; Internet https://
failure to comply with a collection of www.myboeingfleet.com. You may view
information subject to the requirements of DEPARTMENT OF TRANSPORTATION
this referenced service information at
the Paperwork Reduction Act unless that
Federal Aviation Administration the FAA, Transport Airplane
collection of information displays a current
valid OMB Control Number. The OMB Directorate, 1601 Lind Avenue SW.,
Control Number for this information 14 CFR Part 39 Renton, WA. For information on the
collection is 2120–0056. Public reporting for availability of this material at the FAA,
this collection of information is estimated to [Docket No. FAA–2016–9306; Directorate call 425–227–1221. It is also available
be approximately 5 minutes per response, Identifier 2016–NM–169–AD; Amendment on the Internet at http://
including the time for reviewing instructions, 39–18707; AD 2016–22–18]
www.regulations.gov by searching for
completing and reviewing the collection of RIN 2120–AA64 and locating Docket No. FAA–2016–
information. All responses to this collection 9306.
of information are mandatory. Comments Airworthiness Directives; The Boeing
concerning the accuracy of this burden and Company Airplanes Examining the AD Docket
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence AGENCY: Federal Aviation You may examine the AD docket on
Ave. SW., Washington, DC 20591, Attn: Administration (FAA), DOT. the Internet at http://
Information Collection Clearance Officer, www.regulations.gov by searching for
ACTION: Final rule; request for
AES–200. and locating Docket No. FAA–2016–
comments.
9306; or in person at the Docket
(i) Related Information
SUMMARY: We are adopting a new Management Facility between 9 a.m.
Refer to MCAI European Aviation Safety and 5 p.m., Monday through Friday,
Agency (EASA) AD No. 2016–0202–E, dated airworthiness directive (AD) for all The
Boeing Company Model MD–90–30 except Federal holidays. The AD docket
October 7, 2016, and Pilatus Aircraft Ltd. PC–
6 Service Bulletin No. 53–003, dated October airplanes. This AD requires a detailed contains this AD, the regulatory
4, 2016. You may examine the MCAI on the inspection of the forward and aft evaluation, any comments received, and
Internet at http://www.regulations.gov by surfaces on the left and right sides at the other information. The street address for
searching for and locating Docket No. FAA– cant station 1520 bulkhead for any crack the Docket Office (phone: 800–647–
2016–9356. in the upper cap and (cap) doubler, 5527) is in the ADDRESSES section.
rmajette on DSK2TPTVN1PROD with RULES
(j) Material Incorporated by Reference webs and doublers, stiffeners, and the Comments will be available in the AD
lower tee cap between longerons 3 docket shortly after receipt.
(1) The Director of the Federal Register
approved the incorporation by reference through 11, and repairs if necessary. FOR FURTHER INFORMATION CONTACT:
(IBR) of the service information listed in this This AD was prompted by a report of George Garrido, Aerospace Engineer,
paragraph under 5 U.S.C. 552(a) and 1 CFR cracking in various structures in the Airframe Branch, ANM–120L, FAA, Los
part 51. fuselage cant station 1520 bulkhead. We Angeles Aircraft Certification Office
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Document Created: 2018-02-14 08:26:25
Document Modified: 2018-02-14 08:26:25
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule; request for comments. | |
| Dates | This AD is effective November 4, 2016. | |
| 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] | |
| FR Citation | 81 FR 76845 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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