80 FR 19873 - Airworthiness Directives; Agusta S.p.A. Helicopters
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 71 (April 14, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 71 (April 14, 2015)
| Page Range | 19873-19876 | |
| FR Document | 2015-08384 |
[Federal Register Volume 80, Number 71 (Tuesday, April 14, 2015)] [Rules and Regulations] [Pages 19873-19876] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-08384] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-0908; Directorate Identifier 2015-SW-007-AD; Amendment 39-18136; AD 2015-05-52] RIN 2120-AA64 Airworthiness Directives; Agusta S.p.A. Helicopters AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). [[Page 19874]] ACTION: Final rule; request for comments. ----------------------------------------------------------------------- SUMMARY: We are publishing a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109, A109A, A109A II, A109C, A109K2, A109E, A119, A109S, AW119 MKII, and AW109SP helicopters, which was sent previously to all known U.S. owners and operators of these helicopters. This AD requires inspecting certain tail rotor (T/R) pitch control links (pitch links) for freedom of movement, corrosion, excessive friction of the spherical bearings, and cracks. This AD is prompted by a report of an in-flight failure of a pitch link on an Agusta Model AW119 MKII helicopter. These actions are intended to prevent loss of T/ R pitch control and subsequent loss of control of the helicopter. DATES: This AD becomes effective April 29, 2015 to all persons except those persons to whom it was made immediately effective by Emergency AD (EAD) 2015-05-52, issued on March 4, 2015, which contains the requirements of this AD. The Director of the Federal Register approved the incorporation by reference of certain documents listed in this AD as of April 29, 2015. We must receive comments on this AD by June 15, 2015. ADDRESSES: You may send comments by any of the following methods:Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically. Fax: 202-493-2251. Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001. Hand Delivery: Deliver to the ``Mail'' address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, any incorporated by reference service information, the European Aviation Safety Agency (EASA) AD, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (telephone 800-647- 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. For service information identified in this AD, contact AgustaWestland, Product Support Engineering, Via del Gregge, 100, 21015 Lonate Pozzolo (VA) Italy, ATTN: Maurizio D'Angelo; telephone 39-0331- 664757; fax 39 0331-664680; or at http://www.agustawestland.com/technical-bulletins. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. It is also available on the Internet at http://www.regulations.gov in Docket No. FAA-2015- 0908. FOR FURTHER INFORMATION CONTACT: Martin Crane, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments prior to it becoming effective. However, we invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that resulted from adopting this AD. The most helpful comments reference a specific portion of the AD, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit them only one time. We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this rulemaking during the comment period. We will consider all the comments we receive and may conduct additional rulemaking based on those comments. Discussion On March 4, 2015, we issued EAD 2015-05-52, which requires inspecting each pitch link part number (P/N) 109-0130-05-117 with 100 hours or less time-in-service since overhaul for freedom of movement, corrosion, and to determine the force required to rotate the spherical bearings. If there is any corrosion or if the force exceeds a certain amount, then the pitch link is unairworthy. If there is no corrosion and the force does not exceed the amount, then EAD 2015-05-52 requires cleaning and visually inspecting the pitch link rod for a crack. If there is a crack, then the pitch link is unairworthy. EAD 2015-05-52 was sent previously to all known U.S. owners and operators of these helicopters and resulted from a report of an in-flight failure of a pitch link P/N 109-0130-05-117 on an Agusta Model AW119 MKII helicopter. EAD 2015-05-52 was prompted by EAD No. 2015-0035-E, dated February 27, 2015, issued by EASA, which is the Technical Agent for the Member States of the European Union, to correct an unsafe condition for AgustaWestland S.p.A. Model A109A, A109AII, A109C, A109E, A109K2, A109LUH, A109S, AW109SP, A119, and AW119MKII helicopters. EASA advises of the reported ``in-flight breaking'' of the T/R pitch control link P/ N 109-0130-05-117. EASA EAD 2015-0035-E requires inspecting the T/R pitch control link for corrosion, rotation resistance or binding, and cracks. FAA's Determination These helicopters have been approved by the aviation authority of Italy and are approved for operation in the United States. Pursuant to our bilateral agreement with Italy, EASA, its technical representative, has notified us of the unsafe condition described in the EASA AD. We are issuing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs. Related Service Information Under 1 CFR Part 51 AgustaWestland issued Alert Bollettino Tecnico (BT) Nos. 109-145, 109EP-141, 109K-65, 109S-065, 109SP-087, and 119-072, all revision A, and all dated February 27, 2015. These alert BTs specify inspections of pitch link P/N 109-0130-05-117 for corrosion, freedom of movement, excessive friction of the spherical bearings, and cracks. This information is reasonably available at http://www.regulations.gov in Docket No. FAA-2015-0908. Or see ADDRESSES for other ways to access this service information. AD Requirements This AD retains the requirements of EAD 2015-05-52 and requires inspecting the pitch link for freedom of movement for rotation resistance or binding. This AD also requires removing [[Page 19875]] the pitch link and inspecting each pitch link spherical bearing for corrosion and the force required to rotate each pitch link spherical bearing. If there is any corrosion, the pitch link is unairworthy. If the force required to rotate a spherical bearing in either end of the pitch link is greater than 7.30 N (1.64 pounds force), the pitch link is unairworthy. If the force required to rotate the spherical bearings in both ends of the pitch link is equal to or less than 7.30 N (1.64 pounds force), this AD requires cleaning and visually inspecting the pitch link rod for a crack using a 10x or higher power magnifying glass or by performing a dye penetrant inspection. If there is a crack, the pitch link is unairworthy. Interim Action We consider this AD to be an interim action. If final action is later identified, we might consider further rulemaking. Costs of Compliance We estimate that this AD affects 253 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. It takes about 2.5 work-hours at $85 per work-hour to perform the inspections, for a total cost of $213 per helicopter and $53,889 for the U.S. operator fleet. If required, replacing a pitch link will cost about $1,957 for parts. We do not anticipate any additional labor costs to install a new pitch link as opposed to re- installing the existing pitch link. According to AgustaWestland's service information some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage by Agusta. Accordingly, we have included all costs in our cost estimate. FAA's Justification and Determination of the Effective Date Providing an opportunity for public comments prior to adopting these AD requirements would delay implementing the safety actions needed to correct this known unsafe condition. Therefore, we found and continue to find that the risk to the flying public justifies waiving notice and comment prior to the adoption of this rule because the previously described unsafe condition can adversely affect the controllability of the helicopter and the initial required action must be accomplished before further flight. Since it was found that immediate corrective action was required, notice and opportunity for prior public comment before issuing this AD were impracticable and contrary to the public interest and good cause existed to make the AD effective immediately by EAD 2015-05-52, issued on March 4, 2015, to all known U.S. owners and operators of these helicopters. These conditions still exist and the AD is hereby published in the Federal Register as an amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 39.13) to make it effective to all persons. 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, I certify that this AD: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; 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. We prepared an economic evaluation of the estimated costs to comply with this AD and placed it in the AD docket. 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 airworthiness directive (AD): 2015-05-52 Agusta S.p.A.: Amendment 39-18136; Docket No. FAA-2015- 0908; Directorate Identifier 2015-SW-007-AD. (a) Applicability This AD applies to Agusta S.p.A. Model A109, A109A, A109A II, A109C, A109K2, A109E, A119, A109S, AW119 MKII, and AW109SP helicopters, certificated in any category, with a tail rotor pitch control link (pitch link) part number 109-0130-05-117 with 100 hours or less time-in-service since overhaul. (b) Unsafe Condition This AD defines the unsafe condition as failure of a pitch link. This condition could result in loss of tail rotor pitch control and subsequent loss of control of the helicopter. (c) Effective Date This AD becomes effective April 29, 2015 to all persons except those persons to whom it was made immediately effective by Emergency AD 2015-05-52, issued on March 4, 2015, which contains the requirements of this AD. (d) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (e) Required Actions (1) Before further flight, inspect the pitch link for freedom of movement while it is installed on the helicopter. (i) If there is rotation resistance or binding, before further flight, perform the actions in paragraphs (e)(2) through (e)(3) of this AD. (ii) If there is no rotation resistance and no binding, within 5 hours time-in-service, perform the actions in paragraphs (e)(2) through (e)(3) of this AD. (2) Remove the pitch link and inspect each pitch link spherical bearing for corrosion. If there is any corrosion, the pitch link is unairworthy. (3) Determine the force required to rotate each pitch link spherical bearing as depicted in Figure 1 of AgustaWestland Alert Bollettino Tecnico (BT) No. 109-145, 109EP-141, 109K-65, 109S-065, 109SP-087, or 119-072, all Revision A, and all dated February 27, 2015, as applicable to your model helicopter. [[Page 19876]] (i) If the force required to rotate a spherical bearing in either end of the pitch link is greater than 7.30 N (1.64 pounds force), the pitch link is unairworthy. (ii) If the force required to rotate the spherical bearings in both ends of the pitch link is equal to or less than 7.30 N (1.64 pounds force), after cleaning the pitch link rod using aliphatic naphtha or equivalent and a soft non-metallic bristle brush, visually inspect the pitch link rod for a crack in the area depicted in Figure 1 of AgustaWestland Alert BT No. 109-145, 109EP-141, 109K- 65, 109S-065, 109SP-087, or 119-072, all Revision A, and all dated February 27, 2015, as applicable to your model helicopter, using a 10x or higher power magnifying glass or by dye penetrant inspection. If there is a crack, the pitch link is unairworthy. (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Martin Crane, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email [email protected]. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC. (g) Additional Information The subject of this AD is addressed in European Aviation Safety Agency (EASA) Emergency AD No. 2015-0035-E, dated February 27, 2015. You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No. FAA-2015-0908. (h) Subject Joint Aircraft Service Component (JASC) Code: 6720, Tail Rotor Controls. (i) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference 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) AgustaWestland Alert Bollettino Tecnico (BT) No. 109-145, Revision A, dated February 27, 2015. (ii) AgustaWestland Alert BT No. 109EP-141, Revision A, dated February 27, 2015. (iii) AgustaWestland Alert BT No. 109K-65, Revision A, dated February 27, 2015. (iv) AgustaWestland Alert BT No. 109S-065, Revision A, dated February 27, 2015. (v) AgustaWestland Alert BT No. 109SP-087, Revision A, dated February 27, 2015. (vi) AgustaWestland Alert BT No. 119-072, Revision A, dated February 27, 2015. (3) For AgustaWestland service information identified in this AD, contact AgustaWestland, Product Support Engineering, Via del Gregge, 100, 21015 Lonate Pozzolo (VA) Italy, ATTN: Maurizio D'Angelo; telephone 39-0331-664757; fax 39 0331-664680; or at http://www.agustawestland.com/technical-bulletins. (4) You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. For information on the availability of this material at the FAA, call (817) 222-5110. (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 Fort Worth, Texas, on April 6, 2015. Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2015-08384 Filed 4-13-15; 8:45 am] BILLING CODE 4910-13-P
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RJ100A airplanes; certificated in any the DOA, the approval must include the September 9, 2013, for related information.
category. DOA-authorized signature. Accomplishment This MCAI may be found in the AD docket
of the repair does not constitute a terminating on the Internet at http://
(d) Subject action for the inspections required by www.regulations.gov/
Air Transport Association (ATA) of paragraph (g) of this AD. #!documentDetail;D=FAA-2014-0621-0002.
America Code 53, Fuselage. (2) Service information identified in this
(i) Credit for Previous Actions
(e) Reason AD that is not incorporated by reference is
(1) This paragraph provides credit for the available at the addresses specified in
This AD was prompted by a report of a initial inspection and corrective action on paragraphs (l)(3) and (l)(4) of this AD.
pressurization problem on an airplane during stringer 30, left hand (LH) and right hand
climb-out; a subsequent investigation showed (RH), as required by paragraph (g) of this AD, (l) Material Incorporated by Reference
a crack in the fuselage skin. We are issuing if those actions were performed before the (1) The Director of the Federal Register
this AD to detect and correct cracking, effective date of this AD using BAE Systems approved the incorporation by reference
corrosion, and other defects, which could (Operations) Limited Inspection Service (IBR) of the service information listed in this
affect the structural integrity of the airplane. Bulletin 53–239, dated June 13, 2012, which paragraph under 5 U.S.C. 552(a) and 1 CFR
is not incorporated by reference in this AD. part 51.
(f) Compliance (2) This paragraph provides credit for the (2) You must use this service information
Comply with this AD within the initial inspection and corrective action, as as applicable to do the actions required by
compliance times specified, unless already required by paragraph (g) of this AD, if those this AD, unless this AD specifies otherwise.
done. actions were performed before the effective (i) BAE Systems (Operations) Limited
date of this AD using BAE Systems Inspection Service Bulletin 53–239,
(g) Repetitive Inspections
(Operations) Limited Inspection Service including Appendix 2, Revision 3, dated May
(1) Within the compliance times specified Bulletin 53–239, Revision 1, dated June 18, 7, 2014.
in paragraphs (g)(1)(i) and (g)(1)(ii) of this 2013, which is not incorporated by reference (ii) Reserved.
AD, as applicable: Do an external eddy in this AD. (3) For service information identified in
current inspection on the aft skin lap joints (3) This paragraph provides credit for the this AD, contact BAE Systems (Operations)
of the rear fuselage for cracking, corrosion, initial inspection and corrective action, as Limited, Customer Information Department,
and other defects (i.e., surface damage and required by paragraph (g) of this AD, if those Prestwick International Airport, Ayrshire,
spot displacement), in accordance with actions were performed before the effective
paragraph 2.C. of the Accomplishment KA9 2RW, Scotland, United Kingdom;
date of this AD using BAE Systems telephone +44 1292 675207; fax +44 1292
Instructions of BAE Systems (Operations) (Operations) Limited Inspection Service
Limited Inspection Service Bulletin 53–239, 675704; email RApublications@
Bulletin 53–239, Revision 2, dated July 15, baesystems.com; Internet http://
including Appendix 2, Revision 3, dated May 2013, which is not incorporated by reference
7, 2014. www.baesystems.com/Businesses/
in this AD. RegionalAircraft/index.htm.
(i) For any airplane which has accumulated
9,000 flight cycles or more since the (j) Other FAA AD Provisions (4) You may view this service information
airplane’s first flight as of the effective date at the FAA, Transport Airplane Directorate,
The following provisions also apply to this
of this AD: Do the inspection within 1,000 AD: 1601 Lind Avenue SW., Renton, WA. For
flight cycles or 6 months after of the effective (1) Alternative Methods of Compliance information on the availability of this
date of this AD, whichever occurs first. (AMOCs): The Manager, International material at the FAA, call 425–227–1221.
(ii) For any airplane which has Branch, ANM–116, Transport Airplane (5) You may view this service information
accumulated less than 9,000 flight cycles Directorate, FAA, has the authority to that is incorporated by reference at the
since the airplane’s first flight as the effective approve AMOCs for this AD, if requested National Archives and Records
date of this AD: Do the inspection before using the procedures found in 14 CFR 39.19. Administration (NARA). For information on
accumulating 10,000 flight cycles since the In accordance with 14 CFR 39.19, send your the availability of this material at NARA, call
airplane’s first flight. request to your principal inspector or local 202–741–6030, or go to: http://
(2) Repeat the inspection required by Flight Standards District Office, as www.archives.gov/federal-register/cfr/ibr-
paragraph (g)(1) of this AD thereafter at appropriate. If sending information directly locations.html.
intervals not to exceed the times specified in to the International Branch, send it to ATTN: Issued in Renton, Washington, on March
paragraphs (g)(2)(i) and (g)(2)(ii) of this AD, Todd Thompson, Aerospace Engineer, 19, 2015.
as applicable to the airplane’s modification International Branch, ANM–116, Transport Michael Kaszycki,
status. Airplane Directorate, FAA, 1601 Lind
(i) For Model BAe 146 series airplanes and Avenue SW., Renton, WA 98057–3356; Acting Manager, Transport Airplane
Model Avro 146–RJ series airplanes post telephone 425–227–1175; fax 425–227–1149. Directorate, Aircraft Certification Service.
modification HCM50070E, or post Information may be emailed to: 9-ANM-116- [FR Doc. 2015–07800 Filed 4–13–15; 8:45 am]
modification HCM50070F, or post AMOC-REQUESTS@faa.gov. Before using BILLING CODE 4910–13–P
modification HCM50259A, repeat the any approved AMOC, notify your appropriate
inspection at intervals not to exceed 4,000 principal inspector, or lacking a principal
flight cycles. inspector, the manager of the local flight DEPARTMENT OF TRANSPORTATION
(ii) For Model BAe 146 series airplanes and standards district office/certificate holding
Model Avro 146–RJ series airplanes pre- district office. The AMOC approval letter Federal Aviation Administration
modification HCM50070E, and pre- must specifically reference this AD.
modification HCM50070F, and pre- (2) Contacting the Manufacturer: For any
modification HCM50259A, repeat the requirement in this AD to obtain corrective 14 CFR Part 39
inspection at intervals not to exceed 7,500 actions from a manufacturer, the action must
flight cycles. be accomplished using a method approved [Docket No. FAA–2015–0908; Directorate
by the Manager, International Branch, ANM– Identifier 2015–SW–007–AD; Amendment
(h) Corrective Action 39–18136; AD 2015–05–52]
116, Transport Airplane Directorate, FAA; or
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If any cracking, corrosion, or other defect EASA; or BAE Systems (Operations)
is found during any inspection required by Limited’s EASA DOA. If approved by the RIN 2120–AA64
this AD: Before further flight, repair using a DOA, the approval must include the DOA-
method approved by the Manager, authorized signature. Airworthiness Directives; Agusta
International Branch, ANM–116, Transport S.p.A. Helicopters
Airplane Directorate, FAA; or the European (k) Related Information
Aviation Safety Agency (EASA); or BAE (1) Refer to Mandatory Continuing AGENCY: Federal Aviation
Systems (Operations) Limited’s EASA Design Airworthiness Information (MCAI) EASA Administration (FAA), Department of
Organization Approval (DOA). If approved by Airworthiness Directive 2013–0207, dated Transportation (DOT).
VerDate Sep<11>2014 16:01 Apr 13, 2015 Jkt 235001 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 E:\FR\FM\14APR1.SGM 14APR1](https://thefederalregister.org/doc/80_FR_19944/page/1.svg)
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the pitch link and inspecting each pitch interest and good cause existed to make Adoption of the Amendment
link spherical bearing for corrosion and the AD effective immediately by EAD Accordingly, under the authority
the force required to rotate each pitch 2015–05–52, issued on March 4, 2015, delegated to me by the Administrator,
link spherical bearing. If there is any to all known U.S. owners and operators the FAA amends 14 CFR part 39 as
corrosion, the pitch link is unairworthy. of these helicopters. These conditions follows:
If the force required to rotate a spherical still exist and the AD is hereby
bearing in either end of the pitch link published in the Federal Register as an PART 39—AIRWORTHINESS
is greater than 7.30 N (1.64 pounds amendment to section 39.13 of the DIRECTIVES
force), the pitch link is unairworthy. If Federal Aviation Regulations (14 CFR
the force required to rotate the spherical 39.13) to make it effective to all persons. ■ 1. The authority citation for part 39
bearings in both ends of the pitch link continues to read as follows:
Authority for This Rulemaking
is equal to or less than 7.30 N (1.64 Authority: 49 U.S.C. 106(g), 40113, 44701.
pounds force), this AD requires cleaning Title 49 of the United States Code
and visually inspecting the pitch link specifies the FAA’s authority to issue § 39.13 [Amended]
rod for a crack using a 10× or higher rules on aviation safety. Subtitle I, ■ 2. The FAA amends § 39.13 by adding
power magnifying glass or by section 106, describes the authority of the following new airworthiness
performing a dye penetrant inspection. the FAA Administrator. ‘‘Subtitle VII: directive (AD):
If there is a crack, the pitch link is Aviation Programs,’’ describes in more
2015–05–52 Agusta S.p.A.: Amendment 39–
unairworthy. detail the scope of the Agency’s 18136; Docket No. FAA–2015–0908;
authority. Directorate Identifier 2015–SW–007–AD.
Interim Action We are issuing this rulemaking under
We consider this AD to be an interim the authority described in ‘‘Subtitle VII, (a) Applicability
action. If final action is later identified, Part A, Subpart III, Section 44701: This AD applies to Agusta S.p.A. Model
we might consider further rulemaking. General requirements.’’ Under that A109, A109A, A109A II, A109C, A109K2,
section, Congress charges the FAA with A109E, A119, A109S, AW119 MKII, and
Costs of Compliance AW109SP helicopters, certificated in any
promoting safe flight of civil aircraft in
We estimate that this AD affects 253 category, with a tail rotor pitch control link
air commerce by prescribing regulations (pitch link) part number 109–0130–05–117
helicopters of U.S. Registry. We estimate for practices, methods, and procedures with 100 hours or less time-in-service since
that operators may incur the following the Administrator finds necessary for overhaul.
costs in order to comply with this AD. safety in air commerce. This regulation
It takes about 2.5 work-hours at $85 per is within the scope of that authority (b) Unsafe Condition
work-hour to perform the inspections, because it addresses an unsafe condition This AD defines the unsafe condition as
for a total cost of $213 per helicopter that is likely to exist or develop on failure of a pitch link. This condition could
and $53,889 for the U.S. operator fleet. products identified in this rulemaking result in loss of tail rotor pitch control and
If required, replacing a pitch link will subsequent loss of control of the helicopter.
action.
cost about $1,957 for parts. We do not (c) Effective Date
anticipate any additional labor costs to Regulatory Findings
This AD becomes effective April 29, 2015
install a new pitch link as opposed to We determined that this AD will not to all persons except those persons to whom
re-installing the existing pitch link. have federalism implications under it was made immediately effective by
According to AgustaWestland’s Executive Order 13132. This AD will Emergency AD 2015–05–52, issued on March
service information some of the costs of not have a substantial direct effect on 4, 2015, which contains the requirements of
this AD may be covered under warranty, the States, on the relationship between this AD.
thereby reducing the cost impact on the national Government and the States, (d) Compliance
affected individuals. We do not control or on the distribution of power and You are responsible for performing each
warranty coverage by Agusta. responsibilities among the various action required by this AD within the
Accordingly, we have included all costs levels of government. specified compliance time unless it has
in our cost estimate. For the reasons discussed, I certify already been accomplished prior to that time.
FAA’s Justification and Determination that this AD:
(e) Required Actions
of the Effective Date 1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866; (1) Before further flight, inspect the pitch
Providing an opportunity for public 2. Is not a ‘‘significant rule’’ under link for freedom of movement while it is
comments prior to adopting these AD DOT Regulatory Policies and Procedures installed on the helicopter.
requirements would delay (i) If there is rotation resistance or binding,
(44 FR 11034, February 26, 1979); before further flight, perform the actions in
implementing the safety actions needed 3. Will not affect intrastate aviation in paragraphs (e)(2) through (e)(3) of this AD.
to correct this known unsafe condition. Alaska to the extent that it justifies (ii) If there is no rotation resistance and no
Therefore, we found and continue to making a regulatory distinction; and binding, within 5 hours time-in-service,
find that the risk to the flying public 4. Will not have a significant perform the actions in paragraphs (e)(2)
justifies waiving notice and comment economic impact, positive or negative, through (e)(3) of this AD.
prior to the adoption of this rule on a substantial number of small entities (2) Remove the pitch link and inspect each
because the previously described unsafe under the criteria of the Regulatory pitch link spherical bearing for corrosion. If
condition can adversely affect the Flexibility Act. there is any corrosion, the pitch link is
asabaliauskas on DSK5VPTVN1PROD with RULES
controllability of the helicopter and the We prepared an economic evaluation unairworthy.
initial required action must be (3) Determine the force required to rotate
of the estimated costs to comply with
each pitch link spherical bearing as depicted
accomplished before further flight. this AD and placed it in the AD docket. in Figure 1 of AgustaWestland Alert
Since it was found that immediate Bollettino Tecnico (BT) No. 109–145, 109EP–
corrective action was required, notice List of Subjects in 14 CFR Part 39
141, 109K–65, 109S–065, 109SP–087, or 119–
and opportunity for prior public Air transportation, Aircraft, Aviation 072, all Revision A, and all dated February
comment before issuing this AD were safety, Incorporation by reference, 27, 2015, as applicable to your model
impracticable and contrary to the public Safety. helicopter.
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![19876 Federal Register / Vol. 80, No. 71 / Tuesday, April 14, 2015 / Rules and Regulations
(i) If the force required to rotate a spherical AgustaWestland, Product Support essential for safe flight, and consequent
bearing in either end of the pitch link is Engineering, Via del Gregge, 100, 21015 reduced controllability of the airplane.
greater than 7.30 N (1.64 pounds force), the Lonate Pozzolo (VA) Italy, ATTN: Maurizio
DATES: This AD becomes effective April
pitch link is unairworthy. D’Angelo; telephone 39–0331–664757; fax 39
(ii) If the force required to rotate the 0331–664680; or at http:// 29, 2015.
spherical bearings in both ends of the pitch www.agustawestland.com/technical- The Director of the Federal Register
link is equal to or less than 7.30 N (1.64 bulletins. approved the incorporation by reference
pounds force), after cleaning the pitch link (4) You may view this service information of a certain publication listed in this AD
rod using aliphatic naphtha or equivalent at FAA, Office of the Regional Counsel, as of March 6, 2015 (80 FR 5034,
and a soft non-metallic bristle brush, visually Southwest Region, 2601 Meacham Blvd., January 30, 2015).
inspect the pitch link rod for a crack in the Room 663, Fort Worth, Texas 76137. For We must receive comments on this
area depicted in Figure 1 of AgustaWestland information on the availability of this AD by May 29, 2015.
Alert BT No. 109–145, 109EP–141, 109K–65, material at the FAA, call (817) 222–5110. ADDRESSES: You may send comments by
109S–065, 109SP–087, or 119–072, all (5) You may view this service information
Revision A, and all dated February 27, 2015, any of the following methods:
that is incorporated by reference at the
as applicable to your model helicopter, using • Federal eRulemaking Portal: Go to
National Archives and Records
a 10x or higher power magnifying glass or by Administration (NARA). For information on http://www.regulations.gov. Follow the
dye penetrant inspection. If there is a crack, the availability of this material at NARA, call instructions for submitting comments.
the pitch link is unairworthy. (202) 741–6030, or go to: http:// • Fax: 202–493–2251.
www.archives.gov/federal-register/cfr/ibr- • Mail: U.S. Department of
(f) Alternative Methods of Compliance
locations.html. Transportation, Docket Operations, M–
(AMOCs)
30, West Building Ground Floor, Room
(1) The Manager, Safety Management Issued in Fort Worth, Texas, on April 6,
2015. W12–140, 1200 New Jersey Avenue SE.,
Group, FAA, may approve AMOCs for this
Washington, DC 20590.
AD. Send your proposal to: Martin Crane, Lance T. Gant,
Aviation Safety Engineer, Safety Management
• Hand Delivery: U.S. Department of
Acting Directorate Manager, Rotorcraft Transportation, Docket Operations, M–
Group, Rotorcraft Directorate, FAA, 2601 Directorate, Aircraft Certification Service.
Meacham Blvd., Fort Worth, Texas 76137; 30, West Building Ground Floor, Room
[FR Doc. 2015–08384 Filed 4–13–15; 8:45 am] W12–140, 1200 New Jersey Avenue SE.,
telephone (817) 222–5110; email
martin.r.crane@faa.gov. BILLING CODE 4910–13–P Washington, DC, between 9 a.m. and 5
(2) For operations conducted under a 14 p.m., Monday through Friday, except
CFR part 119 operating certificate or under Federal holidays.
14 CFR part 91, subpart K, we suggest that DEPARTMENT OF TRANSPORTATION For service information identified in
you notify your principal inspector, or this AD, contact Dassault Falcon Jet,
lacking a principal inspector, the manager of Federal Aviation Administration P.O. Box 2000, South Hackensack, NJ
the local flight standards district office or
certificate holding district office, before 07606; telephone 201–440–6700;
14 CFR Part 39 Internet http://www.dassaultfalcon.com.
operating any aircraft complying with this
AD through an AMOC. [Docket No. FAA–2015–0825; Directorate You may view this referenced service
Identifier 2015–NM–035–AD; Amendment information at the FAA, Transport
(g) Additional Information 39–18138; AD 2015–08–02] Airplane Directorate, 1601 Lind Avenue
The subject of this AD is addressed in SW., Renton, WA. For information on
European Aviation Safety Agency (EASA) RIN 2120–AA64
the availability of this material at the
Emergency AD No. 2015–0035–E, dated FAA, call 425–227–1221.
February 27, 2015. You may view the EASA Airworthiness Directives; Dassault
AD on the Internet at http:// Aviation Airplanes Examining the AD Docket
www.regulations.gov in Docket No. FAA–
2015–0908. AGENCY: Federal Aviation You may examine the AD docket on
Administration (FAA), Department of the Internet at http://
(h) Subject Transportation (DOT). www.regulations.gov by searching for
Joint Aircraft Service Component (JASC) ACTION: Final rule; request for and locating Docket No. FAA–2015–
Code: 6720, Tail Rotor Controls. 0825; or in person at the Docket
comments.
(i) Material Incorporated by Reference Operations office between 9 a.m. and 5
(1) The Director of the Federal Register SUMMARY: We are superseding p.m., Monday through Friday, except
approved the incorporation by reference of Airworthiness Directive (AD) 2015–02– Federal holidays. The AD docket
the service information listed in this 04 for certain Dassault Aviation Model contains this AD, the regulatory
paragraph under 5 U.S.C. 552(a) and 1 CFR MYSTERE–FALCON 50 airplanes. AD evaluation, any comments received, and
part 51. 2015–02–04 required installing two other information. The street address for
(2) You must use this service information protective plates between the electrical the Docket Operations office (telephone
as applicable to do the actions required by wiring under the glare shield and the 800–647–5527) is in the ADDRESSES
this AD, unless the AD specifies otherwise. engine fire pull handles. This new AD section. Comments will be available in
(i) AgustaWestland Alert Bollettino
Tecnico (BT) No. 109–145, Revision A, dated continues to require installing two the AD docket shortly after receipt.
February 27, 2015. protective plates between the electrical FOR FURTHER INFORMATION CONTACT: Tom
(ii) AgustaWestland Alert BT No. 109EP– wiring under the glare shield and the Rodriguez, Aerospace Engineer,
141, Revision A, dated February 27, 2015. engine fire pull handles. This AD was International Branch, ANM–116,
(iii) AgustaWestland Alert BT No. 109K– prompted by our determination that the Transport Airplane Directorate, FAA,
asabaliauskas on DSK5VPTVN1PROD with RULES
65, Revision A, dated February 27, 2015. published version of AD 2015–02–04 1601 Lind Avenue SW., Renton, WA
(iv) AgustaWestland Alert BT No. 109S– incorrectly identified the AD number as 98057–3356; telephone 425–227–1137;
065, Revision A, dated February 27, 2015. ‘‘AD 2014–02–04’’ in a certain
(v) AgustaWestland Alert BT No. 109SP–
fax 425–227–1149.
087, Revision A, dated February 27, 2015.
paragraph. We are issuing this AD to SUPPLEMENTARY INFORMATION:
(vi) AgustaWestland Alert BT No. 119–072, prevent chafing of the electrical wiring,
which could result in a short circuit and Discussion
Revision A, dated February 27, 2015.
(3) For AgustaWestland service generation of smoke in the cockpit, On January 12, 2015, we issued AD
information identified in this AD, contact potential loss of several functions 2015–02–04, Amendment 39–18071 (80
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Document Created: 2015-12-18 11:09:46
Document Modified: 2015-12-18 11:09:46
| 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 becomes effective April 29, 2015 to all persons except those persons to whom it was made immediately effective by Emergency AD (EAD) 2015-05-52, issued on March 4, 2015, which contains the requirements of this AD. | |
| Contact | Martin Crane, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email [email protected] | |
| FR Citation | 80 FR 19873 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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