81 FR 49575 - Airworthiness Directives; Turbomeca S.A. Turboshaft Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 145 (July 28, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 145 (July 28, 2016)
| Page Range | 49575-49577 | |
| FR Document | 2016-17719 |
[Federal Register Volume 81, Number 145 (Thursday, July 28, 2016)] [Proposed Rules] [Pages 49575-49577] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-17719] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-6990; Directorate Identifier 2016-NE-14-AD] RIN 2120-AA64 Airworthiness Directives; Turbomeca S.A. Turboshaft Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain Turbomeca S.A. Arriel 1, 1A, 1A1, 1A2, 1B, 1B2, 1C, 1C1, 1C2, 1D, 1D1, 1E, 1E2, 1K1, 1S, and 1S1 turboshaft engines. This proposed AD was prompted by an anomaly that occurred during the grinding operation required by modification TU376, which increases the clearance between the rear curvic coupling of the centrifugal impeller and the fuel injection manifold. This proposed AD would require removing the centrifugal impeller and replacing with a part eligible for installation. We are proposing this AD to prevent failure of the centrifugal impeller, uncontained centrifugal impeller release, damage to the engine, and damage to the helicopter. DATES: We must receive comments on this NPRM by September 26, 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. Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-0001. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Fax: 202-493-2251. For service information identified in this proposed AD, contact Turbomeca S.A., 40220 Tarnos, France; phone: 33 (0)5 59 74 40 00; fax: 33 (0)5 59 74 45 15. You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781-238-7125. 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- 6990; 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 proposed AD, the mandatory continuing airworthiness information (MCAI), the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800- 647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Philip Haberlen, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7770; fax: 781- 238-7199; email: [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2016-6990; Directorate Identifier 2016-NE-14-AD'' at the beginning of your comments. We specifically invite [[Page 49576]] comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on 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 with FAA personnel concerning this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA AD 2016-0090, dated May 10, 2016 (referred to hereinafter as ``the MCAI''), to correct an unsafe condition for the specified products. The MCAI states: Turbomeca reported an anomaly that was generated during the grinding operation associated to the application of modification TU376, which increases the clearance between the rear curvic coupling of the centrifugal impeller and the fuel injection manifold. This condition, if not corrected, could lead to crack initiation and propagation in the centrifugal impeller bore area, possibly resulting in centrifugal impeller failure, with consequent damage to, and reduced control of, the helicopter. To address this potential unsafe condition, the life of the affected centrifugal impellers was reduced and Turbomeca published Mandatory Service Bulletin (MSB) 292 72 0848 to inform operators about the life reduction and to provide instructions for the replacement of the affected centrifugal impellers. For the reasons described above, this AD requires replacement of each affected centrifugal impeller before it exceeds the applicable reduced life limit. You may obtain further information by examining the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-6990. Related Service Information Turbomeca S.A. has issued Mandatory Service Bulletin (MSB) 292 72 0848, Version B, dated April 13, 2016. The MSB describes procedures for reducing the life limit of the centrifugal impellers affected by an anomaly that occurred during the grinding operation required by modification TU376. 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. FAA's Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of France, and is approved for operation in the United States. Pursuant to our bilateral agreement with the European Community, EASA has notified us of the unsafe condition described in the MCAI and service information referenced above. We are proposing 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 products of the same type design. This proposed AD would require removal of the centrifugal impeller from service before exceeding the reduced life limit shown in Appendix 1 of EASA AD 2016-0090, dated May 10, 2016, and replacement with a part eligible for installation. Costs of Compliance We estimate that this proposed AD affects 3 engines installed on helicopters of U.S. registry. We also estimate that it would take about 22 hours per engine to comply with this proposed AD. The average labor rate is $85 per hour. Required parts cost about $96,518 per engine. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $295,164. 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: (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 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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): Turbomeca S.A.: Docket No. FAA-2016-6990; Directorate Identifier 2016-NE-14-AD. (a) Comments Due Date We must receive comments by September 26, 2016. (b) Affected ADs None. (c) Applicability This AD applies to certain Arriel 1, 1A, 1A1, 1A2, 1B, 1B2, 1C, 1C1, 1C2, 1D, 1D1, 1E, 1E2, 1K1, 1S, and 1S1 turboshaft engines, with modification TU376 installed. (d) Reason This AD was prompted by an anomaly that occurred during the grinding operation required by modification TU376, which increases the clearance between the rear curvic coupling of the centrifugal impeller and the fuel injection manifold. We are issuing this AD to prevent failure of the centrifugal impeller, uncontained centrifugal impeller release, damage to the engine, and damage to the helicopter. [[Page 49577]] (e) Actions and Compliance Comply with this AD within the compliance times specified, unless already done. (1) Remove from service, any centrifugal impeller listed in Table 1 to paragraph (e) of this AD, before exceeding the applicable cycles since new (CSN) and replace with a centrifugal impeller not listed in Table 1 to paragraph (e) of this AD. Table 1 to Paragraph (e)--Centrifugal Impeller CSNs ------------------------------------------------------------------------ Part No. Serial No. CSN ------------------------------------------------------------------------ 0292254040........................ 44.................. 5,129 0292254040........................ 1762FT.............. 11,476 0292254050........................ 1676CAR............. 6,281 0292254050........................ 5333OTT............. 5,495 0292254050........................ 5017OTT............. 5,491 0292254050........................ 1136CAR............. 8,734 0292254050........................ 3655OTT............. 4,600 0292254050........................ 1757CAR............. 7,913 0292254050........................ 1738CAR............. 10,640 0292254050........................ 1149CAR............. 12,273 0292254050........................ 2677OTT............. 11,145 0292254050........................ 3109OTT............. 10,662 0292254050........................ 3496OTT............. 5,562 0292254050........................ 2074CAR............. 7,423 729225293A........................ 290CAR.............. 6,326 729225293A........................ 1227FT.............. 8,139 729225293A........................ 504FB............... 4,600 729225293A........................ 2517OTT............. 9,732 729225293A........................ 2165OTT............. 6,163 729225293A........................ 2194FT.............. 11,461 729225293A........................ 1331OTT............. 12,513 729225293A........................ 1301FT.............. 7,262 729225293A........................ 1567FT.............. 6,305 729225293A........................ 783FB............... 8,307 729225293A........................ 98OTT............... 9,492 ------------------------------------------------------------------------ (2) Reserved. (f) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. You may email your request to: [email protected]. (g) Related Information (1) For more information about this AD, contact Philip Haberlen, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7770; fax: 781-238-7199; email: [email protected]. (2) Refer to MCAI, European Aviation Safety Agency AD 2016-0090, dated May 10, 2016, for more information. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. FAA-2016-6990. (3) Turbomeca S.A. Mandatory Service Bulletin (MSB) 292 72 0848, Version B, dated April 13, 2016, can be obtained from Turbomeca S.A., using the contact information in paragraph (g)(4) of this proposed AD. (4) For service information identified in this proposed AD, contact Turbomeca S.A., 40220 Tarnos, France; phone: 33 (0)5 59 74 40 00; fax: 33 (0)5 59 74 45 15. (5) You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781-238-7125. Issued in Burlington, Massachusetts, on July 21, 2016. Colleen M. D'Alessandro, Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2016-17719 Filed 7-27-16; 8:45 am] BILLING CODE 4910-13-P
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of the nose wheel well body structure for any (ii) Steps not labeled as RC may be of the centrifugal impeller, uncontained
cracking, and do all applicable related deviated from using accepted methods in centrifugal impeller release, damage to
investigative and corrective actions, in accordance with the operator’s maintenance the engine, and damage to the
accordance with the Accomplishment or inspection program without obtaining
Instructions of Boeing Alert Service Bulletin
helicopter.
approval of an AMOC, provided the RC steps,
747–53A2887, dated December 2, 2015; including substeps and identified figures, can DATES: We must receive comments on
except as required by paragraph (j)(2) of this still be done as specified, and the airplane this NPRM by September 26, 2016.
AD. Do all related investigative and can be put back in an airworthy condition. ADDRESSES: You may send comments by
corrective actions before further flight.
Repeat the detailed inspection thereafter at (l) Related Information any of the following methods:
the applicable intervals specified in (1) For more information about this AD, • Federal eRulemaking Portal: Go to
paragraph 1.E., ‘‘Compliance,’’ of Boeing contact Nathan Weigand, Aerospace http://www.regulations.gov. Follow the
Alert Service Bulletin 747–53A2887, dated Engineer, Airframe Branch, ANM–120S, instructions for submitting comments.
December 2, 2015. FAA, Seattle ACO, 1601 Lind Avenue SW., • Mail: Docket Management Facility,
(j) Exceptions to the Service Information Renton, WA 98057–3356; phone: 425–917– U.S. Department of Transportation, 1200
6428; fax: 425–917–6590; email: New Jersey Avenue SE., West Building
(1) Where Boeing Alert Service Bulletin Nathan.P.Weigand@faa.gov.
747–53A2887, dated December 2, 2015,
Ground Floor, Room W12–140,
(2) For service information identified in Washington, DC 20590–0001.
specifies a compliance time ‘‘after the this AD, contact Boeing Commercial
original issue date of this service bulletin,’’ • Hand Delivery: Deliver to Mail
Airplanes, Attention: Data & Services
this AD requires compliance within the address above between 9 a.m. and 5
Management, P.O. Box 3707, MC 2H–65,
specified compliance time after the effective Seattle, WA 98124–2207; telephone 206– p.m., Monday through Friday, except
date of this AD. 544–5000, extension 1; fax 206–766–5680; Federal holidays.
(2) If any crack is found during any Internet https://www.myboeingfleet.com. You • Fax: 202–493–2251.
inspection required by this AD, and Boeing may view this referenced service information For service information identified in
Alert Service Bulletin 747–53A2887, dated at the FAA, Transport Airplane Directorate, this proposed AD, contact Turbomeca
December 2, 2015, specifies to contact Boeing
1601 Lind Avenue SW., Renton, WA. For S.A., 40220 Tarnos, France; phone: 33
for appropriate action, and specifies that
information on the availability of this (0)5 59 74 40 00; fax: 33 (0)5 59 74 45
action as ‘‘RC’’ (Required for Compliance):
material at the FAA, call 425–227–1221. 15. You may view this service
Before further flight, repair using a method
approved in accordance with the procedures Issued in Renton, Washington, on July 21, information at the FAA, Engine &
specified in paragraph (k) of this AD. 2016. Propeller Directorate, 1200 District
(k) Alternative Methods of Compliance Michael Kaszycki, Avenue, Burlington, MA. For
(AMOCs) Acting Manager, Transport Airplane information on the availability of this
Directorate, Aircraft Certification Service. material at the FAA, call 781–238–7125.
(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the [FR Doc. 2016–17718 Filed 7–27–16; 8:45 am] Examining the AD Docket
authority to approve AMOCs for this AD, if BILLING CODE 4910–13–P
requested using the procedures found in 14 You may examine the AD docket on
CFR 39.19. In accordance with 14 CFR 39.19, the Internet at http://
send your request to your principal inspector DEPARTMENT OF TRANSPORTATION www.regulations.gov by searching for
or local Flight Standards District Office, as and locating Docket No. FAA–2016–
appropriate. If sending information directly Federal Aviation Administration 6990; or in person at the Docket
to the manager of the ACO, send it to the Operations office between 9 a.m. and 5
attention of the person identified in p.m., Monday through Friday, except
14 CFR Part 39
paragraph (l)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOC-
Federal holidays. The AD docket
[Docket No. FAA–2016–6990; Directorate
Requests@faa.gov. Identifier 2016–NE–14–AD]
contains this proposed AD, the
(2) Before using any approved AMOC, mandatory continuing airworthiness
notify your appropriate principal inspector, RIN 2120–AA64 information (MCAI), the regulatory
or lacking a principal inspector, the manager evaluation, any comments received, and
of the local flight standards district office/ Airworthiness Directives; Turbomeca other information. The address for the
certificate holding district office. S.A. Turboshaft Engines Docket Office (phone: 800–647–5527) is
(3) An AMOC that provides an acceptable in the ADDRESSES section. Comments
level of safety may be used for any repair, AGENCY: Federal Aviation
modification, or alteration required by this Administration (FAA), DOT. will be available in the AD docket
AD if it is approved by the Boeing ACTION: Notice of proposed rulemaking
shortly after receipt.
Commercial Airplanes Organization (NPRM). FOR FURTHER INFORMATION CONTACT:
Designation Authorization (ODA) that has Philip Haberlen, Aerospace Engineer,
been authorized by the Manager, Seattle SUMMARY: We propose to adopt a new Engine Certification Office, FAA, Engine
ACO, to make those findings. To be airworthiness directive (AD) for certain & Propeller Directorate, 1200 District
approved, the repair method, modification Turbomeca S.A. Arriel 1, 1A, 1A1, 1A2, Avenue, Burlington, MA 01803; phone:
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
1B, 1B2, 1C, 1C1, 1C2, 1D, 1D1, 1E, 1E2, 781–238–7770; fax: 781–238–7199;
approval must specifically refer to this AD. 1K1, 1S, and 1S1 turboshaft engines. email: philip.haberlen@faa.gov.
(4) Except as required by paragraph (j)(2) This proposed AD was prompted by an SUPPLEMENTARY INFORMATION:
of this AD: For service information that anomaly that occurred during the
contains steps that are labeled as Required grinding operation required by Comments Invited
for Compliance (RC), the provisions of modification TU376, which increases We invite you to send any written
Lhorne on DSK30JT082PROD with PROPOSALS
paragraphs (k)(4)(i) and (k)(4)(ii) of this AD the clearance between the rear curvic relevant data, views, or arguments about
apply. coupling of the centrifugal impeller and this proposed AD. Send your comments
(i) The steps labeled as RC, including
substeps under an RC step and any figures
the fuel injection manifold. This to an address listed under the
identified in an RC step, must be done to proposed AD would require removing ADDRESSES section. Include ‘‘Docket No.
comply with the AD. An AMOC is required the centrifugal impeller and replacing FAA–2016–6990; Directorate Identifier
for any deviations to RC steps, including with a part eligible for installation. We 2016–NE–14–AD’’ at the beginning of
substeps and identified figures. are proposing this AD to prevent failure your comments. We specifically invite
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comments on the overall regulatory, FAA’s Determination and Requirements distribution of power and
economic, environmental, and energy of This Proposed AD responsibilities among the various
aspects of this proposed AD. We will This product has been approved by levels of government.
consider all comments received by the the aviation authority of France, and is For the reasons discussed above, I
closing date and may amend this approved for operation in the United certify this proposed regulation:
proposed AD based on those comments. States. Pursuant to our bilateral (1) Is not a ‘‘significant regulatory
We will post all comments we agreement with the European action’’ under Executive Order 12866,
receive, without change, to http:// Community, EASA has notified us of (2) Is not a ‘‘significant rule’’ under
www.regulations.gov, including any the unsafe condition described in the the DOT Regulatory Policies and
personal information you provide. We MCAI and service information Procedures (44 FR 11034, February 26,
will also post a report summarizing each referenced above. We are proposing this 1979),
substantive verbal contact with FAA AD because we evaluated all
(3) Will not affect intrastate aviation
personnel concerning this proposed AD. information provided by EASA and
in Alaska to the extent that it justifies
determined the unsafe condition exists
Discussion making a regulatory distinction, and
and is likely to exist or develop on other
products of the same type design. This (4) Will not have a significant
The European Aviation Safety Agency economic impact, positive or negative,
(EASA), which is the Technical Agent proposed AD would require removal of
the centrifugal impeller from service on a substantial number of small entities
for the Member States of the European under the criteria of the Regulatory
Community, has issued EASA AD 2016– before exceeding the reduced life limit
shown in Appendix 1 of EASA AD Flexibility Act.
0090, dated May 10, 2016 (referred to
hereinafter as ‘‘the MCAI’’), to correct an 2016–0090, dated May 10, 2016, and List of Subjects in 14 CFR Part 39
unsafe condition for the specified replacement with a part eligible for
installation. Air transportation, Aircraft, Aviation
products. The MCAI states: safety, Incorporation by reference,
Turbomeca reported an anomaly that was Costs of Compliance Safety.
generated during the grinding operation We estimate that this proposed AD
associated to the application of modification The Proposed Amendment
affects 3 engines installed on helicopters
TU376, which increases the clearance of U.S. registry. We also estimate that it Accordingly, under the authority
between the rear curvic coupling of the would take about 22 hours per engine to delegated to me by the Administrator,
centrifugal impeller and the fuel injection comply with this proposed AD. The the FAA proposes to amend 14 CFR part
manifold. average labor rate is $85 per hour.
This condition, if not corrected, could lead
39 as follows:
Required parts cost about $96,518 per
to crack initiation and propagation in the
engine. Based on these figures, we PART 39—AIRWORTHINESS
centrifugal impeller bore area, possibly
resulting in centrifugal impeller failure, with estimate the cost of this proposed AD on DIRECTIVES
consequent damage to, and reduced control U.S. operators to be $295,164.
of, the helicopter. To address this potential ■ 1. The authority citation for part 39
Authority for This Rulemaking continues to read as follows:
unsafe condition, the life of the affected
centrifugal impellers was reduced and Title 49 of the United States Code Authority: 49 U.S.C. 106(g), 40113, 44701.
Turbomeca published Mandatory Service specifies the FAA’s authority to issue
Bulletin (MSB) 292 72 0848 to inform rules on aviation safety. Subtitle I, § 39.13 [Amended]
operators about the life reduction and to section 106, describes the authority of ■ 2. The FAA amends § 39.13 by adding
provide instructions for the replacement of the FAA Administrator. ‘‘Subtitle VII: the following new airworthiness
the affected centrifugal impellers. Aviation Programs,’’ describes in more directive (AD):
For the reasons described above, this AD detail the scope of the Agency’s
requires replacement of each affected authority. Turbomeca S.A.: Docket No. FAA–2016–
centrifugal impeller before it exceeds the We are issuing this rulemaking under 6990; Directorate Identifier 2016–NE–
applicable reduced life limit. the authority described in ‘‘Subtitle VII, 14–AD.
Part A, Subpart III, Section 44701: (a) Comments Due Date
You may obtain further information
General requirements.’’ Under that We must receive comments by September
by examining the MCAI in the AD
section, Congress charges the FAA with 26, 2016.
docket on the Internet at http://
promoting safe flight of civil aircraft in
www.regulations.gov by searching for air commerce by prescribing regulations (b) Affected ADs
and locating Docket No. FAA–2016– for practices, methods, and procedures None.
6990. the Administrator finds necessary for (c) Applicability
Related Service Information safety in air commerce. This regulation This AD applies to certain Arriel 1, 1A,
is within the scope of that authority 1A1, 1A2, 1B, 1B2, 1C, 1C1, 1C2, 1D, 1D1,
Turbomeca S.A. has issued because it addresses an unsafe condition 1E, 1E2, 1K1, 1S, and 1S1 turboshaft engines,
Mandatory Service Bulletin (MSB) 292 that is likely to exist or develop on with modification TU376 installed.
72 0848, Version B, dated April 13, products identified in this rulemaking
2016. The MSB describes procedures for (d) Reason
action.
reducing the life limit of the centrifugal This AD was prompted by an anomaly that
impellers affected by an anomaly that Regulatory Findings occurred during the grinding operation
Lhorne on DSK30JT082PROD with PROPOSALS
occurred during the grinding operation We determined that this proposed AD required by modification TU376, which
required by modification TU376. This would not have federalism implications increases the clearance between the rear
curvic coupling of the centrifugal impeller
service information is reasonably under Executive Order 13132. This and the fuel injection manifold. We are
available because the interested parties proposed AD would not have a issuing this AD to prevent failure of the
have access to it through their normal substantial direct effect on the States, on centrifugal impeller, uncontained centrifugal
course of business or by the means the relationship between the national impeller release, damage to the engine, and
identified in the ADDRESSES section. Government and the States, or on the damage to the helicopter.
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(e) Actions and Compliance (1) Remove from service, any centrifugal centrifugal impeller not listed in Table 1 to
Comply with this AD within the impeller listed in Table 1 to paragraph (e) of paragraph (e) of this AD.
compliance times specified, unless already this AD, before exceeding the applicable
done. cycles since new (CSN) and replace with a
TABLE 1 TO PARAGRAPH (e)—CENTRIFUGAL IMPELLER CSNS
Part No. Serial No. CSN
0292254040 ................................................................................ 44 ................................................................................................ 5,129
0292254040 ................................................................................ 1762FT ....................................................................................... 11,476
0292254050 ................................................................................ 1676CAR .................................................................................... 6,281
0292254050 ................................................................................ 5333OTT .................................................................................... 5,495
0292254050 ................................................................................ 5017OTT .................................................................................... 5,491
0292254050 ................................................................................ 1136CAR .................................................................................... 8,734
0292254050 ................................................................................ 3655OTT .................................................................................... 4,600
0292254050 ................................................................................ 1757CAR .................................................................................... 7,913
0292254050 ................................................................................ 1738CAR .................................................................................... 10,640
0292254050 ................................................................................ 1149CAR .................................................................................... 12,273
0292254050 ................................................................................ 2677OTT .................................................................................... 11,145
0292254050 ................................................................................ 3109OTT .................................................................................... 10,662
0292254050 ................................................................................ 3496OTT .................................................................................... 5,562
0292254050 ................................................................................ 2074CAR .................................................................................... 7,423
729225293A ............................................................................... 290CAR ...................................................................................... 6,326
729225293A ............................................................................... 1227FT ....................................................................................... 8,139
729225293A ............................................................................... 504FB ......................................................................................... 4,600
729225293A ............................................................................... 2517OTT .................................................................................... 9,732
729225293A ............................................................................... 2165OTT .................................................................................... 6,163
729225293A ............................................................................... 2194FT ....................................................................................... 11,461
729225293A ............................................................................... 1331OTT .................................................................................... 12,513
729225293A ............................................................................... 1301FT ....................................................................................... 7,262
729225293A ............................................................................... 1567FT ....................................................................................... 6,305
729225293A ............................................................................... 783FB ......................................................................................... 8,307
729225293A ............................................................................... 98OTT ........................................................................................ 9,492
(2) Reserved. information on the availability of this Series 900) airplanes, and Model CL–
material at the FAA, call 781–238–7125. 600–2E25 (Regional Jet Series 1000)
(f) Alternative Methods of Compliance
(AMOCs) Issued in Burlington, Massachusetts, on airplanes. This proposed AD was
July 21, 2016. prompted by a determination that the
The Manager, Engine Certification Office,
FAA, may approve AMOCs for this AD. Use Colleen M. D’Alessandro, protective polyurethane tapes applied to
the procedures found in 14 CFR 39.19 to Manager, Engine & Propeller Directorate, the upper surfaces of the aluminum and
make your request. You may email your Aircraft Certification Service. titanium floor structural members may
request to: ANE-AD-AMOC@faa.gov. [FR Doc. 2016–17719 Filed 7–27–16; 8:45 am] not be trimmed properly, and on some
BILLING CODE 4910–13–P
places may overhang the profiles of the
(g) Related Information floor structural parts. Subsequent tests
(1) For more information about this AD, revealed that the overhanging pieces of
contact Philip Haberlen, Aerospace Engineer, DEPARTMENT OF TRANSPORTATION tapes that are not bonded to the
Engine Certification Office, FAA, Engine & structure do not meet the flammability
Propeller Directorate, 1200 District Avenue, Federal Aviation Administration requirements and may allow fire
Burlington, MA 01803; phone: 781–238–
propagation below the floor structure.
7770; fax: 781–238–7199; email:
14 CFR Part 39 This proposed AD would require an
philip.haberlen@faa.gov.
(2) Refer to MCAI, European Aviation [Docket No. FAA–2016–8180; Directorate inspection of the polyurethane
Safety Agency AD 2016–0090, dated May 10, Identifier 2016–NM–083–AD] protective tapes installed on the floor
2016, for more information. You may structure for excess tape or incorrect
RIN 2120–AA64 tape installation, and corrective actions
examine the MCAI in the AD docket on the
Internet at http://www.regulations.gov by if necessary. We are proposing this AD
Airworthiness Directives; Bombardier,
searching for and locating it in Docket No. to detect and correct overhanging pieces
Inc. Airplanes
FAA–2016–6990. of protective polyurethane tapes, which
(3) Turbomeca S.A. Mandatory Service AGENCY: Federal Aviation are not bonded to the structure and do
Bulletin (MSB) 292 72 0848, Version B, dated Administration (FAA), DOT. not meet the flammability requirements;
April 13, 2016, can be obtained from this condition may allow fire
ACTION: Notice of proposed rulemaking
Turbomeca S.A., using the contact propagation below the floor structure.
information in paragraph (g)(4) of this (NPRM).
Lhorne on DSK30JT082PROD with PROPOSALS
proposed AD. DATES: We must receive comments on
SUMMARY: We propose to adopt a new this proposed AD by September 12,
(4) For service information identified in
this proposed AD, contact Turbomeca S.A.,
airworthiness directive (AD) for certain 2016.
40220 Tarnos, France; phone: 33 (0)5 59 74 Bombardier, Inc. Model CL–600–2C10
40 00; fax: 33 (0)5 59 74 45 15. (Regional Jet Series 700, 701, & 702) ADDRESSES: You may send comments,
(5) You may view this service information airplanes, Model CL–600–2D15 using the procedures found in 14 CFR
at the FAA, Engine & Propeller Directorate, (Regional Jet Series 705) airplanes, 11.43 and 11.45, by any of the following
1200 District Avenue, Burlington, MA. For Model CL–600–2D24 (Regional Jet methods:
VerDate Sep<11>2014 14:42 Jul 27, 2016 Jkt 238001 PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 E:\FR\FM\28JYP1.SGM 28JYP1](https://thefederalregister.org/doc/81_FR_49720/page/3.svg)
Document Created: 2016-07-28 01:47:38
Document Modified: 2016-07-28 01:47:38
| 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 | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this NPRM by September 26, 2016. | |
| Contact | Philip Haberlen, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7770; fax: 781- 238-7199; email: [email protected] | |
| FR Citation | 81 FR 49575 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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