82 FR 42443 - Airworthiness Directives; Rolls-Royce Corporation Turboshaft Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 173 (September 8, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 173 (September 8, 2017)
| Page Range | 42443-42445 | |
| FR Document | 2017-18910 |
[Federal Register Volume 82, Number 173 (Friday, September 8, 2017)] [Rules and Regulations] [Pages 42443-42445] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-18910] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2011-0961; Product Identifier 2011-NE-22-AD; Amendment 39-19023; AD 2017-18-14] RIN 2120-AA64 Airworthiness Directives; Rolls-Royce Corporation Turboshaft Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2015-02-22 for certain Rolls-Royce Corporation (RRC) model 250 turboprop and turboshaft engines. AD 2015-02-22 required repetitive visual inspections and fluorescent-penetrant inspection (FPIs) on certain 3rd- stage and 4th-stage turbine wheels for cracks in the turbine wheel blades. This AD requires repetitive visual inspections and FPIs of 3rd- stage turbine wheels while removing from service 4th-stage turbine wheels. We are also revising the applicability to remove all RRC turboprop engines and add additional turboshaft engines. This AD was prompted by our finding that it is necessary to remove the 4th-stage wheels at the next inspection. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective October 13, 2017. ADDRESSES: See the FOR FURTHER INFORMATION CONTACT section. 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-2011- 0961; 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 final rule, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800-647-5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: John Tallarovic, Aerospace Engineer, FAA, Chicago ACO Branch, Compliance and Airworthiness Division, 2300 E. Devon Ave., Des Plaines, IL 60018; phone: [[Page 42444]] 847-294-8180; fax: 847-294-7834; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2015-02-22, Amendment 39-18090 (80 FR 5452, February 2, 2015), (``AD 2015-02-22''). AD 2015-02-22 applied to certain RRC 250-B17, -B17B, -B17C, -B17D, -B17E, -B17F, -B17F/1, -B17F/ 2, turboprop engines; and 250-C20, -C20B, -C20F, -C20J, -C20R, -C20R/1, -C20R/2, -C20R/4, -C20S, and -C20W turboshaft engines. The NPRM published in the Federal Register on March 29, 2017 (82 FR 15474). The NPRM was prompted by our determination that it is necessary to remove the 4th-stage wheels at the next inspection. The NPRM proposed to require repetitive visual inspections and FPIs of 3rd-stage turbine wheels while removing from service 4th-stage turbine wheels. We are also revising the applicability to remove all RRC turboprop engines and add additional turboshaft engines. We are issuing this AD to prevent failure of the 3rd-stage and 4th-stage turbine wheel blades, damage to the engine, and damage to the aircraft. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Request To Remove Certain 3rd Stage Turbine Wheel From AD RRC requested that we remove references in this AD to the 3rd stage turbine wheel, part number (P/N) RR30000236, installed on the RRC 250- C300/A1 and 250-C300/B1 turboshaft engines. RRC indicated that 3rd stage turbine wheels, P/N RR30000236, are not susceptible to cracks. RRC noted that there have been no cracks observed on 3rd stage wheels installed on RRC 250-C300/A1 or 250-C300B/1 engines. We agree. The 3rd stage turbine wheel, P/N RR30000236, installed on RRC 250-C300/A1 and 250-C300/B1 engines does not require inspections. They are subject to less severe operating conditions and are not susceptible to this type of failure. We removed references to the 3rd stage turbine wheel, P/N RR30000236, from this AD. Request To Revise Power Turbine Reference RRC requested that we change references in this AD from ``power turbine'' to ``turbine.'' RRC noted that this AD should refer to the entire turbine module rather than just to the power turbine. RRC also commented that the risk analysis for this AD is based on changing the parts anytime the turbine is being serviced, not just the power turbine. Revising the reference in this AD to ``turbine'' would remove the affected 4th stage turbine wheels from the fleet in a shorter time period since the actions specified in this AD are to be complied with whenever the turbine is at the shop and is dissembled for any reason, or at the next turbine wheel replacement, whichever occurs first. We agree. We changed the reference in the Compliance section of this AD from ``power turbine'' to ``turbine.'' RRC also commented that changing the references to ``turbine'' would allow for removal of the Definition section from this AD. We disagree. The term ``engine shop visit'' is used as one of the criteria in this AD to determine when an inspection of affected applicable turbine wheels is required. Given that ``engine shop visit'' may be interpreted in different ways, we provide a definition for this term in this AD. We did not change this AD. Request To Clarify Removal of Blades With Cracks From Service RRC requested that we revise the Compliance section of this AD so that it does not require removal from service all turbine wheels found with cracks. RRC commented that only certain cracks are related to this AD and are a safety concern. We agree. The intent of this AD is to address cracks at the trailing edge of the turbine wheel blades, near the fillet at the rim. The maintenance manuals for these engines allow certain cracks in areas of the turbine wheels not subject to this AD. Engines may still operate safety with turbine wheels that have allowable cracks. We revised paragraph (f)(3) of this AD to refer to cracks found at the trailing edge, near the fillet at the rim, of the turbine blades. Revision to Costs of Compliance We reduced the estimated cost of inspection of 3rd stage wheels from $320,365 to $288,320 since we removed the 3rd stage wheel, P/N RR30000236, from the applicability of this AD. As noted in our previous comment response, these P/N 3rd stage wheels are not subject to the unsafe condition identified in this AD. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Costs of Compliance We estimate that this AD affects 3,769 engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Inspect 3rd-stage wheels, P/N 1 work-hour x $85 $0.................... $85 $288,320 23065818. per hour = $85. Replace 4th-stage wheel, P/N 0 work-hours x $85 5,653 (pro-rated cost 5,653 21,306,157 23055944 or RR30000240. per hour = $0. of part). ---------------------------------------------------------------------------------------------------------------- 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, [[Page 42445]] 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. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to engines, propellers, and appliances to the Manager, Engine and Propeller Standards Branch, Policy and Innovation Division. Regulatory Findings We have 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 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. 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 removing Airworthiness Directive (AD) 2015-02-22, Amendment 39-18090 (80 FR 5452, February 2, 2015), and adding the following new AD: 2017-18-14 Rolls-Royce Corporation: Amendment 39-19023; Docket No. FAA-2011-0961; Product Identifier 2011-NE-22-AD. (a) Effective Date This AD is effective October 13, 2017. (b) Affected ADs This AD replaces Airworthiness Directive (AD) 2015-02-22, Amendment 39-18090 (80 FR 5452, February 2, 2015). (c) Applicability This AD applies to Rolls-Royce Corporation (RRC) 250-C20, -C20B, -C20F, -C20J, -C20R, -C20R/1, -C20R/2, -C20R/4, -C20W, -C300/A1, and -C300/B1 turboshaft engines with either a 3rd-stage turbine wheel, part number (P/N) 23065818, or a 4th-stage turbine wheel, P/N 23055944 or RR30000240, installed. (d) Subject Joint Aircraft System Component (JASC) Code 7250, Turbine Section. (e) Unsafe Condition This AD was prompted by in-service turbine wheel blade failures that revealed the need for changes to the inspections of certain 3rd-stage turbine wheels and removal from service of certain 4th- stage turbine wheels. We are issuing this AD to prevent failure of the 3rd-stage and 4th-stage turbine wheel blades, damage to the engine, and damage to the aircraft. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (1) Within 1,775 hours since last visual inspection and fluorescent-penetrant inspection (FPI) or before the next flight after the effective date of this AD, whichever occurs later: (i) Remove 3rd-stage turbine wheels, P/N 23065818, and perform a visual inspection and an FPI on the removed turbine wheels for cracks at the trailing edge of the turbine blades, near the fillet at the rim. (ii) Thereafter, re-inspect the affected turbine wheels every 1,775 hours since last inspection (HSLI). (2) Any time the turbine is disassembled, perform a visual inspection and an FPI on 3rd-stage turbine wheels, P/N 23065818, for cracks at the trailing edge of the turbine blades, near the fillet at the rim. (3) Do not return to service any turbine wheels found to have cracks at the trailing edge, near the fillet at the rim, of the turbine blades. (4) Within 1,775 HSLI, or at the next engine shop visit, whichever occurs later, remove 4th-stage turbine wheels, P/N 23055944, from service. (5) Within 2,025 HSLI, or at the next engine shop visit, whichever occurs later, remove 4th-stage turbine wheels, P/N RR30000240, from service. (g) Definition For the purpose of this AD, an ``engine shop visit'' is the induction of an engine into the shop for maintenance involving the separation of pairs of major mating engine flanges, except that the separation of engine flanges solely for the purposes of transportation without subsequent engine maintenance does not constitute an engine shop visit. (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, FAA, Chicago ACO Branch, Compliance and Airworthiness Division, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO Branch, send it to the attention of the person identified in paragraph (i) of this AD. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (i) Related Information For more information about this AD, contact John Tallarovic, Aerospace Engineer, FAA, Chicago ACO Branch, Compliance and Airworthiness Division, 2300 E. Devon Ave., Des Plaines, IL 60018; phone: 847-294-8180; fax: 847-294-7834; email: [email protected]. (j) Material Incorporated by Reference None. Issued in Burlington, Massachusetts, on August 31, 2017. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2017-18910 Filed 9-7-17; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 82, No. 173 / Friday, September 8, 2017 / Rules and Regulations 42443
2. Is not a ‘‘significant rule’’ under (f) Required Actions DEPARTMENT OF TRANSPORTATION
DOT Regulatory Policies and Procedures Before further flight, unless already done
(44 FR 11034, February 26, 1979); within the last 5 hours TIS, and thereafter at Federal Aviation Administration
3. Will not affect intrastate aviation in intervals not to exceed 5 hours TIS:
Alaska to the extent that it justifies (1) Using a 3X or higher power magnifying 14 CFR Part 39
making a regulatory distinction; and glass, visually inspect the top and bottom
surface of each blade for a crack in the area [Docket No. FAA–2011–0961; Product
4. Will not have a significant Identifier 2011–NE–22–AD; Amendment 39–
between the station at the end of the doublers
economic impact, positive or negative, (station 1550) and the station at the 19023; AD 2017–18–14]
on a substantial number of small entities beginning of the abrasion strip (station 3100).
under the criteria of the Regulatory RIN 2120–AA64
(2) If there is a crack, replace the blade
Flexibility Act. before further flight. Replacing the blade with Airworthiness Directives; Rolls-Royce
We prepared an economic evaluation blade P/N 109–0103–01–7, P/N 109–0103–
Corporation Turboshaft Engines
of the estimated costs to comply with 01–9, or P/N 109–0103–01–115 does not
this AD and placed it in the AD docket. constitute terminating action for the AGENCY: Federal Aviation
repetitive inspections required by this AD.
Administration (FAA), DOT.
List of Subjects in 14 CFR Part 39
(g) Special Flight Permits ACTION: Final rule.
Air transportation, Aircraft, Aviation Special flight permits are prohibited.
safety, Incorporation by reference, SUMMARY: We are superseding
Safety. (h) Alternative Methods of Compliance Airworthiness Directive (AD) 2015–02–
(AMOCs)
22 for certain Rolls-Royce Corporation
Adoption of the Amendment (1) The Manager, Safety Management (RRC) model 250 turboprop and
Accordingly, under the authority Section, FAA, may approve AMOCs for this turboshaft engines. AD 2015–02–22
delegated to me by the Administrator, AD. Send your proposal to: Matt Fuller,
required repetitive visual inspections
Senior Aviation Safety Engineer, Safety
the FAA amends 14 CFR part 39 as Management Section, Rotorcraft Standards and fluorescent-penetrant inspection
follows: Branch, FAA, 10101 Hillwood Pkwy, Fort (FPIs) on certain 3rd-stage and 4th-stage
Worth, TX 76177; telephone (817) 222–5110; turbine wheels for cracks in the turbine
PART 39—AIRWORTHINESS email 9-ASW-FTW-AMOC-Requests@faa.gov. wheel blades. This AD requires
DIRECTIVES (2) For operations conducted under a 14 repetitive visual inspections and FPIs of
CFR part 119 operating certificate or under 3rd-stage turbine wheels while
■ 1. The authority citation for part 39 14 CFR part 91, subpart K, we suggest that removing from service 4th-stage turbine
continues to read as follows: you notify your principal inspector, or
wheels. We are also revising the
Authority: 49 U.S.C. 106(g), 40113, 44701. lacking a principal inspector, the manager of
the local flight standards district office or applicability to remove all RRC
§ 39.13 [Amended] certificate holding district office, before turboprop engines and add additional
operating any aircraft complying with this turboshaft engines. This AD was
■ 2. The FAA amends § 39.13 by AD through an AMOC. prompted by our finding that it is
removing Airworthiness Directive (AD) necessary to remove the 4th-stage
2015–22–51, Amendment 39–18386 (81 (i) Additional Information
wheels at the next inspection. We are
FR 5037, February 1, 2016), and adding (1) Leonardo Helicopters Alert Bollettino
issuing this AD to address the unsafe
the following new AD: Tecnico No. 109–150, Revision B, dated
October 21, 2016, which is not incorporated condition on these products.
2017–18–13 Agusta S.p.A.: Amendment 39– by reference, contains additional information DATES: This AD is effective October 13,
19022; Docket No. FAA–2017–0308; about the subject of this AD. For service 2017.
Product Identifier 2016–SW–083–AD. information identified in this AD, contact ADDRESSES: See the FOR FURTHER
(a) Applicability Leonardo S.p.A. Helicopters, Matteo Ragazzi, INFORMATION CONTACT section.
Head of Airworthiness, Viale G.Agusta 520,
This AD applies to Model A109A and 21017 C.Costa di Samarate (Va) Italy; Examining the AD Docket
A109A II helicopters with a main rotor blade telephone +39–0331–711756; fax +39–0331–
(blade) part number (P/N) 109–0103–01–7, 229046; or at http://www.leonardo You may examine the AD docket on
P/N 109–0103–01–9, or P/N 109–0103–01– company.com/-/bulletins. You may review a the Internet at http://
115 that has 500 or more hours time-in- copy of the service information at the FAA, www.regulations.gov by searching for
service (TIS) installed, certificated in any Office of the Regional Counsel, Southwest and locating Docket No. FAA–2011–
category. Region, 10101 Hillwood Pkwy, Room 6N– 0961; or in person at the Docket
(b) Unsafe Condition 321, Fort Worth, TX 76177. Management Facility between 9 a.m.
(2) The subject of this AD is addressed in and 5 p.m., Monday through Friday,
This AD defines the unsafe condition as a European Aviation Safety Agency (EASA) AD
crack in a blade. This condition could result except Federal holidays. The AD docket
No. 2016–0213, dated October 26, 2016. You
in failure of a blade and subsequent loss of contains this final rule, the regulatory
may view the EASA AD on the Internet at
control of the helicopter. http://www.regulations.gov by searching for evaluation, any comments received, and
(c) Affected ADs and locating it in Docket No. FAA–2017– other information. The address for the
0308. Docket Office (phone: 800–647–5527) is
This AD supersedes AD 2015–22–51,
Document Management Facility, U.S.
Amendment 39–18386 (81 FR 5037, February (j) Subject
1, 2016). Department of Transportation, Docket
Joint Aircraft Service Component (JASC) Operations, M–30, West Building
(d) Effective Date Code: 6210, Main Rotor Blade. Ground Floor, Room W12–140, 1200
sradovich on DSK3GMQ082PROD with RULES
This AD becomes effective September 25, Issued in Fort Worth, Texas, on August 30, New Jersey Avenue SE., Washington,
2017. 2017. DC 20590.
(e) Compliance Lance T. Gant, FOR FURTHER INFORMATION CONTACT: John
Director, Compliance & Airworthiness Tallarovic, Aerospace Engineer, FAA,
You are responsible for performing each
Division, Aircraft Certification Service. Chicago ACO Branch, Compliance and
action required by this AD within the
specified compliance time unless it has [FR Doc. 2017–18972 Filed 9–7–17; 8:45 am] Airworthiness Division, 2300 E. Devon
already been accomplished prior to that time. BILLING CODE 4910–13–P Ave., Des Plaines, IL 60018; phone:
VerDate Sep<11>2014 16:18 Sep 07, 2017 Jkt 241001 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 E:\FR\FM\08SER1.SGM 08SER1](https://thefederalregister.org/doc/82_FR_42616/page/1.svg)
![Federal Register / Vol. 82, No. 173 / Friday, September 8, 2017 / Rules and Regulations 42445
Part A, Subpart III, Section 44701, Authority: 49 U.S.C. 106(g), 40113, 44701. (5) Within 2,025 HSLI, or at the next
‘‘General requirements.’’ Under that engine shop visit, whichever occurs later,
§ 39.13 [Amended] remove 4th-stage turbine wheels, P/N
section, Congress charges the FAA with
■ 2. The FAA amends § 39.13 by RR30000240, from service.
promoting safe flight of civil aircraft in
air commerce by prescribing regulations removing Airworthiness Directive (AD) (g) Definition
for practices, methods, and procedures 2015–02–22, Amendment 39–18090 (80 For the purpose of this AD, an ‘‘engine
the Administrator finds necessary for FR 5452, February 2, 2015), and adding shop visit’’ is the induction of an engine into
safety in air commerce. This regulation the following new AD: the shop for maintenance involving the
is within the scope of that authority 2017–18–14 Rolls-Royce Corporation: separation of pairs of major mating engine
because it addresses an unsafe condition Amendment 39–19023; Docket No. flanges, except that the separation of engine
that is likely to exist or develop on FAA–2011–0961; Product Identifier flanges solely for the purposes of
2011–NE–22–AD. transportation without subsequent engine
products identified in this rulemaking
maintenance does not constitute an engine
action. (a) Effective Date shop visit.
This AD is issued in accordance with
This AD is effective October 13, 2017. (h) Alternative Methods of Compliance
authority delegated by the Executive
Director, Aircraft Certification Service, (b) Affected ADs (AMOCs)
as authorized by FAA Order 8000.51C. This AD replaces Airworthiness Directive (1) The Manager, FAA, Chicago ACO
In accordance with that order, issuance (AD) 2015–02–22, Amendment 39–18090 (80 Branch, Compliance and Airworthiness
of ADs is normally a function of the FR 5452, February 2, 2015). Division, has the authority to approve
Compliance and Airworthiness AMOCs for this AD, if requested using the
(c) Applicability procedures found in 14 CFR 39.19. In
Division, but during this transition accordance with 14 CFR 39.19, send your
This AD applies to Rolls-Royce
period, the Executive Director has request to your principal inspector or local
Corporation (RRC) 250–C20, –C20B, –C20F,
delegated the authority to issue ADs –C20J, –C20R, –C20R/1, –C20R/2, –C20R/4, Flight Standards District Office, as
applicable to engines, propellers, and –C20W, –C300/A1, and –C300/B1 turboshaft appropriate. If sending information directly
appliances to the Manager, Engine and engines with either a 3rd-stage turbine wheel, to the manager of the ACO Branch, send it
Propeller Standards Branch, Policy and part number (P/N) 23065818, or a 4th-stage to the attention of the person identified in
Innovation Division. turbine wheel, P/N 23055944 or RR30000240, paragraph (i) of this AD.
installed. (2) Before using any approved AMOC,
Regulatory Findings notify your appropriate principal inspector,
(d) Subject or lacking a principal inspector, the manager
We have determined that this AD will
Joint Aircraft System Component (JASC) of the local flight standards district office/
not have federalism implications under
Code 7250, Turbine Section. certificate holding district office.
Executive Order 13132. This AD will
not have a substantial direct effect on (e) Unsafe Condition (i) Related Information
the States, on the relationship between This AD was prompted by in-service For more information about this AD,
the national government and the States, turbine wheel blade failures that revealed the contact John Tallarovic, Aerospace Engineer,
or on the distribution of power and need for changes to the inspections of certain FAA, Chicago ACO Branch, Compliance and
responsibilities among the various 3rd-stage turbine wheels and removal from Airworthiness Division, 2300 E. Devon Ave.,
levels of government. service of certain 4th-stage turbine wheels. Des Plaines, IL 60018; phone: 847–294–8180;
We are issuing this AD to prevent failure of fax: 847–294–7834; email: john.m.tallarovic@
For the reasons discussed above, I
the 3rd-stage and 4th-stage turbine wheel faa.gov.
certify that this AD: blades, damage to the engine, and damage to
(1) Is not a ‘‘significant regulatory the aircraft. (j) Material Incorporated by Reference
action’’ under Executive Order 12866, None.
(2) Is not a ‘‘significant rule’’ under (f) Compliance
DOT Regulatory Policies and Procedures Comply with this AD within the Issued in Burlington, Massachusetts, on
compliance times specified, unless already August 31, 2017.
(44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation done. Robert J. Ganley,
in Alaska to the extent that it justifies (1) Within 1,775 hours since last visual Manager, Engine and Propeller Standards
making a regulatory distinction, and inspection and fluorescent-penetrant Branch, Aircraft Certification Service.
(4) Will not have a significant inspection (FPI) or before the next flight after [FR Doc. 2017–18910 Filed 9–7–17; 8:45 am]
the effective date of this AD, whichever
economic impact, positive or negative, occurs later: BILLING CODE 4910–13–P
on a substantial number of small entities (i) Remove 3rd-stage turbine wheels, P/N
under the criteria of the Regulatory 23065818, and perform a visual inspection
Flexibility Act. and an FPI on the removed turbine wheels DEPARTMENT OF TRANSPORTATION
for cracks at the trailing edge of the turbine
List of Subjects in 14 CFR Part 39 blades, near the fillet at the rim. Federal Aviation Administration
Air transportation, Aircraft, Aviation (ii) Thereafter, re-inspect the affected
safety, Incorporation by reference, turbine wheels every 1,775 hours since last 14 CFR Part 71
Safety. inspection (HSLI).
(2) Any time the turbine is disassembled, [Docket No. FAA–2016–9593; Airspace
Adoption of the Amendment perform a visual inspection and an FPI on Docket No. 16–ACE–12]
3rd-stage turbine wheels, P/N 23065818, for
Accordingly, under the authority Amendment of Class E Airspace; Falls
cracks at the trailing edge of the turbine
delegated to me by the Administrator, blades, near the fillet at the rim. City, NE
the FAA amends 14 CFR part 39 as
sradovich on DSK3GMQ082PROD with RULES
(3) Do not return to service any turbine
follows: wheels found to have cracks at the trailing AGENCY: Federal Aviation
edge, near the fillet at the rim, of the turbine Administration (FAA), DOT.
PART 39—AIRWORTHINESS blades. ACTION: Final rule.
DIRECTIVES (4) Within 1,775 HSLI, or at the next
engine shop visit, whichever occurs later, SUMMARY: This action modifies Class E
■ 1. The authority citation for part 39 remove 4th-stage turbine wheels, P/N airspace extending upward from 700
continues to read as follows: 23055944, from service. feet above the surface at Brenner Field
VerDate Sep<11>2014 16:18 Sep 07, 2017 Jkt 241001 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 E:\FR\FM\08SER1.SGM 08SER1](https://thefederalregister.org/doc/82_FR_42616/page/3.svg)
Document Created: 2018-10-24 14:09:45
Document Modified: 2018-10-24 14:09:45
| 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. | |
| Dates | This AD is effective October 13, 2017. | |
| Contact | John Tallarovic, Aerospace Engineer, FAA, Chicago ACO Branch, Compliance and Airworthiness Division, 2300 E. Devon Ave., Des Plaines, IL 60018; phone: 847-294-8180; fax: 847-294-7834; email: [email protected] | |
| FR Citation | 82 FR 42443 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
2025 Federal Register | Disclaimer | Privacy Policy
USC | CFR | eCFR