83 FR 6125 - Airworthiness Directives; General Electric Company Turboprop Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 30 (February 13, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 30 (February 13, 2018)
| Page Range | 6125-6127 | |
| FR Document | 2018-02917 |
[Federal Register Volume 83, Number 30 (Tuesday, February 13, 2018)] [Rules and Regulations] [Pages 6125-6127] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-02917] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0943; Product Identifier 2017-NE-34-AD; Amendment 39-19186; AD 2018-03-13] RIN 2120-AA64 Airworthiness Directives; General Electric Company Turboprop Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for certain General Electric Company (GE) CT7-5A2, CT7-5A3, CT7-7A, CT7-7A1, CT7- 9B, CT7-9B1, CT7-9B2, CT7-9C and CT7-9C3 model turboprop engines. This AD requires initial and repetitive visual inspection and fluorescent- penetrant inspection (FPI) of the main propeller shaft. This AD was prompted by the failure of a main propeller shaft. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective February 28, 2018. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 28, 2018. We must receive comments on this AD by March 30, 2018. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590. Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this final rule, contact General Electric Company, GE-Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 45215; phone: 513-552-3272; fax: 513-552-3329; email: [email protected]. You may view this service information at the FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781-238-7759. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-0943. 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-2017- 0943; 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 street 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: Michael Richardson-Bach, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7747; fax: 781-238-7199; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We received a report that a condition was found after an incident where the main propeller shaft on a GE CT7-9B failed in flight, resulting in the loss of the propeller. The condition is cracking initiating from undiscovered corrosion in the dowel pin hole on the flange of the main propeller shaft. This proposed AD would require visually inspecting the main propeller shaft for wear and corrosion and FPI for cracks. This condition, if not addressed, could result in failure of the main propeller shaft, resulting in in-flight loss of the propeller, loss of engine thrust control, and damage to the airplane. We are issuing this AD to address the unsafe condition on these products. A similar propeller separation incident occurred in 1992 because of a material defect. The affected parts were purged from the field at that time. Related Service Information Under 1 CFR Part 51 We reviewed SPM 70-32-03, SPOT-FLUORESCENT PENETRANT INSPECTION, TASK 70-32-03-230-002, from the GE Commercial Engine Standard Practices Manual GEK 9250, Rev. 106, dated April 01, 2007. This procedure provides instruction for spot FPI. We also reviewed MM 72-10-00, PROPELLER GEARBOX INSPECTION and MM 72-10-00, PROPELLER GEARBOX--CLEANING, from the GE CT7B Maintenance Manual SEI-576, Rev. 60, dated October 1, 2017. These procedures provides instructions for inspection and cleaning, respectively, of the main propeller shaft. 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. Other Related Service Information We reviewed GE Service Bulletin (SB) CT7-TP S/B 72-0531, dated June 22, 2017. The SB references standard procedures for initial and repetitive visual and FPI of the main propeller shaft for SF340 aircraft. We also reviewed GE SB CT7-TP S/B 72-0533, dated October 3, 2017. The SB references standard procedures for initial and repetitive visual and FPI [[Page 6126]] of the main propeller shaft for CN235 aircraft. FAA's Determination We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. AD Requirements This AD requires visually inspecting the main propeller shaft for wear and corrosion and FPI for cracks. Differences Between This AD and the Service Information The inspection plan in this AD adds visual inspection and FPI to the repetitive inspections. This AD adds upper limits to the ``inspect within'' times to avoid conflicting times to inspect. FAA's Justification and Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD without providing an opportunity for public comments prior to adoption. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because the compliance time for the action is less than the time required for public comment. Therefore, we find that notice and opportunity for prior public comment are impracticable. In addition, for the reason stated above, we find that good cause exists for making this amendment effective in less than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment. However, we invite you to send any written data, views, or arguments about this final rule. Send your comments to an address listed under the ADDRESSES section. Include the docket number Docket No. FAA-2017-0943 and Product Identifier 2017-NE-34-AD at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this final rule. We will consider all comments received by the closing date and may amend this final rule because of those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this final rule. Costs of Compliance We estimate that this AD affects 176 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 ---------------------------------------------------------------------------------------------------------------- Initial FPI........................... 2 work-hours x $85 per $0 $170 $29,920 hour = $170. ---------------------------------------------------------------------------------------------------------------- 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. 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 associated appliances to the Manager, Engine and Propeller Standards Branch, Policy and Innovation Division. Regulatory Findings 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, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): 2018-03-13 General Electric Company: Amendment 39-19186; Docket No. FAA-2017-0943; Product Identifier 2017-NE-34-AD. (a) Effective Date This AD is effective February 28, 2018. (b) Affected ADs None. [[Page 6127]] (c) Applicability This AD applies to General Electric Company (GE) CT7-5A2, CT7- 5A3, CT7-7A, CT7-7A1, CT7-9B, CT7-9B1, CT7-9B2, CT7-9C and CT7-9C3 model turboprop engines with main propeller shaft, part number 77581-11, installed. (d) Subject Joint Aircraft System Component (JASC) Code 7210, Turbine Engine Reduction Gear. (e) Unsafe Condition This AD was prompted by the failure of a main propeller shaft. We are issuing this AD to prevent failure of the main propeller shaft. The unsafe condition, if not addressed, could result in in- flight loss of the propeller, loss of engine thrust control, and damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) For propeller gear boxes (PGBs) with 46,000 hours time since new (TSN) or more, perform cleaning, visual inspection, and fluorescent-penetrant inspection (FPI) within 150 hours time in service (TIS) after the effective date of this AD, or one month after the effective date of this AD, whichever occurs first. (2) For PGBs with 40,000 hours TSN or more, but less than 46,000 hours TSN, perform cleaning, visual inspection, and FPI within 500 hours TIS after the effective date of this AD, not to exceed 46,150 TSN or four months after the effective date of this AD, whichever occurs first. (3) For PGBs with 30,000 hours TSN or more, but less than 40,000 hours TSN, perform cleaning, visual inspection, and FPI within 1,000 hours TIS after the effective date of this AD, not to exceed 40,500 TSN or eight months after the effective date of this AD, whichever occurs first. (4) For PGBs with less than 30,000 hours TSN, perform cleaning, visual inspection, and FPI at the next propeller removal, not to exceed 31,000 hours TSN. (5) Perform the cleaning, visual inspection and FPI, as follows: (i) Clean the main propeller shaft flange. Use the instructions in paragraph 5, ``Main Propeller Shaft,'' in MM 72-10-00, PROPELLER GEARBOX--CLEANING from GE CT7B Maintenance Manual SEI-576, Rev. 60, dated October 1, 2017. (ii) Visually inspect the main propeller shaft for wear, corrosion, and cracking. Use the instructions in paragraph 5.A., ``Main Propeller Shaft,'' in MM 72-10-00, PROPELLER GEARBOX-- INSPECTION from GE CT7B Maintenance Manual SEI-576, Rev. 60, dated October 1, 2017. (iii) Spot-fluorescent-penetrant inspect the area on the main propeller shaft flange face within 0.5 inches radially adjacent to the dowel pin holes for cracks. Use the instructions in SPM 70-32- 03, SPOT-FLUORESCENT PENETRANT--INSPECTION, Task 70-32-03-230-002 from GE GEK 9250, Commercial Engine Standard Practices Manual, Rev. 106, dated April 1, 2007. (6) Repeat the cleaning, visual inspection, and FPI of the main propeller shaft at each removal of the propeller. (7) Before further flight, remove from service any main propeller shaft found cracked, or with corrosion or wear beyond the limits specified in SPM 70-32-03, SPOT-FLUORESCENT PENETRANT-- INSPECTION, Task 70-32-03-230-002, from GE GEK 9250, Commercial Engine Standard Practices Manual, Rev. 106, dated April 1, 2007. (h) Credit for Previous Actions Main propeller shafts that were replaced with new zero-time parts at an overhaul of the PGB within the last 10,000 hours TIS, or inspected in accordance with GE Service Bulletin (SB) CT7-TP S/B 72- 0531, dated June 22, 2017, or GE SB CT7-TP S/B 72-0533, dated October 3, 2017, satisfy the requirements specified in paragraph (g)(5) of this AD. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, ECO Branch, FAA, 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 ECO Branch, send it to the attention of the person identified in paragraph (j) of this AD. You may email your request to: [email protected]. (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. (j) Related Information For more information about this AD, contact Michael Richardson- Bach, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7747; fax: 781-238-7199; email: [email protected]. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 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) SPM 70-32-03, SPOT-FLUORESCENT PENETRANT INSPECTION, TASK 70-32-03-230-002, from the GE Commercial Engine Standard Practices Manual GEK 9250, Rev. 106, dated April 01, 2007. (ii) MM 72-10-00, PROPELLER GEARBOX INSPECTION, from the GE CT7B Maintenance Manual SEI-576, Rev. 60, dated October 1, 2017. (iii) MM 72-10-00, PROPELLER GEARBOX--CLEANING, from the GE CT7B Maintenance Manual SEI-576, Rev. 60, dated October 1, 2017. (3) For GE service information identified in this AD, contact General Electric Company, GE-Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 45215; phone: 513-552-3272; fax: 513-552-3329; email: [email protected]. (4) You may view this service information at FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781-238-7759. (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 Burlington, Massachusetts, on February 8, 2018. Robert J. Ganley, Acting Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2018-02917 Filed 2-12-18; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 83, No. 30 / Tuesday, February 13, 2018 / Rules and Regulations 6125
(j) Material Incorporated by Reference and CT7–9C3 model turboprop engines. FOR FURTHER INFORMATION CONTACT:
(1) The Director of the Federal Register This AD requires initial and repetitive Michael Richardson-Bach, Aerospace
approved the incorporation by reference visual inspection and fluorescent- Engineer, ECO Branch, FAA, 1200
(IBR) of the service information listed in this penetrant inspection (FPI) of the main District Avenue, Burlington, MA 01803;
paragraph under 5 U.S.C. 552(a) and 1 CFR propeller shaft. This AD was prompted phone: 781–238–7747; fax: 781–238–
part 51. by the failure of a main propeller shaft. 7199; email: michael.richardson-bach@
(2) You must use this service information We are issuing this AD to address the faa.gov.
as applicable to do the actions required by
unsafe condition on these products. SUPPLEMENTARY INFORMATION:
this AD, unless the AD specifies otherwise.
(i) Aeroclubul Romaniei Service Bulletin DATES: This AD is effective February 28,
2018. Discussion
No.: SB–IS–28B2–AR–01, Revision 003,
dated February 9, 2017. The Director of the Federal Register We received a report that a condition
(ii) Aeroclubul Romaniei Service Bulletin approved the incorporation by reference was found after an incident where the
No.: SB–IS–28B2–AR–02, Revision 01, dated of a certain publication listed in this AD main propeller shaft on a GE CT7–9B
February 24, 2017. as of February 28, 2018. failed in flight, resulting in the loss of
(3) For Aeroclubul Romaniei service We must receive comments on this the propeller. The condition is cracking
information identified in this AD, contact: AD by March 30, 2018. initiating from undiscovered corrosion
Aeroclubul Romaniei, Bd.Lascar Catargiu,
ADDRESSES: You may send comments, in the dowel pin hole on the flange of
Nr.54, cod: 010673, Sector 1, Bucharest,
Romania; telephone: 011+40 021–312–36–19; using the procedures found in 14 CFR the main propeller shaft. This proposed
fax: 011+40 021–312–36–19; internet: 11.43 and 11.45, by any of the following AD would require visually inspecting
www.aeroclubulromaniei.ro; email: methods: the main propeller shaft for wear and
www.aeroclubulromaniei.ro/contact/. • Federal eRulemaking Portal: Go to corrosion and FPI for cracks. This
(4) You may view this service information http://www.regulations.gov. Follow the condition, if not addressed, could result
at the FAA, Policy and Innovation Division, instructions for submitting comments. in failure of the main propeller shaft,
901 Locust, Kansas City, Missouri 64106. For • Fax: 202–493–2251. resulting in in-flight loss of the
information on the availability of this • Mail: U.S. Department of propeller, loss of engine thrust control,
material at the FAA, call (816) 329–4148. In Transportation, Docket Operations, M– and damage to the airplane. We are
addition, you can access this service 30, West Building Ground Floor, Room
information on the internet at http:// issuing this AD to address the unsafe
W12–140, 1200 New Jersey Avenue SE, condition on these products.
www.regulations.gov by searching for and
Washington, DC 20590. A similar propeller separation
locating Docket No. FAA–2017–1068.
• Hand Delivery: U.S. Department of incident occurred in 1992 because of a
(5) You may view this service information
that is incorporated by reference at the Transportation, Docket Operations, M– material defect. The affected parts were
National Archives and Records 30, West Building Ground Floor, Room purged from the field at that time.
Administration (NARA). For information on W12–140, 1200 New Jersey Avenue SE,
the availability of this material at NARA, call Washington, DC 20590, between 9 a.m. Related Service Information Under 1
202–741–6030, or go to: http:// and 5 p.m., Monday through Friday, CFR Part 51
www.archives.gov/federal-register/cfr/ibr- except Federal holidays. We reviewed SPM 70–32–03, SPOT–
locations.html. For service information identified in FLUORESCENT PENETRANT
Issued in Kansas City, Missouri, on this final rule, contact General Electric INSPECTION, TASK 70–32–03–230–
February 5, 2018. Company, GE-Aviation, Room 285, 1 002, from the GE Commercial Engine
Melvin J. Johnson, Neumann Way, Cincinnati, OH 45215; Standard Practices Manual GEK 9250,
Deputy Director, Policy & Innovation Division, phone: 513–552–3272; fax: 513–552– Rev. 106, dated April 01, 2007. This
Aircraft Certification Service. 3329; email: geae.aoc@ge.com. You may procedure provides instruction for spot
[FR Doc. 2018–02601 Filed 2–12–18; 8:45 am] view this service information at the FPI.
BILLING CODE 4910–13–P
FAA, Engine and Propeller Standards We also reviewed MM 72–10–00,
Branch, 1200 District Avenue, PROPELLER GEARBOX INSPECTION
Burlington, MA 01803. For information and MM 72–10–00, PROPELLER
DEPARTMENT OF TRANSPORTATION on the availability of this material at the GEARBOX—CLEANING, from the GE
FAA, call 781–238–7759. It is also CT7B Maintenance Manual SEI–576,
Federal Aviation Administration available on the internet at http:// Rev. 60, dated October 1, 2017. These
www.regulations.gov by searching for procedures provides instructions for
14 CFR Part 39 and locating Docket No. FAA–2017– inspection and cleaning, respectively, of
0943. the main propeller shaft.
[Docket No. FAA–2017–0943; Product
Identifier 2017–NE–34–AD; Amendment 39– Examining the AD Docket This service information is reasonably
19186; AD 2018–03–13] available because the interested parties
You may examine the AD docket on have access to it through their normal
RIN 2120–AA64 the internet at http:// course of business or by the means
www.regulations.gov by searching for identified in the ADDRESSES section.
Airworthiness Directives; General and locating Docket No. FAA–2017–
Electric Company Turboprop Engines 0943; or in person at the Docket Other Related Service Information
AGENCY: Federal Aviation Management Facility between 9 a.m. We reviewed GE Service Bulletin (SB)
Administration (FAA), DOT. and 5 p.m., Monday through Friday, CT7–TP S/B 72–0531, dated June 22,
ACTION: Final rule; request for except Federal holidays. The AD docket 2017. The SB references standard
sradovich on DSK3GMQ082PROD with RULES
comments. contains this final rule, the regulatory procedures for initial and repetitive
evaluation, any comments received, and visual and FPI of the main propeller
SUMMARY: We are adopting a new other information. The street address for shaft for SF340 aircraft.
airworthiness directive (AD) for certain the Docket Office (phone: 800–647– We also reviewed GE SB CT7–TP
General Electric Company (GE) CT7– 5527) is in the ADDRESSES section. S/B 72–0533, dated October 3, 2017.
5A2, CT7–5A3, CT7–7A, CT7–7A1, Comments will be available in the AD The SB references standard procedures
CT7–9B, CT7–9B1, CT7–9B2, CT7–9C docket shortly after receipt. for initial and repetitive visual and FPI
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of the main propeller shaft for CN235 FAA’s Justification and Determination this final rule. Send your comments to
aircraft. of the Effective Date an address listed under the ADDRESSES
An unsafe condition exists that section. Include the docket number
FAA’s Determination Docket No. FAA–2017–0943 and
requires the immediate adoption of this
We are issuing this AD because we AD without providing an opportunity Product Identifier 2017–NE–34–AD at
evaluated all the relevant information for public comments prior to adoption. the beginning of your comments. We
and determined the unsafe condition The FAA has found that the risk to the specifically invite comments on the
flying public justifies waiving notice overall regulatory, economic,
described previously is likely to exist or
and comment prior to adoption of this environmental, and energy aspects of
develop in other products of the same
rule because the compliance time for the this final rule. We will consider all
type design.
action is less than the time required for comments received by the closing date
AD Requirements public comment. Therefore, we find that and may amend this final rule because
notice and opportunity for prior public of those comments.
This AD requires visually inspecting comment are impracticable. In addition, We will post all comments we
the main propeller shaft for wear and for the reason stated above, we find that receive, without change, to http://
corrosion and FPI for cracks. good cause exists for making this www.regulations.gov, including any
amendment effective in less than 30 personal information you provide. We
Differences Between This AD and the
days. will also post a report summarizing each
Service Information
substantive verbal contact we receive
Comments Invited about this final rule.
The inspection plan in this AD adds
visual inspection and FPI to the This AD is a final rule that involves
Costs of Compliance
repetitive inspections. This AD adds requirements affecting flight safety and
upper limits to the ‘‘inspect within’’ was not preceded by notice and an We estimate that this AD affects 176
times to avoid conflicting times to opportunity for public comment. engines installed on airplanes of U.S.
However, we invite you to send any registry. We estimate the following costs
inspect.
written data, views, or arguments about to comply with this AD:
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Initial FPI ......................................................... 2 work-hours × $85 per hour = $170 ............. $0 $170 $29,920
Authority for This Rulemaking delegated the authority to issue ADs List of Subjects in 14 CFR Part 39
applicable to engines, propellers, and
Title 49 of the United States Code Air transportation, Aircraft, Aviation
specifies the FAA’s authority to issue associated appliances to the Manager,
Engine and Propeller Standards Branch, safety, Incorporation by reference,
rules on aviation safety. Subtitle I, Safety.
section 106, describes the authority of Policy and Innovation Division.
the FAA Administrator. ‘‘Subtitle VII: Regulatory Findings Adoption of the Amendment
Aviation Programs’’ describes in more
This AD will not have federalism Accordingly, under the authority
detail the scope of the Agency’s
authority. implications under Executive Order delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
We are issuing this rulemaking under 13132. This AD will not have a
follows:
the authority described in Subtitle VII, substantial direct effect on the States, on
Part A, Subpart III, Section 44701: the relationship between the national PART 39—AIRWORTHINESS
‘‘General requirements.’’ Under that government and the States, or on the DIRECTIVES
section, Congress charges the FAA with distribution of power and
promoting safe flight of civil aircraft in responsibilities among the various ■ 1. The authority citation for part 39
air commerce by prescribing regulations levels of government. continues to read as follows:
for practices, methods, and procedures
For the reasons discussed above, I Authority: 49 U.S.C. 106(g), 40113, 44701.
the Administrator finds necessary for
safety in air commerce. This regulation certify that this AD:
(1) Is not a ‘‘significant regulatory § 39.13 [Amended]
is within the scope of that authority
because it addresses an unsafe condition action’’ under Executive Order 12866, ■ 2. The FAA amends § 39.13 by adding
that is likely to exist or develop on (2) Is not a ‘‘significant rule’’ under the following new airworthiness
products identified in this rulemaking DOT Regulatory Policies and Procedures directive (AD):
action. (44 FR 11034, February 26, 1979), 2018–03–13 General Electric Company:
This AD is issued in accordance with
(3) Will not affect intrastate aviation Amendment 39–19186; Docket No.
authority delegated by the Executive
FAA–2017–0943; Product Identifier
sradovich on DSK3GMQ082PROD with RULES
Director, Aircraft Certification Service, in Alaska, and
2017–NE–34–AD.
as authorized by FAA Order 8000.51C. (4) Will not have a significant
In accordance with that order, issuance economic impact, positive or negative, (a) Effective Date
of ADs is normally a function of the on a substantial number of small entities This AD is effective February 28, 2018.
Compliance and Airworthiness under the criteria of the Regulatory
Division, but during this transition Flexibility Act. (b) Affected ADs
period, the Executive Director has None.
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(c) Applicability Practices Manual, Rev. 106, dated April 1, GE-Aviation, Room 285, 1 Neumann Way,
This AD applies to General Electric 2007. Cincinnati, OH 45215; phone: 513–552–3272;
Company (GE) CT7–5A2, CT7–5A3, CT7–7A, (6) Repeat the cleaning, visual inspection, fax: 513–552–3329; email: geae.aoc@ge.com.
CT7–7A1, CT7–9B, CT7–9B1, CT7–9B2, and FPI of the main propeller shaft at each (4) You may view this service information
CT7–9C and CT7–9C3 model turboprop removal of the propeller. at FAA, Engine and Propeller Standards
engines with main propeller shaft, part (7) Before further flight, remove from Branch, 1200 District Avenue, Burlington,
number 77581–11, installed. service any main propeller shaft found MA 01803. For information on the
cracked, or with corrosion or wear beyond availability of this material at the FAA, call
(d) Subject the limits specified in SPM 70–32–03, SPOT- 781–238–7759.
Joint Aircraft System Component (JASC) FLUORESCENT PENETRANT— (5) You may view this service information
Code 7210, Turbine Engine Reduction Gear. INSPECTION, Task 70–32–03–230–002, from that is incorporated by reference at the
GE GEK 9250, Commercial Engine Standard National Archives and Records
(e) Unsafe Condition Practices Manual, Rev. 106, dated April 1, Administration (NARA). For information on
This AD was prompted by the failure of a 2007. the availability of this material at NARA, call
main propeller shaft. We are issuing this AD (h) Credit for Previous Actions 202–741–6030, or go to: http://
to prevent failure of the main propeller shaft. www.archives.gov/federal-register/cfr/ibr-
The unsafe condition, if not addressed, could Main propeller shafts that were replaced locations.html.
result in in-flight loss of the propeller, loss with new zero-time parts at an overhaul of
the PGB within the last 10,000 hours TIS, or Issued in Burlington, Massachusetts, on
of engine thrust control, and damage to the February 8, 2018.
airplane. inspected in accordance with GE Service
Bulletin (SB) CT7–TP S/B 72–0531, dated Robert J. Ganley,
(f) Compliance June 22, 2017, or GE SB CT7–TP S/B 72– Acting Manager, Engine and Propeller
Comply with this AD within the 0533, dated October 3, 2017, satisfy the Standards Branch, Aircraft Certification
compliance times specified, unless already requirements specified in paragraph (g)(5) of Service.
done. this AD.
[FR Doc. 2018–02917 Filed 2–12–18; 8:45 am]
(g) Required Actions (i) Alternative Methods of Compliance BILLING CODE 4910–13–P
(AMOCs)
(1) For propeller gear boxes (PGBs) with
46,000 hours time since new (TSN) or more, (1) The Manager, ECO Branch, FAA, has
perform cleaning, visual inspection, and the authority to approve AMOCs for this AD, DEPARTMENT OF TRANSPORTATION
fluorescent-penetrant inspection (FPI) within if requested using the procedures found in 14
150 hours time in service (TIS) after the CFR 39.19. In accordance with 14 CFR 39.19, Federal Aviation Administration
effective date of this AD, or one month after send your request to your principal inspector
the effective date of this AD, whichever or local Flight Standards District Office, as 14 CFR Part 71
occurs first. appropriate. If sending information directly
to the manager of the ECO Branch, send it to [Docket No. FAA–2017–1082 Airspace
(2) For PGBs with 40,000 hours TSN or
the attention of the person identified in Docket No. 17–AGL–22]
more, but less than 46,000 hours TSN,
perform cleaning, visual inspection, and FPI paragraph (j) of this AD. You may email your
within 500 hours TIS after the effective date request to: ANE–AD–AMOC@faa.gov. Amendment of Multiple Air Traffic
of this AD, not to exceed 46,150 TSN or four (2) Before using any approved AMOC, Service (ATS) Routes; North Central
months after the effective date of this AD, notify your appropriate principal inspector, United States
whichever occurs first. or lacking a principal inspector, the manager
of the local flight standards district office/ AGENCY: Federal Aviation
(3) For PGBs with 30,000 hours TSN or
more, but less than 40,000 hours TSN,
certificate holding district office. Administration (FAA), DOT.
perform cleaning, visual inspection, and FPI (j) Related Information ACTION: Final rule, technical
within 1,000 hours TIS after the effective For more information about this AD,
amendment.
date of this AD, not to exceed 40,500 TSN or contact Michael Richardson-Bach, Aerospace
eight months after the effective date of this SUMMARY: The FAA is amending four
Engineer, ECO Branch, FAA, 1200 District
AD, whichever occurs first. high altitude Area Navigation (RNAV)
Avenue, Burlington, MA 01803; phone: 781–
(4) For PGBs with less than 30,000 hours 238–7747; fax: 781–238–7199; email: Q-routes (Q–140, Q–818, Q–935, and Q–
TSN, perform cleaning, visual inspection, michael.richardson-bach@faa.gov. 947) that cross the United States (U.S.)/
and FPI at the next propeller removal, not to Canada border in the north central U.S.
exceed 31,000 hours TSN. (k) Material Incorporated by Reference This action updates the latitude/
(5) Perform the cleaning, visual inspection (1) The Director of the Federal Register longitude coordinates for three
and FPI, as follows: approved the incorporation by reference
(i) Clean the main propeller shaft flange.
Canadian waypoints listed in the Q-
(IBR) of the service information listed in this route descriptions contained in the FAA
Use the instructions in paragraph 5, ‘‘Main paragraph under 5 U.S.C. 552(a) and 1 CFR
Propeller Shaft,’’ in MM 72–10–00, part 51. aeronautical database to match the
PROPELLER GEARBOX—CLEANING from (2) You must use this service information Canadian aeronautical database source
GE CT7B Maintenance Manual SEI–576, Rev. as applicable to do the actions required by information.
60, dated October 1, 2017. this AD, unless the AD specifies otherwise. DATES: Effective date 0901 UTC, May 24,
(ii) Visually inspect the main propeller (i) SPM 70–32–03, SPOT-FLUORESCENT
shaft for wear, corrosion, and cracking. Use
2018. The Director of the Federal
PENETRANT INSPECTION, TASK 70–32–
the instructions in paragraph 5.A., ‘‘Main 03–230–002, from the GE Commercial Engine
Register approves this incorporation by
Propeller Shaft,’’ in MM 72–10–00, Standard Practices Manual GEK 9250, Rev. reference action under title 1, Code of
PROPELLER GEARBOX—INSPECTION from 106, dated April 01, 2007. Federal Regulations, part 51, subject to
GE CT7B Maintenance Manual SEI–576, Rev. (ii) MM 72–10–00, PROPELLER GEARBOX the annual revision of FAA Order
60, dated October 1, 2017. INSPECTION, from the GE CT7B 7400.11 and publication of conforming
sradovich on DSK3GMQ082PROD with RULES
(iii) Spot-fluorescent-penetrant inspect the Maintenance Manual SEI–576, Rev. 60, dated amendments.
area on the main propeller shaft flange face October 1, 2017. ADDRESSES: FAA Order 7400.11B,
within 0.5 inches radially adjacent to the (iii) MM 72–10–00, PROPELLER
dowel pin holes for cracks. Use the GEARBOX—CLEANING, from the GE CT7B Airspace Designations and Reporting
instructions in SPM 70–32–03, SPOT- Maintenance Manual SEI–576, Rev. 60, dated Points, and subsequent amendments can
FLUORESCENT PENETRANT— October 1, 2017. be viewed online at http://www.faa.gov/
INSPECTION, Task 70–32–03–230–002 from (3) For GE service information identified in air_traffic/publications/. For further
GE GEK 9250, Commercial Engine Standard this AD, contact General Electric Company, information, you can contact the
VerDate Sep<11>2014 15:52 Feb 12, 2018 Jkt 244001 PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 E:\FR\FM\13FER1.SGM 13FER1](https://thefederalregister.org/doc/83_FR_6155/page/3.svg)
Document Created: 2018-02-13 02:32:18
Document Modified: 2018-02-13 02:32:18
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule; request for comments. | |
| Dates | This AD is effective February 28, 2018. | |
| Contact | Michael Richardson-Bach, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7747; fax: 781-238-7199; email: michael.richardson- [email protected] | |
| FR Citation | 83 FR 6125 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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