Airworthiness Directives; Engine Alliance Turbofan Engines, 66609-66612 [2018-27926]

Download as PDF khammond on DSK30JT082PROD with RULES Federal Register / Vol. 83, No. 247 / Thursday, December 27, 2018 / Rules and Regulations hazardous loads on the airplane, nor create hazardous deviations in the flight path. This applies to both fault-free operation and in the event of a malfunction, and assumes the pilot begins corrective action within a reasonable period of time. (h) When the flight guidance system is in use, a means must be provided to avoid excursions beyond an acceptable margin from the speed range of the normal flight envelope. If the airplane experiences an excursion outside this range, a means must be provided to prevent the flight guidance system from providing guidance or control to an unsafe speed. (i) The flight guidance system functions, controls, indications, and alerts must be designed to minimize flight crew errors and confusion concerning the behavior and operation of the flight guidance system. Means must be provided to indicate the current mode of operation, including any armed modes, transitions, and reversions. Selector switch position is not an acceptable means of indication. The controls and indications must be grouped and presented in a logical and consistent manner. The indications must be visible to each pilot under all expected lighting conditions. (j) Following disengagement of the autothrust function, a caution (visual and auditory) must be provided to each pilot. (k) During autothrust operation, it must be possible for the flightcrew to move the thrust levers without requiring excessive force. The autothrust may not create a potential hazard when the flightcrew applies an override force to the thrust levers. (l) For purposes of this section, a transient is a disturbance in the control or flight path of the airplane that is not consistent with response to flight crew inputs or environmental conditions. (1) A minor transient would not significantly reduce safety margins and would involve flightcrew actions that are well within their capabilities. A minor transient may involve a slight increase in flight crew workload or some physical discomfort to passengers or cabin crew. (2) A significant transient may lead to a significant reduction in safety margins, an increase in flight crew workload, discomfort to the flightcrew, or physical distress to the passengers or cabin crew, possibly including non-fatal injuries. Significant transients do not require, in order to remain within or recover to the normal flight envelope, any of the following: (i) Exceptional piloting skill, alertness, or strength. VerDate Sep<11>2014 16:19 Dec 26, 2018 Jkt 247001 (ii) Forces applied by the pilot that are greater than those specified in § 23.143(c). (iii) Accelerations or attitudes in the airplane that might result in further hazard to secured or non-secured occupants. Issued in Kansas City, Missouri on December 17, 2018. Pat Mullen, Manager, Small Airplane Standards Branch, Aircraft Certification Service. [FR Doc. 2018–28116 Filed 12–26–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0938; Product Identifier 2018–NE–36–AD; Amendment 39– 19480; AD 2018–22–07] RIN 2120–AA64 Airworthiness Directives; Engine Alliance Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for all Engine Alliance (EA) GP7270, GP7272, and GP7277 model turbofan engines. This AD requires inspection of the stage 6 seal ring for correct installation and inspection of the high-pressure compressor (HPC) stages 2–5 spool for cracks. This AD also requires replacement of the HPC stages 2–5 spool if the stage 6 seal ring is incorrectly installed or if the HPC stages 2–5 spool is found cracked. This AD was prompted by a shop finding of axial cracks in the interstage 5–6 seal teeth of the HPC stages 2–5 spool spacer arm, due to an incorrectly installed stage 6 seal ring. We are issuing this AD to address the unsafe condition on these products. This AD is effective January 11, 2019. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 11, 2019. We must receive comments on this AD by February 11, 2019. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: PO 00000 Frm 00053 Fmt 4700 Sfmt 4700 • 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 Engine Alliance, 411 Silver Lane, East Hartford, CT 06118; phone: 800–565–0140; email: help24@pw.utc.com; website: www.engineallianceportal.com. 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–2018– 0938. Examining the AD Docket SUMMARY: DATES: 66609 You may examine the AD docket on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0938; or in person at Docket Operations 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 Operations (phone: 800–647– 5527) is listed above. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Matthew Smith, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781–238–7735; fax: 781–238–7199; email: Matthew.C.Smith@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We were informed about the discovery of axial cracks in the interstage 5–6 seal teeth of the HPC stages 2–5 spool spacer arm, due to an incorrectly installed stage 6 seal ring, in a GP7270 model turbofan engine. The incorrect installation of the stage 6 seal ring created a leakage path from the aft cavity to the forward cavity of the HPC stage 6 disk. This leakage elevated the E:\FR\FM\27DER1.SGM 27DER1 66610 Federal Register / Vol. 83, No. 247 / Thursday, December 27, 2018 / Rules and Regulations temperature in the cavity and adversely affected the material properties of the HPC stages 2–5 spool. This condition, if not addressed, could result in failure of the HPC stages 2–5 spool, an uncontained HPC stages 2–5 spool release, damage to the engine, and damage to the airplane. We are issuing this AD to address the unsafe condition on these products. Related Service Information Under 1 CFR Part 51 We reviewed EA Alert Service Bulletin (ASB) EAGP7–A72–395, Revision No. 2, dated August 2, 2018. The SB describes procedures for performing a borescope inspection of the installed HPC stages 2–5 spool for cracks, visual inspection of the stage 6 seal ring for correct installation, visual inspection of the interstage 5–6 seal teeth for damage, and removal and replacement of parts if damage or defects are found that are outside serviceable limits, within the identified cycles. 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 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 inspection of the stage 6 seal ring for correct installation and inspection of the HPC stages 2–5 spool for cracks. This AD also requires removal and replacement of the HPC stages 2–5 spool if the stage 6 seal ring is incorrectly installed or the interstage 5–6 seal teeth are found cracked. FAA’s Justification and Determination of the Effective Date No domestic operators use this product. Therefore, we find good cause that notice and opportunity for prior public comment are unnecessary. 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 FAA–2018–0938 and Product Identifier 2018–NE–36–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 zero engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Borescope inspection of stage 6 seal ring and interstage 5–6 seal teeth forward and aft faces only. 4 work-hours × $85 per hour = $340 ............. We estimate the following costs to do any necessary replacements that would be required based on the results of the inspection. We have no way of Cost per product Parts cost $0 Cost on U.S. operators $340 $0 determining the number of aircraft that might need these replacements: ON-CONDITION COSTS Action Labor cost Replacement of HPC stages 2 to 5 spool ................... 8 work-hours × $85 per hour = $680 ........................... khammond on DSK30JT082PROD with RULES 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 VerDate Sep<11>2014 16:19 Dec 26, 2018 Jkt 247001 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 PO 00000 Frm 00054 Fmt 4700 Sfmt 4700 Parts cost $346,540 Cost per product $347,220 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 E:\FR\FM\27DER1.SGM 27DER1 Federal Register / Vol. 83, No. 247 / Thursday, December 27, 2018 / Rules and Regulations 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 1. The authority citation for part 39 continues to read as follows: ■ khammond on DSK30JT082PROD with RULES Authority: 49 U.S.C. 106(g), 40113, 44701. (h) 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 certification office, send it to the attention of the person identified in paragraph (i) of this AD. You may email your request to: ANE-AD-AMOC@ faa.gov. VerDate Sep<11>2014 16:19 Dec 26, 2018 Jkt 247001 § 39.13 (f) Compliance [Amended] ■ 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): Comply with this AD within the compliance times specified, unless already done. AD 2018–22–07 Engine Alliance: Amendment 39–19480; Docket No. FAA–2018–0938; Product Identifier 2018–NE–36–AD. (g) Required Actions (a) Effective Date This AD is effective January 11, 2019. (b) Affected ADs None. (c) Applicability This AD applies to all Engine Alliance (EA) GP7270, GP7272, and GP7277 model turbofan engines. (d) Subject Joint Aircraft System Component (JASC) Code 7230, Turbine Engine Compressor Section. (e) Unsafe Condition This AD was prompted by a shop finding of axial cracks in the interstage 5–6 seal teeth of the high-pressure compressor (HPC) stages 2–5 spool spacer arm, due to an incorrectly installed stage 6 seal ring. We are issuing this AD to prevent failure of the HPC stage 5–6 seal teeth and uncontained HPC stages 2–5 spool release. The unsafe condition, if not addressed, could result in an uncontained failure of the HPC stages 2–5 spool, damage to the engine, and damage to the airplane. (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 Matthew Smith, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781–238– 7735; fax: 781–238–7199; email: Matthew.C.Smith@faa.gov. PO 00000 Frm 00055 Fmt 4700 Sfmt 4700 (1) Borescope inspect the stage 6 seal ring location in accordance with the Accomplishment Instructions, paragraph 1.F, in EA Alert Service Bulletin (ASB) EAGP7– A72–395, Revision No. 2, dated August 2, 2018, and within the compliance times specified in Table 1 to paragraph (g) of this AD. If the stage 6 seal ring is incorrectly installed, remove the HPC stages 2–5 spool from service within 50 cycles and replace with a part eligible for installation. (2) Borescope inspect the interstage 5–6 seal tooth aft face and interstage 5–6 forward face for cracks and missing coating in accordance with the Accomplishment Instructions, paragraphs 2.C and 2.E, in EA ASB EAGP7–A72–395, Revision No. 2, dated August 2, 2018, and within the compliance times specified in Table 1 to paragraph (g) of this AD. (i) If coating is missing on the interstage 5– 6 seal tooth forward or aft faces, repeat the borescope inspection required by paragraph (g)(2) of this AD for cracks every 150 cycles. (ii) If cracks are found in the interstage 5– 6 seal tooth forward or aft faces, remove the HPC stages 2–5 spool from service and replace with a part eligible for installation before further flight. (j) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Engine Alliance (EA) Alert Service Bulletin EAGP7–A72–395, Revision No. 2, dated August 2, 2018. (ii) [Reserved] E:\FR\FM\27DER1.SGM 27DER1 ER27DE18.041</GPH> 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. 66611 66612 Federal Register / Vol. 83, No. 247 / Thursday, December 27, 2018 / Rules and Regulations (3) For EA service information identified in this AD, contact Engine Alliance, 411 Silver Lane, East Hartford, CT 06118; phone: 800– 565–0140; email: help24@pw.utc.com; website: www.engineallianceportal.com. (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/ibrlocations.html. Issued in Burlington, Massachusetts, on December 19, 2018. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. Examining the AD Docket [FR Doc. 2018–27926 Filed 12–26–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0711; Product Identifier 2018–NM–062–AD; Amendment 39–19533; AD 2018–26–03] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 757–200 series airplanes. This AD was prompted by reports of uncommanded movement of the captain’s and first officer’s seats. This AD requires, for the captain’s and first officer’s seats, repetitive horizontal actuator identifications, repetitive checks of the horizontal movement system (HMS), a detailed inspection of the HMS, as applicable, and applicable on-condition actions. This AD also requires a general visual inspection to determine the seat part numbers of the captain’s and first officer’s seats, a cable adjustment check on seats with certain seat part numbers, and applicable oncondition actions. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective January 31, 2019. The Director of the Federal Register approved the incorporation by reference khammond on DSK30JT082PROD with RULES SUMMARY: VerDate Sep<11>2014 16:19 Dec 26, 2018 Jkt 247001 of certain publications listed in this AD as of January 31, 2019. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone 562–797–1717; internet https://www.myboeingfleet.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2018– 0711. You may examine the AD docket on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0711; or in person at Docket Operations 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 Docket Operations (phone: 800–647–5527) is 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: Myra Kuck, Aerospace Engineer, Cabin Safety and Environmental Systems Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5316; fax: 562–627–5210; email: myra.j.kuck@ faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all The Boeing Company Model 757–200 series airplanes. The NPRM published in the Federal Register on August 16, 2018 (83 FR 40710). The NPRM was prompted by reports of uncommanded movement of the captain’s and first officer’s seats. The NPRM proposed to require, for the captain’s and first officer’s seats, repetitive horizontal actuator identifications, repetitive checks of the HMS, a detailed inspection of the HMS, as applicable, and applicable oncondition actions. The NPRM also proposed to require a general visual inspection to determine seat part PO 00000 Frm 00056 Fmt 4700 Sfmt 4700 numbers of the captain’s and first officer’s seats, a cable adjustment check on seats with certain seat part numbers, and applicable on-condition actions. Comments We gave the public the opportunity to participate in developing this final rule. The following presents the comments received on the NPRM and the FAA’s response to each comment. Support for the NPRM Air Line Pilots Association, International (ALPA) stated its support for the NPRM. United Airlines stated that it has no technical objections to the NPRM. Effect of Winglets on Accomplishment of the Proposed Actions Aviation Partners Boeing (APB) stated that the installation of winglets per Supplemental Type Certificate (STC) ST01518SE does not affect the accomplishment of the manufacturer’s service instructions. We agree with APB that STC ST01518SE does not affect the accomplishment of the manufacturer’s service instructions. Therefore, the installation of STC ST01518SE does not affect the ability to accomplish the actions required by this AD. We have not changed this AD in this regard. Request To Add Airplane Models to Applicability Delta Air Lines (DAL) requested that the FAA consider expanding the applicability of the proposed AD to address all affected fleets that share the identified unsafe condition, or consider requiring effectivity at the manufacturer part number. DAL reasoned that expanding the applicability of the proposed AD to include all affected airplane models or affected manufacturer part numbers would ease the burden on operators by allowing them to forgo commenting on multiple proposed fleet ADs and processing separate AD-related service information by individual fleet type. DAL pointed out that this would greatly assist operators with implementation for operators that share the same affected part number among different affected fleets. We disagree with the commenter’s request. Not all of the service information for all affected airplane models is available, and we do not agree to delay issuance of this AD until new service information is released. Moreover, adding airplanes to the applicability would necessitate (under the provisions of the Administrative Procedure Act) reissuing the notice, E:\FR\FM\27DER1.SGM 27DER1

Agencies

[Federal Register Volume 83, Number 247 (Thursday, December 27, 2018)]
[Rules and Regulations]
[Pages 66609-66612]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-27926]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0938; Product Identifier 2018-NE-36-AD; Amendment 
39-19480; AD 2018-22-07]
RIN 2120-AA64


Airworthiness Directives; Engine Alliance Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Engine Alliance (EA) GP7270, GP7272, and GP7277 model turbofan engines. 
This AD requires inspection of the stage 6 seal ring for correct 
installation and inspection of the high-pressure compressor (HPC) 
stages 2-5 spool for cracks. This AD also requires replacement of the 
HPC stages 2-5 spool if the stage 6 seal ring is incorrectly installed 
or if the HPC stages 2-5 spool is found cracked. This AD was prompted 
by a shop finding of axial cracks in the interstage 5-6 seal teeth of 
the HPC stages 2-5 spool spacer arm, due to an incorrectly installed 
stage 6 seal ring. We are issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective January 11, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 11, 
2019.
    We must receive comments on this AD by February 11, 2019.

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 
Engine Alliance, 411 Silver Lane, East Hartford, CT 06118; phone: 800-
565-0140; email: help24@pw.utc.com; website: 
www.engineallianceportal.com. 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-2018-0938.

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-2018-
0938; or in person at Docket Operations 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 Operations (phone: 
800-647-5527) is listed above. Comments will be available in the AD 
docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Matthew Smith, Aerospace Engineer, ECO 
Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-
238-7735; fax: 781-238-7199; email: Matthew.C.Smith@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We were informed about the discovery of axial cracks in the 
interstage 5-6 seal teeth of the HPC stages 2-5 spool spacer arm, due 
to an incorrectly installed stage 6 seal ring, in a GP7270 model 
turbofan engine. The incorrect installation of the stage 6 seal ring 
created a leakage path from the aft cavity to the forward cavity of the 
HPC stage 6 disk. This leakage elevated the

[[Page 66610]]

temperature in the cavity and adversely affected the material 
properties of the HPC stages 2-5 spool. This condition, if not 
addressed, could result in failure of the HPC stages 2-5 spool, an 
uncontained HPC stages 2-5 spool release, damage to the engine, and 
damage to the airplane. We are issuing this AD to address the unsafe 
condition on these products.

Related Service Information Under 1 CFR Part 51

    We reviewed EA Alert Service Bulletin (ASB) EAGP7-A72-395, Revision 
No. 2, dated August 2, 2018. The SB describes procedures for performing 
a borescope inspection of the installed HPC stages 2-5 spool for 
cracks, visual inspection of the stage 6 seal ring for correct 
installation, visual inspection of the interstage 5-6 seal teeth for 
damage, and removal and replacement of parts if damage or defects are 
found that are outside serviceable limits, within the identified 
cycles. 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

    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 inspection of the stage 6 seal ring for correct 
installation and inspection of the HPC stages 2-5 spool for cracks. 
This AD also requires removal and replacement of the HPC stages 2-5 
spool if the stage 6 seal ring is incorrectly installed or the 
interstage 5-6 seal teeth are found cracked.

FAA's Justification and Determination of the Effective Date

    No domestic operators use this product. Therefore, we find good 
cause that notice and opportunity for prior public comment are 
unnecessary. 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 FAA-2018-
0938 and Product Identifier 2018-NE-36-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 zero 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
----------------------------------------------------------------------------------------------------------------
Borescope inspection of stage 6 seal    4 work-hours x $85 per                $0            $340              $0
 ring and interstage 5-6 seal teeth      hour = $340.
 forward and aft faces only.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the inspection. We have 
no way of determining the number of aircraft that might need these 
replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement of HPC stages 2 to 5 spool.....  8 work-hours x $85 per hour = $680.        $346,540        $347,220
----------------------------------------------------------------------------------------------------------------

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

[[Page 66611]]

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):

AD 2018-22-07 Engine Alliance: Amendment 39-19480; Docket No. FAA-
2018-0938; Product Identifier 2018-NE-36-AD.

(a) Effective Date

    This AD is effective January 11, 2019.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Engine Alliance (EA) GP7270, GP7272, and 
GP7277 model turbofan engines.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7230, Turbine Engine 
Compressor Section.

(e) Unsafe Condition

    This AD was prompted by a shop finding of axial cracks in the 
interstage 5-6 seal teeth of the high-pressure compressor (HPC) 
stages 2-5 spool spacer arm, due to an incorrectly installed stage 6 
seal ring. We are issuing this AD to prevent failure of the HPC 
stage 5-6 seal teeth and uncontained HPC stages 2-5 spool release. 
The unsafe condition, if not addressed, could result in an 
uncontained failure of the HPC stages 2-5 spool, damage to the 
engine, and damage to the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Actions

    (1) Borescope inspect the stage 6 seal ring location in 
accordance with the Accomplishment Instructions, paragraph 1.F, in 
EA Alert Service Bulletin (ASB) EAGP7-A72-395, Revision No. 2, dated 
August 2, 2018, and within the compliance times specified in Table 1 
to paragraph (g) of this AD. If the stage 6 seal ring is incorrectly 
installed, remove the HPC stages 2-5 spool from service within 50 
cycles and replace with a part eligible for installation.
    (2) Borescope inspect the interstage 5-6 seal tooth aft face and 
interstage 5-6 forward face for cracks and missing coating in 
accordance with the Accomplishment Instructions, paragraphs 2.C and 
2.E, in EA ASB EAGP7-A72-395, Revision No. 2, dated August 2, 2018, 
and within the compliance times specified in Table 1 to paragraph 
(g) of this AD.
    (i) If coating is missing on the interstage 5-6 seal tooth 
forward or aft faces, repeat the borescope inspection required by 
paragraph (g)(2) of this AD for cracks every 150 cycles.
    (ii) If cracks are found in the interstage 5-6 seal tooth 
forward or aft faces, remove the HPC stages 2-5 spool from service 
and replace with a part eligible for installation before further 
flight.
[GRAPHIC] [TIFF OMITTED] TR27DE18.041

(h) 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 
certification office, send it to the attention of the person 
identified in paragraph (i) of this AD. You may email your request 
to: ANE-AD-AMOC@faa.gov.
    (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 Matthew Smith, 
Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: 781-238-7735; fax: 781-238-7199; email: 
Matthew.C.Smith@faa.gov.

(j) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Engine Alliance (EA) Alert Service Bulletin EAGP7-A72-395, 
Revision No. 2, dated August 2, 2018.
    (ii) [Reserved]

[[Page 66612]]

    (3) For EA service information identified in this AD, contact 
Engine Alliance, 411 Silver Lane, East Hartford, CT 06118; phone: 
800-565-0140; email: help24@pw.utc.com; website: 
www.engineallianceportal.com.
    (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 December 19, 2018.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2018-27926 Filed 12-26-18; 8:45 am]
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