83 FR 29474 - Airworthiness Directives; General Electric Company Turbofan Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 122 (June 25, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 122 (June 25, 2018)
| Page Range | 29474-29476 | |
| FR Document | 2018-13444 |
[Federal Register Volume 83, Number 122 (Monday, June 25, 2018)] [Proposed Rules] [Pages 29474-29476] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-13444] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0406; Product Identifier 2013-NE-30-AD] RIN 2120-AA64 Airworthiness Directives; General Electric Company Turbofan Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 2017-07- 04, which applies to General Electric Company (GE) GE90-110B1 and GE90- 115B turbofan engines with certain high-pressure compressor (HPC) rotor stage 2-5 spools installed. AD 2017-07-04 resulted from reports of cracks in HPC rotor stage 2-5 spool aft spacer arms. Since we issued AD 2017-07-04, GE released a new service bulletin (SB) that increases the number of affected HPC rotor stage 2-5 spools. Additionally, we learned that we inadvertently omitted certain HPC rotor stage 2-5 spools from the applicability of AD 2017-07-04. This proposed AD would require removing certain HPC rotor stage 2-5 spools from service before reaching the new reduced life limit and replacing them with parts eligible for installation. We are proposing this AD to correct the unsafe condition on these products. DATES: We must receive comments on this proposed AD by August 9, 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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact General Electric Company, One Neumann Way, Room 285, Cincinnati, OH; phone: 513-552-3272; email: geae.aoc@ge.com. You may view this service information at the FAA, Engine and Propeller Standards Branch, 1200 District Avenue, [[Page 29475]] Burlington, MA 01803. For information on the availability of this material at the FAA, call 781-238-7759. 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- 0406; 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 NPRM, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations (phone: 800-647- 5527) is listed above. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: David Bethka, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781- 238-7129; fax: 781-238-7199; email: david.bethka@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2018-0406; Product Identifier 2013-NE-30-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM 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 proposed AD. Discussion We issued AD 2017-07-04, Amendment 39-18842 (82 FR 16728, April 6, 2017), (``AD 2017-07-04''), for GE GE90-110B1 and GE90-115B turbofan engines with certain HPC rotor stage 2-5 spools installed. AD 2017-07- 04 requires removing these spools from service at times determined by a drawdown plan. AD 2017-07-04 resulted from reports of cracks in HPC rotor stage 2-5 spool aft spacer arms. We issued AD 2017-07-04 to prevent failure of a critical life-limited rotating engine part, which could result in an uncontained engine failure and damage to the airplane. Actions Since AD 2017-07-04 Was Issued Since we issued AD 2017-07-04, GE released GE SB GE90-100 SB 72- 0714 R01, dated February 16, 2018, for the HPC rotor stage 2-5 spools, which increases the number of affected parts. Additionally, GE and Boeing provided comments on AD-2017-07-04 that some HPC rotor stage 2-5 spools listed in AD 2013-24-17 (superseded by AD 2017-07-04), were omitted from AD 2017-07-04. Related Service Information Under 1 CFR Part 51 We reviewed GE SB GE90-100 SB 72-0499 R01, dated February 5, 2014; GE SB GE90-100 SB 72-0659 R01, dated February 18, 2016; and GE SB GE90- 100 SB 72-0714 R01, dated February 16, 2018. GE SB GE90-100 SB 72-0499 R01 describes procedures for identification and removal from service of HPC rotor stage 2-5 spools that use the original seal tooth coating process. GE SB GE90-100 SB 72- 0659 R01 describes procedures for identification and removal from service of HPC rotor stage 2-5 spools that use a modified seal tooth coating process. GE SB GE90-100 SB 72-0714 R01 describes procedures for identification and removal from service of HPC rotor stage 2-5 spools that use the modified seal tooth coating process, without coating between the seal teeth. 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 proposing 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. Proposed AD Requirements This proposed AD would retain all requirements of AD 2017-07-04. This proposed AD would require removing certain HPC rotor stage 2-5 spools from service at times specified in the required actions section. Costs of Compliance We estimate that this proposed AD affects 85 engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Paragraph (g)(1) Spools Replacement... 0 work-hours x $85 per $229,737 $229,737 $5,054,214 hour = $0. Paragraph (g)(2) Spools Replacement... 0 work-hours x $85 per 39,048 39,048 2,460,024 hour = $0. ---------------------------------------------------------------------------------------------------------------- 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 We have determined that this proposed AD would not have federalism [[Page 29476]] implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed regulation: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2017-07-04, Amendment 39-18842 (82 FR 16728, April 6, 2017), and adding the following new AD: General Electric Company: Docket No. FAA-2018-0406; Product Identifier 2013-NE-30-AD. (a) Comments Due Date The FAA must receive comments on this AD action by August 9, 2018. (b) Affected ADs This AD replaces AD 2017-07-04, Amendment 39-18842 (82 FR 16728, April 6, 2017) (``AD 2017-07-04''). (c) Applicability This AD applies to General Electric Company (GE) GE90-110B1 and GE90-115B turbofan engines with HPC rotor stage 2-5 spools, with: (1) A serial number listed in either, paragraph 4, Appendix A of GE Service Bulletin (SB) No. GE90-100 SB 72-0499 R01, dated February 5, 2014, in paragraph 4, Appendix A of GE SB GE90-100 SB 72-0659 R01, dated February 18, 2016, or in paragraph 4, Appendix A, of GE SB GE90-100 SB 72-0714 R01, dated February 16, 2018. (2) A part number (P/N) 351-103-109-0, P/N 351-103-110-0, P/N 351-103-147-0 or P/N 351-103-152-0, with any serial number. (d) Subject Joint Aircraft System Component (JASC) Code 7230, Turbine Engine Compressor Section. (e) Unsafe Condition This AD was prompted by reports of cracks in HPC rotor stage 2-5 spool aft spacer arms. We are issuing this AD to prevent failure of the HPC rotor stage 2-5 spools. The unsafe condition, if not addressed, could result in uncontained spool release, 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) Remove from service HPC rotor stage 2-5 spools with serial numbers listed in paragraph 4, Appendix A, of GE SB GE90-100 SB 72- 0659 R01, dated February 18, 2016, as follows, or before further flight, whichever occurs later: (i) For spools with fewer than 4,500 flight CSN as of April 21, 2017, remove before exceeding 5,000 CSN. (ii) For spools with 4,500 CSN or more but fewer than 5,200 CSN as of April 21, 2017, remove within 500 CIS but not to exceed 5,500 CSN. (iii) For spools with 5,200 CSN or more but fewer than 5,600 CSN as of April 21, 2017, remove within 300 CIS but not to exceed 5,800 CSN. (iv) For spools with 5,600 CSN or more but fewer than 5,800 CSN as of April 21, 2017, remove within 200 CIS but not to exceed 5,850 CSN. (v) For spools with 5,800 CSN or more but fewer than 6,000 CSN as of April 21, 2017, remove within 50 CIS but not to exceed 6,000 CSN. (vi) For spools with 6,000 CSN or more as of April 21, 2017, remove before the next flight. (2) Remove from service HPC rotor stage 2-5 spools listed in paragraph (c)(2) of this AD and HPC rotor stage 2-5 spools with serial numbers listed in paragraph 4, Appendix A, of GE SB GE90-100 SB 72-0714 R01, dated February 16, 2018, before exceeding 8,200 CSN, or before further flight, whichever occurs later. (h) Installation Prohibition (1) After the effective date of this AD, do not install or reinstall onto any engine, any HPC rotor stage 2-5 spool with a serial number listed in paragraph 4, Appendix A, of GE SB No. GE90- 100 SB 72-0499 R01, dated February 5, 2014, or paragraph 4, Appendix A, of GE SB GE90-100 SB72-0659 R01, dated February 18, 2016, that exceeds 5,000 CSN. (2) After the effective date of this AD, do not install or reinstall onto any engine, any HPC rotor stage 2-5 spool listed in paragraph (c)(2) of this AD, or HPC rotor stage 2-5 spool with a serial number listed in paragraph 4, Appendix A, of GE SB GE90-100 SB 72-0714 R01, dated February 16, 2018, that exceeds 8,200 CSN. (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 certification office, send it to the attention of the person identified in paragraph (j)(1) 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. (j) Related Information (1) For more information about this AD, contact David Bethka, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7129; fax: 781-238-7199; email: david.bethka@faa.gov. (2) For service information identified in this AD, contact General Electric Company, One Neumann Way, Room 285, Cincinnati, OH; phone: 513-552-3272; email: geae.aoc@ge.com. You may view this referenced 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. Issued in Burlington, Massachusetts, on June 19, 2018. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2018-13444 Filed 6-22-18; 8:45 am] BILLING CODE 4910-13-P
![29474 Federal Register / Vol. 83, No. 122 / Monday, June 25, 2018 / Proposed Rules
requirements. Ultramagic’s change 1. Hot Air Balloon Crashworthiness DEPARTMENT OF TRANSPORTATION
application applied the language in the Requirements for Seat Installations and
EASA proposed special condition for CS Restraints for Seated and Restrained Federal Aviation Administration
31HA.14(c), ‘‘Occupant mass,’’ CS Occupants
31HA.43(d), ‘‘Fitting factor,’’ CS 14 CFR Part 39
a. Occupant Mass
31HA.561(a) and (b)(1), ‘‘Emergency [Docket No. FAA–2018–0406; Product
landing conditions—General,’’ and CS For calculation purposes, it should be Identifier 2013–NE–30–AD]
31HA.785(a), (c), and (d), ‘‘Seats and assumed the mass of an occupant is at
RIN 2120–AA64
seat belts’’ to the CV–08 basket. The least 86 kilograms (190 pounds).
FAA finds that these standards are b. Seats, Safety Belts, and Harnesses Airworthiness Directives; General
appropriate for a seated, restrained Factor of Safety Electric Company Turbofan Engines
occupant.
For each seat, safety belt, and harness, AGENCY: Federal Aviation
Applicability its attachment to the structure must be Administration (FAA), DOT.
shown, by analysis, tests, or both, to be ACTION: Notice of proposed rulemaking
As discussed above, these special
able to withstand the inertia forces (NPRM).
conditions are applicable to the Model prescribed in paragraph (c) of these
M–56, M–56C, M–65, M–65C, M–77, M– special conditions multiplied by a SUMMARY: We propose to supersede
77C, M–90, M–105, M–120, M–130, M– fitting factor of 1.33. Airworthiness Directive (AD) 2017–07–
145, M–160, N–180, N–210, N–250, N– 04, which applies to General Electric
300, N–355, N–425, S–70, S–90, S–105, c. Emergency Landing Conditions— Company (GE) GE90–110B1 and GE90–
S–130, S–160, T–150, T–180, T–210, V– General 115B turbofan engines with certain
56, V–65, V–77, V–90, and V–105 The balloon—although it may be high-pressure compressor (HPC) rotor
balloons. Should Ultramagic apply at a damaged under emergency landing stage 2–5 spools installed. AD 2017–07–
later date for a change to the type conditions—must be designed to give 04 resulted from reports of cracks in
certificate to include another model each occupant every reasonable chance HPC rotor stage 2–5 spool aft spacer
incorporating the same novel or unusual of avoiding serious injury in a crash arms. Since we issued AD 2017–07–04,
design feature, the FAA would apply landing—when seat belts provided for GE released a new service bulletin (SB)
these special conditions to that model as in the design are properly used—and that increases the number of affected
well. the occupant is subject to the following HPC rotor stage 2–5 spools.
ultimate inertia forces acting relative to Additionally, we learned that we
Conclusion inadvertently omitted certain HPC rotor
the surrounding structure as well as
independently of each other. stage 2–5 spools from the applicability
This action affects only certain novel of AD 2017–07–04. This proposed AD
or unusual design features on the (1) Forward 6g would require removing certain HPC
balloon models specified in these (2) Sideways 6g rotor stage 2–5 spools from service
special conditions. It is not a rule of (3) Downward 6g before reaching the new reduced life
general applicability and it affects only limit and replacing them with parts
the applicant who applied to the FAA d. Seats and Seatbelts eligible for installation. We are
for approval of these features on the (1) Each seat and its supporting proposing this AD to correct the unsafe
airplane. These proposed special structure must be designed for an condition on these products.
conditions are identical in intent to the occupant mass in accordance paragraph DATES: We must receive comments on
EASA special conditions, although the (a) of these special conditions and for this proposed AD by August 9, 2018.
formatting has been altered to meet the maximum load factors ADDRESSES: You may send comments,
these special condition requirements. corresponding to the specified flight and using the procedures found in 14 CFR
List of Subjects in 14 CFR Part 23 ground load conditions, including the 11.43 and 11.45, by any of the following
emergency landing conditions methods:
Aircraft, Aviation safety. prescribed in paragraph (c) of these • Federal eRulemaking Portal: Go to
special conditions. http://www.regulations.gov. Follow the
The authority citation for these instructions for submitting comments.
special conditions is as follows: (2) Each seat or berth shall be fitted
with an individual approved seat belt or • Fax: 202–493–2251.
Authority: 49 U.S.C. 106(g), 40113, 44701– harness. • Mail: U.S. Department of
44702, 44704. Transportation, Docket Operations, M–
(3) Seat belts installed on the balloon
30, West Building Ground Floor, Room
The Proposed Special Conditions must not fail under flight or ground load
W12–140, 1200 New Jersey Avenue SE,
conditions or emergency landing
Accordingly, the FAA proposes the Washington, DC 20590.
conditions in accordance with
following special conditions as part of • Hand Delivery: Deliver to Mail
paragraph (c) of these special
the type certification basis for address above between 9 a.m. and 5
conditions, taking into account the
p.m., Monday through Friday, except
Ultramagic S.A. Model M–56, M–56C, geometrical arrangement of the belt
Federal holidays.
amozie on DSK3GDR082PROD with PROPOSALS1
M–65, M–65C, M–77, M–77C, M–90, M– attachment and the seat.
For service information identified in
105, M–120, M–130, M–145, M–160, N– Issued in Kansas City, Missouri, on June this NPRM, contact General Electric
180, N–210, N–250, N–300, N–355, N– 15, 2018. Company, One Neumann Way, Room
425, S–70, S–90, S–105, S–130, S–160, Pat Mullen, 285, Cincinnati, OH; phone: 513–552–
T–150, T–180, T–210, V–56, V–65, V– Manager, Small Airplane Standards Branch, 3272; email: geae.aoc@ge.com. You may
77, V–90, and V–105 balloons with a Aircraft Certification Service. view this service information at the
basket Model no. CV–08. [FR Doc. 2018–13499 Filed 6–22–18; 8:45 am] FAA, Engine and Propeller Standards
BILLING CODE 4910–13–P Branch, 1200 District Avenue,
VerDate Sep<11>2014 16:25 Jun 22, 2018 Jkt 244001 PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 E:\FR\FM\25JNP1.SGM 25JNP1](https://thefederalregister.org/doc/83_FR_29596/page/1.svg)
![29476 Federal Register / Vol. 83, No. 122 / Monday, June 25, 2018 / Proposed Rules
implications under Executive Order R01, dated February 18, 2016, or in HPC rotor stage 2–5 spool listed in paragraph
13132. This proposed AD would not paragraph 4, Appendix A, of GE SB GE90– (c)(2) of this AD, or HPC rotor stage 2–5 spool
have a substantial direct effect on the 100 SB 72–0714 R01, dated February 16, with a serial number listed in paragraph 4,
2018. Appendix A, of GE SB GE90–100 SB 72–0714
States, on the relationship between the
(2) A part number (P/N) 351–103–109–0, P/ R01, dated February 16, 2018, that exceeds
national Government and the States, or N 351–103–110–0, P/N 351–103–147–0 or P/ 8,200 CSN.
on the distribution of power and N 351–103–152–0, with any serial number.
responsibilities among the various (i) Alternative Methods of Compliance
levels of government. (d) Subject (AMOCs)
For the reasons discussed above, I Joint Aircraft System Component (JASC) (1) The Manager, ECO Branch, FAA, has
certify that the proposed regulation: Code 7230, Turbine Engine Compressor the authority to approve AMOCs for this AD,
(1) Is not a ‘‘significant regulatory Section. if requested using the procedures found in 14
action’’ under Executive Order 12866, CFR 39.19. In accordance with 14 CFR 39.19,
(e) Unsafe Condition
send your request to your principal inspector
(2) Is not a ‘‘significant rule’’ under This AD was prompted by reports of cracks or local Flight Standards District Office, as
the DOT Regulatory Policies and in HPC rotor stage 2–5 spool aft spacer arms. appropriate. If sending information directly
Procedures (44 FR 11034, February 26, We are issuing this AD to prevent failure of to the manager of the certification office,
1979), the HPC rotor stage 2–5 spools. The unsafe send it to the attention of the person
(3) Will not affect intrastate aviation condition, if not addressed, could result in identified in paragraph (j)(1) of this AD. You
in Alaska, and uncontained spool release, damage to the may email your request to: ANE-AD-AMOC@
engine, and damage to the airplane. faa.gov.
(4) Will not have a significant
economic impact, positive or negative, (f) Compliance (2) Before using any approved AMOC,
on a substantial number of small entities notify your appropriate principal inspector,
Comply with this AD within the or lacking a principal inspector, the manager
under the criteria of the Regulatory compliance times specified, unless already of the local flight standards district office/
Flexibility Act. done.
certificate holding district office.
List of Subjects in 14 CFR Part 39 (g) Required Actions
(j) Related Information
Air transportation, Aircraft, Aviation (1) Remove from service HPC rotor stage 2–
(1) For more information about this AD,
5 spools with serial numbers listed in
safety, Incorporation by reference, paragraph 4, Appendix A, of GE SB GE90–
contact David Bethka, Aerospace Engineer,
Safety. ECO Branch, FAA, 1200 District Avenue,
100 SB 72–0659 R01, dated February 18,
Burlington, MA 01803; phone: 781–238–
The Proposed Amendment 2016, as follows, or before further flight,
7129; fax: 781–238–7199; email:
whichever occurs later:
Accordingly, under the authority david.bethka@faa.gov.
(i) For spools with fewer than 4,500 flight
(2) For service information identified in
delegated to me by the Administrator, CSN as of April 21, 2017, remove before
exceeding 5,000 CSN. this AD, contact General Electric Company,
the FAA proposes to amend 14 CFR part One Neumann Way, Room 285, Cincinnati,
39 as follows: (ii) For spools with 4,500 CSN or more but
fewer than 5,200 CSN as of April 21, 2017, OH; phone: 513–552–3272; email: geae.aoc@
remove within 500 CIS but not to exceed ge.com. You may view this referenced service
PART 39—AIRWORTHINESS information at the FAA, Engine and Propeller
DIRECTIVES 5,500 CSN.
(iii) For spools with 5,200 CSN or more but Standards Branch, 1200 District Avenue,
fewer than 5,600 CSN as of April 21, 2017, Burlington, MA 01803. For information on
■ 1. The authority citation for part 39 the availability of this material at the FAA,
remove within 300 CIS but not to exceed
continues to read as follows: 5,800 CSN. call 781–238–7759.
Authority: 49 U.S.C. 106(g), 40113, 44701. (iv) For spools with 5,600 CSN or more but Issued in Burlington, Massachusetts, on
fewer than 5,800 CSN as of April 21, 2017, June 19, 2018.
§ 39.13 [Amended] remove within 200 CIS but not to exceed Robert J. Ganley,
■ 2. The FAA amends § 39.13 by 5,850 CSN.
(v) For spools with 5,800 CSN or more but Manager, Engine and Propeller Standards
removing Airworthiness Directive (AD) Branch, Aircraft Certification Service.
2017–07–04, Amendment 39–18842 (82 fewer than 6,000 CSN as of April 21, 2017,
remove within 50 CIS but not to exceed 6,000 [FR Doc. 2018–13444 Filed 6–22–18; 8:45 am]
FR 16728, April 6, 2017), and adding CSN. BILLING CODE 4910–13–P
the following new AD: (vi) For spools with 6,000 CSN or more as
General Electric Company: Docket No. of April 21, 2017, remove before the next
FAA–2018–0406; Product Identifier 2013– flight. DEPARTMENT OF TRANSPORTATION
NE–30–AD. (2) Remove from service HPC rotor stage 2–
5 spools listed in paragraph (c)(2) of this AD Federal Aviation Administration
(a) Comments Due Date and HPC rotor stage 2–5 spools with serial
The FAA must receive comments on this numbers listed in paragraph 4, Appendix A,
of GE SB GE90–100 SB 72–0714 R01, dated 14 CFR Part 39
AD action by August 9, 2018.
February 16, 2018, before exceeding 8,200
(b) Affected ADs CSN, or before further flight, whichever [Docket No. FAA–2018–0552; Product
This AD replaces AD 2017–07–04, occurs later. Identifier 2018–NM–049–AD]
Amendment 39–18842 (82 FR 16728, April 6,
(h) Installation Prohibition RIN 2120–AA64
2017) (‘‘AD 2017–07–04’’).
(1) After the effective date of this AD, do
(c) Applicability not install or reinstall onto any engine, any Airworthiness Directives; Airbus
amozie on DSK3GDR082PROD with PROPOSALS1
This AD applies to General Electric HPC rotor stage 2–5 spool with a serial Defense and Space S.A. (Formerly
Company (GE) GE90–110B1 and GE90–115B number listed in paragraph 4, Appendix A, Known as Construcciones
turbofan engines with HPC rotor stage 2–5 of GE SB No. GE90–100 SB 72–0499 R01, Aeronauticas, S.A. (CASA)) Airplanes
spools, with: dated February 5, 2014, or paragraph 4,
(1) A serial number listed in either, Appendix A, of GE SB GE90–100 SB72–0659 AGENCY: Federal Aviation
paragraph 4, Appendix A of GE Service R01, dated February 18, 2016, that exceeds Administration (FAA), DOT.
Bulletin (SB) No. GE90–100 SB 72–0499 R01, 5,000 CSN. ACTION: Notice of proposed rulemaking
dated February 5, 2014, in paragraph 4, (2) After the effective date of this AD, do (NPRM).
Appendix A of GE SB GE90–100 SB 72–0659 not install or reinstall onto any engine, any
VerDate Sep<11>2014 16:25 Jun 22, 2018 Jkt 244001 PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 E:\FR\FM\25JNP1.SGM 25JNP1](https://thefederalregister.org/doc/83_FR_29596/page/3.svg)
Document Created: 2018-06-23 02:29:35
Document Modified: 2018-06-23 02:29:35
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by August 9, 2018. | |
| Contact | David Bethka, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781- 238-7129; fax: 781-238-7199; email: [email protected] | |
| FR Citation | 83 FR 29474 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft and Aviation Safety |
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