83 FR 36724 - Airworthiness Directives; General Electric Company Turbofan Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 147 (July 31, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 147 (July 31, 2018)
| Page Range | 36724-36727 | |
| FR Document | 2018-16309 |
[Federal Register Volume 83, Number 147 (Tuesday, July 31, 2018)] [Rules and Regulations] [Pages 36724-36727] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-16309] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0630; Product Identifier 2018-NE-25-AD; Amendment 39-19347; AD 2018-16-07] RIN 2120-AA64 Airworthiness Directives; General Electric Company Turbofan 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) GEnx-1B54, -1B58, -1B64, -1B67, -1B70, - 1B54/P1, -1B58/P1, -1B64/P1, -1B67/ [[Page 36725]] P1, -1B70/P1, -1B54/P2, -1B58/P2, -1B64/P2, -1B67/P2, -1B70/P2, -1B70C/ P1, -1B70/72/P1, -1B70/75/P1, -1B74/75/P1, -1B75/P1, -1B70C/P2, -1B70/ 72/P2, -1B70/75/P2, -1B74/75/P2, -1B75/P2, -1B76/P2, -1B76A/P2, -1B78/ P2, -2B67, -2B67B, and -2B67/P turbofan engines. This AD requires removal of affected high-pressure turbine (HPT) stator cases (HPT cases) from service and their replacement with a part eligible for installation. This AD was prompted by the discovery of a quality escape at a manufacturing facility. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective August 15, 2018. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 15, 2018. We must receive comments on this AD by September 14, 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; email: [email protected]. You may view this service information at the FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA. 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-2018-0630. 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- 0630; 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: Herman Mak, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781- 238-7147; fax: 781-238-7199; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We learned from GE of a quality escape at one of their suppliers. This supplier was performing welds on newly-manufactured components to correct errors introduced in their manufacturing process. These welds were not reviewed or approved by either GE or the FAA. GE's review of manufacturing records determined that these parts include HPT cases installed on GEnx engines. These HPT cases are life limited. The unapproved repairs reduced the material capability of these cases which requires their removal prior to reaching their published Airworthiness Limitation Section life limit. This condition, if not addressed, could result in failure of the HPT case, engine fire, 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 GE Service Bulletin (SB) GEnx-1B S/B 72-0424, Revision 03, dated June 29, 2018 and GEnx-2B S/B 72-0360, Revision 03, dated June 29, 2018. The SBs describe procedures for removing the affected HPT cases from the engine. GE SB GEnx-1B S/B 72-0424 is effective for GEnx-1B engines with the serial numbers of HPT cases listed in that SB. GE SB GEnx-2B S/B 72-0360 is effective for GEnx-2B engines with the serial numbers of HPT cases listed in that SB. 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 Inspection 001, Subtask 72-52-01-230-001 of GEnx-1B Cleaning, Inspection, and Repair Manual GEK112862, Rev 27, dated April 30, 2018, and GEnx-2B Cleaning, Inspection, and Repair Manual GEK114120, Rev 20, dated April 30, 2018. These manuals provide guidance for conducting Class A fluorescent penetrant inspections. 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 removal of the affected HPT cases from service and their replacement with a part eligible for installation. 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 required action is shorter than the time necessary for the public to comment and for us to publish the final rule. Therefore, we find good cause 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 FAA-2018- 0630 and Product Identifier 2018-NE-25-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. [[Page 36726]] Costs of Compliance We estimate that this AD affects 13 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 ---------------------------------------------------------------------------------------------------------------- Replacement of HPT case........... 0 work-hours x $85 per $362,400 $362,400 $4,711,200 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 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): 2018-16-07 General Electric Company: Amendment 39-19347; Docket No. FAA-2018-0630; Product Identifier 2018-NE-25-AD. (a) Effective Date This AD is effective August 15, 2018. (b) Affected ADs None. (c) Applicability This AD applies to General Electric Company (GE) GEnx-1B54, - 1B58, -1B64, -1B67, -1B70, -1B54/P1, -1B58/P1, -1B64/P1, -1B67/P1, - 1B70/P1, -1B54/P2, -1B58/P2, -1B64/P2, -1B67/P2, -1B70/P2, -1B70C/ P1, -1B70/72/P1, -1B70/75/P1, -1B74/75/P1, -1B75/P1, -1B70C/P2, - 1B70/72/P2, -1B70/75/P2, -1B74/75/P2, -1B75/P2, -1B76/P2, -1B76A/P2, -1B78/P2, -2B67, -2B67B, and -2B67/P turbofan engines with a high- pressure turbine (HPT) stator case (HPT case), part number (P/N) 2302M90G04 installed, and with any serial number (S/N) listed in Table 1, 2, or 3, in the Planning Information section of GE Service Bulletin (SB) GEnx-2B S/B 72-0360, Revision 03, dated June 29, 2018, or GEnx-1B S/B 72-0424, Revision 03, dated June 29, 2018, installed. (d) Subject Joint Aircraft System Component (JASC) Code 7250, Turbine Section. (e) Unsafe Condition This AD was prompted by the discovery of a quality escape at a manufacturing facility involving unapproved welds on HPT cases. We are issuing this AD to prevent failure of the HPT case. The unsafe condition, if not addressed, could result in engine fire and damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) For HPT cases listed in Planning Information, Table 1 or 2, of GE SBs GEnx-2B S/B 72-0360, Revision 03, dated June 29, 2018 and GEnx-1B S/B 72-0424, Revision 03, dated June 29, 2018, determine the lesser of the following: Cycles since new (CSN) or cycles since Class A fluorescent penetrant inspection (CSFPI) of the entire HPT case. (2) Using the determination made in paragraph (g)(1) of this AD, remove from service the HPT case after the effective date of this AD as specified in Table 1 to paragraph (g) of this AD. Replace the removed HPT case with a part eligible for installation. [[Page 36727]] [GRAPHIC] [TIFF OMITTED] TR31JY18.000 (3) Remove from service HPT cases listed in Planning Information, Table 3, of GE SBs GEnx-2B S/B 72-0360, Revision 03, dated June 29, 2018 or GEnx-1B S/B 72-0424, Revision 03, dated June 29, 2018, prior to exceeding 10 cycles after the effective date of this AD or exceeding the CSN limits listed in Table 3, whichever comes later. Replace the removed HPT case with a part eligible for installation. (h) Installation Prohibition (1) After the effective date of this AD, do not install any affected HPT case onto any engine. (2) After the effective date of this AD, HPT cases listed in Planning Information, Table 3, in GE SB GEnx-2B S/B 72-0360, Revision 03, dated June 29, 2018 or GEnx-1B S/B 72-0424, Revision 03, dated June 29, 2018, and any higher level assemblies with these parts installed, may not be removed from a GEnx-2B engine and installed on a GEnx-1B engine or removed from a GEnx-1B engine and installed on a GEnx-2B engine. (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) 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 Herman Mak, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7147; 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) General Electric Company (GE) Service Bulletin (SB) GEnx-2B S/B 72-0360, Revision 03, dated June 29, 2018. (ii) GE SB GEnx-1B S/B 72-0424, Revision 03, dated June 29, 2018. (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; email: [email protected]. (4) You may view this service information at FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA. 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 July 25, 2018. Karen M. Grant, Acting Manager, Engine & Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2018-16309 Filed 7-30-18; 8:45 am] BILLING CODE 4910-13-P
![36724 Federal Register / Vol. 83, No. 147 / Tuesday, July 31, 2018 / Rules and Regulations
Special conditions are initially developed in the Aviation Rulemaking flight-control system (EFCS) pitch- and
applicable to the model for which they Advisory Committee (ARAC) Flight Test roll-limiting functions:
are issued. Should the type certificate Harmonization Working Group 1. The pitch-limiting function must
for that model be amended later to (FTHWG). The FAA concurs with this not impede normal maneuvering for
include any other model that request. pitch angles up to the maximum
incorporates the same novel or unusual The basic envelope protection required for normal maneuvering,
design feature, or should any other requirement, historically applied, is to including a normal, all-engines-
model already included on the same not unduly limit the maneuver operating takeoff, plus a suitable margin
type certificate be modified to capability of the airplane, or interfere to allow for satisfactory speed control.
incorporate the same novel or unusual with its ability to perform maneuvers 2. The pitch- and roll-limiting
design feature, these special conditions required for normal and emergency functions must not restrict or prevent
would also apply to the other model operations. Since the design details attaining pitch attitudes necessary for
under § 21.101. used to meet this requirement vary from emergency maneuvering, or roll angles
In addition to the applicable airplane to airplane, this amendment up to 65 degrees. Spiral stability, which
airworthiness regulations and special recognizes and adopts that philosophy is introduced above 30 degrees of roll
conditions, the Bombardier Model BD– for this specific design implementation. angle, must not require excessive pilot
700–2A12 and BD–700–2A13 series The substance of the special conditions strength to achieve these roll angles.
airplanes must comply with the fuel- is unchanged, in that, for this specific Other protections, which further limit
vent and exhaust-emission requirements design, the design details support the the roll capability under certain extreme
of 14 CFR part 34, and the noise- objective of not unduly limiting the angle-of-attack, attitude, or high-speed
certification requirements of 14 CFR maneuver capability, while also conditions, are acceptable, as long as the
part 36. protecting the airplane from adverse airplane is able to perform coordinated
The FAA issues special conditions, as attitudes. turns as per § 25.143(h). A roll attitude
defined in 14 CFR 11.19, in accordance These special conditions are in limit of approximately 45 degrees at
with § 11.38, and they become part of addition to the requirements of § 25.143. high angle-of-attack conditions is
the type certification basis under These special conditions contain the acceptable.
§ 21.101. additional safety standards that the 3. A reduced roll attitude limit is
Novel or Unusual Design Features Administrator considers necessary to acceptable at extreme nose down pitch
establish a level of safety equivalent to attitudes and beyond the overspeed
The Model BD–700–2A12 and BD– that established by the existing warning to provide protection against
700–2A13 series airplanes will airworthiness standards. high-speed combined pitch and roll
incorporate the following novel or upsets. The airplane should be able to
unusual design features: Applicability
perform operational turns at these
Fly-by-wire EFCS that will limit pitch As discussed above, these special speeds. A roll attitude limit of
and roll functions to prevent the conditions are applicable to the Model approximately 30 degrees at Vdf/Mdf is
airplane from attaining certain pitch BD–700–2A12 and BD–700–2A13 series considered acceptable.
attitudes and roll angles greater than airplanes. Should Bombardier apply at a
plus or minus 65 degrees, and introduce later date for a change to the type Issued in Des Moines, Washington.
positive spiral stability introduced for certificate to include another model Victor Wicklund,
roll angles greater than 30 degrees at incorporating the same novel or unusual Manager, Transport Standards Branch, Policy
speeds below VMO/MMO. This system design feature, these special conditions and Innovation Division, Aircraft
generates the actual surface commands would apply to that model as well. Certification Service.
that provide for stability augmentation [FR Doc. 2018–16360 Filed 7–30–18; 8:45 am]
and flight control for all three airplane Conclusion BILLING CODE 4910–13–P
axes (longitudinal, lateral, and This action affects only certain novel
directional). or unusual design features on one model
series of airplanes. It is not a rule of DEPARTMENT OF TRANSPORTATION
Discussion
general applicability.
Part 25 of title 14 of the CFR does not Federal Aviation Administration
specifically relate to flight List of Subjects in 14 CFR Part 25
characteristics associated with fixed Aircraft, Aviation safety, Reporting 14 CFR Part 39
attitude limits. Bombardier proposes to and recordkeeping requirements. [Docket No. FAA–2018–0630; Product
implement on the airplanes pitch and Identifier 2018–NE–25–AD; Amendment 39–
Authority Citation
roll attitude-limiting functions via the 19347; AD 2018–16–07]
EFCS normal mode. This will prevent The authority citation for these
special conditions is as follows: RIN 2120–AA64
the airplane from attaining certain pitch
attitudes and roll angles greater than Authority: 49 U.S.C. 106(f), 106(g), 40113, Airworthiness Directives; General
plus or minus 65 degrees. In addition, 44701, 44702, 44704.
Electric Company Turbofan Engines
positive spiral stability, introduced for
The Special Conditions
roll angles greater than 30 degrees at AGENCY: Federal Aviation
speeds below VMO/MMO, and spiral ■ Accordingly, pursuant to the authority Administration (FAA), DOT.
stability characteristics, must not delegated to me by the Administrator, ACTION: Final rule; request for
daltland on DSKBBV9HB2PROD with RULES
require excessive pilot strength to the following special conditions are comments.
achieve bank angles up to the bank- issued as part of the type certification
angle limit. basis for Bombardier Model BD–700– SUMMARY: We are adopting a new
Bombardier requested this 2A12 and BD–700–2A13 series airworthiness directive (AD) for certain
amendment, in order to be performance- airplanes: General Electric Company (GE) GEnx–
based rather than prescriptive and to In addition to § 25.143, the following 1B54, –1B58, –1B64, –1B67, –1B70,
more closely follow the language requirements apply to the electronic –1B54/P1, –1B58/P1, –1B64/P1, –1B67/
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![36726 Federal Register / Vol. 83, No. 147 / Tuesday, July 31, 2018 / Rules and Regulations
Costs of Compliance We estimate the following costs to
We estimate that this AD affects 13 comply with this AD:
engines installed on airplanes of U.S.
registry.
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Replacement of HPT case .............................. 0 work-hours × $85 per hour = $0 ................. $362,400 $362,400 $4,711,200
Authority for This Rulemaking For the reasons discussed above, I –1B67, –1B70, –1B54/P1, –1B58/P1, –1B64/
certify that this AD: P1, –1B67/P1, –1B70/P1, –1B54/P2, –1B58/
Title 49 of the United States Code
(1) Is not a ‘‘significant regulatory P2, –1B64/P2, –1B67/P2, –1B70/P2, –1B70C/
specifies the FAA’s authority to issue P1, –1B70/72/P1, –1B70/75/P1, –1B74/75/P1,
rules on aviation safety. Subtitle I, action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under –1B75/P1, –1B70C/P2, –1B70/72/P2, –1B70/
section 106, describes the authority of 75/P2, –1B74/75/P2, –1B75/P2, –1B76/P2,
the FAA Administrator. ‘‘Subtitle VII: DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979), –1B76A/P2, –1B78/P2, –2B67, –2B67B, and
Aviation Programs’’ describes in more –2B67/P turbofan engines with a high-
(3) Will not affect intrastate aviation
detail the scope of the Agency’s pressure turbine (HPT) stator case (HPT
in Alaska, and
authority. (4) Will not have a significant case), part number (P/N) 2302M90G04
We are issuing this rulemaking under installed, and with any serial number (S/N)
economic impact, positive or negative,
the authority described in Subtitle VII, listed in Table 1, 2, or 3, in the Planning
on a substantial number of small entities
Part A, Subpart III, Section 44701: Information section of GE Service Bulletin
under the criteria of the Regulatory
‘‘General requirements.’’ Under that (SB) GEnx–2B S/B 72–0360, Revision 03,
Flexibility Act.
section, Congress charges the FAA with dated June 29, 2018, or GEnx–1B S/B 72–
promoting safe flight of civil aircraft in List of Subjects in 14 CFR Part 39 0424, Revision 03, dated June 29, 2018,
air commerce by prescribing regulations Air transportation, Aircraft, Aviation installed.
for practices, methods, and procedures safety, Incorporation by reference, (d) Subject
the Administrator finds necessary for Safety.
safety in air commerce. This regulation Joint Aircraft System Component (JASC)
is within the scope of that authority Adoption of the Amendment Code 7250, Turbine Section.
because it addresses an unsafe condition Accordingly, under the authority (e) Unsafe Condition
that is likely to exist or develop on delegated to me by the Administrator, This AD was prompted by the discovery of
products identified in this rulemaking the FAA amends 14 CFR part 39 as a quality escape at a manufacturing facility
action. follows: involving unapproved welds on HPT cases.
This AD is issued in accordance with We are issuing this AD to prevent failure of
authority delegated by the Executive PART 39—AIRWORTHINESS the HPT case. The unsafe condition, if not
Director, Aircraft Certification Service, DIRECTIVES addressed, could result in engine fire and
as authorized by FAA Order 8000.51C. damage to the airplane.
In accordance with that order, issuance ■ 1. The authority citation for part 39
of ADs is normally a function of the continues to read as follows: (f) Compliance
Compliance and Airworthiness Authority: 49 U.S.C. 106(g), 40113, 44701. Comply with this AD within the
Division, but during this transition compliance times specified, unless already
period, the Executive Director has § 39.13 [Amended] done.
delegated the authority to issue ADs ■ 2. The FAA amends § 39.13 by adding (g) Required Actions
applicable to engines, propellers, and the following new airworthiness (1) For HPT cases listed in Planning
associated appliances to the Manager, directive (AD): Information, Table 1 or 2, of GE SBs GEnx–
Engine and Propeller Standards Branch, 2018–16–07 General Electric Company: 2B S/B 72–0360, Revision 03, dated June 29,
Policy and Innovation Division. Amendment 39–19347; Docket No. 2018 and GEnx–1B S/B 72–0424, Revision
Regulatory Findings FAA–2018–0630; Product Identifier 03, dated June 29, 2018, determine the lesser
2018–NE–25–AD. of the following: Cycles since new (CSN) or
This AD will not have federalism cycles since Class A fluorescent penetrant
implications under Executive Order (a) Effective Date
inspection (CSFPI) of the entire HPT case.
13132. This AD will not have a This AD is effective August 15, 2018. (2) Using the determination made in
substantial direct effect on the States, on (b) Affected ADs paragraph (g)(1) of this AD, remove from
the relationship between the national service the HPT case after the effective date
None.
government and the States, or on the of this AD as specified in Table 1 to
distribution of power and (c) Applicability paragraph (g) of this AD. Replace the
responsibilities among the various This AD applies to General Electric removed HPT case with a part eligible for
levels of government. Company (GE) GEnx–1B54, –1B58, –1B64, installation.
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Document Created: 2018-11-06 10:29:41
Document Modified: 2018-11-06 10:29:41
| 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 August 15, 2018. | |
| Contact | Herman Mak, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781- 238-7147; fax: 781-238-7199; email: [email protected] | |
| FR Citation | 83 FR 36724 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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