Airworthiness Directives; General Electric Company Turbofan Engines, 63569-63571 [2019-24898]

Download as PDF Federal Register / Vol. 84, No. 222 / Monday, November 18, 2019 / Rules and Regulations Appendix B to Part 73 [Amended] 26. In appendix B, section VI.B.1(a)(4) remove the last sentence. ■ PART 110—EXPORT AND IMPORT OF NUCLEAR EQUIPMENT AND MATERIAL 27. The authority citation for part 110 continues to read as follows: ■ Authority: Atomic Energy Act of 1954, secs. 11, 51, 53, 54, 57, 62, 63, 64, 65, 81, 82, 103, 104, 109, 111, 121, 122, 123, 124, 126, 127, 128, 129, 133, 134, 161, 170H, 181, 182, 183, 184, 186, 187, 189, 223, 234 (42 U.S.C. 2014, 2071, 2073, 2074, 2077, 2092, 2093, 2094, 2095, 2111, 2112, 2133, 2134, 2139, 2141, 2151, 2152, 2153, 2154, 2155, 2156, 2157, 2158, 2160c, 2160d, 2201, 2210h, 2231, 2232, 2233, 2234, 2236, 2237, 2239, 2273, 2282); Energy Reorganization Act of 1974, sec. 201 (42 U.S.C. 5841); Administrative Procedure Act (5 U.S.C. 552, 553); 42 U.S.C. 2139a, 2155a; 44 U.S.C. 3504 note. Section 110.1(b) also issued under 22 U.S.C. 2403; 22 U.S.C. 2778a; 50 App. U.S.C. 2401 et seq. § 110.42 [Amended] 28. In § 110.42(e)(1) remove the reference ‘‘§ 110.32(h)’’ and add in its place the reference ‘‘§ 110.32(g)’’. ■ Dated at Rockville, Maryland, this 8th day of November 2019. For the Nuclear Regulatory Commission. Pamela J. Shepherd-Vladimir, Acting Chief, Regulatory Analysis and Rulemaking Support Branch, Office of Nuclear Material Safety and Safeguards. [FR Doc. 2019–25021 Filed 11–15–19; 8:45 am] BILLING CODE 7590–01–M DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0394; Product Identifier 2017–NE–36–AD; Amendment 39– 19784; AD 2019–22–05] RIN 2120–AA64 Airworthiness Directives; General Electric Company Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is superseding Airworthiness Directive (AD) 2017–23– 06, for certain General Electric Company (GE) CF34–8C1, CF34–8C5, CF34– 8C5A1, and CF34–8C5B1 engines. AD 2017–23–06 required an inspection of the bleed air manifold link rod assemblies and the supply, return, and SUMMARY: VerDate Sep<11>2014 15:41 Nov 15, 2019 Jkt 250001 drain fuel fittings on the operability bleed valve (OBV). This AD requires repetitive inspections of the OBV fuel tubes, OBV bleed air manifold link rod assemblies, and the OBV fuel fittings and replacement of OBVs or related hardware that fail inspection. In addition, this AD expands the applicability of these inspections to include additional GE CF34–8C model turbofan engines. This AD was prompted by multiple engine fires that have occurred as a result of malfunctions related to the OBV. The FAA is issuing this AD to address the unsafe condition on these products. DATES: This AD is effective December 23, 2019. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 23, 2019. ADDRESSES: For service information identified in this final rule, contact General Electric Company, GE-Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 45215, phone: 513–552–3272; fax: 513–552–3329; email: geae.aoc@ge.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 https://www.regulations.gov by searching for and locating Docket No. FAA–2019–0394. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.govby searching for and locating Docket No. FAA–2019– 0394; 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 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: Michael Richardson-Bach, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781–238–7747; fax: 781–238– 7199; email: michael.richardson-bach@ faa.gov. SUPPLEMENTARY INFORMATION: Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 63569 part 39 to supersede AD 2017–23–06, Amendment 39–19100 (82 FR 52830, November 15, 2017), (‘‘AD 2017–23– 06’’). AD 2017–23–06 applied to certain GE CF34–8C1, CF34–8C5, CF34–8C5A1, and CF34–8C5B1 engines. The NPRM published in the Federal Register on June 28, 2019 (84 FR 30956). The NPRM was prompted by multiple engine fires that have occurred as a result of malfunctions related to the OBV. The NPRM proposed to require repetitive inspections of the OBV fuel tubes, OBV bleed air manifold link rod assemblies, and the OBV fuel fittings and replacement of OBVs or related hardware that fail inspection. In addition, the NPRM proposed to expand the applicability of these inspections to include additional GE CF34–8C model turbofan engines. The FAA is issuing this AD to address the unsafe condition on these products. Comments The FAA gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA’s response to each comment. Request To Change the Inspection Intervals GE requested that the FAA extend the initial and repetitive inspection intervals to 16,000 flight hours (FHs) and 1,680 FHs, respectively, for engines equipped with OBV part number (P/N) 4123T71P05. GE reasoned that based on testing and analysis, OBV P/N 4123T71P05 is more resistant to wear than OBV P/N 4123T71P04, and earlier versions, if the installation support links are regularly inspected and maintained. The FAA disagrees with extending the inspection intervals for engines equipped with OBV P/N 4123T71P05 because the FAA did not find GE’s test and analysis data sufficient to justify the extended inspection intervals. The FAA did not change this AD. Request To Update the Applicability The National Transportation Safety Board (NTSB) supported this AD and requested that the FAA consider similar rulemaking to include the GE CF34–8E model turbofan engines. The NTSB suggested that the unsafe condition exists on this engine and that the FAA should identify the higher-risk OBVs and publish an AD that mandates a repetitive inspection for the GE CF34– 8E OBVs. The FAA agrees to consider future rulemaking for the GE CF34–8E model turbofan engines because those engines have experienced the same unsafe condition addressed by the engine E:\FR\FM\18NOR1.SGM 18NOR1 63570 Federal Register / Vol. 84, No. 222 / Monday, November 18, 2019 / Rules and Regulations models of this AD. The FAA did not change this AD. Support for the AD The Air Line Pilots Association International and an individual commenter expressed support for the AD as written. Conclusion The FAA reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. The FAA has determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. bleed air manifold link rod assemblies; the supply, return, and drain fuel fittings; and the fuel tubes on the OBV. 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. Related Service Information Under 1 CFR Part 51 Costs of Compliance The FAA reviewed GE Service Bulletin (SB) CF34–8C S/B 75–0020, R04, dated May 10, 2019. The SB describes procedures for inspecting the The FAA estimates that this AD affects 1,297 engines installed on airplanes of U.S. registry. The FAA estimates the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Inspection of OBV fuel tubes, assemblies, and fittings. 1 work-hour × $85 per hour = $85 ................. The FAA estimates the following costs to do any necessary replacements that would be required based on the results of the inspection. The FAA has no way of determining the number of Cost per product Parts cost $0 Cost on U.S. operators $85 $110,245 aircraft that might need these replacements: ON-CONDITION COSTS Action Labor cost Replace OBV ................................................................ Replace OBV support hardware .................................. 2 work-hours × $85 per hour = $170 ........................... 2.25 work-hours × $85 per hour = $191.25 ................. 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. The FAA is 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 VerDate Sep<11>2014 15:41 Nov 15, 2019 Jkt 250001 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 The FAA has determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Will not affect intrastate aviation in Alaska, and (3) 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. PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Parts cost $17,230 3,595 Cost per product $17,400 3,786.25 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: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2017–23–06, Amendment 39–19100 (82 FR 52830, November 15, 2017), and adding the following new AD: ■ 2019–22–05 General Electric Company: Amendment 39–19784; Docket No. FAA–2019–0394; Product Identifier 2017–NE–36–AD. (a) Effective Date This AD is effective December 23, 2019. E:\FR\FM\18NOR1.SGM 18NOR1 Federal Register / Vol. 84, No. 222 / Monday, November 18, 2019 / Rules and Regulations (b) Affected ADs This AD replaces AD 2017–23–06, Amendment 39–19100 (82 FR 52830, November 15, 2017). (c) Applicability This AD applies to all General Electric Company (GE) CF34–8C1, CF34–8C5, CF34– 8C5A1, CF34–8C5B1, CF34–8C5A2, and CF34–8C5A3 model turbofan engines. (d) Subject Joint Aircraft System Component (JASC) Code 7531, Compressor bleed governor. (e) Unsafe Condition This AD was prompted by multiple engine fires that have occurred as a result of malfunctions related to the operability bleed valve (OBV). The FAA is issuing this AD to prevent failure of the OBV. 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 CF34–8C1, CF34–8C5, CF34– 8C5A1, and CF34–8C5B1 model turbofan engines with serial numbers (S/Ns): 965101 through 965670 inclusive; 194101 through 194999 inclusive; and 195101 through 195653 inclusive: (i) Perform an inspection of the OBV bleed air manifold link rod assemblies and the OBV fuel fittings within 500 flight hours after November 30, 2017 (effective date of AD 2017–23–06), or before next flight after the effective date of this AD, whichever occurs later. (ii) Within 880 flight hours since the previous inspection, 500 flight hours from the effective date of this AD, or 6,880 flight hours since new, whichever occurs later, inspect the OBV bleed air manifold link rod assemblies, the OBV fuel fittings, and the OBV fuel tubes. (iii) Thereafter, perform additional repeat inspections of the OBV bleed air manifold link rod assemblies, the OBV fuel fittings, and the OBV fuel tubes within every 880 flight hours since the previous inspection. (iv) Use the Accomplishment Instructions, Paragraph 3.B., of GE CF34–8C S/B 75–0020, R04, dated May 10, 2019 (‘‘the SB’’), to perform the inspections in paragraphs (g)(1)(i) through (iii) of this AD and, per the criteria for the results of inspections in Paragraph 3.B. of the SB, do the following: (A) Replace any OBV or fuel tube that is leaking and tighten or replace any loose OBV fuel tube clamps with a part eligible for installation before further flight. (B) Replace any worn OBV link rod assembly hardware within 50 flight cycles after the inspection required by paragraphs (g)(1)(i), (ii), or (iii) of this AD. The engine can be returned to service each day for up to the 50 flight cycles if the OBV fittings are inspected each day for fuel leaks and looseness and, if they do not require removal based on the criteria in Table 1, ‘‘OBV Inspection,’’ of GE SB CF34–8C S/B 75–0020, R04, dated May 10, 2019. VerDate Sep<11>2014 15:41 Nov 15, 2019 Jkt 250001 (2) For CF34–8C5B1 model turbofan engines with S/Ns not listed in paragraph (g)(1) of this AD and for all CF34–8C5A2 and CF34–8C5A3 model turbofan engines, perform the following: (i) For engines with 6,000 flight hours or more since new on the effective date of this AD, perform an initial inspection of the OBV bleed air manifold link rod assemblies, OBV fuel fittings, and OBV fuel tubes within 880 flight hours after the effective date of this AD. (ii) For engines with less than 6,000 flight hours since new on the effective date of this AD, perform an initial inspection of the OBV bleed air manifold link rod assemblies, OBV fuel fittings, and OBV fuel tubes within 880 flight hours time in service or 6,880 flight hours since new, whichever occurs later. (iii) Thereafter, repeat the inspection of the OBV bleed air manifold link rod assemblies, OBV fuel fittings, and OBV fuel tubes within 880 flight hours since the last inspection. (iv) Use the Accomplishment Instructions, Paragraph 3.B., of GE CF34–8C S/B 75–0020, R04, dated May 10, 2019, to perform the inspections in paragraphs (g)(2)(i) through (iii) of this AD. (v) Replace any parts according to the criteria in paragraph (g)(1)(iv) of this AD after the inspection required by paragraphs (g)(2)(i), (ii), or (iii) of this AD. (3) For all affected engines, the reporting instructions in GE SB CF34–8C S/B 75–0020, R04, dated May 10, 2019, are not required by this AD. (h) Credit for Previous Actions (1) For engines identified in paragraph (g)(1) of this AD, you may take credit for the inspection of the OBV bleed air manifold link rod assemblies and the OBV fuel fittings required by paragraph (g)(1)(i) of this AD if you performed this inspection before November 30, 2017 (the effective date of AD 2017–23–06) using GE SB CF34–8C SB 75– 0019, Revision 01, dated October 24, 2017, or R00, dated August 4, 2017. (2) For all affected engines, you may take credit for the inspection of the OBV bleed air manifold link rod assemblies and the OBV fuel fittings required by paragraph (g)(1)(i) or (g)(2)(i) of this AD if you performed this inspection before the effective date of this AD using GE SB CF34–8C SB 75–0020, Revision 03, dated December 14, 2018. (3) You are still required to perform the repeat inspections and any replacements, as needed, required by paragraphs (g)(1)(ii) through (g)(1)(iv) of this AD. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, ECO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (j) 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, PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 63571 or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (j) Related Information For more information about this AD, contact Michael Richardson-Bach, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781– 238–7747; fax: 781–238–7199; email: michael.richardson-bach@faa.gov. (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 CF34–8C SB 75–0020, R04, dated May 10, 2019. (ii) [Reserved] (3) For GE service information identified in this AD, contact General Electric Company, GE-Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 45215, phone: 513–552–3272; fax: 513–552–3329; email: geae.aoc@ge.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 at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email: fedreg.legal@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ ibr-locations.html. Issued in Burlington, Massachusetts, on November 6, 2019. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2019–24898 Filed 11–15–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 97 [Docket No. 31281; Amdt. No. 3878] Standard Instrument Approach Procedures, and Takeoff Minimums and Obstacle Departure Procedures; Miscellaneous Amendments Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: This rule amends, suspends, or removes Standard Instrument Approach Procedures (SIAPs) and associated Takeoff Minimums and Obstacle Departure Procedures for SUMMARY: E:\FR\FM\18NOR1.SGM 18NOR1

Agencies

[Federal Register Volume 84, Number 222 (Monday, November 18, 2019)]
[Rules and Regulations]
[Pages 63569-63571]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-24898]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0394; Product Identifier 2017-NE-36-AD; Amendment 
39-19784; AD 2019-22-05]
RIN 2120-AA64


Airworthiness Directives; General Electric Company Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2017-23-
06, for certain General Electric Company (GE) CF34-8C1, CF34-8C5, CF34-
8C5A1, and CF34-8C5B1 engines. AD 2017-23-06 required an inspection of 
the bleed air manifold link rod assemblies and the supply, return, and 
drain fuel fittings on the operability bleed valve (OBV). This AD 
requires repetitive inspections of the OBV fuel tubes, OBV bleed air 
manifold link rod assemblies, and the OBV fuel fittings and replacement 
of OBVs or related hardware that fail inspection. In addition, this AD 
expands the applicability of these inspections to include additional GE 
CF34-8C model turbofan engines. This AD was prompted by multiple engine 
fires that have occurred as a result of malfunctions related to the 
OBV. The FAA is issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective December 23, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 23, 
2019.

ADDRESSES: For service information identified in this final rule, 
contact General Electric Company, GE-Aviation, Room 285, 1 Neumann Way, 
Cincinnati, OH 45215, phone: 513-552-3272; fax: 513-552-3329; email: 
[email protected]. You may view this service information at the FAA, 
Engine and Propeller Standards Branch, 1200 District Avenue, 
Burlington, MA 01803. For information on the availability of this 
material at the FAA, call 781-238-7759. It is also available on the 
internet at https://www.regulations.gov by searching for and locating 
Docket No. FAA-2019-0394.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.govby searching for and locating Docket No. FAA-2019-
0394; 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 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: Michael Richardson-Bach, Aerospace 
Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; 
phone: 781-238-7747; fax: 781-238-7199; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2017-23-06, Amendment 39-19100 (82 FR 
52830, November 15, 2017), (``AD 2017-23-06''). AD 2017-23-06 applied 
to certain GE CF34-8C1, CF34-8C5, CF34-8C5A1, and CF34-8C5B1 engines. 
The NPRM published in the Federal Register on June 28, 2019 (84 FR 
30956). The NPRM was prompted by multiple engine fires that have 
occurred as a result of malfunctions related to the OBV. The NPRM 
proposed to require repetitive inspections of the OBV fuel tubes, OBV 
bleed air manifold link rod assemblies, and the OBV fuel fittings and 
replacement of OBVs or related hardware that fail inspection. In 
addition, the NPRM proposed to expand the applicability of these 
inspections to include additional GE CF34-8C model turbofan engines. 
The FAA is issuing this AD to address the unsafe condition on these 
products.

Comments

    The FAA gave the public the opportunity to participate in 
developing this AD. The following presents the comments received on the 
NPRM and the FAA's response to each comment.

Request To Change the Inspection Intervals

    GE requested that the FAA extend the initial and repetitive 
inspection intervals to 16,000 flight hours (FHs) and 1,680 FHs, 
respectively, for engines equipped with OBV part number (P/N) 
4123T71P05. GE reasoned that based on testing and analysis, OBV P/N 
4123T71P05 is more resistant to wear than OBV P/N 4123T71P04, and 
earlier versions, if the installation support links are regularly 
inspected and maintained.
    The FAA disagrees with extending the inspection intervals for 
engines equipped with OBV P/N 4123T71P05 because the FAA did not find 
GE's test and analysis data sufficient to justify the extended 
inspection intervals. The FAA did not change this AD.

Request To Update the Applicability

    The National Transportation Safety Board (NTSB) supported this AD 
and requested that the FAA consider similar rulemaking to include the 
GE CF34-8E model turbofan engines. The NTSB suggested that the unsafe 
condition exists on this engine and that the FAA should identify the 
higher-risk OBVs and publish an AD that mandates a repetitive 
inspection for the GE CF34-8E OBVs.
    The FAA agrees to consider future rulemaking for the GE CF34-8E 
model turbofan engines because those engines have experienced the same 
unsafe condition addressed by the engine

[[Page 63570]]

models of this AD. The FAA did not change this AD.

Support for the AD

    The Air Line Pilots Association International and an individual 
commenter expressed support for the AD as written.

Conclusion

    The FAA reviewed the relevant data, considered the comments 
received, and determined that air safety and the public interest 
require adopting this AD as proposed except for minor editorial 
changes. The FAA has determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed GE Service Bulletin (SB) CF34-8C S/B 75-0020, R04, 
dated May 10, 2019. The SB describes procedures for inspecting the 
bleed air manifold link rod assemblies; the supply, return, and drain 
fuel fittings; and the fuel tubes on the OBV. 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.

Costs of Compliance

    The FAA estimates that this AD affects 1,297 engines installed on 
airplanes of U.S. registry.
    The FAA estimates the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspection of OBV fuel tubes,           1 work-hour x $85 per                 $0             $85        $110,245
 assemblies, and fittings.               hour = $85.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary 
replacements that would be required based on the results of the 
inspection. The FAA has no way of determining the number of aircraft 
that might need these replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace OBV...................................  2 work-hours x $85 per hour =            $17,230         $17,400
                                                 $170.
Replace OBV support hardware..................  2.25 work-hours x $85 per hour =           3,595        3,786.25
                                                 $191.25.
----------------------------------------------------------------------------------------------------------------

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.
    The FAA is 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

    The FAA has determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Will not affect intrastate aviation in Alaska, and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2017-23-06, Amendment 39-19100 (82 FR 52830, November 15, 2017), and 
adding the following new AD:

2019-22-05 General Electric Company: Amendment 39-19784; Docket No. 
FAA-2019-0394; Product Identifier 2017-NE-36-AD.

(a) Effective Date

    This AD is effective December 23, 2019.

[[Page 63571]]

(b) Affected ADs

    This AD replaces AD 2017-23-06, Amendment 39-19100 (82 FR 52830, 
November 15, 2017).

(c) Applicability

    This AD applies to all General Electric Company (GE) CF34-8C1, 
CF34-8C5, CF34-8C5A1, CF34-8C5B1, CF34-8C5A2, and CF34-8C5A3 model 
turbofan engines.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7531, Compressor 
bleed governor.

(e) Unsafe Condition

    This AD was prompted by multiple engine fires that have occurred 
as a result of malfunctions related to the operability bleed valve 
(OBV). The FAA is issuing this AD to prevent failure of the OBV. 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 CF34-8C1, CF34-8C5, CF34-8C5A1, and CF34-8C5B1 model 
turbofan engines with serial numbers (S/Ns): 965101 through 965670 
inclusive; 194101 through 194999 inclusive; and 195101 through 
195653 inclusive:
    (i) Perform an inspection of the OBV bleed air manifold link rod 
assemblies and the OBV fuel fittings within 500 flight hours after 
November 30, 2017 (effective date of AD 2017-23-06), or before next 
flight after the effective date of this AD, whichever occurs later.
    (ii) Within 880 flight hours since the previous inspection, 500 
flight hours from the effective date of this AD, or 6,880 flight 
hours since new, whichever occurs later, inspect the OBV bleed air 
manifold link rod assemblies, the OBV fuel fittings, and the OBV 
fuel tubes.
    (iii) Thereafter, perform additional repeat inspections of the 
OBV bleed air manifold link rod assemblies, the OBV fuel fittings, 
and the OBV fuel tubes within every 880 flight hours since the 
previous inspection.
    (iv) Use the Accomplishment Instructions, Paragraph 3.B., of GE 
CF34-8C S/B 75-0020, R04, dated May 10, 2019 (``the SB''), to 
perform the inspections in paragraphs (g)(1)(i) through (iii) of 
this AD and, per the criteria for the results of inspections in 
Paragraph 3.B. of the SB, do the following:
    (A) Replace any OBV or fuel tube that is leaking and tighten or 
replace any loose OBV fuel tube clamps with a part eligible for 
installation before further flight.
    (B) Replace any worn OBV link rod assembly hardware within 50 
flight cycles after the inspection required by paragraphs (g)(1)(i), 
(ii), or (iii) of this AD. The engine can be returned to service 
each day for up to the 50 flight cycles if the OBV fittings are 
inspected each day for fuel leaks and looseness and, if they do not 
require removal based on the criteria in Table 1, ``OBV 
Inspection,'' of GE SB CF34-8C S/B 75-0020, R04, dated May 10, 2019.
    (2) For CF34-8C5B1 model turbofan engines with S/Ns not listed 
in paragraph (g)(1) of this AD and for all CF34-8C5A2 and CF34-8C5A3 
model turbofan engines, perform the following:
    (i) For engines with 6,000 flight hours or more since new on the 
effective date of this AD, perform an initial inspection of the OBV 
bleed air manifold link rod assemblies, OBV fuel fittings, and OBV 
fuel tubes within 880 flight hours after the effective date of this 
AD.
    (ii) For engines with less than 6,000 flight hours since new on 
the effective date of this AD, perform an initial inspection of the 
OBV bleed air manifold link rod assemblies, OBV fuel fittings, and 
OBV fuel tubes within 880 flight hours time in service or 6,880 
flight hours since new, whichever occurs later.
    (iii) Thereafter, repeat the inspection of the OBV bleed air 
manifold link rod assemblies, OBV fuel fittings, and OBV fuel tubes 
within 880 flight hours since the last inspection.
    (iv) Use the Accomplishment Instructions, Paragraph 3.B., of GE 
CF34-8C S/B 75-0020, R04, dated May 10, 2019, to perform the 
inspections in paragraphs (g)(2)(i) through (iii) of this AD.
    (v) Replace any parts according to the criteria in paragraph 
(g)(1)(iv) of this AD after the inspection required by paragraphs 
(g)(2)(i), (ii), or (iii) of this AD.
    (3) For all affected engines, the reporting instructions in GE 
SB CF34-8C S/B 75-0020, R04, dated May 10, 2019, are not required by 
this AD.

(h) Credit for Previous Actions

    (1) For engines identified in paragraph (g)(1) of this AD, you 
may take credit for the inspection of the OBV bleed air manifold 
link rod assemblies and the OBV fuel fittings required by paragraph 
(g)(1)(i) of this AD if you performed this inspection before 
November 30, 2017 (the effective date of AD 2017-23-06) using GE SB 
CF34-8C SB 75-0019, Revision 01, dated October 24, 2017, or R00, 
dated August 4, 2017.
    (2) For all affected engines, you may take credit for the 
inspection of the OBV bleed air manifold link rod assemblies and the 
OBV fuel fittings required by paragraph (g)(1)(i) or (g)(2)(i) of 
this AD if you performed this inspection before the effective date 
of this AD using GE SB CF34-8C SB 75-0020, Revision 03, dated 
December 14, 2018.
    (3) You are still required to perform the repeat inspections and 
any replacements, as needed, required by paragraphs (g)(1)(ii) 
through (g)(1)(iv) of this AD.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, ECO Branch, FAA, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19. In accordance with 14 CFR 39.19, send your request to your 
principal inspector or local Flight Standards District Office, as 
appropriate. If sending information directly to the manager of the 
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 Michael Richardson-
Bach, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: 781-238-7747; fax: 781-238-7199; email: 
[email protected].

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) General Electric Company (GE) Service Bulletin CF34-8C SB 
75-0020, R04, dated May 10, 2019.
    (ii) [Reserved]
    (3) For GE service information identified in this AD, contact 
General Electric Company, GE-Aviation, Room 285, 1 Neumann Way, 
Cincinnati, OH 45215, phone: 513-552-3272; fax: 513-552-3329; email: 
[email protected].
    (4) You may view this service information at FAA, Engine and 
Propeller Standards Branch, 1200 District Avenue, Burlington, MA 
01803. For information on the availability of this material at the 
FAA, call 781-238-7759.
    (5) You may view this service information at the National 
Archives and Records Administration (NARA). For information on the 
availability of this material at NARA, email: [email protected], 
or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on November 6, 2019.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2019-24898 Filed 11-15-19; 8:45 am]
 BILLING CODE 4910-13-P