Airworthiness Directives; General Electric Company Turbofan Engines, 30956-30958 [2019-13761]

Download as PDF 30956 Proposed Rules Federal Register Vol. 84, No. 125 Friday, June 28, 2019 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0394; Product Identifier 2017–NE–36–AD] RIN 2120–AA64 Airworthiness Directives; General Electric Company Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to supersede Airworthiness Directive (AD) 2017–23–06, which applies to certain General Electric Company (GE) CF34– 8C1, CF34–8C5, CF34–8C5A1, and CF34–8C5B1 engines. AD 2017–23–06 requires an inspection of the bleed air manifold link rod assemblies and the supply, return, and drain fuel fittings on the operability bleed valve (OBV). Since the FAA issued AD 2017–23–06, the manufacturer developed improved inspection techniques and determined these inspections should be applied to additional engine models. This proposed AD would 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. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by August 12, 2019. SUMMARY: 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 https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– khammond on DSKBBV9HB2PROD with PROPOSALS ADDRESSES: VerDate Sep<11>2014 16:43 Jun 27, 2019 Jkt 247001 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, 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. For information on the availability of this material at the FAA, call 781–238–7125. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by 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 NPRM, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations is listed above. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Michael Richardson-Bach, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781–238–7747; fax: 781–238– 7199; email: michael.richardson-bach@ faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited The FAA invites 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–2019–0394; Product Identifier 2017–NE–36–AD’’ at the beginning of your comments. The FAA specifically invites comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. The FAA will consider all comments received by the closing date and may amend this NPRM because of those comments. The FAA will post all comments, without change, to https:// PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 www.regulations.gov, including any personal information you provide. The FAA will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The FAA issued AD 2017–23–06, Amendment 39–19100 (82 FR 52830, November 15, 2017), (‘‘AD 2017–23– 06’’), for certain General Electric Company (GE) CF34–8C1, CF34–8C5, CF34–8C5A1, and CF34–8C5B1 engines. AD 2017–23–06 requires an inspection of the bleed air manifold link rod assemblies and the supply, return, and drain fuel fittings on the OBV. AD 2017–23–06 resulted from reports that significant fuel leaks, some resulting in engine fires, occurred on multiple occasions due to malfunctions related to the OBVs. The FAA issued AD 2017– 23–06 to address the unsafe condition on these products. Actions Since AD 2017–23–06 Was Issued Since the FAA issued AD 2017–23– 06, the manufacturer has developed improved inspections of the OBV bleed air manifold link rod assemblies and OBV fuel fittings, added an inspection of the OBV fuel tubes, and determined that these inspections should be applied to additional engine models. GE published these improved inspections in GE Service Bulletin (SB) CF34–8C– AL S/B 75–0020, R04, dated May 10, 2019. Related Service Information Under 1 CFR Part 51 The FAA reviewed GE SB CF34–8C– AL 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. FAA’s Determination The FAA is 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. E:\FR\FM\28JNP1.SGM 28JNP1 30957 Federal Register / Vol. 84, No. 125 / Friday, June 28, 2019 / Proposed Rules Proposed AD Requirements This proposed AD would retain all the requirements of AD 2017–23–06. This proposed AD would revise the inspections of the OBV bleed air manifold link rod assemblies and OBV fuel fittings and require inspections of the OBV fuel tubes. In addition, this proposed AD would expand the applicability of these inspections to include additional GE CF34–8C model turbofan engines. Interim Action The FAA considers this proposed AD interim action. The FAA will consider further rulemaking based on the continued investigation and development of corrective action by the manufacturer. Costs of Compliance The FAA estimates that this proposed AD affects 1,297 engines installed on airplanes of U.S. registry. The FAA estimates the following costs to comply with this proposed 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 Cost per product Parts cost results of the proposed inspection. The FAA has no way of determining the $0 Cost on U.S. operators $85 $110,245 number of 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 ................. khammond on DSKBBV9HB2PROD with PROPOSALS 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, VerDate Sep<11>2014 16:43 Jun 27, 2019 Jkt 247001 Parts cost Cost per product $17,230 3,595 Engine and Propeller Standards Branch, Policy and Innovation Division. PART 39—AIRWORTHINESS DIRECTIVES Regulatory Findings ■ The FAA has determined that this proposed AD would not have federalism 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) 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. $17,400 3,786.25 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: ■ General Electric Company: Docket No. FAA– 2019–0394; Product Identifier 2017–NE– 36–AD. (a) Comments Due Date The FAA must receive comments on this AD action by August 12, 2019. (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. The Proposed Amendment (d) Subject Joint Aircraft System Component (JASC) Code 7531, Compressor bleed governor. Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: (e) Unsafe Condition This AD was prompted by multiple engine fires that have occurred as a result of malfunctions related to the operability bleed PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 E:\FR\FM\28JNP1.SGM 28JNP1 30958 Federal Register / Vol. 84, No. 125 / Friday, June 28, 2019 / Proposed Rules 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. khammond on DSKBBV9HB2PROD with PROPOSALS (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–AL 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), (g)(1)(ii), or (g)(1)(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–AL 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 flights 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. VerDate Sep<11>2014 16:43 Jun 27, 2019 Jkt 247001 (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–AL 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), (g)(2)(ii), or (g)(2)(iii) of this AD. (3) For all affected engines, the reporting instructions in GE SB CF34–8C–AL 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, 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 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. (2) For 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. You may view this service information at the FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 MA. For information on the availability of this material at the FAA, call 781–238–7125. Issued in Burlington, Massachusetts, on June 24, 2019. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2019–13761 Filed 6–27–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0438; Product Identifier 2019–NM–033–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for all The Boeing Company Model 757 airplanes. This proposed AD was prompted by a report that during a maintenance check an operator discovered cracking in the station 1460 frame web and inner chord between certain stringers. This proposed AD would require an inspection of the fuselage frames for any existing repair, repetitive surface high frequency eddy current (HFEC) inspections of the fuselage frames with a cargo liner support channel for any cracking, and applicable on-condition actions. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by August 12, 2019. SUMMARY: 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 https://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 Boeing Commercial ADDRESSES: E:\FR\FM\28JNP1.SGM 28JNP1

Agencies

[Federal Register Volume 84, Number 125 (Friday, June 28, 2019)]
[Proposed Rules]
[Pages 30956-30958]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-13761]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 84, No. 125 / Friday, June 28, 2019 / 
Proposed Rules

[[Page 30956]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0394; Product Identifier 2017-NE-36-AD]
RIN 2120-AA64


Airworthiness Directives; General Electric Company Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 
2017-23-06, which applies to certain General Electric Company (GE) 
CF34-8C1, CF34-8C5, CF34-8C5A1, and CF34-8C5B1 engines. AD 2017-23-06 
requires an inspection of the bleed air manifold link rod assemblies 
and the supply, return, and drain fuel fittings on the operability 
bleed valve (OBV). Since the FAA issued AD 2017-23-06, the manufacturer 
developed improved inspection techniques and determined these 
inspections should be applied to additional engine models. This 
proposed AD would 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. The 
FAA is proposing this AD to address the unsafe condition on these 
products.

DATES: The FAA must receive comments on this proposed AD by August 12, 
2019.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://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, 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. For information 
on the availability of this material at the FAA, call 781-238-7125.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by 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 NPRM, the regulatory evaluation, any comments received, and other 
information. The street address for Docket Operations is listed above. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Michael Richardson-Bach, Aerospace 
Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; 
phone: 781-238-7747; fax: 781-238-7199; email: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites 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-2019-0394; 
Product Identifier 2017-NE-36-AD'' at the beginning of your comments. 
The FAA specifically invites comments on the overall regulatory, 
economic, environmental, and energy aspects of this NPRM. The FAA will 
consider all comments received by the closing date and may amend this 
NPRM because of those comments.
    The FAA will post all comments, without change, to https://www.regulations.gov, including any personal information you provide. 
The FAA will also post a report summarizing each substantive verbal 
contact we receive about this proposed AD.

Discussion

    The FAA issued AD 2017-23-06, Amendment 39-19100 (82 FR 52830, 
November 15, 2017), (``AD 2017-23-06''), for certain General Electric 
Company (GE) CF34-8C1, CF34-8C5, CF34-8C5A1, and CF34-8C5B1 engines. AD 
2017-23-06 requires an inspection of the bleed air manifold link rod 
assemblies and the supply, return, and drain fuel fittings on the OBV. 
AD 2017-23-06 resulted from reports that significant fuel leaks, some 
resulting in engine fires, occurred on multiple occasions due to 
malfunctions related to the OBVs. The FAA issued AD 2017-23-06 to 
address the unsafe condition on these products.

Actions Since AD 2017-23-06 Was Issued

    Since the FAA issued AD 2017-23-06, the manufacturer has developed 
improved inspections of the OBV bleed air manifold link rod assemblies 
and OBV fuel fittings, added an inspection of the OBV fuel tubes, and 
determined that these inspections should be applied to additional 
engine models. GE published these improved inspections in GE Service 
Bulletin (SB) CF34-8C-AL S/B 75-0020, R04, dated May 10, 2019.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed GE SB CF34-8C-AL 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.

FAA's Determination

    The FAA is 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.

[[Page 30957]]

Proposed AD Requirements

    This proposed AD would retain all the requirements of AD 2017-23-
06. This proposed AD would revise the inspections of the OBV bleed air 
manifold link rod assemblies and OBV fuel fittings and require 
inspections of the OBV fuel tubes. In addition, this proposed AD would 
expand the applicability of these inspections to include additional GE 
CF34-8C model turbofan engines.

Interim Action

    The FAA considers this proposed AD interim action. The FAA will 
consider further rulemaking based on the continued investigation and 
development of corrective action by the manufacturer.

Costs of Compliance

    The FAA estimates that this proposed AD affects 1,297 engines 
installed on airplanes of U.S. registry.
    The FAA estimates the following costs to comply with this proposed 
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 
proposed 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 proposed AD would not have 
federalism 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) 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.

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) 
2017-23-06, Amendment 39-19100 (82 FR 52830, November 15, 2017), and 
adding the following new AD:

General Electric Company: Docket No. FAA-2019-0394; Product 
Identifier 2017-NE-36-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by August 12, 
2019.

(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

[[Page 30958]]

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-AL 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), 
(g)(1)(ii), or (g)(1)(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-AL 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 flights 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-AL 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), (g)(2)(ii), or (g)(2)(iii) of this AD.
    (3) For all affected engines, the reporting instructions in GE 
SB CF34-8C-AL 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

    (1) 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].
    (2) For 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]. 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 781-238-7125.

    Issued in Burlington, Massachusetts, on June 24, 2019.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2019-13761 Filed 6-27-19; 8:45 am]
BILLING CODE 4910-13-P

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