Airworthiness Directives; General Electric Company Turbofan Engines, 52830-52832 [2017-24700]

Download as PDF 52830 Federal Register / Vol. 82, No. 219 / Wednesday, November 15, 2017 / Rules and Regulations March 31, 2017; or Rockwell Collins Service Information Letter TSSA–4100–SIL–10–1, Revision No. 10, dated July 10, 2017. (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, Wichita ACO 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 ACO, send it to the attention of the person identified in paragraph (i) of this AD. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (i) Related Information For more information about this AD, contact Paul Rau, Aerospace Engineer, Wichita ACO, FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209; phone: 316–946–4149; fax: 316–946–4107; email: paul.rau@faa.gov. sradovich on DSK3GMQ082PROD with RULES (j) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Rockwell Collins Service Information Letter, TSSA–4100–SIL–10–1, Revision No. 9, dated March 31, 2017. (ii) Rockwell Collins Service Information Letter, TSSA–4100–SIL–10–1, Revision No. 10, dated July 10, 2017. (3) For service information identified in this AD, contact Rockwell Collins, Inc., Collins Aviation Services, 400 Collins Road NE., M/S 164–100, Cedar Rapids, IA 52498– 0001; telephone: 888–265–5467 (U.S.) or 319–265–5467; fax: 319–295–4941 (outside U.S.); email: techmanuals@ rockwellcollins.com; Internet: https:// portal.rockwellcollins.com/web/publicationsand-training. (4) You may view this service information at FAA, Policy and Innovation Division, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. It is also available on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017–0659. (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: Issued in Kansas City, Missouri, on October 26, 2017. Pat Mullen, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–24066 Filed 11–14–17; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 15:48 Nov 14, 2017 Jkt 244001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Examining the AD Docket [Docket No. FAA–2017–1000; Product Identifier 2017–NE–36–AD; Amendment 39– 19100; AD 2017–23–06] RIN 2120–AA64 Airworthiness Directives; General Electric Company Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for certain General Electric Company (GE) CF34– 8C1, CF34–8C5, CF34–8C5A1, and CF34–8C5B1 engines. This AD 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). This AD was prompted by an engine fire that occurred as a result of malfunctions related to the OBV. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective November 30, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 30, 2017. We must receive comments on this AD by January 2, 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; fax: 513–552– 3329; email: geae.aoc@ge.com. You may view this service information at the FAA, Engine and Propeller Standards SUMMARY: PO 00000 Frm 00008 Fmt 4700 Branch, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. Sfmt 4700 You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 1000; or in person at the Docket Management Facility 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 Office (phone: 800–647– 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: John Frost, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781–238–7756; fax: 781–238–7199; email: john.frost@ faa.gov. SUPPLEMENTARY INFORMATION: Discussion We learned that significant fuel leaks, some resulting in engine fires, have occurred on multiple occasions due to malfunctions related to the OBVs. These valves typically dump operability air into the bleed plenum attached to the engine inner nacelle. The fuel fitting threads have pulled out of the valve body which has led to significant fuel leaks on at least four occasions. On two occasions, these leaks resulted in uncontrolled fires, resulting in significant damage to one of the affected airplanes. This condition, if not corrected, could result in failure of the OBV, engine fire, and damage to the airplane. We are issuing this AD to correct the unsafe condition on these products. Related Service Information Under 1 CFR Part 51 We reviewed GE Service Bulletin (SB) CF34–8C–AL S/B 75–0019, Revision 01, dated October 24, 2017. The SB describes procedures for inspecting 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. Other Related Service Information We reviewed GE CF34–8C SB 75– 0019 R00, dated August 4, 2017. The SB describes procedures for inspecting the OBV. E:\FR\FM\15NOR1.SGM 15NOR1 Federal Register / Vol. 82, No. 219 / Wednesday, November 15, 2017 / Rules and Regulations FAA’s Determination We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. AD Requirements This AD requires inspection of the bleed air manifold link rod assemblies and the supply, return, and drain fuel fittings on the OBVs. Interim Action We consider this AD interim action. We will consider further rulemaking action depending on the results of the investigation. 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 52831 section. Include the docket number FAA–2017–1000 and Product Identifier 2017–NE–36–AD at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this final rule. We will consider all comments received by the closing date and may amend this final rule because of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this final rule. Costs of Compliance We estimate that this AD affects 1,282 engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Labor cost Inspection of OBV fittings ............................... sradovich on DSK3GMQ082PROD with RULES Action 1 work-hour × $85 per hour = $85 ................. 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 VerDate Sep<11>2014 15:48 Nov 14, 2017 Jkt 244001 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. PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 Cost per product Parts cost $0 Cost on U.S. operators $85 $108,970 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 adding the following new airworthiness directive (AD): ■ 2017–23–06 General Electric Company: Amendment 39–19100; Docket No. FAA–2017–1000; Product Identifier 2017–NE–36–AD. (a) Effective Date This AD is effective November 30, 2017. (b) Affected ADs None. (c) Applicability This AD applies to General Electric Company (GE) CF34–8C1, CF34–8C5, CF34– 8C5A1, and CF34–8C5B1 engines with serial numbers: 965101 through 965670 inclusive; 194101 through 194999 inclusive; and 195101 through 195653 inclusive. E:\FR\FM\15NOR1.SGM 15NOR1 52832 Federal Register / Vol. 82, No. 219 / Wednesday, November 15, 2017 / Rules and Regulations (d) Subject Joint Aircraft System Component (JASC) Code 7531, Compressor bleed governor. Burlington, MA 01803; phone: 781–238– 7754; fax: 781–238–7199; email: john.frost@ faa.gov. (e) Unsafe Condition This AD was prompted by an engine fire that occurred as a result of malfunctions related to the operability bleed valve (OBV). We are issuing this AD to prevent failure of the OBV. The unsafe condition, if not corrected, could result in failure of the OBV, engine fire, and damage to the airplane. (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–AL S/B 75–0019 Revision 01, dated October 24, 2017. (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, FAA, Engine & Propeller Standards Branch, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions (1) Inspect the bleed air manifold link rod assemblies and the OBV supply, return, and drain fuel fittings within 500 flight hours after the effective date of this AD. (2) Use the Accomplishment Instructions, paragraph 3.B., in GE Service Bulletin (SB) CF34–8C–AL S/B 75–0019 Revision 01, dated October 24, 2017, to do the inspection. Replace parts that fail this inspection according to the following criteria: (i) Replace any OBV that fails the inspection with a part eligible for installation before further flight. (ii) Replace any additional hardware that fails inspection within 50 flight cycles. The engine can be returned to service each day for up to the 50 flight cycles if the OBV rosan rings and fittings are examined each day for fuel leaks and looseness based on the criteria in Table 1 of GE SB CF34–8C–AL S/B 75– 0019 Revision 01, dated October 24, 2017. (3) The reporting instructions in paragraphs 3.B.(3), 3.B.(5)(e), 3.B.(6)(e), and 3.B.(8) of GE SB CF34–8C–AL S/B 75–0019 Revision 01, dated October 24, 2017, are not required by this AD. sradovich on DSK3GMQ082PROD with RULES (h) Credit for Previous Actions You may take credit for the actions that are required by paragraph (g) of this AD if you performed these actions before the effective date of this AD using GE CF34–8C SB 75– 0019 R00, dated August 4, 2017. (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 For more information about this AD, contact John Frost, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, VerDate Sep<11>2014 15:48 Nov 14, 2017 Jkt 244001 Issued in Burlington, Massachusetts, on November 9, 2017. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2017–24700 Filed 11–14–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0710; Product Identifier 2017–NM–019–AD; Amendment 39–19098; AD 2017–23–04] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4–600R series airplanes; Model A300 B4–603, B4–620, and B4–622 airplanes; Model A300 C4– 605R Variant F airplanes; and Model A300 F4–605R airplanes. This AD was prompted by a determination that the top stringer joints at rib 18 are an area of uniform stress distribution, which SUMMARY: PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 indicates that cracks may develop in adjacent stringers at the same time. This AD requires an inspection of the upper wing skin and top stringer joints, and modification of the stringer joint couplings if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective December 20, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 20, 2017. ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office— EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet http:// www.airbus.com. You may view this referenced service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2017– 0710. 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–2017– 0710; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647– 5527) is Docket Management Facility, 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: Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; fax 425–227– 1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Airbus Model A300 B4– 600R series airplanes; Model A300 B4– 603, B4–620, and B4–622 airplanes; E:\FR\FM\15NOR1.SGM 15NOR1

Agencies

[Federal Register Volume 82, Number 219 (Wednesday, November 15, 2017)]
[Rules and Regulations]
[Pages 52830-52832]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-24700]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-1000; Product Identifier 2017-NE-36-AD; Amendment 
39-19100; AD 2017-23-06]
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) CF34-8C1, CF34-8C5, CF34-8C5A1, and CF34-
8C5B1 engines. This AD 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). This AD was prompted by an engine 
fire that occurred as a result of malfunctions related to the OBV. We 
are issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective November 30, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of November 30, 
2017.
    We must receive comments on this AD by January 2, 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; 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 http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
1000; or in person at the Docket Management Facility 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 
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: John Frost, Aerospace Engineer, ECO 
Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-
238-7756; fax: 781-238-7199; email: john.frost@faa.gov.

SUPPLEMENTARY INFORMATION: 

Discussion

    We learned that significant fuel leaks, some resulting in engine 
fires, have occurred on multiple occasions due to malfunctions related 
to the OBVs. These valves typically dump operability air into the bleed 
plenum attached to the engine inner nacelle. The fuel fitting threads 
have pulled out of the valve body which has led to significant fuel 
leaks on at least four occasions. On two occasions, these leaks 
resulted in uncontrolled fires, resulting in significant damage to one 
of the affected airplanes. This condition, if not corrected, could 
result in failure of the OBV, engine fire, and damage to the airplane. 
We are issuing this AD to correct the unsafe condition on these 
products.

Related Service Information Under 1 CFR Part 51

    We reviewed GE Service Bulletin (SB) CF34-8C-AL S/B 75-0019, 
Revision 01, dated October 24, 2017. The SB describes procedures for 
inspecting 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.

Other Related Service Information

    We reviewed GE CF34-8C SB 75-0019 R00, dated August 4, 2017. The SB 
describes procedures for inspecting the OBV.

[[Page 52831]]

FAA's Determination

    We are issuing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

AD Requirements

    This AD requires inspection of the bleed air manifold link rod 
assemblies and the supply, return, and drain fuel fittings on the OBVs.

Interim Action

    We consider this AD interim action. We will consider further 
rulemaking action depending on the results of the investigation.

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-2017-
1000 and Product Identifier 2017-NE-36-AD at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this final rule. We will 
consider all comments received by the closing date and may amend this 
final rule because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this final rule.

Costs of Compliance

    We estimate that this AD affects 1,282 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
----------------------------------------------------------------------------------------------------------------
Inspection of OBV fittings.........  1 work-hour x $85 per hour               $0             $85        $108,970
                                      = $85.
----------------------------------------------------------------------------------------------------------------

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):

2017-23-06 General Electric Company: Amendment 39-19100; Docket No. 
FAA-2017-1000; Product Identifier 2017-NE-36-AD.

(a) Effective Date

    This AD is effective November 30, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to General Electric Company (GE) CF34-8C1, CF34-
8C5, CF34-8C5A1, and CF34-8C5B1 engines with serial numbers: 965101 
through 965670 inclusive; 194101 through 194999 inclusive; and 
195101 through 195653 inclusive.

[[Page 52832]]

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by an engine fire that occurred as a result 
of malfunctions related to the operability bleed valve (OBV). We are 
issuing this AD to prevent failure of the OBV. The unsafe condition, 
if not corrected, could result in failure of the OBV, 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) Inspect the bleed air manifold link rod assemblies and the 
OBV supply, return, and drain fuel fittings within 500 flight hours 
after the effective date of this AD.
    (2) Use the Accomplishment Instructions, paragraph 3.B., in GE 
Service Bulletin (SB) CF34-8C-AL S/B 75-0019 Revision 01, dated 
October 24, 2017, to do the inspection. Replace parts that fail this 
inspection according to the following criteria:
    (i) Replace any OBV that fails the inspection with a part 
eligible for installation before further flight.
    (ii) Replace any additional hardware that fails inspection 
within 50 flight cycles. The engine can be returned to service each 
day for up to the 50 flight cycles if the OBV rosan rings and 
fittings are examined each day for fuel leaks and looseness based on 
the criteria in Table 1 of GE SB CF34-8C-AL S/B 75-0019 Revision 01, 
dated October 24, 2017.
    (3) The reporting instructions in paragraphs 3.B.(3), 
3.B.(5)(e), 3.B.(6)(e), and 3.B.(8) of GE SB CF34-8C-AL S/B 75-0019 
Revision 01, dated October 24, 2017, are not required by this AD.

(h) Credit for Previous Actions

    You may take credit for the actions that are required by 
paragraph (g) of this AD if you performed these actions before the 
effective date of this AD using GE CF34-8C SB 75-0019 R00, dated 
August 4, 2017.

(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

    For more information about this AD, contact John Frost, 
Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: 781-238-7754; fax: 781-238-7199; email: 
john.frost@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-AL S/
B 75-0019 Revision 01, dated October 24, 2017.
    (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, FAA, Engine & 
Propeller Standards Branch, 1200 District Avenue, Burlington, MA. 
For information on the availability of this material at the FAA, 
call 781-238-7125.
    (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 November 9, 2017.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2017-24700 Filed 11-14-17; 8:45 am]
 BILLING CODE 4910-13-P