Airworthiness Directives; General Electric Company CF34-8E Engines, 16794-16796 [2018-07819]

Download as PDF 16794 Federal Register / Vol. 83, No. 74 / Tuesday, April 17, 2018 / Proposed Rules (b) Affected ADs This AD replaces AD 2016–13–06, Amendment 39–18570 (81 FR 41432, June 27, 2016) (‘‘AD 2016–13–06’’). (c) Applicability This AD applies to Saab AB, Saab Aeronautics (formerly known as Saab AB, Saab Aerosystems) airplanes, certificated in any category, identified in paragraphs (c)(1) and (c)(2), of this AD. (1) Saab AB, Saab Aeronautics Model 340A (SAAB/SF340A) airplanes, serial numbers 004 through 138 inclusive, if Saab modification 1462 has been embodied in production, or Saab Service Bulletin 340–55– 008 has been embodied in service, except those that have also embodied Saab modification 1793 in production, or Saab Service Bulletin 340–55–010 in service; and serial numbers 139 through 159 inclusive. (2) Saab AB, Saab Aeronautics Model SAAB 340B airplanes, serial numbers 160 through 459 inclusive. (d) Subject Air Transport Association (ATA) of America Code 30, Ice and rain protection. (e) Reason This AD was prompted by reports of ruptured horizontal stabilizer de-icing boots. We are issuing this AD to detect and correct ruptured horizontal stabilizer de-icing boots, which could lead to complete loss of the deicing function within its associated zone and severe vibrations, possibly resulting in reduced control of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. amozie on DSK30RV082PROD with PROPOSALS (g) Retained Revision of the Airplane Flight Manual (AFM), With No Changes This paragraph restates the requirements of paragraph (g) of AD 2016–13–06, with no changes. Within 30 days after August 1, 2016 (the effective date of AD 2016–13–06), revise the ‘‘Abnormal Procedures’’ section of the applicable Saab 340 AFM to incorporate the revision specified in paragraphs (g)(1) through (g)(3) of this AD. (1) For Saab AB, Saab Aeronautics Model 340A (SAAB/SF340A) airplanes, revise AFM 340A 001 by incorporating Revision 57, dated March 27, 2015. (2) For Saab AB, Saab Aeronautics Model SAAB 340B airplanes, revise AFM 340B 001 by incorporating Revision 35, dated March 27, 2015. (3) For Saab AB, Saab Aeronautics Model SAAB 340B airplanes with extended wing tips, revise AFM 340B 010 by incorporating Revision 28, dated March 27, 2015. (h) Retained Inspection/Replacement, With No Changes This paragraph restates the requirements of paragraph (h) of AD 2016–13–06, with no changes. Within 400 flight hours or 6 months, whichever occurs first after August 1, 2016 (the effective date of AD 2016–13– 06), do a detailed inspection for damage of the horizontal stabilizer de-icing boots, and existing repairs of horizontal stabilizer de- VerDate Sep<11>2014 17:36 Apr 16, 2018 Jkt 244001 icing boots, in accordance with the Accomplishment Instructions of Saab Service Bulletin 340–30–094, dated March 27, 2015. Repeat the inspection thereafter at intervals not to exceed 400 flight hours. If, during any inspection required by this paragraph, any damage or existing repair outside the limits specified in Saab Service Bulletin 340–30– 094, dated March 27, 2015, is found, before further flight, repair or replace the horizontal stabilizer de-icing boots, in accordance with the Accomplishment Instructions of Saab Service Bulletin 340–30–094, dated March 27, 2015. Repair or replacement on an airplane of the horizontal stabilizer de-icing boots, as required by this paragraph, does not constitute terminating action for the repetitive inspections required by this paragraph for that airplane. (i) New Requirement of This AD: Modification Within 18 months after the effective date of this AD, modify the airplane by replacing the single stitched de-icing boots installed on the left-hand (LH) and right-hand (RH) horizontal stabilizers with double stitched de-icing boots and re-identify the LH and RH horizontal stabilizer leading edge, in accordance with the Accomplishment Instructions of Saab Service Bulletin 340–30– 095, dated April 3, 2017. (j) Terminating Action Modification of the airplane as required by paragraph (i) of this AD, constitutes terminating action for the repetitive inspections required by paragraph (h) of this AD, for that airplane. (k) Other FAA AD Provisions (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards 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 International Section, send it to the attention of the person identified in paragraph (l)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. 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. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Saab AB, Saab Aeronautics EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOAauthorized signature. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017–0144, dated August 9, 2017, for related PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 information. This MCAI may be found in the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2018–0271. (2) For more information about this AD, contact Shahram Daneshmandi, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax: 206–231–3220. (3) For service information identified in this AD, contact Saab AB, Saab Aeronautics, ¨ SE–581 88, Linkoping, Sweden; telephone: +46 13 18 5591; fax: +46 13 18 4874; email: saab340techsupport@saabgroup.com; internet: https://www.saabgroup.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. Issued in Des Moines, Washington, on March 30, 2018. Chris Spangenberg, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–07636 Filed 4–16–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0142; Product Identifier 2018–NE–04–AD] RIN 2120–AA64 Airworthiness Directives; General Electric Company CF34–8E Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all General Electric Company (GE) CF34–8E turbofan engines. This proposed AD was prompted by a report from GE regarding a quality escape of nonconforming thrust reverser fire seals. This proposed AD would require a one-time inspection of the gap between the core cowl seal and the pylon seal of the thrust reverser for correct gap width, and replacement of the seals, if needed. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by June 1, 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 https://www.regulations.gov. Follow the instructions for submitting comments. SUMMARY: E:\FR\FM\17APP1.SGM 17APP1 16795 Federal Register / Vol. 83, No. 74 / Tuesday, April 17, 2018 / Proposed Rules • 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, 1 Neumann Way, Cincinnati, OH 45215; telephone 513–552–3272; email aviation.fleetsupport@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. 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–2018– 0142; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this NPRM, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations (phone: 800–647–5527) is listed above. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: David Bethka, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781– 238–7129; fax: 781–238–7199; email: david.bethka@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2018–0142; Product Identifier 2018– NE–04–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this NPRM. Discussion We received a report from the manufacturer about a fire seal gap quality escape on GE CF34–8E turbofan engines. Some thrust reverser fire seals, installed on thrust reverser part numbers (P/Ns) 15G0002–013, 15G0002–014, 15G0003–013, and 15G0003–014, were shipped from a supplier with nonconforming seal gaps. An analysis by the manufacturer has shown that a gap between the 12 o’clock core cowl seal and pylon seal that is greater than the 1 mm design requirement could result in fire outside the fire zone. This unsafe condition, if not addressed, could result in an uncontrolled fire, damage to the engine, and damage to the airplane. Related Service Information We reviewed GE CF34–8E Service Bulletin (SB) 78–0066 R00, dated December 11, 2017. The SB describes procedures for measuring the width of the RTV filled gap between the thrust reverser fire seals at the 12 o’clock core cowl seal and pylon seal installed on thrust reverser P/Ns 15G0002–013, 15G0002–014, 15G0003–013, and 15G0003–014, and replacing with parts eligible for installation, if needed. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require a one-time inspection of the gap between the core cowl seal and the pylon seal of the thrust reverser for correct gap width, and replacement of the thrust reverser fire seals, if needed. Costs of Compliance We estimate that this proposed AD affects 936 engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Inspection ................................ 0.25 work-hours × $85 per hour = $21.25 ............................. We estimate the following costs to do any necessary replacements that would Cost per product Parts cost be required based on the results of the proposed inspection. We have no way of $0 $21.25 Cost on U.S. operators $19,890 determining the number of aircraft that might need these replacements: ON-CONDITION COSTS Labor cost Remove and replace thrust reverser fire seals ............ amozie on DSK30RV082PROD with PROPOSALS Action 2.75 work-hours × $85 per hour = $233.75 ................. 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 VerDate Sep<11>2014 17:36 Apr 16, 2018 Jkt 244001 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 PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 Parts cost $3,228 Cost per product $3,461.75 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 E:\FR\FM\17APP1.SGM 17APP1 16796 Federal Register / Vol. 83, No. 74 / Tuesday, April 17, 2018 / Proposed Rules products identified in this rulemaking action. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to engines, propellers, and associated appliances to the Manager, Engine and Propeller Standards Branch, Policy and Innovation Division. Regulatory Findings We 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 this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ amozie on DSK30RV082PROD with PROPOSALS 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): ■ General Electric Company: Docket No. FAA– 2018–0142; Product Identifier 2018–NE– 04–AD. VerDate Sep<11>2014 17:36 Apr 16, 2018 Jkt 244001 (a) Comments Due Date We must receive comments by June 1, 2018. (b) Affected ADs None. (c) Applicability This AD applies to all General Electric Company (GE) CF34–8E turbofan engines. (d) Subject Joint Aircraft System Component (JASC) Code 7830, Thrust Reverser. (e) Unsafe Condition This AD was prompted by a report from GE regarding a quality escape of nonconforming thrust reverser fire seal gaps. We are issuing this AD to inspect for nonconforming thrust reverser fire seal gaps that could result in a fire outside the fire zone. The unsafe condition, if not addressed, could result in an uncontrolled fire, damage to the engine, and damage to the airplane. (i) Related Information (1) For more information about this AD, contact David Bethka, Aerospace Engineer, ECO Branch, FAA,1200 District Avenue, Burlington, MA 01803; phone: 781–238– 7129; fax: 781–238–7199; email: david.bethka@faa.gov. (2) For service information identified in this AD, contact General Electric Company, 1 Neumann Way, Cincinnati, OH 45215; telephone 513–552–3272; email aviation.fleetsupport@ge.com. You may view this referenced service information at the FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781–238–7759. Issued in Burlington, Massachusetts, on April 9, 2018. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2018–07819 Filed 4–16–18; 8:45 am] (f) Compliance Comply with this AD within the compliance times specified, unless already done. BILLING CODE 4910–13–P (g) Required Actions (1) For all CF34–8E turbofan engines, before the engine accumulates 8,000 flight hours after the effective date of this AD, perform the following one-time inspection, and, if needed, replace the core cowl seal and pylon seal. (i) Measure the width of the RTV filled gap between thrust reverser fire seals at the junction between 12 o’clock core cowl seal and pylon seal, at the following half thrust reverser locations: engine 1 left hand (LH) half thrust reverser, part number (P/N) 15G0002–013; engine 2 LH half thrust reverser, P/N 15G0002–014; engine 1 right hand (RH) half thrust reverser, P/N 15G0003– 013; and engine 2 RH half thrust reverser P/N 15G0003–014. (ii) If the gap width between the 12 o’clock core cowl seal and the pylon seal is greater than 1 mm, replace both seals with parts eligible for installation to form a new gap of 1 mm or less, prior to return to service. (2) You may refer to GE CF34–8E Service Bulletin 78–0066 R00, dated December 11, 2017 for guidance on inspecting and replacing the thrust reverser fire seals. Federal Aviation Administration (h) 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 (i)(1) 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. PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 DEPARTMENT OF TRANSPORTATION 14 CFR Part 39 [Docket No. FAA–2018–0276; Product Identifier 2017–NM–079–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 747–100, –100B, –100B SUD, –200B, –200C, –200F, –300, –400, –400D, 747SP, and 747SR, and 747–8 series airplanes. This proposed AD was prompted by reports indicating that additional areas of Boeing Material Specification (BMS) 8– 39 flexible urethane foam were found during an inspection required by a related AD. This proposed AD would require inspecting for BMS 8–39 flexible urethane foam insulation in the floor panel assemblies and the power drive unit (PDU) cover assemblies; doing applicable on-condition actions; modifying certain dripshields; and replacing BMS 8–39 foam strips on certain dripshields with BMS 8–371 foam strips. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by June 1, 2018. SUMMARY: E:\FR\FM\17APP1.SGM 17APP1

Agencies

[Federal Register Volume 83, Number 74 (Tuesday, April 17, 2018)]
[Proposed Rules]
[Pages 16794-16796]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-07819]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0142; Product Identifier 2018-NE-04-AD]
RIN 2120-AA64


Airworthiness Directives; General Electric Company CF34-8E 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
General Electric Company (GE) CF34-8E turbofan engines. This proposed 
AD was prompted by a report from GE regarding a quality escape of 
nonconforming thrust reverser fire seals. This proposed AD would 
require a one-time inspection of the gap between the core cowl seal and 
the pylon seal of the thrust reverser for correct gap width, and 
replacement of the seals, if needed. We are proposing this AD to 
address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by June 1, 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 https://www.regulations.gov. Follow the instructions for submitting comments.

[[Page 16795]]

     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, 1 Neumann Way, Cincinnati, OH 45215; telephone 513-
552-3272; email [email protected]. You may view this service 
information at the FAA, Engine and Propeller Standards Branch, 1200 
District Avenue, Burlington, MA 01803. For information on the 
availability of this material at the FAA, call 781-238-7759.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0142; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this NPRM, the regulatory evaluation, any comments received, and other 
information. The street address for Docket Operations (phone: 800-647-
5527) is listed above. Comments will be available in the AD docket 
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: David Bethka, Aerospace Engineer, ECO 
Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781-
238-7129; fax: 781-238-7199; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2018-0142; 
Product Identifier 2018-NE-04-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this NPRM. We will consider all 
comments received by the closing date and may amend this NPRM because 
of those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this NPRM.

Discussion

    We received a report from the manufacturer about a fire seal gap 
quality escape on GE CF34-8E turbofan engines. Some thrust reverser 
fire seals, installed on thrust reverser part numbers (P/Ns) 15G0002-
013, 15G0002-014, 15G0003-013, and 15G0003-014, were shipped from a 
supplier with nonconforming seal gaps.
    An analysis by the manufacturer has shown that a gap between the 12 
o'clock core cowl seal and pylon seal that is greater than the 1 mm 
design requirement could result in fire outside the fire zone. This 
unsafe condition, if not addressed, could result in an uncontrolled 
fire, damage to the engine, and damage to the airplane.

Related Service Information

    We reviewed GE CF34-8E Service Bulletin (SB) 78-0066 R00, dated 
December 11, 2017. The SB describes procedures for measuring the width 
of the RTV filled gap between the thrust reverser fire seals at the 12 
o'clock core cowl seal and pylon seal installed on thrust reverser P/Ns 
15G0002-013, 15G0002-014, 15G0003-013, and 15G0003-014, and replacing 
with parts eligible for installation, if needed.

FAA's Determination

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

Proposed AD Requirements

    This proposed AD would require a one-time inspection of the gap 
between the core cowl seal and the pylon seal of the thrust reverser 
for correct gap width, and replacement of the thrust reverser fire 
seals, if needed.

Costs of Compliance

    We estimate that this proposed AD affects 936 engines installed on 
airplanes of U.S. registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspection.........................  0.25 work-hours x $85 per                $0          $21.25         $19,890
                                      hour = $21.25.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the proposed inspection. 
We have no way of determining the number of aircraft that might need 
these replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Remove and replace thrust reverser fire      2.75 work-hours x $85 per hour =             $3,228       $3,461.75
 seals.                                       $233.75.
----------------------------------------------------------------------------------------------------------------

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

[[Page 16796]]

products identified in this rulemaking action.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to engines, propellers, and 
associated appliances to the Manager, Engine and Propeller Standards 
Branch, Policy and Innovation Division.

Regulatory Findings

    We 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 this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

General Electric Company: Docket No. FAA-2018-0142; Product 
Identifier 2018-NE-04-AD.

(a) Comments Due Date

    We must receive comments by June 1, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all General Electric Company (GE) CF34-8E 
turbofan engines.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7830, Thrust 
Reverser.

(e) Unsafe Condition

    This AD was prompted by a report from GE regarding a quality 
escape of nonconforming thrust reverser fire seal gaps. We are 
issuing this AD to inspect for nonconforming thrust reverser fire 
seal gaps that could result in a fire outside the fire zone. The 
unsafe condition, if not addressed, could result in an uncontrolled 
fire, damage to the engine, and damage to the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Actions

    (1) For all CF34-8E turbofan engines, before the engine 
accumulates 8,000 flight hours after the effective date of this AD, 
perform the following one-time inspection, and, if needed, replace 
the core cowl seal and pylon seal.
    (i) Measure the width of the RTV filled gap between thrust 
reverser fire seals at the junction between 12 o'clock core cowl 
seal and pylon seal, at the following half thrust reverser 
locations: engine 1 left hand (LH) half thrust reverser, part number 
(P/N) 15G0002-013; engine 2 LH half thrust reverser, P/N 15G0002-
014; engine 1 right hand (RH) half thrust reverser, P/N 15G0003-013; 
and engine 2 RH half thrust reverser P/N 15G0003-014.
    (ii) If the gap width between the 12 o'clock core cowl seal and 
the pylon seal is greater than 1 mm, replace both seals with parts 
eligible for installation to form a new gap of 1 mm or less, prior 
to return to service.
    (2) You may refer to GE CF34-8E Service Bulletin 78-0066 R00, 
dated December 11, 2017 for guidance on inspecting and replacing the 
thrust reverser fire seals.

(h) 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 (i)(1) 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

    (1) For more information about this AD, contact David Bethka, 
Aerospace Engineer, ECO Branch, FAA,1200 District Avenue, 
Burlington, MA 01803; phone: 781-238-7129; fax: 781-238-7199; email: 
[email protected].
    (2) For service information identified in this AD, contact 
General Electric Company, 1 Neumann Way, Cincinnati, OH 45215; 
telephone 513-552-3272; email [email protected]. You may 
view this referenced service information at the FAA, Engine and 
Propeller Standards Branch, 1200 District Avenue, Burlington, MA 
01803. For information on the availability of this material at the 
FAA, call 781-238-7759.

    Issued in Burlington, Massachusetts, on April 9, 2018.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2018-07819 Filed 4-16-18; 8:45 am]
 BILLING CODE 4910-13-P
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