83 FR 16794 - Airworthiness Directives; General Electric Company CF34-8E Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 74 (April 17, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 74 (April 17, 2018)
| Page Range | 16794-16796 | |
| FR Document | 2018-07819 |
[Federal Register Volume 83, Number 74 (Tuesday, April 17, 2018)] [Proposed Rules] [Pages 16794-16796] From the Federal Register Online [www.thefederalregister.org] [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 http://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 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 http://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 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 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: 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] BILLING CODE 4910-13-P
![16794 Federal Register / Vol. 83, No. 74 / Tuesday, April 17, 2018 / Proposed Rules
(b) Affected ADs icing boots, in accordance with the information. This MCAI may be found in the
This AD replaces AD 2016–13–06, Accomplishment Instructions of Saab Service AD docket on the internet at http://
Amendment 39–18570 (81 FR 41432, June Bulletin 340–30–094, dated March 27, 2015. www.regulations.gov by searching for and
27, 2016) (‘‘AD 2016–13–06’’). Repeat the inspection thereafter at intervals locating Docket No. FAA–2018–0271.
not to exceed 400 flight hours. If, during any (2) For more information about this AD,
(c) Applicability inspection required by this paragraph, any contact Shahram Daneshmandi, Aerospace
This AD applies to Saab AB, Saab damage or existing repair outside the limits Engineer, International Section, Transport
Aeronautics (formerly known as Saab AB, specified in Saab Service Bulletin 340–30– Standards Branch, FAA, 2200 South 216th
Saab Aerosystems) airplanes, certificated in 094, dated March 27, 2015, is found, before St., Des Moines, WA 98198; telephone and
any category, identified in paragraphs (c)(1) further flight, repair or replace the horizontal fax: 206–231–3220.
and (c)(2), of this AD. stabilizer de-icing boots, in accordance with (3) For service information identified in
(1) Saab AB, Saab Aeronautics Model 340A the Accomplishment Instructions of Saab this AD, contact Saab AB, Saab Aeronautics,
(SAAB/SF340A) airplanes, serial numbers Service Bulletin 340–30–094, dated March SE–581 88, Linköping, Sweden; telephone:
004 through 138 inclusive, if Saab 27, 2015. Repair or replacement on an +46 13 18 5591; fax: +46 13 18 4874; email:
modification 1462 has been embodied in airplane of the horizontal stabilizer de-icing saab340techsupport@saabgroup.com;
production, or Saab Service Bulletin 340–55– boots, as required by this paragraph, does not internet: http://www.saabgroup.com. You
008 has been embodied in service, except constitute terminating action for the may view this service information at the
those that have also embodied Saab repetitive inspections required by this FAA, Transport Standards Branch, 2200
modification 1793 in production, or Saab paragraph for that airplane. South 216th St., Des Moines, WA. For
Service Bulletin 340–55–010 in service; and (i) New Requirement of This AD: information on the availability of this
serial numbers 139 through 159 inclusive. Modification material at the FAA, call 206–231–3195.
(2) Saab AB, Saab Aeronautics Model
Within 18 months after the effective date Issued in Des Moines, Washington, on
SAAB 340B airplanes, serial numbers 160
of this AD, modify the airplane by replacing March 30, 2018.
through 459 inclusive.
the single stitched de-icing boots installed on Chris Spangenberg,
(d) Subject the left-hand (LH) and right-hand (RH) Acting Director, System Oversight Division,
Air Transport Association (ATA) of horizontal stabilizers with double stitched Aircraft Certification Service.
America Code 30, Ice and rain protection. de-icing boots and re-identify the LH and RH
[FR Doc. 2018–07636 Filed 4–16–18; 8:45 am]
horizontal stabilizer leading edge, in
(e) Reason accordance with the Accomplishment BILLING CODE 4910–13–P
This AD was prompted by reports of Instructions of Saab Service Bulletin 340–30–
ruptured horizontal stabilizer de-icing boots. 095, dated April 3, 2017.
We are issuing this AD to detect and correct DEPARTMENT OF TRANSPORTATION
(j) Terminating Action
ruptured horizontal stabilizer de-icing boots,
which could lead to complete loss of the de- Modification of the airplane as required by Federal Aviation Administration
icing function within its associated zone and paragraph (i) of this AD, constitutes
severe vibrations, possibly resulting in terminating action for the repetitive 14 CFR Part 39
reduced control of the airplane. inspections required by paragraph (h) of this
AD, for that airplane. [Docket No. FAA–2018–0142; Product
(f) Compliance Identifier 2018–NE–04–AD]
(k) Other FAA AD Provisions
Comply with this AD within the
compliance times specified, unless already (1) Alternative Methods of Compliance RIN 2120–AA64
done. (AMOCs): The Manager, International
Section, Transport Standards Branch, FAA, Airworthiness Directives; General
(g) Retained Revision of the Airplane Flight has the authority to approve AMOCs for this Electric Company CF34–8E Engines
Manual (AFM), With No Changes AD, if requested using the procedures found
This paragraph restates the requirements of in 14 CFR 39.19. In accordance with 14 CFR AGENCY: Federal Aviation
paragraph (g) of AD 2016–13–06, with no 39.19, send your request to your principal Administration (FAA), DOT.
changes. Within 30 days after August 1, 2016 inspector or local Flight Standards District ACTION: Notice of proposed rulemaking
(the effective date of AD 2016–13–06), revise Office, as appropriate. If sending information (NPRM).
the ‘‘Abnormal Procedures’’ section of the directly to the International Section, send it
applicable Saab 340 AFM to incorporate the to the attention of the person identified in SUMMARY: We propose to adopt a new
revision specified in paragraphs (g)(1) paragraph (l)(2) of this AD. Information may airworthiness directive (AD) for all
through (g)(3) of this AD. be emailed to: 9-ANM-116-AMOC- General Electric Company (GE) CF34–8E
(1) For Saab AB, Saab Aeronautics Model REQUESTS@faa.gov. Before using any turbofan engines. This proposed AD was
340A (SAAB/SF340A) airplanes, revise AFM approved AMOC, notify your appropriate
prompted by a report from GE regarding
340A 001 by incorporating Revision 57, principal inspector, or lacking a principal
dated March 27, 2015. inspector, the manager of the local flight a quality escape of nonconforming
(2) For Saab AB, Saab Aeronautics Model standards district office/certificate holding thrust reverser fire seals. This proposed
SAAB 340B airplanes, revise AFM 340B 001 district office. AD would require a one-time inspection
by incorporating Revision 35, dated March (2) Contacting the Manufacturer: As of the of the gap between the core cowl seal
27, 2015. effective date of this AD, for any requirement and the pylon seal of the thrust reverser
(3) For Saab AB, Saab Aeronautics Model in this AD to obtain corrective actions from for correct gap width, and replacement
SAAB 340B airplanes with extended wing a manufacturer, the action must be of the seals, if needed. We are proposing
tips, revise AFM 340B 010 by incorporating accomplished using a method approved by
this AD to address the unsafe condition
Revision 28, dated March 27, 2015. the Manager, International Section, Transport
Standards Branch, FAA; or the European on these products.
(h) Retained Inspection/Replacement, With Aviation Safety Agency (EASA); or Saab AB, DATES: We must receive comments on
No Changes this proposed AD by June 1, 2018.
amozie on DSK30RV082PROD with PROPOSALS
Saab Aeronautics EASA Design Organization
This paragraph restates the requirements of Approval (DOA). If approved by the DOA, ADDRESSES: You may send comments,
paragraph (h) of AD 2016–13–06, with no the approval must include the DOA- using the procedures found in 14 CFR
changes. Within 400 flight hours or 6 authorized signature.
months, whichever occurs first after August 11.43 and 11.45, by any of the following
1, 2016 (the effective date of AD 2016–13– (l) Related Information methods:
06), do a detailed inspection for damage of (1) Refer to Mandatory Continuing • Federal eRulemaking Portal: Go to
the horizontal stabilizer de-icing boots, and Airworthiness Information (MCAI) EASA AD http://www.regulations.gov. Follow the
existing repairs of horizontal stabilizer de- 2017–0144, dated August 9, 2017, for related instructions for submitting comments.
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![16796 Federal Register / Vol. 83, No. 74 / Tuesday, April 17, 2018 / Proposed Rules
products identified in this rulemaking (a) Comments Due Date (i) Related Information
action. We must receive comments by June 1, (1) For more information about this AD,
This AD is issued in accordance with 2018. contact David Bethka, Aerospace Engineer,
authority delegated by the Executive ECO Branch, FAA,1200 District Avenue,
(b) Affected ADs Burlington, MA 01803; phone: 781–238–
Director, Aircraft Certification Service,
as authorized by FAA Order 8000.51C. None. 7129; fax: 781–238–7199; email:
In accordance with that order, issuance david.bethka@faa.gov.
(c) Applicability
(2) For service information identified in
of ADs is normally a function of the This AD applies to all General Electric this AD, contact General Electric Company,
Compliance and Airworthiness Company (GE) CF34–8E turbofan engines. 1 Neumann Way, Cincinnati, OH 45215;
Division, but during this transition telephone 513–552–3272; email
period, the Executive Director has (d) Subject
aviation.fleetsupport@ge.com. You may view
delegated the authority to issue ADs Joint Aircraft System Component (JASC) this referenced service information at the
applicable to engines, propellers, and Code 7830, Thrust Reverser. FAA, Engine and Propeller Standards
associated appliances to the Manager, (e) Unsafe Condition Branch, 1200 District Avenue, Burlington,
Engine and Propeller Standards Branch, MA 01803. For information on the
This AD was prompted by a report from GE availability of this material at the FAA, call
Policy and Innovation Division. regarding a quality escape of nonconforming 781–238–7759.
Regulatory Findings thrust reverser fire seal gaps. We are issuing
this AD to inspect for nonconforming thrust Issued in Burlington, Massachusetts, on
We determined that this proposed AD reverser fire seal gaps that could result in a April 9, 2018.
would not have federalism implications fire outside the fire zone. The unsafe Robert J. Ganley,
under Executive Order 13132. This condition, if not addressed, could result in an Manager, Engine and Propeller Standards
proposed AD would not have a uncontrolled fire, damage to the engine, and Branch, Aircraft Certification Service.
substantial direct effect on the States, on damage to the airplane. [FR Doc. 2018–07819 Filed 4–16–18; 8:45 am]
the relationship between the national (f) Compliance BILLING CODE 4910–13–P
government and the States, or on the Comply with this AD within the
distribution of power and compliance times specified, unless already
responsibilities among the various done. DEPARTMENT OF TRANSPORTATION
levels of government.
For the reasons discussed above, I (g) Required Actions Federal Aviation Administration
certify this proposed regulation: (1) For all CF34–8E turbofan engines,
(1) Is not a ‘‘significant regulatory before the engine accumulates 8,000 flight 14 CFR Part 39
action’’ under Executive Order 12866, hours after the effective date of this AD,
perform the following one-time inspection, [Docket No. FAA–2018–0276; Product
(2) Is not a ‘‘significant rule’’ under
and, if needed, replace the core cowl seal and Identifier 2017–NM–079–AD]
the DOT Regulatory Policies and pylon seal.
Procedures (44 FR 11034, February 26, (i) Measure the width of the RTV filled gap RIN 2120–AA64
1979), between thrust reverser fire seals at the
(3) Will not affect intrastate aviation junction between 12 o’clock core cowl seal Airworthiness Directives; The Boeing
in Alaska, and and pylon seal, at the following half thrust Company Airplanes
(4) Will not have a significant reverser locations: engine 1 left hand (LH)
AGENCY: Federal Aviation
economic impact, positive or negative, half thrust reverser, part number (P/N)
15G0002–013; engine 2 LH half thrust Administration (FAA), DOT.
on a substantial number of small entities
under the criteria of the Regulatory reverser, P/N 15G0002–014; engine 1 right ACTION: Notice of proposed rulemaking
Flexibility Act. hand (RH) half thrust reverser, P/N 15G0003– (NPRM).
013; and engine 2 RH half thrust reverser
List of Subjects in 14 CFR Part 39 P/N 15G0003–014. SUMMARY: We propose to adopt a new
(ii) If the gap width between the 12 o’clock airworthiness directive (AD) for certain
Air transportation, Aircraft, Aviation core cowl seal and the pylon seal is greater
safety, Incorporation by reference, The Boeing Company Model 747–100,
than 1 mm, replace both seals with parts –100B, –100B SUD, –200B, –200C,
Safety. eligible for installation to form a new gap of
–200F, –300, –400, –400D, 747SP, and
1 mm or less, prior to return to service.
The Proposed Amendment 747SR, and 747–8 series airplanes. This
(2) You may refer to GE CF34–8E Service
Accordingly, under the authority Bulletin 78–0066 R00, dated December 11, proposed AD was prompted by reports
delegated to me by the Administrator, 2017 for guidance on inspecting and indicating that additional areas of
the FAA proposes to amend 14 CFR part replacing the thrust reverser fire seals. Boeing Material Specification (BMS) 8–
39 as follows: 39 flexible urethane foam were found
(h) Alternative Methods of Compliance
(AMOCs) during an inspection required by a
PART 39—AIRWORTHINESS related AD. This proposed AD would
(1) The Manager, ECO Branch, FAA, has
DIRECTIVES require inspecting for BMS 8–39 flexible
the authority to approve AMOCs for this AD,
if requested using the procedures found in 14 urethane foam insulation in the floor
■ 1. The authority citation for part 39 panel assemblies and the power drive
CFR 39.19. In accordance with 14 CFR 39.19,
continues to read as follows: send your request to your principal inspector unit (PDU) cover assemblies; doing
Authority: 49 U.S.C. 106(g), 40113, 44701. or local Flight Standards District Office, as applicable on-condition actions;
appropriate. If sending information directly modifying certain dripshields; and
amozie on DSK30RV082PROD with PROPOSALS
§ 39.13 [Amended] to the manager of the certification office, replacing BMS 8–39 foam strips on
■ 2. The FAA amends § 39.13 by adding send it to the attention of the person certain dripshields with BMS 8–371
identified in paragraph (i)(1) of this AD. foam strips. We are proposing this AD
the following new airworthiness
(2) Before using any approved AMOC,
directive (AD): to address the unsafe condition on these
notify your appropriate principal inspector,
General Electric Company: Docket No. FAA– or lacking a principal inspector, the manager products.
2018–0142; Product Identifier 2018–NE– of the local Flight Standards District Office/ DATES: We must receive comments on
04–AD. Certificate Holding District Office. this proposed AD by June 1, 2018.
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Document Created: 2018-04-17 02:51:43
Document Modified: 2018-04-17 02:51:43
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by June 1, 2018. | |
| 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] | |
| FR Citation | 83 FR 16794 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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