Airworthiness Directives; General Electric Company Turbofan Engines, 74125-74126 [2012-30072]

Download as PDF Federal Register / Vol. 77, No. 240 / Thursday, December 13, 2012 / Proposed Rules (e) Actions and Compliance Unless already done, do the following. For engines that have operated to the Plan D Flight Mission configuration, remove the LPC rotor disc assembly from service before accumulating 18,700 engine flight cycles. Do not return to service nor approve for return to service any engine with the affected discs installed that exceeds 18,700 engine flight cycles. (f) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. (g) Related Information (1) For more information about this AD, contact Frederick Zink, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; email: Frederick.zink@faa.gov; phone: 781– 238–7779; fax: 781–238–7199. (2) Refer to European Aviation Safety Agency AD 2012–0204, dated October 1, 2012, and RRD Alert Service Bulletin TAY– 72–A1772, dated August 9, 2012, for related information. (3) For service information identified in this AD, contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11 Dahlewitz 15827, Blankenfelde-Mahlow, Germany; phone: +49 0 33–7086–1944; fax: +49 0 33–7086–3276. (4) You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. Issued in Burlington, Massachusetts, on December 6, 2012. Robert J. Ganley, Acting Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2012–30065 Filed 12–12–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–1288; Directorate Identifier 2012–NE–37–AD] RIN 2120–AA64 Airworthiness Directives; General Electric Company Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). wreier-aviles on DSK5TPTVN1PROD with AGENCY: We propose to adopt a new airworthiness directive (AD) for all General Electric Company (GE) CF34– 8C and CF34–8E turbofan engines with certain part numbers (P/N) of SUMMARY: VerDate Mar<15>2010 14:58 Dec 12, 2012 Jkt 229001 74125 operability bleed valves (OBV) installed. This proposed AD was prompted by three failure events of ring lock fuel fittings on the OBV. Two of those events led to an engine fire. This proposed AD would require the affected OBVs be removed from service and replaced with OBVs eligible for installation. We are proposing this AD to prevent failure of OBV ring lock fuel fittings, engine fuel leakage, uncontrolled fire, and damage to the airplane. DATES: We must receive comments on this proposed AD by February 11, 2013. 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: 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 proposed AD, contact General Electric, One Neumann Way, MD Y–75, Cincinnati, OH; phone: 513–552–2913; email: geae.aoc@ge.com; and Web site: www.GE.com. You view the referenced service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2012–1288; Directorate Identifier 2012– NE–37–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD 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 proposed AD. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; 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 proposed AD, 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, Engine & Propeller Directorate, FAA, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7756; fax: 781– 238–7199; email: john.frost@faa.gov. SUPPLEMENTARY INFORMATION: We reviewed GE Service Bulletin (SB) No. CF34–8C–AL S/B 75–0017, dated September 14 2012. We also reviewed GE SB No. CF34–8E–AL S/B 75–0012, dated September 14, 2012. These bulletins describe procedures for removing from service OBVs having an affected P/N. Comments Invited We invite you to send any written relevant data, views, or arguments about PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 Discussion We received reports of three failure events of OBV ring lock fuel fittings on GE CF34–8C turbofan engines. Two of those events led to an engine fire. Investigation revealed that the ring lock fittings failed due to fatigue caused by improper broaching of the OBV housing during manufacture, and, improper installation of the ring lock fittings during OBV assembly. GE CF34–8E turbofan engines also use the affected OBVs and would be affected by this proposed AD. This condition, if not corrected, could result in failure of OBV ring lock fuel fittings, engine fuel leakage, uncontrolled fire, and damage to the airplane. Relevant Service Information 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 for all GE CF34–8C and CF34–8E turbofan engines with an OBV P/N 4121T67P02, P/N 4121T67P03, P/N 4121T67P04, parts manufacturer approval (PMA) P/N 392155–2, PMA P/N 392155–3, or PMA P/N 392155–4 installed, removal of the OBV from service. E:\FR\FM\13DEP1.SGM 13DEP1 74126 Federal Register / Vol. 77, No. 240 / Thursday, December 13, 2012 / Proposed Rules Costs of Compliance We estimate that this proposed AD would affect 300 engines installed on airplanes of U.S. registry. We also estimate that it would take about two hours per engine to perform the actions required by this proposed AD, and that the average labor rate is $85 per hour. Required parts would cost about $25,000 per engine. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $7,551,000. 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. wreier-aviles on DSK5TPTVN1PROD with 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. VerDate Mar<15>2010 14:58 Dec 12, 2012 Jkt 229001 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: 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– 2012–1288; Directorate Identifier 2012– NE–37–AD. (a) Comments Due Date We must receive comments by February 11, 2013. (b) Affected ADs None. (c) Applicability This AD applies to General Electric Company (GE) CF34–8C1, CF34–8C5, CF34– 8C5A1, CF34–8C5A2, CF34–8C5A3, CF34– 8C5B1, CF34–8E2, CF34–8E2A1, CF34–8E5, CF34–8E5A1, CF34–8E5A2, CF34–8E6, and CF34–8E6A1 turbofan engines, with an operability bleed valve (OBV) part number (P/N) 4121T67P02, P/N 4121T67P03, P/N 4121T67P04, parts manufacturer approval (PMA) P/N 392155–2, PMA P/N 392155–3, or PMA P/N 392155–4, installed. (d) Unsafe Condition This AD was prompted by three failure events of ring lock fuel fittings on the OBV. Two of those events led to an engine fire. We are issuing this AD to prevent failure of OBV ring lock fuel fittings, engine fuel leakage, uncontrolled fire, and damage to the airplane. (e) Compliance Comply with this AD within the compliance times specified, unless already done. (f) Remove OBVs (1) For OBVs with fewer than 6,000 operating hours since new on the effective date of this AD, remove the OBV from service before accumulating 12,000 operating hours since new, or within four years after the effective date of this AD, whichever occurs first. (2) For OBVs with 6,000 or more operating hours since new on the effective date of this AD, remove the OBV from service before accumulating an additional 6,000 operating hours, or within two years after the effective date of this AD, whichever occurs first. PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 (g) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. (h) Related Information (1) For more information about this AD, contact John Frost, Aerospace Engineer, Engine & Propeller Directorate, FAA, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7756; fax: 781–238– 7199; email: john.frost@faa.gov. (2) Refer to GE SB No. CF34–8C–AL S/B 75–0017, dated September 14 2012, and SB No. CF34–8E–AL S/B 75–0012, dated September 14, 2012, for related information. (3) For service information identified in this AD, contact General Electric, One Neumann Way, MD Y–75, Cincinnati, OH; phone: 513–552–2913; email: geae.aoc@ge.com; and Web site: www.GE.com. You may view the referenced service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. Issued in Burlington, Massachusetts, on December 4, 2012. Robert J. Ganley, Acting Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2012–30072 Filed 12–12–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–1226; Directorate Identifier 2012–NM–122–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC–8–400 series airplanes. This proposed AD was prompted by a report of a translating door handle jamming during opening of an aft door. This proposed AD would require replacing the handle shaft with a new single-piece machined handle shaft on the aft entry and service doors, and require revising the maintenance program by incorporating a new airworthiness limitation task. We are proposing this AD to prevent a migrated pin from jamming a translating door handle, which could prevent opening of SUMMARY: E:\FR\FM\13DEP1.SGM 13DEP1

Agencies

[Federal Register Volume 77, Number 240 (Thursday, December 13, 2012)]
[Proposed Rules]
[Pages 74125-74126]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-30072]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1288; Directorate Identifier 2012-NE-37-AD]
RIN 2120-AA64


Airworthiness Directives; General Electric Company Turbofan 
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) CF34-8C and CF34-8E turbofan engines with 
certain part numbers (P/N) of operability bleed valves (OBV) installed. 
This proposed AD was prompted by three failure events of ring lock fuel 
fittings on the OBV. Two of those events led to an engine fire. This 
proposed AD would require the affected OBVs be removed from service and 
replaced with OBVs eligible for installation. We are proposing this AD 
to prevent failure of OBV ring lock fuel fittings, engine fuel leakage, 
uncontrolled fire, and damage to the airplane.

DATES: We must receive comments on this proposed AD by February 11, 
2013.

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: 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 proposed AD, contact 
General Electric, One Neumann Way, MD Y-75, Cincinnati, OH; phone: 513-
552-2913; email: geae.aoc@ge.com; and Web site: www.GE.com. You view 
the referenced service information at the FAA, Engine & Propeller 
Directorate, 12 New England Executive Park, 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; 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 proposed AD, 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, Engine 
& Propeller Directorate, FAA, 12 New England Executive Park, 
Burlington, MA 01803; phone: 781-238-7756; fax: 781-238-7199; email: 
john.frost@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-2012-1288; 
Directorate Identifier 2012-NE-37-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD 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 proposed AD.

Discussion

    We received reports of three failure events of OBV ring lock fuel 
fittings on GE CF34-8C turbofan engines. Two of those events led to an 
engine fire. Investigation revealed that the ring lock fittings failed 
due to fatigue caused by improper broaching of the OBV housing during 
manufacture, and, improper installation of the ring lock fittings 
during OBV assembly. GE CF34-8E turbofan engines also use the affected 
OBVs and would be affected by this proposed AD. This condition, if not 
corrected, could result in failure of OBV ring lock fuel fittings, 
engine fuel leakage, uncontrolled fire, and damage to the airplane.

Relevant Service Information

    We reviewed GE Service Bulletin (SB) No. CF34-8C-AL S/B 75-0017, 
dated September 14 2012. We also reviewed GE SB No. CF34-8E-AL S/B 75-
0012, dated September 14, 2012. These bulletins describe procedures for 
removing from service OBVs having an affected P/N.

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 for all GE CF34-8C and CF34-8E 
turbofan engines with an OBV P/N 4121T67P02, P/N 4121T67P03, P/N 
4121T67P04, parts manufacturer approval (PMA) P/N 392155-2, PMA P/N 
392155-3, or PMA P/N 392155-4 installed, removal of the OBV from 
service.

[[Page 74126]]

Costs of Compliance

    We estimate that this proposed AD would affect 300 engines 
installed on airplanes of U.S. registry. We also estimate that it would 
take about two hours per engine to perform the actions required by this 
proposed AD, and that the average labor rate is $85 per hour. Required 
parts would cost about $25,000 per engine. Based on these figures, we 
estimate the total cost of the proposed AD to U.S. operators to be 
$7,551,000.

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.

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:

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


Sec.  39.13  [Amended]

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

General Electric Company: Docket No. FAA-2012-1288; Directorate 
Identifier 2012-NE-37-AD.

(a) Comments Due Date

    We must receive comments by February 11, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to General Electric Company (GE) CF34-8C1, CF34-
8C5, CF34-8C5A1, CF34-8C5A2, CF34-8C5A3, CF34-8C5B1, CF34-8E2, CF34-
8E2A1, CF34-8E5, CF34-8E5A1, CF34-8E5A2, CF34-8E6, and CF34-8E6A1 
turbofan engines, with an operability bleed valve (OBV) part number 
(P/N) 4121T67P02, P/N 4121T67P03, P/N 4121T67P04, parts manufacturer 
approval (PMA) P/N 392155-2, PMA P/N 392155-3, or PMA P/N 392155-4, 
installed.

(d) Unsafe Condition

    This AD was prompted by three failure events of ring lock fuel 
fittings on the OBV. Two of those events led to an engine fire. We 
are issuing this AD to prevent failure of OBV ring lock fuel 
fittings, engine fuel leakage, uncontrolled fire, and damage to the 
airplane.

(e) Compliance

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

(f) Remove OBVs

    (1) For OBVs with fewer than 6,000 operating hours since new on 
the effective date of this AD, remove the OBV from service before 
accumulating 12,000 operating hours since new, or within four years 
after the effective date of this AD, whichever occurs first.
    (2) For OBVs with 6,000 or more operating hours since new on the 
effective date of this AD, remove the OBV from service before 
accumulating an additional 6,000 operating hours, or within two 
years after the effective date of this AD, whichever occurs first.

(g) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA, may approve AMOCs 
for this AD. Use the procedures found in 14 CFR 39.19 to make your 
request.

(h) Related Information

    (1) For more information about this AD, contact John Frost, 
Aerospace Engineer, Engine & Propeller Directorate, FAA, 12 New 
England Executive Park, Burlington, MA 01803; phone: 781-238-7756; 
fax: 781-238-7199; email: john.frost@faa.gov.
    (2) Refer to GE SB No. CF34-8C-AL S/B 75-0017, dated September 
14 2012, and SB No. CF34-8E-AL S/B 75-0012, dated September 14, 
2012, for related information.
    (3) For service information identified in this AD, contact 
General Electric, One Neumann Way, MD Y-75, Cincinnati, OH; phone: 
513-552-2913; email: geae.aoc@ge.com; and Web site: www.GE.com. You 
may view the referenced service information at the FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, 
MA. For information on the availability of this material at the FAA, 
call 781-238-7125.

    Issued in Burlington, Massachusetts, on December 4, 2012.
Robert J. Ganley,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-30072 Filed 12-12-12; 8:45 am]
BILLING CODE 4910-13-P