Airworthiness Directives; General Electric Company CF34-10E Series Turbofan Engines, 64287-64289 [2011-26824]

Download as PDF Federal Register / Vol. 76, No. 201 / Tuesday, October 18, 2011 / Proposed Rules 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); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. Aviation Safety Agency (EASA) Supplemental Type Certificate (STC) No. EASA.A.S.01527); Piper PA–28 series (EASA STC No. EASA.A.S. 01632); APEX (Robin) DR 400 series (EASA STC No. A.S.01380); and Diamond Aircraft Industries Models DA40 and DA42 airplanes. Reason (d) As a consequence of occurrences and service experience, Thielert Aircraft Engines GmbH has introduced a new rail pressure control valve part number (P/N) 05–7320– E000702 and has amended the Airworthiness Limitation Section (ALS) of the Operation & Maintenance Manual OM–02–02 to include a replacement of the rail pressure control valve. Failure of this part could result in inflight shutdowns of the engine(s). TAE has also amended the ALS of the Operation & Maintenance Manual OM–02–01 to include a replacement of the rail pressure valve. This AD results from mandatory continuing airworthiness information (MCAIs) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product and from a comment received from EASA on AD 2010–06–12. We are issuing this AD to prevent engine in-flight shutdown, possibly resulting in reduced control of the aircraft. products identified in this rulemaking action. 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 removing Amendment 39–16236, and adding the following new AD: Thielert Aircraft Engines GmbH: Docket No. FAA–2009–0948; Directorate Identifier 2009–NE–30–AD. srobinson on DSK4SPTVN1PROD with PROPOSALS Comments Due Date (a) We must receive comments by November 17, 2011. Affected Airworthiness Directives (ADs) (b) This AD revises AD 2010–06–12, Amendment 39–16236. Applicability (c) This AD applies to Thielert Aircraft Engines GmbH (TAE) models TAE 125–01 and TAE 125–02–99 reciprocating engines installed in, but not limited to, Cessna 172 and (Reims-built) F172 series (European VerDate Mar<15>2010 16:08 Oct 17, 2011 Jkt 226001 Actions and Compliance (e) Unless already done, do the following actions. TAE 125–02–99 Reciprocating Engines (1) For TAE 125–02–99 reciprocating engines, within 100 flight hours after the effective date of this AD, replace the existing rail pressure control valve with a rail pressure control valve P/N 05–7320– E000702, and modify the Vrail plug to make it compatible with the replacement rail pressure control valve. (2) Guidance on the valve replacement and rail modification specified in paragraph (e)(1) of this AD can be found in Thielert Repair Manual RM–02–02, Chapter 73–10.08, and Chapter 39–40.08, respectively. TAE 125–01 Reciprocating Engines (3) For TAE 125–01 reciprocating engines, before 600 flight hours time-since-new, or within 100 flight hours after the effective date of this AD, whichever occurs later, replace the existing rail pressure control valve with a rail pressure control valve, P/N 02–7320–04100R3. (4) Guidance on the valve replacement specified in paragraph (e)(3) of this AD can be found in Thielert Repair Manual RM–02– 01, Chapter 29.0. TAE 125–02–99 and TAE 125–01 Engines, Repetitive Replacements of Rail Pressure Control Valves (5) Thereafter, for affected TAE 125–02–99 and TAE 125–01 engines, replace the rail pressure control valve with the same P/N valve within every 600 flight hours. FAA AD Differences (f) This AD differs from the Mandatory Continuing Airworthiness Information (MCAI) and/or service information as follows: PO 00000 Frm 00038 Fmt 4702 Sfmt 4702 64287 (1) For the TAE 125–02–99 reciprocating engines, we reduced the initial compliance time from within 110 flight hours to within 100 flight hours after the effective date of this AD. (2) The MCAIs instruct the operators to follow Thielert Maintenance Manual, Chapter 5, Airworthiness Limitations, for the repetitive compliance time for the rail pressure control valve, which, in the manual, is 600 flight hours. We found it necessary to specify the repetitive replacement compliance time in this AD, to within every 600 flight hours. Alternative Methods of Compliance (AMOCs) (g) The Manager, Engine Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information (h) Refer to MCAI EASA AD 2008–0128, dated July 9, 2008, EASA AD 2008–0215, dated December 5, 2008, Thielert Service Bulletin No. TAE 125–1008 P1, Revision 1, dated September 29, 2008, and Thielert Repair Manual RM–02–02, for related information. Contact Thielert Aircraft Engines GmbH, Platanenstrasse 14 D–09350, Lichtenstein, Germany, telephone: +49– 37204–696–0; fax: +49–37204–696–55; e-mail: info@centurion-engines.com, for a copy of this service information. (i) Contact Alan Strom, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone 781–238–7143; fax 781– 238–7199; e-mail: alan.strom@faa.gov, for more information about this AD. Issued in Burlington, Massachusetts, on October 6, 2011. Peter A. White, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 2011–26822 Filed 10–17–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0599; Directorate Identifier 2011–NE–19–AD] RIN 2120–AA64 Airworthiness Directives; General Electric Company CF34–10E Series Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for General Electric Company (GE) CF34–10E series turbofan engines. This proposed AD was SUMMARY: E:\FR\FM\18OCP1.SGM 18OCP1 64288 Federal Register / Vol. 76, No. 201 / Tuesday, October 18, 2011 / Proposed Rules prompted by a report of heavy wear found on the seating surface of the center vent duct (CVD) (commonly referred to as center vent tube) support ring and on the inside diameter of the fan drive shaft at the mating location. This proposed AD would require removing from service CVD support assemblies from certain serial numbers (S/Ns) of CF34–10E series turbofan engines. This proposed AD would also require removing any fan drive shaft from service if wear is found on either the CVD support ring or the fan drive shaft. We are proposing this AD to prevent fan drive shaft failure, leading to uncontained engine failure and damage to the airplane. DATES: We must receive comments on this proposed AD by December 2, 2011. 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 AD, contact GE-Aviation, M/D Rm. 285, One Neumann Way, Cincinnati, OH 45215, phone: 513–552–3272; e-mail: geae.aoc@ge.com. 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. srobinson on DSK4SPTVN1PROD with PROPOSALS 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 Certification Office, FAA, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7756; fax: 781– 238–7199; e-mail: john.frost@faa.gov. VerDate Mar<15>2010 16:08 Oct 17, 2011 Jkt 226001 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– 2011–0599; Directorate Identifier 2011– NE–19–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 a report of wear found on the seating surface of the CVD support ring and on the inside diameter of the fan drive shaft, where the two parts are in contact with each other. The wear was caused by relative motion between the CVD support assembly and the fan drive shaft during engine operation. The relative motion resulted from CVD support assemblies with improper sleeve thread lengths. This nonconformance was caused during manufacture, and the affected parts were released into service. A subpopulation of engines has been identified by engine S/N, that could have the same quality escape. Once removed, the CVD support assembly (consisting of self-locking nut, part number (P/N) 2226M57G03, threaded sleeve, P/N 2226M55P03, and support ring, P/N 2226M56P01) will be inspected for evidence of wear, and then never used again. This condition, if not corrected, could result in low-cyclefatigue failure of the fan drive shaft, leading to engine failure. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the condition described previously is unsafe and is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require: • First inspecting the seating surface of the CVD support ring for wear, and then inspecting the fan drive shaft PO 00000 Frm 00039 Fmt 4702 Sfmt 4702 inside diameter for wear, where the two parts come in contact with each other; • If wear is found on either the CVD support ring seating surface or the corresponding contact area inside the fan drive shaft, then removing the fan drive shaft from service; and • Removing from service all of the CVD support assemblies from the affected S/N engines identified in the proposed AD. Costs of Compliance We estimate that this proposed AD would affect 71 GE CF34–10E series turbofan engines installed on airplanes of U.S. registry. We also estimate that it would take about 8 work-hours per engine to perform a replacement of the CVD support assembly and visual inspections, and that the average labor rate is $85 per work-hour. A replacement CVD support assembly costs about $3,080. We estimate that two fan drive shafts would fail inspection and require replacement. A replacement fan drive shaft costs about $126,900. We estimate that no additional labor costs would be incurred to perform the required part replacements as the replacements are done at time of scheduled engine shop visit. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $520,760. 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 E:\FR\FM\18OCP1.SGM 18OCP1 Federal Register / Vol. 76, No. 201 / Tuesday, October 18, 2011 / Proposed Rules 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. failure, leading to uncontained engine failure and damage to the airplane. DEPARTMENT OF TRANSPORTATION (e) Compliance Federal Aviation Administration Comply with this AD before accumulating 11,500 total cycles-in-service on the engine, unless already done. 14 CFR Part 39 (f) Inspection and Removal From Service of CVD Support Assembly; and Determination of Fan Drive Shaft Serviceability Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Visually inspect the seating surface of the CVD support ring for wear. (1) If there is sign of wear on the CVD support ring, remove the CVD support assembly and the fan drive shaft from service before further flight. (2) If there is no sign of wear on the CVD support ring, remove the CVD support assembly from service and borescope inspect the inside diameter of the fan drive shaft at the CVD support ring contact area, for wear. (3) If there is sign of wear on the fan drive shaft, remove the fan drive shaft from service before further flight. The Proposed Amendment (g) Installation Prohibition Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: After the effective date of this AD, do not return to service any CVD support assembly (consisting of self-locking nut, P/N 2226M57G03, threaded sleeve, P/N 2226M55P03, and support ring, P/N 2226M56P01) removed from service as specified in this AD. List of Subjects in 14 CFR Part 39 PART 39—AIRWORTHINESS DIRECTIVES (h) Definition 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– 2011–0599; Directorate Identifier 2011– NE–19–AD. (a) Comments Due Date We must receive comments by December 2, 2011. (b) Affected ADs None. srobinson on DSK4SPTVN1PROD with PROPOSALS (c) Applicability This AD applies to General Electric Company (GE) CF34–10E series turbofan engines, serial number (S/N) 994116, and S/Ns 994118 through 994186 inclusive. (d) Unsafe Condition This AD was prompted by a report of heavy wear found on the seating surface of the center vent duct (CVD) (commonly referred to as center vent tube) support ring and on the inside diameter of the fan drive shaft at the mating location. The wear is caused by relative motion between the CVD support assembly (consisting of self-locking nut, part number (P/N) 2226M57G03, threaded sleeve, P/N 2226M55P03, and support ring, P/N 2226M56P01) and the fan drive shaft, during engine operation. We are issuing this AD to prevent fan drive shaft VerDate Mar<15>2010 16:08 Oct 17, 2011 Jkt 226001 64289 For the purposes of this AD, the phrase ‘‘any sign of wear’’ is defined as any visual indication of removal of parent material from the CVD seating surface or the fan drive shaft. (i) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (j) Related Information (1) For more information about this AD, contact John Frost, Aerospace Engineer, Engine Certification Office, FAA, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7756; fax: 781–238– 7199; e-mail: john.frost@faa.gov. (2) Refer to GE Service Bulletin No. CF34– 10E S/B 72–0188, for related information. Contact GE–Aviation, M/D Rm. 285, One Neumann Way, Cincinnati, OH 45215, phone: 513–552–3272; e-mail: geae.aoc@ge.com, for a copy of this service information. You may review copies of 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 October 6, 2011. Peter A. White, Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2011–26824 Filed 10–17–11; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00040 Fmt 4702 Sfmt 4702 [Docket No. FAA–2011–0956; Directorate Identifier 2011–NE–23–AD] RIN 2120–AA64 Airworthiness Directives; Thielert Aircraft Engines GmbH (TAE) TAE 125–02–99 and TAE 125–02–114 Reciprocating Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: SUMMARY: In-flight engine shutdown incidents have been reported on aeroplanes equipped with TAE 125 engines. Preliminary investigations showed that it was mainly the result of the sensitivity of friction disk Part Number (P/N) 05–7211–K010201 against possible misalignment of gearbox and core engine during assembly. This condition, if not corrected, could result in further cases of engine in-flight shutdown and consequent loss of control of the aeroplane. To address this unsafe condition, Thielert Aircraft Engines GmbH has developed a new friction disk. We are proposing this AD to prevent in-flight engine shutdown, which could result in loss of control of the airplane. DATES: We must receive comments on this proposed AD by December 2, 2011. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: 202–493–2251. Examining the AD Docket You may examine the AD docket on the Internet at http:// E:\FR\FM\18OCP1.SGM 18OCP1

Agencies

[Federal Register Volume 76, Number 201 (Tuesday, October 18, 2011)]
[Proposed Rules]
[Pages 64287-64289]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-26824]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0599; Directorate Identifier 2011-NE-19-AD]
RIN 2120-AA64


Airworthiness Directives; General Electric Company CF34-10E 
Series 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 
General Electric Company (GE) CF34-10E series turbofan engines. This 
proposed AD was

[[Page 64288]]

prompted by a report of heavy wear found on the seating surface of the 
center vent duct (CVD) (commonly referred to as center vent tube) 
support ring and on the inside diameter of the fan drive shaft at the 
mating location. This proposed AD would require removing from service 
CVD support assemblies from certain serial numbers (S/Ns) of CF34-10E 
series turbofan engines. This proposed AD would also require removing 
any fan drive shaft from service if wear is found on either the CVD 
support ring or the fan drive shaft. We are proposing this AD to 
prevent fan drive shaft failure, leading to uncontained engine failure 
and damage to the airplane.

DATES: We must receive comments on this proposed AD by December 2, 
2011.

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 AD, contact GE-Aviation, 
M/D Rm. 285, One Neumann Way, Cincinnati, OH 45215, phone: 513-552-
3272; e-mail: geae.aoc@ge.com. 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 
Certification Office, FAA, 12 New England Executive Park, Burlington, 
MA 01803; phone: 781-238-7756; fax: 781-238-7199; e-mail: 
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-2011-0599; 
Directorate Identifier 2011-NE-19-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 a report of wear found on the seating surface of the 
CVD support ring and on the inside diameter of the fan drive shaft, 
where the two parts are in contact with each other. The wear was caused 
by relative motion between the CVD support assembly and the fan drive 
shaft during engine operation. The relative motion resulted from CVD 
support assemblies with improper sleeve thread lengths. This 
nonconformance was caused during manufacture, and the affected parts 
were released into service. A subpopulation of engines has been 
identified by engine S/N, that could have the same quality escape. Once 
removed, the CVD support assembly (consisting of self-locking nut, part 
number (P/N) 2226M57G03, threaded sleeve, P/N 2226M55P03, and support 
ring, P/N 2226M56P01) will be inspected for evidence of wear, and then 
never used again. This condition, if not corrected, could result in 
low-cycle-fatigue failure of the fan drive shaft, leading to engine 
failure.

FAA's Determination

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

Proposed AD Requirements

    This proposed AD would require:
     First inspecting the seating surface of the CVD support 
ring for wear, and then inspecting the fan drive shaft inside diameter 
for wear, where the two parts come in contact with each other;
     If wear is found on either the CVD support ring seating 
surface or the corresponding contact area inside the fan drive shaft, 
then removing the fan drive shaft from service; and
     Removing from service all of the CVD support assemblies 
from the affected S/N engines identified in the proposed AD.

Costs of Compliance

    We estimate that this proposed AD would affect 71 GE CF34-10E 
series turbofan engines installed on airplanes of U.S. registry. We 
also estimate that it would take about 8 work-hours per engine to 
perform a replacement of the CVD support assembly and visual 
inspections, and that the average labor rate is $85 per work-hour. A 
replacement CVD support assembly costs about $3,080. We estimate that 
two fan drive shafts would fail inspection and require replacement. A 
replacement fan drive shaft costs about $126,900. We estimate that no 
additional labor costs would be incurred to perform the required part 
replacements as the replacements are done at time of scheduled engine 
shop visit. Based on these figures, we estimate the total cost of the 
AD to U.S. operators to be $520,760.

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

[[Page 64289]]

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-2011-0599; Directorate 
Identifier 2011-NE-19-AD.

(a) Comments Due Date

    We must receive comments by December 2, 2011.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to General Electric Company (GE) CF34-10E series 
turbofan engines, serial number (S/N) 994116, and S/Ns 994118 
through 994186 inclusive.

(d) Unsafe Condition

    This AD was prompted by a report of heavy wear found on the 
seating surface of the center vent duct (CVD) (commonly referred to 
as center vent tube) support ring and on the inside diameter of the 
fan drive shaft at the mating location. The wear is caused by 
relative motion between the CVD support assembly (consisting of 
self-locking nut, part number (P/N) 2226M57G03, threaded sleeve, P/N 
2226M55P03, and support ring, P/N 2226M56P01) and the fan drive 
shaft, during engine operation. We are issuing this AD to prevent 
fan drive shaft failure, leading to uncontained engine failure and 
damage to the airplane.

(e) Compliance

    Comply with this AD before accumulating 11,500 total cycles-in-
service on the engine, unless already done.

(f) Inspection and Removal From Service of CVD Support Assembly; and 
Determination of Fan Drive Shaft Serviceability

    Visually inspect the seating surface of the CVD support ring for 
wear.
    (1) If there is sign of wear on the CVD support ring, remove the 
CVD support assembly and the fan drive shaft from service before 
further flight.
    (2) If there is no sign of wear on the CVD support ring, remove 
the CVD support assembly from service and borescope inspect the 
inside diameter of the fan drive shaft at the CVD support ring 
contact area, for wear.
    (3) If there is sign of wear on the fan drive shaft, remove the 
fan drive shaft from service before further flight.

(g) Installation Prohibition

    After the effective date of this AD, do not return to service 
any CVD support assembly (consisting of self-locking nut, P/N 
2226M57G03, threaded sleeve, P/N 2226M55P03, and support ring, P/N 
2226M56P01) removed from service as specified in this AD.

(h) Definition

    For the purposes of this AD, the phrase ``any sign of wear'' is 
defined as any visual indication of removal of parent material from 
the CVD seating surface or the fan drive shaft.

(i) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA, has the authority 
to approve AMOCs for this AD, if requested using the procedures 
found in 14 CFR 39.19.

(j) Related Information

    (1) For more information about this AD, contact John Frost, 
Aerospace Engineer, Engine Certification Office, FAA, 12 New England 
Executive Park, Burlington, MA 01803; phone: 781-238-7756; fax: 781-
238-7199; e-mail: john.frost@faa.gov.
    (2) Refer to GE Service Bulletin No. CF34-10E S/B 72-0188, for 
related information. Contact GE-Aviation, M/D Rm. 285, One Neumann 
Way, Cincinnati, OH 45215, phone: 513-552-3272; e-mail: 
geae.aoc@ge.com, for a copy of this service information. You may 
review copies of 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 October 6, 2011.
Peter A. White,
Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-26824 Filed 10-17-11; 8:45 am]
BILLING CODE 4910-13-P