Federal Register / Vol. 77, No. 240 / Thursday, December 13, 2012 / Proposed Rules 74125 

(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 

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. 


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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. 

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. 

§ 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. 

(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 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: 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 


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