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[Federal Register Volume 77, Number 156 (Monday, August 13, 2012)]
[Proposed Rules]
[Pages 48110-48111]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-19824]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0817; Directorate Identifier 99-NE-24-AD]
RIN 2120-AA64

Airworthiness Directives; General Electric Company Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede an existing airworthiness directive 
(AD) that applies to certain General Electric Company (GE) CF6-80C2 
series turbofan engines. The existing AD requires replacement of the 
fuel tubes connected to the fuel flowmeter. Since we issued that AD, we 
received several additional reports of fuel leaks and two reports of 
engine fire due to mis-assembled supporting brackets on the fuel tube 
connecting the flowmeter to the Integrated Drive Generator (IDG) fuel-
oil cooler. This proposed AD would require installing a new simplified 
one-piece bracket to eliminate mis-assembly. We are proposing this AD 
to prevent high-pressure fuel leaks caused by improper seating of fuel 
tube flanges, which could result in an engine fire and damage to the 
airplane.

DATES: We must receive comments on this proposed AD by October 12, 
2012.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal Rulemaking 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 General 
Electric Company, GE-Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 
45215, phone: (513) 552-3272; email: geae.aoc@ge.com. 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.

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: Jason Yang, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; phone: 781-238-7747; fax: 
781-238-7199; email: jason.yang@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2012-0817; 
Directorate Identifier 99-NE-24-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

    On February 17, 2000, we issued AD 2000-04-14, Amendment 39-11597 
(65 FR 10698, February 29, 2000), for all GE CF6-80C2 series turbofan 
engines. That AD requires replacement of the fuel tube connecting the 
fuel flowmeter to the IDG fuel-oil cooler and the fuel tubes connecting 
the fuel flowmeter to the Main Engine Control (MEC) or Hydromechanical 
Unit (HMU) with improved fuel tubes. That AD resulted from reports of 
fuel leaking in the core cowl cavity under high pressure that can be 
ignited by contact with hot engine case surfaces. We issued that AD to 
prevent high-pressure fuel leaks caused by improper seating of fuel 
tube flanges, which could result in an engine fire and damage to the 
airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 2000-04-14, Amendment 39-11597 (65 FR 10698, 
February 29, 2000), we received several reports of fuel leaks and two 
reports of engine fire due to mis-assembled supporting brackets on the 
fuel tube connecting the fuel flowmeter to the IDG fuel-oil cooler. 
Investigation of these two fires determined the root cause was due to a 
design shortfall, which allowed improper installation of the two-piece 
bracket and subsequent fuel leaks from the fuel tube connection.

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 replacement of the fuel tube 
connecting the fuel flowmeter to the IDG fuel-oil cooler and the fuel 
tubes connecting the fuel flowmeter to the MEC or HMU with improved 
fuel tubes. This proposed AD would also require installing a simplified 
one-piece bracket to eliminate mis-assembly when the fuel tubes 
connecting the fuel flowmeter to the IDG fuel-oil cooler are 
disconnected.

Costs of Compliance

    We estimate that this proposed AD would affect 2,300 CF6-80C2 
engines installed on airplanes of U.S. registry. We also estimate that 
one work-hour would be required per engine to accomplish the actions 
required by this AD. The average labor rate is $85 per work-hour. We 
also estimate that the required parts will cost about $180 per engine. 
Based on these figures, we estimate the total cost of the proposed AD 
to U.S. operators is $609,500.

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,

[[Page 48111]]

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 have 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 that the 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 removing airworthiness directive 
(AD) 2000-04-14, Amendment 39-11597 (65 FR 10698, February 29, 2000), 
and adding the following new AD:

General Electric Company: Docket No. FAA-2012-0817; Directorate 
Identifier 99-NE-24-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by October 12, 
2012.

(b) Affected ADs

    This AD supersedes AD 2000-04-14, Amendment 39-11597 (65 FR 
10698, February 29, 2000).

(c) Applicability

    This AD applies to all General Electric Company (GE) CF6-80C2 
A1/A2/A3/A5/A8/A5F/B1/B2/B4/B6/B1F/B2F/B4F/B6F/B7F/D1F turbofan 
engines with fuel tubes, part number (P/N) 1321M42G01, 1334M88G01, 
1374M30G01 or 1383M12G01, or supporting bracket, P/N 1321M88P001A, 
installed.

(d) Unsafe Condition

    This AD was prompted by several reports of fuel leaks and two 
reports of fire due to mis-assembled supporting brackets on the fuel 
tube connecting the fuel flowmeter to the Integrated Drive Generator 
(IDG) fuel-oil cooler. We are issuing this AD to prevent high-
pressure fuel leaks caused by improper seating of fuel tube flanges, 
which could result in an engine fire and damage to the airplane.

(e) Compliance

    Unless already done, do the following.

(f) Replacement

    After the effective date of this AD, if the fuel tubes are 
disconnected for any reason, or at the next engine shop visit, 
whichever occurs first, replace the fuel tubes and brackets with 
improved tubes and brackets eligible for installation. Do the 
following:
    (1) Replace the fuel flowmeter to IDG fuel-oil cooler fuel tube, 
P/N 1321M42G01, with a part eligible for installation.
    (2) For engines with Power Management Controls, replace the Main 
Engine Control (MEC) to fuel flowmeter fuel tube, P/N 1334M88G01, 
and bolts, P/N MS9557-12, with a part eligible for installation.
    (3) For engines with Full Authority Digital Electronic Controls, 
replace the Hydromechanical Unit (HMU) to fuel flowmeter fuel tubes, 
P/Ns 1383M12G01 and 1374M30G01, with a part eligible for 
installation.
    (4) Replace supporting bracket, P/N 1321M88P001A, and spray 
shields, P/Ns 1606M57G01 and 1775M61G01, with one-piece supporting 
bracket, P/N 2021M83G01.
    (5) Perform an idle leak check after accomplishing paragraphs 
(f)(1), (f)(2), (f)(3) or (f)(4), or any combination thereof.

(g) Definition

    For the purpose of this AD, an engine shop visit is defined as 
the induction of an engine into the shop for any reason.

(h) Prohibition

    After the effective date of this AD, do not install any of the 
following parts into any GE CF6-80C2 series turbofan engines: P/Ns 
1321M42G01, 1321M88P001A, 1334M88G01, 1374M30G01, 1383M12G01, 
1606M57G01, 1775M61G01, and MS9557-12.

(i) Alternative Methods of Compliance (AMOCs)

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

(j) Related Information

    For more information about this AD, contact Jason Yang, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: 781-238-7747; fax: 781-238-7199; email: 
jason.yang@faa.gov.

    Issued in Burlington, Massachusetts, on July 31, 2012.
Diane Cook,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-19824 Filed 8-10-12; 8:45 am]
BILLING CODE 4910-13-P
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