[Federal Register Volume 79, Number 12 (Friday, January 17, 2014)]
[Proposed Rules]
[Pages 3139-3142]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-00833]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28413; Directorate Identifier 2007-NE-25-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 airworthiness directives (ADs) 90-26-
01, 91-20-02, and 2009-05-02, which apply to all General Electric 
Company (GE) CF6-80C2 and CF6-80E1 series turbofan engines. Since we 
issued ADs 90-26-01, 91-20-02, and 2009-05-02, we received a report of 
an undercowl fire caused by a manifold high-pressure fuel leak, and 
several additional reports of fuel leaks. This proposed AD would 
require additional repetitive inspections, replacement of tube (block) 
clamp, and inspection of fuel manifolds for wear at each tube (block) 
clamp location. We are proposing this AD to

[[Page 3140]]

prevent failure of the fuel manifold, which could lead to uncontrolled 
engine fire, engine damage, and damage to the airplane.

DATES: We must receive comments on this proposed AD by March 3, 2014.

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 Company, GE Aviation, Room 285, 1 Neumann Way, 
Cincinnati, OH 45215; phone: 513-552-3272; email: [email protected]. 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.

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-2007-
28413; 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: Kasra Sharifi, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA. 01830; phone 781-238-7773; 
fax: 781-238-7199; email: [email protected].

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-2007-
28413; Directorate Identifier 2007-NE-25-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 December 20, 1990, we issued AD 90-26-01 (55 FR 49611, November 
30, 1990), for GE CF6-80C2 series turbofan engines. That AD requires 
replacing fuel manifold, part numbers (P/Ns) 1303M31G04 and 1303M32G04, 
within 30 calendar days after the effective date of the AD. That AD 
resulted from a report of an engine fire.
    On November 15, 1991, we issued AD 91-20-02 (56 FR 55231, October 
25, 1991), for the same engines. That AD requires replacing fuel 
manifold, P/Ns 1303M31G06, 1303M32G06, 1303M31G07, 1303M32G07, 
1303M31G08, and 1303M32G08, at the next engine removal, but no later 
than June 30, 1993. That AD also resulted from a report of an engine 
fire.
    On March 31, 2009, we issued AD 2009-05-02 (74 FR 8161, February 
24, 2009), for GE CF6-80C2 and CF6-80E1 series turbofan engines with 
fuel manifolds, P/Ns 1303M31G12 and 1303M32G12, installed in drainless 
fuel manifold assemblies. That AD requires removing the loop clamps 
that hold the fuel manifold to the compressor rear frame damper 
brackets, inspecting the fuel manifold for wear at each clamp location, 
and replacing the clamps with new zero-time parts. That AD also 
requires revising the Airworthiness Limitations Section to require 
repetitive fuel manifold inspection and loop clamp replacement. That AD 
resulted from reports of fuel leaks during engine operation.
    We issued these ADs to prevent failure of the fuel manifold, which 
could lead to uncontrolled engine fire, engine damage, and damage to 
the airplane. We are superseding these ADs to eliminate potentially 
confusing and contradictory requirements in these ADs. This proposed AD 
expands the inspection mandated by AD 2009-05-02 and it expands the 
list of banned fuel manifolds mandated by AD 90-26-01 and AD 91-20-02.

Actions Since Previous ADs Were Issued

    Since we issued AD 90-26-01 (55 FR 49611, November 30, 1990); AD 
91-20-02 (56 FR 55231, October 25, 1991); and AD 2009-05-02 (74 FR 
8161, February 24, 2009); we received a report of an undercowl fire 
caused by a fuel manifold high-pressure fuel leak in engine model CF6-
80C2, and several additional reports of fuel leaks; four in the CF6-
80C2 and one in the CF6-80E1 model engine.

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 retain the requirements of AD 90-26-01 (55 
FR 49611, November 30, 1990); and AD 91-20-02 (56 FR 55231, October 25, 
1991); to remove certain fuel manifold P/Ns, and the requirements of AD 
2009-05-02 (74 FR 8161, February 24, 2009); to inspect certain fuel 
manifold P/Ns and replace certain consumable components. This proposed 
AD would add a requirement to inspect an additional fuel manifold 
configuration and replacement of certain loop clamps. This proposed AD 
would also require repetitive inspection and replacement of tube 
(block) clamp, and inspection of the fuel manifold for wear at each 
tube (block) clamp location. This proposed AD would also require 
removing certain drainless fuel manifold assembly P/Ns from service.

Costs of Compliance

    We estimate that this proposed AD would affect 1,126 engines 
installed on airplanes of U.S. registry. We also estimate that required 
parts cost about $34,894 per engine. We also estimate that is would 
take about 6 hours to accomplish the actions required by this AD. The 
average labor rate is $85 per hour. Based on these figures, we estimate 
the total cost of the proposed AD to U.S. operators to be $39,864,904.

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,

[[Page 3141]]

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 proposed 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 to the extent 
that it justifies making a regulatory distinction, 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:
0
a. Removing airworthiness directive (AD) 90-26-01 (55 FR 49611, 
November 30, 1990); AD 91-20-02 (56 FR 55231, October 25, 1991); and AD 
2009-05-02 (74 FR 8161, February 24, 2009); and
0
b. Adding the following new AD:

General Electric Company: Docket No. FAA-2007-28413; Directorate 
Identifier 2007-NE-25-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by March 3, 
2014.

(b) Affected ADs

    This AD supersedes AD 90-26-01 (55 FR 49611, November 30, 1990); 
AD 91-20-02 (56 FR 55231, October 25, 1991); and AD 2009-05-02 (74 
FR 8161, February 24, 2009).

(c) Applicability

    This AD applies to all General Electric Company (GE) CF6-80C2 
and CF6-80E1 turbofan engines with fuel manifold, part numbers (P/
Ns) 1303M31G04,1303M32G04, 1303M31G06, 1303M32G06, 1303M31G07, 
1303M32G07, 1303M31G08, 1303M32G08,1308M31G12, 1308M32G12, 
2420M70G01, and 2420M71G01, installed.

(d) Unsafe Condition

    This AD was prompted by a report of an undercowl fire caused by 
a fuel manifold high-pressure fuel leak, and several additional 
reports of fuel leaks. We are issuing this AD to prevent failure of 
the fuel manifold, which could lead to uncontrolled engine fire, 
engine damage, and damage to the airplane.

(e) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Fuel Manifold Removal.
    (i) For CF6-80C2 and CF6-80E1 series engines, before further 
flight after the effective date of this AD, remove fuel manifold, P/
Ns 1303M31G04, 1303M32G04, 1303M31G06, 1303M32G06, 1303M31G07, 
1303M32G07, 1303M31G08, and 1303M32G08, from service.
    (ii) For CF6-80C2 and CF6-80E1 series engines, at the next 
engine shop visit after effective date of this AD, remove fuel 
manifold, P/Ns 1303M31G12, 1303M32G12, 2420M70G01, and 2420M71G01, 
from service.
    (2) Fuel Manifold, Loop Clamp, and Tube (Block) Clamp Inspection 
and Replacement--Drainless Assembly.
    (i) For CF6-80C2 series engines, with fuel manifold, P/N 
1303M31G12 or 1303M32G12, installed, refer to Table 1 to paragraph 
(e) of this AD, accomplish the initial inspections of the fuel 
manifold and replacement of the loop clamps in accordance with 
paragraphs 3.A and 3.D of GE Service Bulletin (SB) CF6-80C2 S/B 73-
0326, Revision 4, dated December 23, 2009.
    (ii) For CF6-80C2 series engines, with fuel manifold, P/Ns 
2420M70G01 or 2420M71G01, installed, refer to Table 1 to paragraph 
(e) of this AD, accomplish the initial inspection of the fuel 
manifold and replacement of the loop clamps in accordance with 
paragraphs 3.C and 3.D of GE SB CF6-80C2 S/B 73-0326, Revision 4, 
dated December 23, 2009.
    (iii) For CF6-80E1 series engines, with fuel manifold, P/Ns 
1303M31G12 or 1303M32G12, installed, refer to Table 1 to paragraph 
(e) of this AD, accomplish the initial inspection of the fuel 
manifold and replacement of the loop clamps in accordance with 
paragraphs 3.A and 3.C of GE SB CF6-80E1 S/B 73-0061, Revision 4, 
dated December 23, 2009.
    (iv) For CF6-80E1 series engines, with fuel manifold P/Ns 
2420M70G01 or 2420M71G01 installed, refer to Table 1 to paragraph 
(e) of this AD, accomplish the initial inspection of the fuel 
manifold and replacement of the loop clamps in accordance with 
paragraphs 3.B and 3.C of GE SB CF6-80E1 S/B 73-0061, Revision 4, 
dated December 23, 2009.
    (v) Thereafter, inspect fuel manifolds P/Ns 1303M31G12, 
1303M32G12, 2420M70G01, and 2420M71G01 installed, within every 7,500 
flight hours (FH) since the last inspection, in accordance with 
paragraphs (e)(2)(i) through (e)(2)(iv) of this AD.

    Table 1 to Paragraph (e)--Fuel Manifold Inspection and Loop Clamp
                   Replacement and Inspection Criteria
------------------------------------------------------------------------
                  If:                                 Then:
------------------------------------------------------------------------
1--If the engine was previously
 inspected using any of the following:
     GE SB CF6-80C2 SB 73-0326   Then inspect fuel manifold and
     R04, Revision 4, dated December      replace clamps within 7,500
     23, 2009;                            flight hours (FH) time-since-
                                          last-inspection (TSLI) or
                                          within 6 months after the
                                          effective date of this AD,
                                          whichever occurs first.
     GE SB CF6-80C2 SB 73-0326,
     Revision 3, dated April 24, 2009;
     GE SB CF6-80E1 SB 73-0061
     R04, Revision 4, dated December
     23, 2009 or;
     GE SB CF6-80E1 SB 73-0061,
     Revision 3, dated April, 24, 2009.
2--If the loop clamps installed at last
 shop visit were previously used or of
 unknown heritage or the engine was
 previously inspected using either of
 the following:

[[Page 3142]]

 
     GE CF6-80C2 SB 73-0326,     Then inspect fuel manifold and
     Revision 2, dated August 30, 2007    replace clamps within 1,750 FH
     or earlier;                          time-since-last-shop-visit or
                                          within 4 months after the
                                          effective date of this AD,
                                          whichever occurs first.
     GE CF6-80E1 SB 73-0061,
     Revision 2, dated August 30, 2007
     or earlier.
3--If the engine is a first-run engine,  Then inspect fuel manifold and
 an engine with zero-time, or has new     replace clamps within 7,500 FH
 loop clamps previously installed on-     time-since-new or since zero-
 wing or at shop visit.                   time that new loop clamps were
                                          installed.
4--If the engine has already exceeded    Then inspect fuel manifold and
 the 1,750 FH initial inspection          replace clamps within 4,500 FH
 threshold on the effective date of       TSLI or 4 months after the
 this AD but has fewer than 4,500         effective date of this AD,
 flight hours TSLI.                       whichever occurs first.
5--If the engine has already exceeded    Then inspect fuel manifold and
 the 4,500 FH initial inspection          replace clamps within 4 months
 threshold on the effective date of       after the effective date of
 this AD.                                 this AD.
------------------------------------------------------------------------

    (3) For CF6-80C2 series engines, with fuel manifold, P/Ns 
1303M31G12, 1303M32G12, 2420M70G01, or 2420M71G01, with tube (block) 
clamp, P/N 1153M26G15, refer to Table 2 to paragraph (e) of this AD, 
accomplish the initial inspection of the fuel manifold and tube 
(block) clamp, and replacement of the fuel manifold and tube (block) 
clamp, if required based on inspection results, in accordance with 
paragraph 3.A of GE SB CF6-80C2 S/B 73-0414, dated July 2, 2013.
    (4) For CF6-80E1 series engines, with fuel manifold, P/Ns 
1303M31G12, 1303M32G12, 2420M70G01, or 2420M71G01, with tube (block) 
clamp, P/N 1153M26G15, refer to Table 2 to paragraph (e) of this AD, 
accomplish the initial inspections of the fuel manifold and tube 
(block) clamp, and replacement of the fuel manifold and tube (block) 
clamp, if required based on inspection results, in accordance with 
paragraph 3.A of GE SB CF6-80E1 S/B 73-0121, dated July 2, 2013.
    (5) Thereafter, inspect fuel manifold, P/Ns 1303M31G12, 
1303M32G12, 2420M70G01, and 2420M71G01, within every 7,500 flight 
hours (FH) since the last inspection, in accordance with paragraphs 
(e)(3) and (e)(4) of this AD.

     Table 2 to Paragraph (e)--Fuel Manifold and Tube (Block) Clamp
                   Inspection and Replacement Criteria
------------------------------------------------------------------------
                  If:                                 Then:
------------------------------------------------------------------------
1--If the engine is a first run engine
 or the engine was previously inspected
 using either of the following:
     GE SB CF6-80C2 S/B 73-      Then inspect clamps and replace
     0414, dated July 2, 2013;            within 7,500 FH TSLI.
     GE SB CF6-80E1 S/B 73-0121
     dated July 02, 2013.
2--If the engine has already exceeded    Then inspect clamps and replace
 the 7,500 FH initial inspection          within 3 months after the
 threshold on the effective date of       effective date of this AD.
 this AD.
------------------------------------------------------------------------

(f) Prohibition Statement

    After the effective date of this AD, do not install fuel 
manifold, P/Ns 1308M31G04, 1303M32G04, 1303M31G06, 1303M32G06, 
1303M31G07, 1303M32G07, 1303M31G08, 1303M32G08, 1308M31G12, 
1308M32G12, 2420M70G01, or 2420M71G01, on any engine.

(g) Definition

    For the purpose of this AD, an engine shop visit is the 
induction of an engine into the shop for maintenance involving 
separation of pairs of major mating engine flanges (lettered 
flanges), except that the separation of engine flanges solely for 
the purposes of transporting the engine without subsequent engine 
maintenance does not constitute an engine shop visit.

(h) 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. Previously approved AMOCs for AD 2009-05-02 (74 FR 8161, 
February 24, 2009) remain approved for the corresponding 
requirements of paragraphs (e)(1) through (e)(5) of this AD.

(i) Related Information

    (1) For more information about this AD, contact Kasra Sharifi, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01830; phone 781-238-7773; fax: 781-238-7199; email: 
[email protected].
    (2) General Electric Service Bulletin (SB) CF6-80C2 S/B 73-0326, 
Revision 4, dated December 23, 2009, SB CF6-80E1 S/B 73-0061, 
Revision 4, dated December 23, 2009, SB CF6-80C2 S/B 73-0414, dated 
July 2, 2013, and SB CF6-80E1 S/B 73-0121, dated July 2, 2013, 
pertain to the subject of this AD and can be obtained from GE using 
the contact information in paragraph (i)(3) of this AD.
    (3) 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: [email protected].
    (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, 24, 2013.
Frank P. Paskiewicz,
Acting Director, Aircraft Certification Service.
[FR Doc. 2014-00833 Filed 1-16-14; 8:45 am]
BILLING CODE 4910-13-P