Document ID: FAA-2007-28319-0004
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; General Electric Company (GE) CF6- 80C2D1F Turbofan Engines
Posted Date: 2007-10-24T04:00Z

[Federal Register: October 24, 2007 (Volume 72, Number 205)]
[Rules and Regulations]               
[Page 60227-60228]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr24oc07-1]                         

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[[Page 60227]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28319; Directorate Identifier 2007-NE-27-AD; 
Amendment 39-15243; AD 2007-22-07]
RIN 2120-AA64

 
Airworthiness Directives; General Electric Company (GE) CF6-
80C2D1F Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for GE 
CF6-80C2D1F turbofan engines, installed on, but not limited to, 
McDonnell Douglas Corporation MD-11 series airplanes. This AD requires 
removing previous software versions from the engine electronic control 
unit (ECU). Engines with new version software will have increased 
margin to flameout. This AD results from reports of engine flameout 
events during flight, including reports of events where all engines 
simultaneously experienced a flameout or other adverse operation. 
Although the root cause investigation is not yet complete, we believe 
that exposure to ice crystals during flight is associated with these 
flameout events. We are issuing this AD to minimize engine flameout 
caused by ice accretion and shedding during flight.

DATES: This AD becomes effective November 28, 2007.

ADDRESSES: You can get the service information identified in this AD 
from General Electric Company via Lockheed Martin Technology Services, 
10525 Chester Road, Suite C, Cincinnati, Ohio 45215, telephone (513) 
672-8400, fax (513) 672-8422.
    The Docket Operations office is located at U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: John Golinski, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
john.golinski@faa.gov; telephone: (781) 238-7135, fax: (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed AD. The proposed AD applies to GE CF6-80C2D1F turbofan 
engines, installed on McDonnell Douglas Corporation MD-11 series 
airplanes. We published the proposed AD in the Federal Register on July 
17, 2007 (72 FR 39039). That action proposed to require removing 
previous software versions from the engine ECU.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov
; or in person at the Docket Operations office 

between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is the same as 
the Mail address provided in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments received.

Request for Clarification

    Boeing and GE request clarification of the statement that the AD 
action results from reports of engine flameout events during flight, 
including reports of events where all engines simultaneously 
experienced a flameout or other adverse operation. The commenters point 
out that there have been no all-engine flameout events on MD-11 series 
airplanes.
    We disagree. While we agree that no all-engine flameout events on 
the MD-11 have occurred, single and multiple engine flameout events 
have taken place. We did not change the AD.

Conclusion

    We have carefully reviewed the available data, including the 
comments received, and determined that air safety and the public 
interest require adopting the AD as proposed.

Costs of Compliance

    We estimate that this AD will affect 175 CF6-80C2D1F turbofan 
engines installed on McDonnell Douglas Corporation MD-11 series 
airplanes of U.S. registry. We estimate it will take about 6 work-hours 
per ECU. The average labor rate is $80 per work-hour. Based on these 
figures, we estimate the cost to U.S. operators to be $63,120. Our cost 
estimate is exclusive of warranty coverage.

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 have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will 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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;

[[Page 60228]]

    (2) Is not a ``significant rule'' under 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 summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary at the 
address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends 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 adding the following new airworthiness 
directive:

2007-22-07 General Electric Company: Amendment 39-15243. Docket No. 
FAA-2007-28319; Directorate Identifier 2007-NE-27-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective November 
28, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to General Electric Company (GE) CF6-80C2D1F 
turbofan engines, installed on, but not limited to, McDonnell 
Douglas Corporation MD-11 series airplanes.

Unsafe Condition

    (d) This AD results from reports of engine flameout events 
during flight, including reports of events where all engines 
simultaneously experienced a flameout or other adverse operation. We 
are issuing this AD to minimize engine flameout due to ice accretion 
and shedding during flight. Exposure to ice crystals during flight 
is believed to be associated with these flameout events.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified unless the 
actions have already been done.

Interim Action

    (f) These actions are interim actions due to the on-going 
investigation, and we may take further rulemaking actions in the 
future based on the results of the investigation and field 
experience.

Engine Electronic Control Unit (ECU) Software Removal

    (g) At the next shop visit of the engine or of the ECU, 
whichever occurs first, and not to exceed 60 months from the 
effective date of this AD, remove the following software versions 
from the ECUs:

               Table 1.--Removal of ECU Software Versions
------------------------------------------------------------------------
         Software version                 Installed in ECU Part No.
------------------------------------------------------------------------
(1) 8.5.A.........................  1851M51P01, 1851M51P02, 1851M52P01,
                                     1851M52P02, 1851M53P01, 1851M53P02
(2) 8.3C..........................  1471M69P01, 1471M69P02, 1519M91P01
(3) 8.3.D.........................  1519M91P02
(4) 8.3.E.........................  1519M91P03, 1519M91P04
(5) 8.3.F.........................  1519M91P05
(6) 8.3.G.........................  1519M91P06, 1820M34P01
(7) 8.3.H.........................  1519M91P07, 1820M34P02
(8) 8.3.J.........................  1519M91P09, 1519M91P10, 1820M34P04,
                                     1820M34P05
------------------------------------------------------------------------

Previous Software Versions of ECU Software

    (h) For a period of 24 months after the effective date of this 
AD, once an ECU containing a software version not listed in Table 1 
of this AD is installed on an engine, that ECU can be replaced with 
an ECU containing a previous version of software listed in Table 1.
    (i) Once the software version listed in Table 1 of this AD has 
been removed and new FAA-approved software version is installed in 
an ECU, reverting to those older software versions in that ECU is 
prohibited.
    (j) After 60 months from the effective date of this AD, use of 
an ECU with a software version listed in Table 1 of this AD is 
prohibited.

Definitions

    (k) For the purposes of this AD:
    (1) Next shop visit of the ECU is when the ECU is removed from 
the engine for overhaul or maintenance after the effective date of 
this AD.
    (2) Next shop visit of the engine is when the engine is removed 
from the airplane for maintenance in which a major flange is 
disassembled after the effective date of this AD. The following 
engine maintenance actions, either separately or in combination with 
each other, are not considered a next shop visit of the engine:
    (i) Removal of the upper high pressure compressor (HPC) stator 
case solely for airfoil maintenance.
    (ii) Module-level inspection of the HPC rotor stages 3-9 spool.
    (iii) Replacement of stage 5 HPC variable stator vane bushings 
or lever arms.
    (iv) Removal of the accessory gearbox.
    (v) Replacement of the inlet gearbox polytetrafluoroethylene 
seal.

Alternative Methods of Compliance

    (l) The Manager, Engine Certification Office, has the authority 
to approve alternative methods of compliance for this AD if 
requested using the procedures found in 14 CFR 39.19.

Special Flight Permits

    (m) Special flight permits are not authorized.

Related Information

    (n) Information on removing ECU software and installing new 
software, which provides increased margin to flameout, can be found 
in GE Service Bulletin No. CF6-80C2 S/B 73-0351, dated April 11, 
2007.
    (o) Contact John Golinski, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
john.golinski@faa.gov; telephone: (781) 238-7135, fax: (781) 238-

7199, for more information about this AD.

    Issued in Burlington, Massachusetts, on October 17, 2007.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E7-20813 Filed 10-23-07; 8:45 am]

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