

[Federal Register: September 11, 2007 (Volume 72, Number 175)]
[Rules and Regulations]               
[Page 51697-51699]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr11se07-1]                         


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Rules and Regulations
                                                Federal Register
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[[Page 51697]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28726; Directorate Identifier 2007-NE-32-AD; 
Amendment 39-15190; AD 2007-18-10]
RIN 2120-AA64

 
Airworthiness Directives; General Electric Company CF6-80E1 
Series Turbofan Engines

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

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
General Electric Company (GE) CF6-80E1 series turbofan engines with 
certain part number (P/N) compressor rear frames (CRFs) installed. This 
AD requires revisions to the Airworthiness Limitations Section (ALS) of 
the manufacturer's Instructions for Continued Airworthiness (ICA) and 
air carrier's approved Continued Airworthiness Maintenance Programs 
(CAMP) to include initial and repetitive eddy current inspections 
(ECIs) or fluorescent penetrant inspections (FPIs) of the affected 
CRFs. This AD results from the need to require enhanced inspections of 
the CF6-80E1 series engine CRFs for cracks. We are issuing this AD to 
prevent rupture of the CRF, which could result in an under-cowl engine 
fire.

DATES: This AD becomes effective September 26, 2007.
    We must receive any comments on this AD by November 13, 2007.

ADDRESSES: Use one of the following addresses to comment on this AD:
     DOT Docket Web site: Go to http://dms.dot.gov and follow 

the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov
 and follow the instructions for sending your 

comments electronically.
     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.
     Fax: (202) 493-2251.
    Contact General Electric Company via Lockheed Martin Technology 
Services, 10525 Chester Road, Suite C, Cincinnati, Ohio 45215, 
telephone (513) 672-8400, fax (513) 672-8422, for the service 
information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
Robert.green@faa.gov; telephone (781) 238-7754; fax (781) 238-7199.


SUPPLEMENTARY INFORMATION: GE recently reassessed the original basis 
for certification of the CF6-80E1 series turbofan engine CRFs, using 
updated techniques and materials. The data revealed that the stresses 
in critical areas of the CRF are higher than originally calculated. 
This condition, if not corrected, could result in rupture of the CRF, 
possibly resulting in an under-cowl engine fire.

FAA's Determination and Requirements of This AD

    Although no airplanes that are currently registered in the United 
States use these CF6-80E1 series turbofan engines, the possibility 
exists that the engines could be used on airplanes that are registered 
in the United States in the future. The unsafe condition described 
previously is likely to exist or develop on other engines of the same 
type design. We are issuing this AD to prevent rupture of the CRF, 
which could result in an under-cowl engine fire. This AD requires 
revisions to the ALS of the manufacturer's ICA and air carrier's 
approved CAMP to include required ECIs or FPIs of those certain P/N 
CRFs, for cracks in critical areas.

FAA's Determination of the Effective Date

    Since there are currently no domestic operators of this engine 
model, notice and opportunity for public comment before issuing this AD 
are unnecessary. A situation exists that allows the immediate adoption 
of this regulation.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment. However, we invite you to send us any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. FAA-2007-28726; 
Directorate Identifier 2007-NE-32-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify it.
    We will post all comments we receive, without change, to http://dms.dot.gov
, including any personal information you provide. We will 

also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this AD. Using the search function of the DMS Web 
site, anyone can find and read the comments in any of our dockets, 
including the name of the individual who sent the comment (or signed 
the comment on behalf of an association, business, labor union, etc). 
You may review the DOT's complete Privacy Act Statement in the Federal 
Register published on April 11, 2000 (65 FR 19477-78) or you may visit 
http://dms.dot.gov.


Examining the AD Docket

    You may examine the AD docket on the Internet at http://dms.dot.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 provided in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

[[Page 51698]]

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;
    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 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

    Under the authority delegated to me by the Administrator, the 
Federal Aviation Administration amends part 39 of the Federal Aviation 
Regulations (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:

2007-18-10 General Electric Company: Amendment 39-15190. Docket No. 
FAA-2007-28726; Directorate Identifier 2007-NE-32-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective 
September 26, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to General Electric Company (GE) CF6-80E1A1, 
CF6-80E1A2, CF6-80E1A3, CF6-80E1A4, and CF6-80E1A4/B model turbofan 
engines with compressor rear frame (CRF) part numbers (P/Ns) 
1520M26G03/G06/G08/G11/G12 installed. These engines are installed 
on, but not limited to, Airbus Industrie A330 series airplanes.

Unsafe Condition

    (d) This AD results from the need to require enhanced 
inspections of the CF6-80E1 series turbofan engine CRFs, for cracks. 
We are issuing this AD to prevent rupture of the CRF, which could 
result in an under-cowl engine fire.

Compliance

    (e) Within the next 30 days after the effective date of this AD, 
revise GE's Instructions for Continued Airworthiness ALS, and for 
air carrier operations, revise the approved continuous airworthiness 
maintenance program, by adding the information in Table 1 and in 
paragraphs (f) through (i) of this AD.

                Table 1.--Inspection Compliance Schedule
------------------------------------------------------------------------
If CRF P/Ns 1520M26G03/G06/G08/   Then initially      And repetitively
         G11/G12 are:                inspect:             inspect:
------------------------------------------------------------------------
(1) Operated at a CF6-80E1A3    Before 12,200      Within every 6,300
 or CF6-80E1A4/B engine rating.  cycles-since-new   cycles-since-last-
                                 (CSN).             inspection (CSLI),
                                                    except that igniter
                                                    pad holes on CRFs
                                                    with P/Ns 1520M26G03/
                                                    G06/G08, must be
                                                    inspected within
                                                    every 4,800 CSLI.
(2) Operated at a CF6-80E1A4    Before 13,700 CSN  Within every 6,300
 engine rating.                                     CSLI, except that
                                                    igniter pad holes on
                                                    CRFs with P/Ns
                                                    1520M26G03/G06/G08,
                                                    must be inspected
                                                    within every 6,100
                                                    CSLI.
(3) Operated at a CF6-80E1A1    Before 14,200 CSN  Within every 6,300
 or CF6-80E1A2 engine rating.                       CSLI.
------------------------------------------------------------------------

Module-Level Inspection of CRFs

    (f) For CRF P/Ns 1520M26G03/G06/G08/G11/G12, at module level:
    (1) Clean and eddy current inspect (ECI) the locations numbered 
3 through 8.
    (2) Information on these locations can be found in figure 801, 
sheets 2, 3, and 4, of CF6-80E1 Engine Manual No. GEK 99376, Section 
05-21-01. The remaining engine manual references in this AD are to 
No. GEK 99376.
    (3) Information on cleaning and ECI can be found in CF6-80E1 
Engine Manual, Section 72-00-34, COMPRESSOR REAR FRAME ASSEMBLY--
INSPECTION 001, Subtask 72-00-34-250-001.
    (4) For CRF P/Ns 1520M26G03/G06/G08, clean and fluorescent 
penetrant inspect (FPI) the locations numbered 1 and 2.
    (5) Information on these locations can be found in figure 801, 
sheet 1, of CF6-80E1 Engine Manual, Section 05-21-01.
    (6) Information on cleaning and FPI can be found in CF6-80E1 
Engine Manual, Section 72-00-34, COMPRESSOR REAR FRAME ASSEMBLY--
INSPECTION 001, Subtask 72-00-34-230-051.

Piece-Part Level Inspection of CRFs

    (g) For CRF P/Ns 1520M26G03/G06/G08/G11/G12, at piece-part 
level:
    (1) Clean and FPI the locations numbered 3 through 8.
    (2) Information on these locations can be found in figure 801, 
sheets 2, 3, and 4, of CF6-80E1 Engine Manual, Section 05-21-01.
    (3) Information on cleaning and FPI can be found in CF6-80E1 
Engine Manual, Section 72-34-01, COMPRESSOR REAR FRAME--INSPECTION 
001, Subtask 72-34-01-200-003.
    (4) For CRF P/Ns 1520M26G03/G06/G08, clean and FPI the locations 
numbered 1 and 2.
    (5) Information on these locations can be found in figure 801, 
sheet 1, of CF6-80E1 Engine Manual, Section 05-21-01.
    (6) Information on cleaning and FPI can be found in CF6-80E1 
Engine Manual, Section 72-34-01, COMPRESSOR REAR FRAME--

[[Page 51699]]

INSPECTION 001, Subtask 72-34-01-200-003.

Determining CSN of the Compressor Rear Frame

    (h) Air carriers and operators must use engine operating records 
to determine the CSN of the compressor rear frame. If the number of 
cycles accumulated since new cannot be established, inspect the CRF 
within 300 cycles-in-service after the effective date of this AD.
    (i) For compressor rear frames that have operated in multiple 
engine models or thrust ratings, information on correct cycle 
counting can be found in Method 1 or Method 2 of CF6-80E1 Engine 
Manual No. GEK 99376, Section 05-11-00, LIFE LIMITS OF ENGINE 
ROTATING PARTS.

Definition

    (j) For the purposes of this AD, piece-part level means that the 
CRF is removed and disassembled using the disassembly instructions 
in GE's engine manual.

Alternative Methods of Compliance

    (k) You must perform these mandatory inspections using the ALS 
of the Instructions for Continued Airworthiness and the applicable 
Engine Manual unless you receive approval to use an alternative 
method of compliance under paragraph (l) of this AD. Section 43.16 
of the Federal Aviation Regulations (14 CFR 43.16) may not be used 
to approve alternative methods of compliance or adjustments to the 
times in which these inspections must be performed.
    (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.

Related Information

    (m) GE CF6-80E1 Engine Manual Temporary Revision (TR) 05-0055, 
dated July 3, 2007, and CF6-80E1 Engine Manual TR 72-0088, dated 
July 3, 2007, pertain to the subject of this AD. TR 05-055 adds CRF 
inspection references to the CRF inspection tables and TR 0088 adds 
an ECI for the CRF.
    (n) Contact Robert Green, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
Robert.green@faa.gov; telephone (781) 238-7754; fax (781) 238-7199, 

for more information about this AD.

Material Incorporated by Reference

    (o) None.

    Issued in Burlington, Massachusetts, on August 29, 2007.
Thomas A. Boudreau,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
 [FR Doc. E7-17678 Filed 9-10-07; 8:45 am]

BILLING CODE 4910-13-P
