[Federal Register Volume 65, Number 162 (Monday, August 21, 2000)]
[Rules and Regulations]
[Pages 50623-50626]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-20773]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NE-31-AD; Amendment 39-11868; AD 2000-16-12]
RIN 2120-AA64


Airworthiness Directives; General Electric Company CF6-45, -50, -
80A, -80C2, and -80E1 Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to General Electric Company (GE) CF6-45, -50, -80A, -
80C2, and -80E1 turbofan engines with certain high pressure compressor 
rotor (HPCR) stage 3-9 spools installed. This action requires initial 
ultrasonic and eddy current inspections of certain HPCR stage 3-9 
spools for cracks. This amendment is prompted by an uncontained failure 
of an HPCR 3-9 spool. The actions specified in this AD are intended to 
detect cracks which can cause separation of the HPCR stage 3-9 spool 
and result in an uncontained engine failure.

DATES: Effective September 5, 2000. The incorporation by reference of 
certain publications listed in the rule is approved by the Director of 
the Federal Register as of September 5, 2000.
    Comments for inclusion in the Rules Docket must be received on or 
before October 20, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2000-NE-31-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may also be sent 
via the Internet using the following address: ``[email protected]''. Comments sent via the Internet must contain the 
docket number in the subject line.
    The service information referenced in this AD may be obtained 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. This information may be examined at the FAA, 
New England Region, Office of the Regional Counsel, 12 New England 
Executive Park, Burlington, MA; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Chris Gavriel, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone: (781) 
238-7147, fax: (781) 238-7199.

SUPPLEMENTARY INFORMATION: On June 7, 2000, a Boeing 767 experienced an 
uncontained engine failure of a CF6-80C2 engine during takeoff. That 
failure resulted in a rejected takeoff. Results of an investigation 
indicate that the failure was due to a crack that was located in the 
web of the 7th stage of the spool. The FAA has issued airworthiness 
directive (AD) 99-24-15 (64 FR 66554; November 29, 1999) that was 
effective on January 28, 2000, that requires an inspection program that 
includes an initial inspection of bores and webs of certain CF6 HPCR 3-
9 spools at the next piece-part exposure after 1000 cycles-since-new 
(CSN). Since that AD was issued, additional data suggests that the 
compliance time for the initial inspection is not adequate. This AD 
will decrease the compliance times for the initial inspection for those 
spools. This AD does not reduce the initial inspection time for HPCR 3-
9 spools part numbers 1333M66G10, 1782M22G04, 1854M95P08, 9136M89G28, 
and 9136M89G29 because of differences in manufacturing processes. The 
repetitive inspection schedule required by AD 99-24-15 remains in place 
for all HPCR 3-9 spools affected by that AD. These cracks, if not 
detected, could result in HPCR stage 3-9 spool separation, which can 
result in an uncontained engine failure and airplane damage.

Manufacturer's Service Information

    The FAA has reviewed and approved the technical contents of the 
following GE Alert Service Bulletins (ASB's):

 ASB CF6-50 72-A1108, Revision 3, dated November 12, 1999

[[Page 50624]]

 ASB CF6-80A 72-A0678, Revision 3, dated November 12, 1999
 ASB CF6-80C2 72-A0812, Revision 2, dated October 28, 1999
 ASB CF6-80C2 72-A0848, Revision 5, dated August 3, 2000
 ASB CF6-80E1 72-A0135, Revision 1, dated October 28, 1999
 ASB CF6-80E1 72-A0126, Revision 3, dated August 3, 2000

Those ASB's describe procedures for eddy current and ultrasonic 
inspections of HPCR stage 3-9 spools for cracks.

Determination of an Unsafe Condition

    Since an unsafe condition has been identified that is likely to 
exist or develop on other engines of the same type design, this AD is 
being issued to detect cracks which can cause separation of the HPCR 
stage 3-9 spool and result in an uncontained engine failure. This AD 
requires an initial inspection of spools with 10,500 or more CSN, 
within 500 cycles-in-service (CIS) after the effective date of this AD, 
by the next engine shop visit, or by May, 31, 2001, whichever occurs 
first. This AD also requires an initial inspection of spools with 7,000 
CSN to 10,499 CSN within 1,000 CIS after the effective date of this AD, 
by the next shop visit, or by July 29, 2001, whichever occurs first. 
These initial inspections qualify the HPCR 3-9 spool as having been 
previously inspected when determining the repetitive inspection 
schedules under AD 99-24-15. The actions are required to be 
accomplished in accordance with the alert service bulletins described 
previously.

Immediate Adoption

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications should identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2000-NE-31-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    This proposed rule does not have federalism implications, as 
defined in Executive Order No. 13132, because it 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. 
Accordingly, the FAA has not consulted with state authorities prior to 
publication of this proposed rule.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and is not a ``significant regulatory action'' 
under Executive Order 12866. It has been determined further that this 
action involves an emergency regulation under DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979). If it is determined 
that this emergency regulation otherwise would be significant under DOT 
Regulatory Policies and Procedures, a final regulatory evaluation will 
be prepared and placed in the Rules Docket. A copy of it, if filed, may 
be obtained from the Rules Docket at the location provided under the 
caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to 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

    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. Section 39.13 is amended by adding the following new 
airworthiness directive:

2000-16-12  General Electric Company: Amendment 39-11868. Docket 
2000-NE-31-AD.

Applicability

    This airworthiness directive is applicable to General Electric 
Company (GE) CF6-45, -50, -80A, -80C2, and -80E1 turbofan engines 
with high pressure compressor rotor stage 3-9 spools with the 
following part numbers (P/N's). These engines are installed on, but 
not limited to, Airbus A300, A310, and A330 series, Boeing 747 and 
767 series, and McDonnell Douglas DC-10 and MD-11 series airplanes.

------------------------------------------------------------------------
         Engine model                      HPCR 3-9 spool P/N
------------------------------------------------------------------------
CF6-45/50 Series Engines.....  9136M89G02, 9136M89G03, 9136M89G06,
                                9136M89G07, 9136M89G08, 9136M89G09,
                                9136M89G17, 9136M89G18, 9136M89G19,
                                9136M89G21, 9136M89G22, 9136M89G27,
                                9273M14G01, 9331M29G01, 9253M85G01,
                                9253M85G02
CF6-80A Series Engines.......  99136M89G10, 9136M89G11, 9136M89G20,
                                9136M89G21, 9136M89G22, 9136M89G27
CF6-80C2 Series Engines......  1333M66G01, 1333M66G03, 1333M66G07,
                                1333M66G09, 1781M52P01, 1781M53G01,
                                1854M95P01, 1854M95P02, 1854M95P03,
                                1854M95P04, 1854M95P05, 1854M95P06,
                                1854M95P07, 9380M28P05
CF6-80E1 Series Engines......  1669M22G01, 1669M22G03, 1782M22G01,
                                1782M22G02
------------------------------------------------------------------------


[[Page 50625]]


    Note 1: This airworthiness directive (AD) applies to each engine 
identified in the preceding applicability provision, regardless of 
whether it has been modified, altered, or repaired in the area 
subject to the requirements of this AD. For engines that have been 
modified, altered, or repaired so that the performance of the 
requirements of this AD is affected, the owner/operator must request 
approval for an alternative method of compliance in accordance with 
paragraph (j) of this AD. The request should include an assessment 
of the effect of the modification, alteration, or repair on the 
unsafe condition addressed by this AD; and, if the unsafe condition 
has not been eliminated, the request should include specific 
proposed actions to address it.

Compliance

    Compliance with this AD is required as indicated below, unless 
already done.
    To detect cracks which can cause separation of the HPCR stage 3-
9 spool and result in an uncontained engine failure, perform the 
following inspections:

CF6-45/50 Series Engines

    (a) For HPCR stages 3-9 spools installed in CF6-45/50 series 
engines that have not been inspected in accordance with AD 99-24-15, 
do the following:

------------------------------------------------------------------------
 Number of Cycles-Since-New
            (CSN)                    Action          By the earliest of
------------------------------------------------------------------------
(1) More than 7,000 CSN but   Eddy current and      (i) Within the next
 fewer than 10,500 CSN after   ultrasonic inspect    1,000 cycles-in-
 the effective date of this    bores for cracks in   service (CIS) after
 AD.                           accordance with ASB   the effective date
                               72-A1108, Revision    of this AD, OR
                               3, dated November    (ii) At the next
                               12, 1999.             engine shop visit
                                                     (ESV) after the
                                                     effective date of
                                                     the AD, OR
                                                    (iii) Before July
                                                     29, 2001.
(2) 10,500 or more CSN,       Eddy current and      (i) Within the next
 after the effective date of   ultrasonic inspect    500 CIS after the
 this AD, on HPCR 3-9 spools   bores for cracks in   effective date of
 P/N 9136M89G02, 9136M89G03,   accordance with ASB   this AD, OR
 9136M89G06, 9136M89G07,       72-A1108, Revision   (ii) At the next ESV
 9136M89G08, 9136M89G09,       3, dated November     after the effective
 9136M89G17, 9136M89G18,       12, 1999.             date of the AD, OR
 9273M14G01, 9331M29G01,                            (iii) Before May 31,
 9253M85G01, 9253M85G02.                             2001.
(3) 10,500 or more CSN,       Replace with a        (i) Within the next
 after the effective date of   serviceable HPCR 3-   500 CIS after the
 this AD, on HPCR 3-9 spools   9 spool.              effective date of
 P/N 9136M89G19, 9136M89G21,                         this AD, OR
 9136M89G22, 9136M89G27.                            (ii) At the next ESV
                                                     after the effective
                                                     date of the AD, OR
                                                    (iii) Before May 31,
                                                     2001.
------------------------------------------------------------------------

    (b) Remove any HPCR 3-9 spool from service that equals or 
exceeds the reject criteria established by ASB 72-A1108, Revision 3, 
dated November 12, 1999; and replace it with a serviceable spool 
before further flight.

CF6-80A Series Engines

    (c) For HPCR stages 3-9 spools installed in CF6-80A series 
engines that have not been inspected in accordance with AD 99-24-15, 
do the following:

------------------------------------------------------------------------
 Number of cycles-since-new
            (CSN)                    Action          By the earliest of
------------------------------------------------------------------------
(1) More than 7,000 CSN but   Eddy current and      (i) Within the next
 fewer than 10,500 CSN,        ultrasonic inspect    1,000 CIS after the
 after the effective date of   bores for cracks in   effective date of
 this AD.                      accordance with ASB   this AD, OR.
                               72-A0678, Revision   (ii) At the next ESV
                               3, dated November     after the effective
                               12, 1999.             date of the AD, OR.
                                                    (iii) Before July
                                                     29, 2001.
(2) 10,500 or more CSN,       Eddy current and      (i) Within the next
 after the effective date of   ultrasonic inspect    500 CIS after the
 this AD, on HPCR 3-9 spools   bores for cracks in   effective date of
 P/N 9136M89G10, 9136M89G11.   accordance with ASB   this AD, OR.
                               72-A0678, Revision   (ii) At the next ESV
                               3, dated November     after the effective
                               12, 1999.             date of the AD, OR.
                                                    (iii) Before May 31,
                                                     2001.
(3) 10,500 or more CSN,       Replace with a        (i) Within the next
 after the effective date of   serviceable HPCR 3-   500 CIS after the
 this AD, on HPCR 3-9 spools   9 spool.              effective date of
 P/N 9136M89G20, 9136M89G21,                         this AD, OR.
 9136M89G22, 913M89G27.                             (ii) At the next ESV
                                                     after the effective
                                                     date of the AD, OR.
                                                    (iii) Before May 31,
                                                     2001.
------------------------------------------------------------------------

    (d) Remove any HPCR 3-9 spool from service that equals or 
exceeds the reject criteria established by ASB 72-A0678, Revision 3, 
dated November 12, 1999, and replace it with a serviceable spool 
before further flight.

CF6-80C2 Series Engines

    (e) For HPCR stages 3-9 spools installed in CF6-80C2 series 
engines that have not been inspected in accordance with both ASB 72-
A0812, Revision 2, dated October 28, 1999; and ASB 72-A0848, 
Revision 5, dated August 3, 2000; or AD 99-24-15, do the following:

------------------------------------------------------------------------
 Number of cycles-since-new
            (CSN)                    Action          By the earliest of
------------------------------------------------------------------------
 (1) More than 7,000 CSN but   Eddy current and      (i) Within the next
 fewer than 10,500 CSN,        ultrasonic inspect    1,000 CIS after the
 after the effective date of   the bores and webs    effective date of
 this AD.                      for cracks in         this AD, OR
                               accordance with ASB  (ii) At the next ESV
                               72-A0812, Revision    after the effective
                               2, dated October      date of the AD, OR
                               28, 1999; and ASB    (iii) Before July
                               72-A0848, Revision    29, 2001.
                               5, dated August 3,
                               2000.

[[Page 50626]]

 
 (2) 10,500 or more CSN,       Replace with a        (i) Within the next
 after the effective date of   serviceable HPCR 3-   500 CIS after the
 this AD.                      9 spool.              effective date of
                                                     this AD, OR
                                                    (ii) At the next ESV
                                                     after the effective
                                                     date of the AD, OR
                                                    (iii) Before May 31,
                                                     2001.
------------------------------------------------------------------------

    (f) Remove any HPCR 3-9 spool from service that equals or 
exceeds the reject criteria established by ASB 72-A0812, Revision 2, 
dated October 28, 1999; and ASB 72-A0848, Revision 5, dated August 
3, 2000, and replace it with a serviceable spool before further 
flight.

CF6-80E1 Series Engines

    (g) For HPCR stages 3-9 spools installed in CF6-80E1 series 
engines that have not been inspected in accordance with both ASB 72-
A0135, Revision 1, dated October 28, 1999; and ASB 72-A0126, 
Revision 3, dated August 3, 2000; or AD 99-24-15, do the following:

------------------------------------------------------------------------
 Number of cycles-since-new
            (CSN)                    Action          By the earliest of
------------------------------------------------------------------------
(1) More than 7,000 CSN but   Eddy current and      (i) Within the next
 fewer than 10,500 CSN,        ultrasonic inspect    1,000 CIS after the
 after the effective date of   the bores and webs    effective date of
 this AD.                      for cracks in         this AD, OR
                               accordance with ASB  (ii) At the next ESV
                               72-A0126, Revision    after the effective
                               3, dated August 3,    date of the AD, OR
                               2000, and ASB 72-    (iii) Before July
                               A0135, Revision 1,    29, 2001.
                               dated October 28,
                               1999..
(2) 10,500 or more CSN after  Replace with a        (i) Within the next
 the effective date of this    serviceable HPCR 3-   500 CIS after the
 AD.                           9 spool.              effective date of
                                                     this AD, OR
                                                    (ii) At the next ESV
                                                     after the effective
                                                     date of the AD, OR
                                                    (iii) Before May 31,
                                                     2001.
------------------------------------------------------------------------

    (h) Remove any HPCR 3-9 spool from service before further flight 
that equals or exceeds the reject criteria established by ASB 72-
A0135, revision 1, dated October 28, 1999; or ASB 72-A0126, revision 
3, dated August 3, 2000, and replace it with a serviceable spool.

Definitions

    (i) For the purpose of this AD, an ESV is defined as any time an 
engine is introduced into a shop for the separation of a major 
engine flange.

Alternative Methods of Compliance

    (j) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Engine Certification Office (ECO). 
Operators shall submit their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, ECO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this airworthiness directive, 
if any, may be obtained from the ECO.

Special Flight Permits

    (k) Special flight permits may be issued in accordance with 
Sec. Sec. 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the aircraft to a location where 
the requirements of this AD can be accomplished.
    (l) The inspection shall be done in accordance with the 
following GE Alert Service Bulletins:

----------------------------------------------------------------------------------------------------------------
                Document No.                     Pages       Revision                     Date
----------------------------------------------------------------------------------------------------------------
GE CF6-50 ASB No. 72-A1108.................       1-15               3  November 12, 1999.
    Total pages: 15.
GE CF6-80A ASB No. 72-A0678................       1-18               3  November 12, 1999.
    Total pages: 18.
GE CF6-80C2 ASB No. 72-A0812...............       1-13               2  October 28, 1999.
    Total pages: 13.
GE CF6-80C2 ASB No. 72-A0848...............       1-47               5  August 3, 2000.
    Total pages: 47.
GE CF6-80E1 ASB No. 72-A0126...............       1-47               3  August 3, 2000.
    Total pages: 47.
GE CF6-80E1 ASB No. 72-A0135...............       1-11               1  October 28, 1999.
    Total pages: 11.
----------------------------------------------------------------------------------------------------------------

The incorporations by reference of ASB's No. CF6-50 72-A1108, 
Revision 3; CF6-80A 72-A0678, Revision 3; CF6-80C2 72-A0812, 
Revision 2; and CF6-80E1 72-A0135, Revision 1, were approved by the 
Director of the Federal Register on January 28, 2000 (64 FR 66554; 
November 29, 1999). The incorporations by reference of ASB's CF6-
80C2 72-A0848, Revision 5; and CF6-80E1 72-A0126, Revision 3 were 
approved by the Director of the Federal Register on September 5, 
2000, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies 
may be obtained 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. Copies may be 
inspected at the FAA, New England Region, Office of the Regional 
Counsel, 12 New England Executive Park, Burlington, MA; or at the 
Office of the Federal Register, 800 North Capitol Street, NW, suite 
700, Washington, DC.
    (m) This amendment becomes effective on September 5, 2000.

    Issued in Burlington, Massachusetts, on August 10, 2000.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 00-20773 Filed 8-18-00; 8:45 am]
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