AD 2000-16-12

final rule

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

AD Number: 2000-16-12
Status: final_rule
Effective Date: September 5, 2000
Product Category: engine
Docket: Docket No. 2000-NE-31-AD
FR Citation: 65 FR 50623

Technical illustration of an aircraft turbine engine assembly — Problem area **Engine**

Applicability

Type	Manufacturer	Model	Details
engine	General Electric	Company CF6-45	Airworthiness Directives; General Electric Company CF6-45, -50, -80A, -80C2, and -80E1 Turbofan Engines

Unsafe Condition

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 whi...

Federal Register Abstract

Document Text

Show stored source text (verify against official source)

[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-20773]

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

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.

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

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: ``<a href="/cdn-cgi/l/email-protection#9ea7b3fff0fbb3fffafdf1f3f3fbf0eadef8ffffb0f9f1e8"><span class="__cf_email__" data-cfemail="3d04105c5358105c595e5250505853497d5b5c5c135a524b">[email&#160;protected]</span></a>''. 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):

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

[[Page 50624]]

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

[[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]
BILLING CODE 4910-13-U

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

Applicability

Unsafe Condition

Federal Register Abstract

Document Text

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