[Federal Register Volume 60, Number 224 (Tuesday, November 21, 1995)]
[Rules and Regulations]
[Pages 57803-57807]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-28527]
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Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
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Federal Register / Vol. 60, No. 224 / Tuesday, November 21, 1995 /
Rules and Regulations
[[Page 57803]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-ANE-39; Amendment 39-9423; AD 95-23-03]
Airworthiness Directives; General Electric Company CF6 Series
Turbofan Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to General Electric Company (GE) CF6 series turbofan
engines, that currently requires initial and repetitive ultrasonic and
eddy current inspections of a certain population of high pressure
compressor rotor (HPCR) stage 3-9 spools for cracks. This amendment
retains the inspection requirements of the current AD, but would
accelerate the inspection schedule for parts affected by the current
AD, require initial and repetitive inspections of an expanded
population of HPCR stage 3-9 spools installed on GE CF6-45/-50/-80A
engines, include HPCR stage 3-9 spools installed on GE CF6-80C2 series
engines, and require reporting to the FAA the results of inspections
that equal or exceed the reject criteria. This amendment is prompted by
recent field experience and the associated engineering investigation,
which indicate that cracks are likely to develop in a larger population
of parts than previously thought. The actions specified by this AD are
intended to prevent HPCR stage 3-9 spool cracking and separation, which
can result in an uncontained engine failure and aircraft damage.
DATES: Effective: December 6, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of December 6, 1995.
Comments for inclusion in the Rules Docket must be received on or
before January 22, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 95-ANE-39, 12 New England
Executive Park, Burlington, MA 01803-5299.
The service information referenced in this AD may be obtained from
General Electric Aircraft Engines, CF6 Distribution Clerk, Room 132,
111 Merchant Street, Cincinnati, OH 45246. This information may be
examined at the FAA, New England Region, Office of the Assistant Chief
Counsel, Burlington, MA; or at the Office of the Federal Register, 800
North Capitol Street NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Richard Woldan, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (617)
238-7136, fax (617) 238-7199.
SUPPLEMENTARY INFORMATION: On January 31, 1995, the Federal Aviation
Administration (FAA) issued airworthiness directive (AD) 95-03-01,
Amendment 39-9138 (60 FR 8930, February 16, 1995), applicable to
General Electric Company (GE) CF6-45/-50/-80A series turbofan engines,
to require initial and repetitive ultrasonic and eddy current
inspections of a certain population of high pressure compressor rotor
(HPCR) stage 3-9 spools for cracks. That action was prompted by a
finding of several cracked parts in service. That condition, if not
corrected, could result in HPCR stage 3-9 spool cracking and
separation, which can result in an uncontained engine failure and
aircraft damage.
Since the issuance of that AD, the FAA has received a report of an
in-service uncontained failure of an HPCR stage 3-9 spool. The
investigation revealed that the uncontained failure was caused by a
crack that developed from the same metallurgical condition which
prompted the current AD. However, this spool was not part of the
population required to be inspected by the current AD. Further
investigation has indicated that the scope of the current AD should be
expanded to include other HPCR stage 3-9 spools installed on GE CF6-45/
-50/-80A engines, and also HPCR stage 3-9 spools installed on GE CF6-
80C2 series engines, and that the inspection schedule for the spools
affected by the current AD should be accelerated. This new inspection
program is based on current field experience, knowledge of the
manufacturing processes used to produce the HPCR stage 3-9 spools, and
the operating conditions which these spools are exposed to in the
different GE CF6 series engines. In addition, the FAA has determined
that it is necessary to require operators to submit the findings of
these inspections in order to further analyze this situation. The FAA
may revise this AD based on the results of these inspections.
The FAA has reviewed and approved the technical contents of the
following GE service bulletins (SB's): CF6-50 SB No. 72-1108, Original,
dated November 6, 1995; CF6-80A SB No. 72-678, Original, dated November
6, 1995; CF6-80C2 SB No. 72-812, Original, dated November 6, 1995, and
Table 801 of GE CF6-50 Shop Manual GEK 50481, Temporary Revision 05-
0011, dated November 3, 1995. These SB's describe procedures for eddy
current and ultrasonic inspections of HPCR stage 3-9 spools for cracks.
Since an unsafe condition has been identified that is likely to
exist or develop on other engines of this same type design, this AD
supersedes AD 95-03-01 to retain the inspection requirements of the
current AD, but would accelerate the inspection schedule for parts
affected by the current AD, require initial and repetitive inspections
of an expanded population of HPCR stage 3-9 spools installed on GE CF6-
45/-50/-80A engines, include HPCR stage 3-9 spools installed on GE CF6-
80C2 series engines, and require reporting to the FAA the results of
inspections that equal or exceed the reject criteria. The actions are
required to be accomplished in accordance with the SB's described
previously.
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
[[Page 57804]]
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 95-ANE-39.'' The postcard will be date stamped and
returned to the commenter.
The regulations adopted herein will not have substantial direct
effects 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. Therefore, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
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), 40101, 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing Amendment 39-9138 (60 FR
8930, February 16, 1995), and by adding a new airworthiness directive,
Amendment 39-9423, to read as follows:
95-23-03 General Electric Company: Amendment 39-9423. Docket 95-
ANE-39. Supersedes AD 95-03-01, Amendment 39-9138.
Applicability: General Electric Company (GE) CF6-45/-50/-80A/-
80C2 series turbofan engines installed with High Pressure Compressor
Stage 3-9 Spools, Part Numbers (P/Ns) 1333M66G01, 1333M66G03;
1333M66G07, 1333M66G09, 1781M52P01, 1781M53G01,1854M95P01,
1854M95P02, 1854M95P03, 1854M95P04, 1854M95P05, 1854M95P06;
9136M89G02, 9136M89G03, 9136M89G06, 9136M89G07, 9136M89G08,
9136M89G09, 9136M89G10, 9136M89G11, 9136M89G17, 9136M89G18,
9136M89G19, 9136M89G20, 9136M89G21, 9136M89G22, 9136M89G27,
9253M85G01, 9253M85G02, 9273M14G01, 9331M29G01, and 9380M28P05
installed on, but not limited to, Airbus A300 and A310 series,
Boeing 747 and 767 series, and McDonnell Douglas DC-10 and MD-11
series aircraft.
Note: 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 use the
authority provided in paragraph (o) to request approval from the
Federal Aviation Administration (FAA). This approval may address
either no action, if the current configuration eliminates the unsafe
condition, or different actions necessary to address the unsafe
condition described in this AD. Such a request should include an
assessment of the effect of the changed configuration on the unsafe
condition addressed by this AD. In no case does the presence of any
modification, alteration, or repair remove any engine from the
applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent high pressure compressor rotor (HPCR) stage 3-9 spool
cracking and separation, which can result in an uncontained engine
failure and aircraft damage, accomplish the following:
(a) Eddy current and ultrasonic inspect for cracks HPCR stage 3-
9 spools, with Part Numbers (P/N's) 9136M89G08, 9253M85G02,
9273M14G01, and 9331M29G01, with serial Numbers (S/N) listed in
Table 801 of GE CF6-50 Shop Manual GEK 50481, Temporary Revision 05-
0011, dated November 3, 1995; and with P/N's 9136M89G02 and
9136M89G06, installed in GE CF6-45/-50 series engines. Perform the
inspections in accordance with GE CF6-50 Service Bulletin (SB) No.
72-1108, Original, dated November 6, 1995, as follows:
(1) For HPCR stage 3-9 spools with 3,000 or more cycles in
service (CIS) on the effective date of this AD since last inspection
in accordance with GE CF6-50 SB No. 72-888, Original, Revision 1,
Revision 2, Revision 3, Revision 4, or Revision 5; or GE CF6-50 SB
No. 72-1000, Original, Revision 1, or Revision 2; or GE CF6-50 SB
No. 72-1008, Original; or GE CF6-50 SB No. 72-1108, Original;
inspect prior to exceeding 500 CIS after the effective date of this
AD, or 4,000 CIS since last inspection, whichever occurs first.
(2) For HPCR stage 3-9 spools with less than 3,000 CIS since
last inspection in accordance with GE CF6-50 SB No. 72-888,
Original, Revision 1, Revision 2, Revision 3, Revision 4, or
Revision 5; or GE CF6-50 SB No. 72-1000, Original, Revision 1, or
Revision 2, or GE CF6-50 SB No. 72-1008, Original; or GE CF6-50 SB
No. 72-1108, Original; inspect at the earliest occurrence of the
following after the effective date of this AD: the next piece-part
exposure after accumulating 1,000 CIS since last inspection, the
next shop visit after accumulating 2,000 CIS since last inspection,
or prior to exceeding 3,500 CIS since last inspection.
(3) For HPCR stage 3-9 spools that have not been previously
inspected in accordance with GE CF6-50 SB No. 72-888, Original,
Revision 1, Revision 2, Revision 3, Revision 4, or Revision 5; or GE
CF6-50 SB No. 72-1000, Original, Revision 1, or Revision 2; or GE
CF6-50 SB No. 72-1008, Original; or GE CF6-50 SB No. 72-1108,
Original; on the effective date of this AD, inspect prior to
exceeding 30 days from the effective date of this AD.
(4) Thereafter, reinspect HPCR stage 3-9 spools for cracks at
intervals not to exceed the earliest occurrence of the following:
the
[[Page 57805]]
next piece-part exposure after accumulating 1,000 CIS since last
inspection, the next shop visit after accumulating 2,000 CIS since
last inspection, or prior to exceeding 3,500 CIS since last
inspection.
(5) Remove from service prior to further flight HPCR stage 3-9
spools that equal or exceed the reject criteria established by GE
CF6-50 SB No. 72-1108, Original, dated November 6, 1995, and replace
with a serviceable part.
(b) Eddy current and ultrasonic inspect for cracks HPCR stage 3-
9 spools, with P/N's 9136M89G08, 9253M85G02, 9273M14G01, and
9331M29G01, with S/N not listed in Table 801 of GE CF6-50 Shop
Manual GEK 50481, Temporary Revision 05-0011, dated November 3,
1995; and with P/N's 9136M89G03, 9136M89G07, 9136M89G09, 9136M89G17,
9136M89G18, and 9253M85G01, installed in GE CF6-45/-50 series
engines. Perform the inspections in accordance with GE CF6-50 SB No.
72-1108, Original, dated November 6, 1995, as follows:
(1) For HPCR stage 3-9 spools that have been inspected in
accordance with GE CF6-50 SB No. 72-888, Original, Revision 1,
Revision 2, Revision 3, Revision 4, or Revision 5; or GE CF6-50 SB
No. 72-1000, Original, Revision 1, or Revision 2; or GE CF6-50 SB
No. 1008, Original; or GE CF6-50 SB No. 72-1108, Original; on the
effective date of this AD, inspect either at the next piece-part
exposure after accumulating 1,000 CIS since last inspection and more
than 4,000 cycles since new (CSN), or the next shop visit after
accumulating 2,000 CIS since last inspection and more than 4,000
CSN, whichever occurs first.
(2) For HPCR stage 3-9 spools that have not been previously
inspected in accordance with GE CF6-50 SB No. 72-888, Original,
Revision 1, Revision 2, Revision 3, Revision 4, or Revision 5; or GE
CF6-50 SB No. 72-1000, Original, Revision 1, or Revision 2; or GE
CF6-50 SB No. 1008, Original; or GE CF6-50 SB No. 72-1108, Original;
on the effective date of this AD, inspect at the next piece-part
exposure after accumulating 1,000 CSN, or at the next shop visit
after accumulating 4,000 CSN, whichever occurs first.
(3) Thereafter, reinspect HPCR stage 3-9 spools at intervals not
to exceed either the next piece-part exposure after accumulating
1,000 CIS since last inspection and more than 4,000 CSN, or the next
shop visit after accumulating 2,000 CIS since last inspection and
more than 4,000 CSN, whichever occurs first.
(4) Remove from service prior to further flight HPCR stage 3-9
spools that equal or exceed the reject criteria established by GE
CF6-50 SB No. 72-1108, Original, dated November 6, 1995, and replace
with a serviceable part.
(c) Eddy current and ultrasonic inspect for cracks HPCR stage 3-
9 spools, with P/N's 9136M89G19, 9136M89G21, 9136M89G22, and
9136M89G27, installed in GE CF6-45/ -50 series engines, in
accordance with GE CF6-50 SB No. 72-1108, Original, dated November
6, 1995, as follows:
(1) For HPCR stage 3-9 spools that have been inspected in
accordance with GE CF6-50 SB No. 72-888, Original, Revision 1,
Revision 2, Revision 3, Revision 4, or Revision 5; or GE CF6-50 SB
No. 72-1000, Original, Revision 1, or Revision 2; or GE CF6-50 SB
No. 1008, Original; or GE CF6-50 SB No. 72-1108, Original; on the
effective date of this AD, inspect at the next piece-part exposure
after accumulating 1,000 CIS since last inspection and more than
4,000 CSN.
(2) For HPCR stage 3-9 spools that have not been previously
inspected in accordance with GE CF6-50 SB No. 72-888, Original,
Revision 1, Revision 2, Revision 3, Revision 4, or Revision 5; or GE
CF6-50 SB No. 72-1000, Original, Revision 1, or Revision 2; or GE
CF6-50 SB No. 1008, Original, or GE CF6-50 SB No. 72-1108, Original;
on the effective date of this AD, inspect at the next piece-part
exposure after accumulating 1,000 CSN, or the next shop visit after
accumulating 4,000 CSN, whichever occurs first.
(3) Thereafter, reinspect HPCR stage 3-9 spools at intervals not
to exceed the next piece-part exposure after accumulating 1,000 CIS
since last inspection and more than 4,000 CSN.
(4) Remove from service prior to further flight HPCR stage 3-9
spools that equal or exceed the reject criteria established by GE
CF6-45/50 SB No. 72-1108, Original, dated November 6, 1995, and
replace with a serviceable part.
(d) Eddy current and ultrasonic inspect for cracks HPCR stage 3-
9 spools, P/N 9136M89G10 with the following S/N's: MPOM0054,
MPOM7090, MPOM8303, MPOM8304, MPOM9263, MPOM9264, MPON0054,
MPON0071, MPON0072, MPON1643, MPON4251, and MPON4253; installed in
GE CF6-80A/-80A1/-80A2/ -80A3 model engines. Perform the
inspections in accordance with GE CF6-80A SB No. 72-678, Original,
dated November 6, 1995, as follows:
(1) For HPCR stage 3-9 spools with 3,000 or more CIS on the
effective date of this AD since last inspection in accordance with
GE CF6-80A SB No. 72-500, Original, Revision 1, Revision 2, Revision
3, Revision 4, or Revision 5; or GE CF6-80A SB No. 72-583, Original,
Revision 1, Revision 2, Revision 3, or Revision 4; or GE CF6-80A SB
No. 72-678, Original; inspect prior to exceeding 500 CIS after the
effective date of this AD, or 4,000 CIS since last inspection,
whichever occurs first.
(2) For HPCR stage 3-9 spools with less than 3,000 CIS on the
effective date of this AD since last inspection in accordance with
GE CF6-80A SB No. 72-500, Original, Revision 1, Revision 2, Revision
3, Revision 4, or Revision 5; or GE CF6-80A SB No. 72-583, Original,
Revision 1, Revision 2, Revision 3, or Revision 4; or GE CF6-80A SB
No. 72-678, Original; inspect at the earliest occurrence of the
following after the effective date of this AD: the next piece-part
exposure after accumulating 1,000 CIS since last inspection, the
next shop visit after accumulating 2,000 CIS since last inspection,
or prior to exceeding 3,500 CIS since last inspection.
(3) For HPCR stage 3-9 spools that have not been previously
inspected in accordance with GE CF6-80A SB No. 72-500, Original,
Revision 1, Revision 2, Revision 3, Revision 4, or Revision 5; GE
CF6-80A SB No. 72-583, Original, Revision 1, Revision 2, Revision 3,
or Revision 4; or GE CF6-80A SB No. 72-678, Original; on the
effective date of this AD, inspect prior to exceeding 30 days from
the effective date of this AD.
(4) Thereafter, reinspect HPCR stage 3-9 spools at intervals not
to exceed the earliest occurrence of the following: the next piece-
part exposure after accumulating 1,000 CIS since last inspection,
the next shop visit after accumulating 2,000 CIS since last
inspection, or prior to exceeding 3,500 CIS since last inspection.
(5) Remove from service prior to further flight HPCR stage 3-9
spools that equal or exceed the reject criteria established by GE
CF6-80A SB No. 72-678, Original, dated November 6, 1995, and replace
with a serviceable part.
(e) Eddy current and ultrasonic inspect for cracks HPCR stage 3-
9 spools, P/N 9136M89G10 with S/N's other than those listed in
paragraph (d) of this AD, and P/N 9136M89G11, installed in GE CF6-
80A/-80A2 model engines, in accordance with GE CF6-80A SB No. 72-
678, Original, dated November 6, 1995, as follows:
(1) For HPCR stage 3-9 spools that have been inspected in
accordance with GE CF6-80A SB No. 72-500, Original, Revision 1,
Revision 2, Revision 3, Revision 4, or Revision 5; GE CF6-80A SB No.
72-583, Original, Revision 1, Revision 2, Revision 3, or Revision 4;
or GE CF6-80A SB No. 72-678, Original; inspect either at the next
piece-part exposure after accumulating 1,000 CIS since last
inspection and more than 5,000 CSN, or at the next shop visit after
accumulating 1,500 CIS since last inspection and more than 5,000
CSN, whichever occurs first.
(2) For HPCR stage 3-9 spools that have not been previously
inspected in accordance with GE CF6-80A SB No. 72-500, Original,
Revision 1, Revision 2, Revision 3, Revision 4, or Revision 5; GE
CF6-80A SB No. 72-583, Original, Revision 1, Revision 2, Revision 3,
or Revision 4; or GE CF6-80A SB No. 72-678, Original; on the
effective date of this AD, inspect at the next piece-part exposure
after accumulating 1,000 CSN, or the next shop visit after
accumulating 5,000 CSN, whichever occurs first.
(3) Thereafter, reinspect HPCR stage 3-9 spools at intervals not
to exceed either the next piece-part exposure after accumulating
1,000 CIS since last inspection and more than 5,000 CSN, or at the
next shop visit after accumulating 1,500 CIS since last inspection
and more than 5,000 CSN, whichever occurs first.
(4) Remove from service prior to further flight HPCR stage 3-9
spools that equal or exceed the reject criteria established by GE
CF6-80A SB No. 72-678, Original, dated November 6, 1995, and replace
with a serviceable part.
(f) Eddy current and ultrasonic inspect for cracks HPCR stage 3-
9 spools, P/N 9136M89G10 with S/N's other than those listed in
paragraph (d) of this AD, installed in GE CF6-80A1/-80A3 model
engines, in accordance with GE CF6-80A SB No. 72-678, Original,
dated November 6, 1995, as follows:
[[Page 57806]]
(1) For HPCR stage 3-9 spools that have been inspected in
accordance with GE CF6-80A SB No. 72-500, Original, Revision 1,
Revision 2, Revision 3, Revision 4, or Revision 5; GE CF6-80A SB No.
72-583, Original, Revision 1, Revision 2, Revision 3, or Revision 4;
or GE CF6-80A SB No. 72-678, Original; inspect either at the next
piece-part exposure after accumulating 1,000 CIS since last
inspection and more than 5,000 CSN, or at the next shop visit after
accumulating 2,000 CIS since last inspection and more than 5,000
CSN, whichever occurs first.
(2) For HPCR stage 3-9 spools that have not been previously
inspected in accordance with GE CF6-80A SB No. 72-500, Original,
Revision 1, Revision 2, Revision 3, Revision 4, or Revision 5; GE
CF6-80A SB No. 72-583, Original, Revision 1, Revision 2, Revision 3,
or Revision 4; or GE CF6-80A SB No. 72-678, Original; on the
effective date of this AD, inspect at the next piece-part exposure
after accumulating 1,000 CSN, or the next shop visit after
accumulating 5,000 CSN, whichever occurs first.
(3) Thereafter, reinspect HPCR stage 3-9 spools at intervals not
to exceed either the next piece-part exposure after accumulating
1,000 CIS since last inspection and more than 5,000 CSN, or at the
next shop visit after accumulating 2,000 CIS since last inspection
and more than 5,000 CSN, whichever occurs first.
(4) Remove from service prior to further flight HPCR stage 3-9
spools that equal or exceed the reject criteria established by GE
CF6-80A SB No. 72-678, Original, dated November 6, 1995, and replace
with a serviceable part.
(g) Eddy current and ultrasonic inspect for cracks HPCR stage 3-
9 spools, P/N's 9136M89G20, 9136M89G21, 9136M89G22, and 9136M89G27,
installed in GE CF6-80A/-80A1/-80A2/-80A3 model engines, in
accordance with GE CF6-80A SB No. 72-678, Original, dated November
6, 1995, as follows:
(1) For HPCR stage 3-9 spools that have been inspected in
accordance with GE CF6-80A SB No. 72-500, Original, Revision 1,
Revision 2, Revision 3, Revision 4, or Revision 5; GE CF6-80A SB No.
72-583, Original, Revision 1, Revision 2, Revision 3, or Revision 4;
or GE CF6-80A SB No. 72-678, Original; inspect at the next piece-
part exposure after accumulating 1,000 CIS since last inspection and
more than 5,000 CSN.
(2) For HPCR stage 3-9 spools that have not been previously
inspected in accordance with GE CF6-80A SB No. 72-500, Original,
Revision 1, Revision 2, Revision 3, Revision 4, or Revision 5; GE
CF6-80A SB No. 72-583, Original, Revision 1, Revision 2, Revision 3,
or Revision 4; or GE CF6-80A SB No. 72-678, Original; on the
effective date of this AD, inspect at the next piece-part exposure
after accumulating 1,000 CSN, or the next shop visit after
accumulating 5,000 CSN, whichever occurs first.
(3) Thereafter, reinspect HPCR stage 3-9 spools at intervals not
to exceed the next piece-part exposure after accumulating 1,000 CIS
since last inspection and more than 5,000 CSN.
(4) Remove from service prior to further flight HPCR stage 3-9
spools that equal or exceed the reject criteria established by GE
CF6-80A SB No. 72-678, Original, dated November 6, 1995, and replace
with a serviceable part.
(h) Eddy current and ultrasonic inspect for cracks HPCR stage 3-
9 spools, P/N's 1781M52P01, 1854M95P02, 1854M95P05, and 9380M28P05,
installed in GE CF6-80C2 series engines, in accordance with GE CF6-
80C2 SB No. 72-812, Original, dated November 6, 1995, as follows:
(1) For HPCR stage 3-9 spools that have not been previously
inspected in accordance with GE CF6-80C2 SB No. 72-418, Original,
Revision 1, Revision 2, or Revision 3; or GE CF6-80C2 SB No. 72-758,
Original; or GE CF6-80C2 SB No. 72-812, Original; inspect at the
next shop visit. However, no uninspected HPCR stage 3-9 spools with
more than 8,000 CSN are to remain in service after May 15, 1996; and
further no uninspected HPCR stage 3-9 spools with more than 3,500
CSN are to remain in service after May 15, 1997.
(2) For HPCR stage 3-9 spools that have been inspected in
accordance with GE CF6-80C2 SB No. 72-418, Original, Revision 1,
Revision 2, Revision 3, or GE CF6-80C2 SB No. 72-758, Original; or
GE CF6-80C2 SB No. 72-812, Original; inspect at the earliest
occurrence after the effective date of this AD of the following: the
next piece-part or core module exposure after accumulating 1,000 CIS
since last inspection, the next shop visit after accumulating 1,500
CIS since last inspection, or prior to exceeding 3,500 CIS since
last inspection after May 15, 1997.
(3) Thereafter, reinspect HPCR stage 3-9 spools at intervals not
to exceed the earliest occurrence of the following: the next piece-
part or core module exposure after accumulating 1,000 CIS since last
inspection, the next shop visit after accumulating 1,500 CIS since
last inspection, or prior to exceeding 3,500 CIS since last
inspection.
(4) For inspections accomplished in accordance with paragraphs
(h)(1), (h)(2), or (h)(3) of this AD, at the first piece-part
exposure, perform the inspection at the piece-part level. Otherwise
the inspection may be performed at either the piece-part or the core
module level.
(5) Remove from service prior to further flight HPCR stage 3-9
spools that equal or exceed the reject criteria established by GE
CF6-80C2 SB No. 72-812, Original, dated November 6, 1995, and
replace with a serviceable part.
(i) Eddy current and ultrasonic inspect for cracks HPCR stage 3-
9 spools, P/N's 1333M66G01, 1333M66G03, 1333M66G07, 1333M66G09,
1781M53G01, 1854M95P01, 1854M95P03, 1854M95P04, and 1854M95P06,
installed in GE CF6-80C2 series engines, in accordance with GE CF6-
80C2 SB No. 72-812, Original, dated November 6, 1995, as follows:
(1) For HPCR stage 3-9 spools that have been inspected in
accordance with GE CF6-80C2 SB No. 72-418, Original, Revision 1,
Revision 2, Revision 3, or GE CF6-80C2 SB No. 72-758, Original; or
GE CF6-80C2 SB No. 72-812, Original; inspect at the next piece-part
or core module exposure after accumulating 1,000 CIS since last
inspection and more than 3,000 CSN.
(2) For HPCR stage 3-9 spools that have not been inspected in
accordance with GE CF6-80C2 SB No. 72-418, Original, Revision 1,
Revision 2, Revision 3, or GE CF6-80C2 SB No. 72-758, Original; or
GE CF6-80C2 SB No. 72-812, Original; on the effective date of this
AD, inspect at the next piece-part or core module exposure after
accumulating 1,000 CSN, or at the next shop visit after accumulating
3,000 CSN, whichever occurs first.
(3) Thereafter, reinspect HPCR stage 3-9 spools at intervals not
to exceed either the next core module exposure or piece-part
exposure after accumulating 1,000 CIS since last inspection and more
than 3,000 CSN.
(4) For inspections accomplished in accordance with paragraph
(i)(1), (i)(2), or (i)(3) of this AD, at the first piece-part
exposure, perform the inspection at the piece-part level. Otherwise
the inspection may be performed at either the piece-part or the core
module level.
(5) Remove from service prior to further flight HPCR stage 3-9
spools that equal or exceed the reject criteria established by GE
CF6-80C2 SB No. 72-812, Original, dated November 6, 1995, and
replace with a serviceable part.
(j) Report within 24 hours of inspection the results of
inspections that equal or exceed the reject criteria to: Richard
Woldan, Aerospace Engineer, Engine Certification Office, FAA, Engine
and Propeller Directorate, 12 New England Executive Park,
Burlington, MA 01803-5299; telephone (617) 238-7136, fax (617) 238-
7199, as follows:
(1) Engine model in which the HPCR stage 3-9 spool was
installed;
(2) P/N;
(3) S/N;
(4) Part CSN;
(5) Part CIS since last inspection; and
(6) Date and location of inspection.
Reporting requirements have been approved by the Office of
Management and Budget and assigned OMB control number 2120-0056.
(k) For the purpose of this AD, a serviceable part for
installation in an engine is defined as an HPCR stage 3-9 spool with
less than 1,000 CSN or with less than 1,000 CIS since last
inspection in accordance with the following SB's, as applicable: GE
CF6-50 SB No. 72-888, Revision 3, Revision 4, or Revision 5; GE CF6-
50 SB No. 72-1000, Original, Revision 1, or Revision 2; GE CF6-50 SB
No. 72-1108, Original; GE CF6-80A SB No. 72-500, Revision 3,
Revision 4, or Revision 5; GE CF6-80A SB No. 72-583, Original,
Revision 1, Revision 2, Revision 3, or Revision 4; GE CF6-80A SB No.
72-678, Original; GE CF6-80C2 SB No. 72-418, Revision 2 or Revision
3; GE CF6-80C2 SB No. 72-758, Original; or GE CF6-80C2 SB No. 72-
812, Original.
(l) For the purpose of this AD, core module exposure is defined
as separation of the fan module from the engine.
(m) For the purpose of this AD, piece-part exposure is defined
as disassembly and removal of the stage 3-9 spool from the HPCR.
(n) For the purpose of this AD, a shop visit is defined as the
introduction of an engine into a shop where the separation of a
major
[[Page 57807]]
engine flange will occur after the effective date of this AD.
(o) 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. The
request should be forwarded through an appropriate FAA Principal
Maintenance Inspector, who may add comments and then send it to the
Manager, Engine Certification Office.
Note: Information concerning the existence of approved
alternative methods of compliance with this airworthiness directive,
if any, may be obtained from the Engine Certification Office.
(p) Special flight permits may be issued in accordance with
sections 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.
(q) The actions required by this AD shall be done in accordance
with the following service documents:
------------------------------------------------------------------------
Document No. Pages Revision Date
------------------------------------------------------------------------
GE CF6-50 SB No. 72-1108..... 1-6 Original..... Nov. 6, 1995.
Total pages: 6.
GE CF6-80A SB No. 72-678..... 1-6 Original..... Nov. 6, 1995.
Total pages: 6.
GE CF6-80C2 SB No. 72-812.... 1-6 Original..... Nov. 6, 1995.
CF6-50 Engine Task Numbered 1-4 ............. Nov. 3, 1995.
Shop Manual Temporary
Revision 05-0011.
Total pages: 4.
------------------------------------------------------------------------
This incorporation by reference was approved by the Director of
the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Copies may be obtained from General Electric Aircraft
Engines, CF6 Distribution Clerk, Room 132, 111 Merchant Street,
Cincinnati, OH 45246. Copies may be inspected at the FAA, New
England Region, Office of the Assistant Chief 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.
(r) This amendment becomes effective on December 6, 1995.
Issued in Burlington, Massachusetts, on November 13, 1995.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 95-28527 Filed 11-20-95; 8:45 am]
BILLING CODE 4910-13-U