[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
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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.

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

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