[Federal Register Volume 63, Number 118 (Friday, June 19, 1998)]
[Rules and Regulations]
[Pages 33530-33532]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-15785]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-ANE-46-AD; Amendment 39-10585; AD 98-12-32]
RIN 2120-AA64
Airworthiness Directives; CFM International CFM56-2, -2A, -2B, -
3, -3B, and -3C Series Turbofan Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to CFM International (CFMI) CFM56-2, -2A, -2B, -3, -3B, and
-3C series turbofan engines, that requires a one-time eddy current
inspection (ECI) for cracks or gouges in certain high pressure turbine
rotor (HPTR) disks. This amendment is prompted by a report of a HPTR
disk found to have a crack in a rim bolt hole during a routine shop
manual ECI. The actions specified by this AD are intended to prevent
the potential for an uncontained failure of the HPTR disk, which could
result in an inflight engine shutdown, aborted takeoff, or damage to
the aircraft.
DATES: Effective July 20, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of July 20, 1998.
ADDRESSES: The service information referenced in this AD may be
obtained from CFM International, Technical Publications Department, 1
Neumann Way, Cincinnati, OH 45215; telephone (513) 552-2981, fax (513)
552-2816. This information may be examined at the Federal Aviation
Administration (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: Glorianne Messemer, Aerospace
Engineer, Engine Certification Office,
[[Page 33531]]
FAA, Engine and Propeller Directorate, 12 New England Executive Park,
Burlington, MA 01803-5299; telephone (781) 238-7132; fax (781) 238-
7199.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to CFM International (CFMI) CFM56-2,
-2A, -2B, -3, -3B, and -3C series turbofan engines was published in the
Federal Register on January 22, 1998 (63 FR 3275). That action proposed
to require a one-time eddy current inspection for cracks or gouges in
certain high pressure turbine rotor (HPTR) disks in accordance with
CFM56-2 Service Bulletin (SB) No. 72-817, dated January 14, 1997,
CFM56-2A SB No. 72-419, Revision 1, dated January 31, 1997, CFM56-2B SB
No. 72-561, Revision 1, dated January 31, 1997, and CFM56-3/-3B/-3C SB
No. 72-843, dated January 14, 1997.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
Three commenters support the rule as proposed.
Since issuance of the proposed rule, CFMI has revised CFM56-2 SB
No. 72-817, CFM56-2A SB No. 72-419, and CFM56-3/-3B/-3C SB No. 72-843.
These revisions include an update of a HPTR disk serial number
identified in Table 1. Therefore, since these SB revisions do not alter
the proposed actions, this AD will include reference to CFM56-2 SB No.
72-817, Revision 1, dated November 25, 1997, CFM56-2A SB No. 72-419,
Revision 2, dated November 14, 1997, and CFM56-3/-3B/-3C SB No. 72-843,
Revision 1, dated November 25, 1997, for the accomplishment of the HPTR
disk inspections.
In addition, this AD revises the compliance date requirement for
CFM56-2, CFM56-3, -3B, and -3C engines to 45 days after the effective
date of this AD.
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule as proposed.
There are approximately 276 engines of the affected design in the
worldwide fleet. The FAA estimates that 100 engines installed on
aircraft of U.S. registry will be affected by this AD, that it will
take approximately 300 work hours per engine to accomplish the required
actions, and that the average labor rate is $60 per work hour.
Replacement parts, if required, would cost approximately $86,000 per
engine. Based on these figures, and assuming that 16 of the inspected
HPTR disks will require replacement, the total cost impact of the AD on
U.S. operators is estimated to be $3,176,000. The manufacturer has
advised the FAA that certain costs incurred from the inspection and
replacement of parts affected by this AD may be borne by the
manufacturer; therefore, the total cost impact of this AD to U.S.
operators may be less than estimated by the FAA.
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.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a
significant economic impact, positive or negative, on a substantial
number of small entities under the criteria of the Regulatory
Flexibility Act. A final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it 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:
98-12-32 CFM International: Amendment 39-10585. Docket 97-ANE-46-
AD.
Applicability: CFM International (CFMI) CFM56-2, -2A, -2B, -3, -
3B, and -3C series turbofan engines installed on, but not limited to
McDonnell Douglas DC-8 series, Boeing 737 series, as well as Boeing
E-3, E-6, and KC-135 (military) series aircraft.
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 (c) 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: Required as indicated, unless accomplished
previously.
To prevent the potential for an uncontained failure of the high
pressure turbine rotor (HPTR) disk, which could result in an
inflight engine shutdown, aborted takeoff, or damage to the
aircraft, accomplish the following:
(a) Eddy current inspect for cracks or gouges in HPTR disks,
Part Numbers 1475M29P01, 1475M29P02, 9514M69P01, 9514M69P04,
9514M69P05, 9514M69P06, and 9514M69P09, with Serial Numbers listed
in Table 1 of the applicable Service Bulletin (SB), as follows:
(1) For CFM56-2 engines, in accordance with CFM56-2 SB No. 72-
817, Revision 1, dated November 25, 1997, within 45 days after the
effective date of this AD.
(2) For CFM56-2A engines, in accordance with CFM56-2A SB No. 72-
419, Revision 2, dated November 14, 1997, within 500 cycles in
service (CIS) after the effective date of this AD, or by December
31, 1999, whichever occurs first.
(3) For CFM56-2B engines, in accordance with CFM56-2B SB No. 72-
561, Revision 1, dated January 31, 1997, within 500 CIS after the
effective date of this AD, or by December 31, 1999, whichever occurs
first.
(4) For CFM56-3, -3B, and -3C engines, in accordance with CFM56-
3/-3B/-3C SB No. 72-843, Revision 1, dated November 25, 1997, within
45 days after the effective date of this AD.
(b) Remove from service HPTR disks found cracked or gouged, and
replace with serviceable parts.
(c) 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.
Operators shall submit their request through an appropriate FAA
Principal Maintenance Inspector, who may
[[Page 33532]]
add comments and then send it to the Manager, Engine Certification
Office.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this airworthiness directive,
if any, may be obtained from the Engine Certification Office.
(d) 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 inspection requirements of this AD can be accomplished.
(e) The actions required by this AD shall be done in accordance
with the following CFMI SBs:
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Document No. Pages Revision Date
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CFM56-2 SB No. 72-817.............. 1-2................... 1..................... November 25, 1997.
3-12.................. Original.............. January 14, 1997.
13.................... 1..................... November 25, 1997.
14-19................. Original.............. January 14, 1997.
Total Pages: 19.
CFM56-2A SB No. 72-419............. 1-2................... 2..................... November 14, 1997.
3-4................... 1..................... January 31, 1997.
5-10.................. Original.............. January 14, 1997.
11-12................. 2..................... November 14, 1997.
13-18................. Original.............. January 14, 1997.
Total Pages: 18.
CFM56-2B SB No. 72-561............. 1..................... 1..................... January 31, 1997.
2..................... Original.............. January 14, 1997.
3-4................... 1..................... January 31, 1997.
5-19.................. Original.............. January 14, 1997.
Total Pages: 19.
CFM56-3/-3B/-3C SB No. 72-843...... 1-2................... 1..................... November 25, 1997.
3-11.................. Original.............. January 14, 1997.
12.................... 1..................... November 25, 1997.
13-18................. Original.............. January 14, 1997.
Total Pages: 18.
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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 CFM International, Technical Publications
Department, 1 Neumann Way, Cincinnati, OH 45215; telephone (513) 552-
2981, fax (513) 552-2816. 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.
(f) This amendment becomes effective on July 20, 1998.
Issued in Burlington, Massachusetts, on June 5, 1998.
Mark C. Fulmer,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 98-15785 Filed 6-18-98; 8:45 am]
BILLING CODE 4910-13-U
