[Federal Register Volume 62, Number 65 (Friday, April 4, 1997)]
[Rules and Regulations]
[Pages 16067-16069]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-7979]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 95-ANE-65; Amendment 39-9958; AD 97-06-01]
RIN 2120-AA64


Airworthiness Directives; CFM International CFM56-5, -5B, and -5C 
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 CFM56-5, -5B, and -5C series turbofan 
engines, that requires initial and repetitive borescope inspections of 
the stage 1 disk bore of certain high pressure compressor rotor (HPCR) 
stage 1-2 spools for rubs and scratches, and replacement, if found 
rubbed or scratched, with a serviceable part. This AD also requires 
removal and replacement of certain stationary number 3 bearing aft air/
oil seals as terminating action to the inspection program. This 
amendment is prompted by a report of an engine found with a rub on the 
forward corner of the HPCR stage 1 disk bore due to contact with the 
stationary number 3 bearing aft air/oil seal. The actions specified by 
this AD are intended to prevent a failure of the stage 1 disk of the 
HPCR stage 1-2 spool, which could result in an uncontained engine 
failure and damage to the aircraft.

DATES: Effective June 3, 1997.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 3, 1997.

ADDRESSES: The service information referenced in this AD may be 
obtained from CFM International, Technical Publications Department, One 
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 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.

FOR FURTHER INFORMATION CONTACT: Robert J. Ganley, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone (617) 
238-7138; fax (617) 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) CFM56-5, 
-5B, and -5C series turbofan engines was published in the Federal 
Register on June 4, 1996 (61 FR 28112). That action proposed to require 
initial and repetitive borescope inspections of the stage 1 disk bore 
of certain high pressure compressor rotor (HPCR) stage 1-2 spools for 
rubs and scratches, and replacement, if found rubbed or scratched, with 
a serviceable part. That action also proposed to require removal and 
replacement of certain stationary number 3 bearing aft air/oil seals as 
terminating action to the inspection program.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

[[Page 16068]]

    The commenter supports the rule as proposed.
    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 131 engines of the affected design in the 
worldwide fleet. The manufacturer has advised the FAA that there are no 
engines installed on U.S. registered aircraft that would be affected by 
this AD. Therefore, there is no associated cost impact on U.S. 
operators as a result of this AD. However, should an affected engine be 
imported on an aircraft and placed on the U.S. registry in the future, 
it will take approximately 402 work hours to accomplish the required 
actions, and the average labor rate is $60 per work hour. Required 
parts will cost approximately $87,700 per engine. Based on these 
figures, the cost impact of the AD is estimated to be $111,820 per 
engine.
    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:

97-06-01  CFM International: Amendment 39-9958. Docket 95-ANE-63.

    Applicability: CFM International (CFMI) CFM56-5, -5B, and -5C 
series turbofan engines, installed on but not limited to Airbus 
A320, A321, and A340 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 (h) 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 a failure of the stage 1 disk of the high pressure 
compressor rotor (HPCR) stage 1-2 spool, which could result in an 
uncontained engine failure and damage to the aircraft, accomplish 
the following:
    (a) For CFM56-5, -5B, and -5C engines that have a stationary 
number 3 bearing aft air/oil seal, Part Number (P/N) 1364M71G02, 
installed, inspect the stage 1 disk of the HPCR stage 1-2 spool in 
accordance with the Accomplishment Instructions of CFM56-5 Service 
Bulletin (SB) No. 72-440, CFM56-5B SB No. 72-064, or CFM56-5C SB No. 
72-229, all Revision 2, dated June 23, 1995, as applicable, as 
follows:
    (1) If the disk has not been previously inspected prior to the 
effective date of this AD, inspect prior to accumulating 2,200 
cycles since new (CSN).
    (2) If the disk has been previously inspected prior to the 
effective date of this AD, and the disk was found not to be rubbed 
or scratched, reinspect prior to accumulating 2,200 cycles since 
last inspection (CSLI).
    (b) Thereafter, for disks that have been inspected in accordance 
with paragraph (a)(1) or (a)(2) of this AD, inspect in accordance 
with the Accomplishment Instructions of CFM56-5 SB No. 72-440, 
CFM56-5B SB No. 72-064, or CFM56-5C SB No. 72-229, all Revision 2, 
dated June 23, 1995, as applicable, at intervals not to exceed 2,200 
CSLI.
    (c) Remove from service HPCR stage 1-2 spools with rubbed or 
scratched stage 1 disks and replace with a serviceable part, as 
follows:
    (1) For spools with less than 2,200 CSN on the effective date of 
this AD, at the next engine shop visit after the effective date of 
this AD, or prior to accumulating 2,200 CSN, whichever occurs first.
    (2) For spools with 2,200 CSN or more on the effective date of 
this AD, at the next engine shop visit after the effective date of 
this AD, or prior to accumulating 2,200 CSLI, whichever occurs 
first.
    (d) Remove from service stationary number 3 aft air/oil seals, 
P/N 1364M71G02, at the next engine shop visit after the effective 
date of this AD, and replace with a serviceable part. Compliance 
with this paragraph constitutes terminating action to the inspection 
requirements of paragraphs (a)(1), (a)(2), and (b) of this AD.
    (e) For the purpose of this AD, a serviceable HPCR stage 1-2 
spool is defined as a spool without a rub or scratch indication on 
the stage 1 disk, a P/N 1834M55G01 spool, or a spool that has 
accomplished the stage 1 disk rework in accordance with any revision 
level of CFM56-5 SB No. 72-442, CFM56-5B SB No. 72-066, or CFM56-5C 
SB No. 72-230, as applicable.
    (f) For the purpose of this AD, a serviceable stationary number 
3 bearing aft air/oil seal is defined as any seal other than a P/N 
1364M71G02 seal.
    (g) For the purpose of this AD, an engine shop visit is defined 
as the induction of an engine into the shop for any reason.
    (h) 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 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.

    (i) Special flight permits may be issued in accordance with 
Secs. 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.
    (j) 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     
------------------------------------------------------------------------
CFM56-5 SB No. 72-440..........  1-9                  2  June 23, 1995. 
  Total pages: 9.                                                       
CFM56-5B SB No. 72-064.........  1-9                  2  June 23, 1995. 
  Total pages: 9.                                                       
CFM56-5C SB No. 72-229.........  1-9                  2  June 23, 1995. 

[[Page 16069]]

                                                                        
  Total Pages: 9.                                                       
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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, One 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 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.
    (k) This amendment becomes effective on June 3, 1997.

    Issued in Burlington, Massachusetts, on February 27, 1997.
James C. Jones,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 97-7979 Filed 4-3-97; 8:45 am]
BILLING CODE 4910-13-U