[Federal Register Volume 67, Number 124 (Thursday, June 27, 2002)]
[Rules and Regulations]
[Pages 43232-43234]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-16173]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-ANE-38-AD; Amendment 39-12790; AD 2002-13-03]
RIN 2120-AA64


Airworthiness Directives; CFM International (CFMI) CFM56-2, -2A, 
-2B, -3, -3B, -3C, -5, -5B, -5C, and -7B Series Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), that is applicable to certain CFM International (CFMI) CFM56 
series turbofan engines. That AD currently requires revisions to the 
Airworthiness Limitations Section of applicable Engine Shop Manuals 
(ESM's) to include required enhanced inspection of selected critical 
life-limited parts at each piece-part exposure. This amendment requires 
revisions to the Airworthiness Limitations Section of the applicable 
manufacturer's manuals and air carrier's approved continuous 
airworthiness maintenance program to incorporate additional inspections 
of selected critical life-limited parts at each piece-part exposure. 
This amendment is prompted by an FAA study of in-service events 
involving uncontained failures of critical rotating parts. The actions 
specified by this AD are intended to prevent critical life-limited 
rotating engine part failure, which could result in an uncontained 
engine failure and damage to the airplane.

DATES: Effective date August 1, 2002.

ADDRESSES: Information regarding this action may be examined, by 
appointment, at the Federal Aviation Administration (FAA), New England 
Region, Office of the Regional Counsel, 12 New England Executive Park, 
Burlington, MA.

FOR FURTHER INFORMATION CONTACT: Diane Cook, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7133, fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 2000-12-01, 
Amendment 39-11779 (65 FR 37031, June 13, 2000), which is applicable to 
certain CFMI CFM56 series turbofan engines, was published in the 
Federal Register on October 5, 2001, (66 FR 50910). That action 
proposed to modify the airworthiness limitations section of the 
manufacturer's manual and an air carrier's approved continuous 
airworthiness maintenance program to incorporate additional inspection 
requirements.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Typographical Errors

    Four commenters requested typographical errors be corrected in the 
Mandatory Inspections Table as follows:
     For HPT Disk, change Engine Manual Section from 75-72-02 
to 75-52-02.
     For HPC Rear (CDP) Air Seal, change Engine Manual Section 
from 72-52-03 to 72-31-08.
     For LPT Stub Shaft, change Engine Models from All to -2, -
2A, -2B, -3, -3B, and -3C.
     For LPT Stub Shaft, change Engine Manual Section from 72-
52-03 to 72-55-02.
     For LPT Shaft, change Inspection from FPI to MPI.
    The FAA agrees and has corrected these typographical errors in the 
final rule.

Concern for Lead Time

    One commenter is concerned that for operators to put procedures and 
tooling in place in time to comply with the AD, the manufacturer should 
release the Engine Manual time limit and procedural changes by 
Temporary Revision before the issuance of the AD, or, revise the AD 
compliance time to state compliance to be within 30 days after the 
issuance of the Engine Manual revision (or Temporary Revision).
    The FAA understands the commenter's concern. The FAA is aware that 
the manufacturer has not yet issued Temporary Revisions to the Engine 
Manual time limits section. However, the existing AD and this final 
rule allow the manufacturer up to 30 days after the effective date of 
the AD to issue the necessary revisions to the time limits section. 
Therefore, no action is necessary to address the commenter's 
observation.

Question on Model Effectivity

    One commenter asks why the proposed rule does not affect the 
various models of the CFM56-5A engine. The FAA understands that the 
commenter is referring to the CFM56-5-A engine in the proposed rule and 
in the final rule that is an engine subset covered under the -5 series. 
The -5 series is listed in the Applicability section, and therefore, 
the CFM56-5-A engine is included in the applicability 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 with the changes described 
previously. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Economic Analysis

    The FAA estimates that 5,100 CFM56 engines installed on airplanes 
of US registry would be affected by this AD and that there are 
approximately 2,300 piece part annual inspections that would be 
required. It would take approximately 2,775 work hours to do these 
inspections. The average labor rate is $60 per work hour. The total 
estimated annual cost of the new inspections on US operators is 
expected to be approximately $166,500.

[[Page 43233]]

Regulatory Analysis

    This final rule does not have federalism implications, as defined 
in Executive Order 13132, because it would not have a substantial 
direct effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government. Accordingly, 
the FAA has not consulted with state authorities prior to publication 
of this final rule.
    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 the DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) if promulgated, 
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 by contacting the Rules Docket at the location provided 
under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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 removing Amendment 39-11779 (65 FR 
3731, June 13, 2000), and by adding a new airworthiness directive, 
Amendment 39-12790, to read as follows:

2002-13-03  CFM International: Amendment 39-12790. Docket No. 98-
ANE-38-AD. Supersedes AD 2000-12-01, Amendment 39-11779.

Applicability

    This airworthiness directive (AD) is applicable to CFM 
International (CFMI) CFM56-2, -2A, -2B, -3, -3B, -3C, -5, -5B, -5C, 
and -7B series turbofan engines, installed on but not limited to 
McDonnell Douglas DC-8 series, Boeing 737 series, Airbus Industrie 
A319, A320, A321, and A340 series, as well as Boeing C-135, E-3, E-
6, KC-135, KE-3, and RC-135 (military) series airplanes.

    Note 1: This 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

    Compliance with this AD is required as indicated, unless already 
accomplished.
    To prevent critical life-limited rotating engine part failure, 
which could result in an uncontained engine failure and damage to 
the airplane, accomplish the following:

Inspections

    (a) Within the next 30 days after the effective date of this AD, 
revise the Airworthiness Limitations Section (chapter 05-00-00) of 
Engine Shop Manual (ESM) CFMI-TP.SM.4, for CFM56-2 series engines, 
ESM CFMI-TP.SM.6, for CFM56-2A/-2B series engines, ESM CFMI-TP.SM.5, 
for CFM56-3/-3B/-3C series engines, ESM CFMI-TP.SM.7 for CFM56-5 
series engines, ESM CFMI-TP.SM.9 for CFM56-5B series engines, ESM 
CFMI-TP.SM.8 for CFM56-5C series engines, and ESM CFMI-TP.SM.10 for 
CFM56-7B series engines, and for air carrier operations, revise the 
approved continuous airworthiness maintenance program, by adding the 
following:
    ``MANDATORY INSPECTIONS
    (1) Perform inspections of the following parts at each piece-
part opportunity in accordance with the Inspection/Check section 
instructions provided in the applicable manual sections listed 
below:

----------------------------------------------------------------------------------------------------------------
                                                                       Engine
            Engine models                       Part name              manual               Inspection
                                                                      section
----------------------------------------------------------------------------------------------------------------
All Models..........................  Fan Disk (All Part Numbers       72-21-03  Disk Fluorescent Penetrant
                                       (P/N)).                                    Inspection (FPI) and Disk Bore
                                                                                  and Dovetail Eddy Current
                                                                                  Inspection (ECI).
----------------------------------------------------------------------------------------------------------------
All Models..........................  Fan Shaft (All P/N).........     72-22-01  Magnetic Particle Inspection
                                                                                  (MPI).
----------------------------------------------------------------------------------------------------------------
CFM56-2, -2A, -2B, -3, -3B, and -3C.  HPT Disk (All P/N)..........     72-52-02  FPI, Disk Bore ECI and Disk Rim
                                                                                  Bolt Hole(s) ECI.
----------------------------------------------------------------------------------------------------------------
CFM56-5,-5B, -5C, and -7B...........  HPT Disk (All P/N)..........     72-52-02  FPI, Disk Bore ECI.
----------------------------------------------------------------------------------------------------------------
CFM56-2.............................  HPT Front Rotating Air Seal      72-52-03  FPI, Seal Bore ECI and Bolt
                                       (All P/N).                                 Hole(s) or Focused FPI as
                                                                                  applicable.
----------------------------------------------------------------------------------------------------------------
CFM56-2A, -2B, -3, -3B, and -3C.....  HPT Front Rotating Air Seal      72-52-03  FPI, Seal Bore ECI and Bolt
                                       (All P/N).                                 Hole(s) ECI.
----------------------------------------------------------------------------------------------------------------
CFM56-5, -5B, -5C, and -7B..........  HPT Front Rotating Air Seal      72-52-03  FPI, Seal Bore ECI and Bolt
                                       (All P/N).                                 Hole(s) Focused FPI.
----------------------------------------------------------------------------------------------------------------
All Models..........................  HPC Stage 1-2 Spool (All P/      72-31-04  FPI.
                                       N).
----------------------------------------------------------------------------------------------------------------
All Models..........................  HPC Stage 3 Disk (All P/N)..     72-31-05  FPI.
----------------------------------------------------------------------------------------------------------------
All Models..........................  HPC Stage 4-9 Spool (All P/      72-31-06  FPI.
                                       N).
----------------------------------------------------------------------------------------------------------------
All Models..........................  HPC Front Shaft (All P/N)...     72-31-07  FPI
----------------------------------------------------------------------------------------------------------------

[[Page 43234]]

 
All Models..........................  HPC Rear (CDP) Air Seal (All     72-31-08  FPI.
                                       P/N).
----------------------------------------------------------------------------------------------------------------
All Models..........................  LPT Stage 1 Disk (All P/N)..     72-54-03  FPI.
----------------------------------------------------------------------------------------------------------------
All Models..........................  LPT Stage 2 Disk (All P/N)..     72-54-03  FPI.
----------------------------------------------------------------------------------------------------------------
All Models..........................  LPT Stage 3 Disk (All P/N)..     72-54-03  FPI
----------------------------------------------------------------------------------------------------------------
All Models..........................  LPT Stage 4 Disk (All P/N)..     72-54-03  FPI.
----------------------------------------------------------------------------------------------------------------
CFM56-5C............................  LPT Stage 5 Disk (All P/N)..     72-54-03  FPI.
----------------------------------------------------------------------------------------------------------------
All Models..........................  LPT Rotor Support (All P/N).     72-54-05  FPI.
----------------------------------------------------------------------------------------------------------------
All Models..........................  LPT Shaft (All P/N).........     72-55-01  MPI.
----------------------------------------------------------------------------------------------------------------
CFM56-2, -2A, -2B, -3, -3B and -3C..  LPT Stub Shaft (All P/N)....     72-55-02  FPI.
----------------------------------------------------------------------------------------------------------------

    (2) For the purposes of these mandatory inspections, piece-part 
opportunity means:
    (i) The part is considered completely disassembled when 
accomplished in accordance with the disassembly instructions in the 
manufacturer's engine manual; and
    (ii) The part has accumulated more than 100 cycles in service 
since the last piece-part opportunity inspection, provided that the 
part was not damaged or related to the cause for its removal from 
the engine.''
    (b) Except as provided in paragraph (c) of this AD, and 
notwithstanding contrary provisions in Sec. 43.16 of the Federal 
Aviation Regulations (14 CFR 43.16), these mandatory inspections 
must be performed only in accordance with the Time Limits section of 
the manufacturer's ESM.

Alternative Methods of Compliance

    (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 must submit their request 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.

Special Flight Permits

    (d) 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 airplane to a location where the 
requirements of this AD can be accomplished.

Continuous Airworthiness Maintenance Program

    (e) FAA-certificated air carriers that have an approved 
continuous airworthiness maintenance program in accordance with the 
record keeping requirement of Sec. 121.369(c) of the Federal 
Aviation Regulations (14 CFR 121.369(c)) of this chapter must 
maintain records of the mandatory inspections that result from 
revising the Airworthiness Limitations Section of the applicable ESM 
and the air carrier's continuous airworthiness program. 
Alternatively, certificated air carriers may establish an approved 
system of record retention that provides a method for preservation 
and retrieval of the maintenance records that include the 
inspections resulting from this AD, and include the policy and 
procedures for implementing this alternate method in the air 
carrier's maintenance manual required by Sec. 121.369(c) of the 
Federal Aviation Regulations (14 CFR 121.369 (c)); however, the 
alternate system must be accepted by the appropriate PMI and require 
the maintenance records be maintained either indefinitely or until 
the work is repeated. Records of the piece-part inspections are not 
required under Sec. 121.380(a)(2)(vi) of the Federal Aviation 
Regulations (14 CFR 121.380(a)(2)(vi)). All other operators must 
maintain the records of mandatory inspections required by the 
applicable regulations governing their operations.

    Note 3: The requirements of this AD have been met when the ESM 
changes are made and air carriers have modified their continuous 
airworthiness maintenance plans to reflect the requirements in the 
applicable ESM.

Effective Date

    (f) This amendment becomes effective on August 1, 2002.

    Issued in Burlington, Massachusetts, on June 17, 2002.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 02-16173 Filed 6-26-02; 8:45 am]
BILLING CODE 4910-13-P