AD 2000-22-07

[Federal Register Volume 65, Number 212 (Wednesday, November 1, 2000)]
[Rules and Regulations]
[Pages 65255-65257]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-27632]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NE-21-AD; Amendment 39-11953; AD 2000-22-07]
RIN 2120-AA64


Airworthiness Directives; International Aero Engines AG (IAE) 
V2500-A5 and -D5 Series Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain International Aero Engines AG (IAE) V2500-A5 
and -D5 series turbofan engines, identified by serial number. This 
amendment requires the removal of engines assembled with an improper 
High Pressure Turbine (HPT) module configuration from service prior to 
accumulating 5,100 or 7,600 cycles in the improper configuration, or at 
the next shop visit, depending on the type of improper HPT 
configuration, and restoration to type design. This amendment is 
prompted by reports of engines that do not conform to the engine type 
design, which could cause a Low Cycle Fatigue (LCF) life reduction of 
the HPT stage 1 disk. The actions specified by this AD are intended to 
restore engines to type design configuration and to prevent possible 
LCF failure of the HPT stage 1 disk, which could result in an 
uncontained engine failure and damage to the airplane.

DATES: Effective December 6, 2000. The incorporation by reference of 
certain publications listed in the rule is approved by the Director of 
the Federal Register as of December 6, 2000.

ADDRESSES: The service information referenced in this AD may be 
obtained from International Aero Engines AG, 400 Main Street, East 
Hartford, CT 06108; telephone: (860) 565-5515; fax: (860) 565-5510. 
This information may be examined 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.

FOR FURTHER INFORMATION CONTACT: Robert Ganley, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone: 781-
238-7138, fax: 781-238-7199.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR 39) to include an airworthiness directive 
(AD) that is applicable to International Aero Engines AG V2500-A5 and -
D5 series turbofan engines was published in the Federal Register on 
June 30, 2000 (65 FR 40555). That action proposed to require the 
removal from service of certain V2500-A5 and -D5 series engines, 
identified by serial numbers, prior to accumulating 5,100 or 7,600 
cycles in the improper configuration, or at the next shop visit, 
depending on the type of improper HPT module configuration and the 
restoration type design.

Comments Received

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the one comment received. The comment states that the manufacturer's 
service documentation is the root cause of the configuration errors, 
and that the documentation should be designed to minimize the 
probability of such errors.
    The FAA disagrees. The FAA believes that the manufacturer's service 
documentation, as currently written, is technically accurate. The 
documentation should not in itself be considered the root cause for 
configuration errors. The FAA recognizes that in some instances, 
service documentation may not be as clear as originally intended. The 
FAA continues to work with all engine manufacturers to ensure that 
clear and precise service documents are issued to alleviate any 
potential confusion by the operators.

Economic Impact

    No comments were received on the economic impact contained in the 
proposed rules.

Regulatory Impact

    This rule does not have federalism implications, as defined in 
Executive Order 13132, because it would not have

[[Page 65256]]

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 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 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:

AD-2000-22-07. International Aero Engines AG: Amendment 39-11953 
Docket No. 2000-NE-21-AD.

    Applicability: International Aero Engines AG (IAE) V2500-A5 and 
-D5 series turbofan engines listed by Serial Number (S/N) as 
follows:

V10011
V10035
V10036
V10039
V10040
V10041
V10054
V10067
V10079
V10080
V10084
V10111
V10121
V10123
V10124
V10130
V10131
V10139
V10166
V10172
V10174
V10180
V10199
V10221
V10341
V20001
V20013
V20017
V20019
V20023
V20033
V20037

These engines are installed on, but not limited to, Airbus 
Industries A319, A320, A321 series, and McDonnell Douglas MD-90 
series airplanes.

    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 (b) 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 restore the engines to type design and to prevent possible 
low cycle fatigue (LCF) failure of the HPT stage 1 disk, which could 
lead to an uncontained engine failure and damage to the airplane, 
accomplish the following:

Removal and Restoration of the HPT Module

    (a) For those engines identified by serial numbers in Table 1 of 
this AD, with HPT modules built to configuration X, X' X*, Y, or Z, 
remove from service in accordance with Table 1 and restore the HPT 
module to type design in accordance with IAE All Operators Wire 
(AOW) 1053, Issue 2, dated June 20, 2000.

                                                     Table 1
----------------------------------------------------------------------------------------------------------------
                                       HPT module                                            Reconfigure at or
         Engine serial no.           configuration               HPT hardware                    prior to--
----------------------------------------------------------------------------------------------------------------
V10084, V10035, V10036, V10039,                  X   High Flow Blades: Post SB72-0242....  The earlier of the
 V10130, V10011, V10040, V10079,                     Low Flow Duct Assembly: Pre SB72-      next shop visit; or
 V10080, V10124, V10123, V10111,                      0241.                                 accumulating either
 V20013, V20017, V10172, V10174,                     Towel Bar Seals, P/N 2A0530:           5100 cycles in
 V20019, V10180, V20023.                              Installed.                            service (CIS) in
                                                                                            configuration X, or
                                                                                            100 CIS after the
                                                                                            effective date of
                                                                                            this AD, whichever
                                                                                            occurs later.
V20037............................              X'   2 High Flow Blades: Post SB72-0242..  The earlier of the
                                                     Low Flow Duct Assembly: Pre SB72-      next shop visit; or
                                                      0241.                                 accumulating either
                                                     Towel Bar Seals, P/N 2A0530: Not       7600 CIS in
                                                      Installed.                            configuration X, or
                                                                                            100 CIS after the
                                                                                            effective date of
                                                                                            this AD, whichever
                                                                                            occurs later.
V20001, V20033....................              X*   3 or fewer High Flow Blades: Post     Next shop visit.
                                                      SB72-0242.
                                                     Low Flow Duct Assembly: Pre SB72-
                                                      0241.
                                                     Towel Bar Seals, P/N 2A0530: Not
                                                      Installed.
V10199, V10166, V10054, V10131,                  Y   High Flow Blades: Pre SB72-0242.....  Next shop visit.
 V10139, V10041, V10121, V10067,                     High Flow Duct Assembly: Post SB72-
 V10341.                                              0241.
                                                     Towel Bar Seals, P/N 2A0530:
                                                      Installed.

[[Page 65257]]

 
V10221............................               Z   Low Flow Blades: Pre SB72-0242......  Next shop visit.
                                                     High Flow Duct Assembly: Post SB72-
                                                      0241.
                                                     Towel Bar Seals, P/N 2A0530:
                                                      Installed.
----------------------------------------------------------------------------------------------------------------

Alternative Methods of Compliance

    (b) 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 (ECO). 
Operators shall submit their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, ECO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this airworthiness directive, 
if any, may be obtained from the ECO.

Special Flight Permits

    (c) 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.

Incorporation by Reference

    (d) The restoration to type design must be done in accordance 
with International Aero Engines AOW 1053, Issue 2, dated June 20, 
2000. 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 International Aero Engines AG, 
400 Main Street, East Hartford, CT 06108; telephone: (860) 565-5515; 
fax (860) 565-5510. 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.

Effective Date of This AD

    (e) This amendment becomes effective on December 6, 2000.

    Issued in Burlington, Massachusetts, on October 23, 2000.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 00-27632 Filed 10-31-00; 8:45 am]
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