[Federal Register Volume 64, Number 232 (Friday, December 3, 1999)]
[Rules and Regulations]
[Pages 67708-67710]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-31070]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-ANE-76-AD Amendment 39-11446; AD 99-25-03]
RIN 2120-AA64


Airworthiness Directives; International Aero Engines AG V2500-A1 
Series Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes two airworthiness directives (ADs) 
that apply to International Aero Engines AG (IAE) V2500-A1 series 
turbofan engines. The first superseded AD, AD 98-20-18, currently 
requires removal from service of affected high pressure turbine (HPT) 
disks, identified by part number and serial number in the applicability 
paragraph of that AD, and replacement with a serviceable part. The 
second superseded AD, AD 99-05-05, requires initial and repetitive 
inspections of certain HPT stage 1 and stage 2 disks utilizing an 
improved ultrasonic method when the disks are exposed during a normal 
shop visit, and if a subsurface anomaly is found, removal from service 
and replacement with a serviceable part. This supersedure requires the 
initial

[[Page 67709]]

inspection mandated by AD 99-05-05 to be completed at the next shop 
visit regardless of the planned maintenance or the reason for shop 
removal. The repetitive inspection interval is redefined to eliminate 
the cyclic limit and thus be less restrictive. This superseding action 
is prompted by results from investigations subsequent to the 
publication of AD 98-20-18 that have revealed that the HPT disks 
affected by that AD are part of the population addressed by AD 99-05-
05. These HPT disks can be safely reintroduced into service after 
completing the initial inspection requirements mandated by this 
proposed AD. This supersedure is also prompted by further analysis that 
indicates a reduction in risk if the initial inspection required by AD 
99-05-05 is completed sooner and the subsequent required inspections 
can be redefined to eliminate the cyclic limit, thereby creating less 
burden on operators. The actions specified by this AD are intended to 
prevent HPT disk fracture, which could result in an uncontained engine 
failure and damage to the airplane.

DATES: Effective January 7, 2000.
    The incorporation by reference of International Aero Engines SB 
V2500-ENG-72-0344, dated December 18, 1998, as listed in the 
regulations, was approved by the Director of the Federal Register as of 
April 30, 1999 (64 FR 9910, March 1, 1999).
    The incorporation by reference of all other publications listed in 
the regulations is approved by the Director of the Federal Register as 
of January 7, 2000.

ADDRESSES: The service information referenced in this AD may be 
obtained from Rolls-Royce Commercial Aero Engine Limited, P.O. Box 31, 
Derby, England, DE2488J, Attention: Publication Services ICL-TP; 
telephone +44-1-33-22-46553, fax +44-1-33-22-46302. The information 
referenced in this AD 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: 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 airworthiness 
directive (AD) 98-20-18, Amendment 39-10871 (63 FR 63398, November 13, 
1998), and AD 99-05-05, Amendment 39-11053 (64 FR 9910, March 1, 1999), 
applicable to International Aero Engines AG (IAE) V2500-A1 series 
turbofan engines was published in the Federal Register on September 15, 
1999 (64 FR 50020).

Supersedure Requirements

    This supersedure requires that the initial inspection mandated by 
AD 99-05-05 be completed at the next shop visit regardless of the 
planned maintenance or the reason for shop removal. The repetitive 
ultrasonic inspection interval is redefined to eliminate the cyclic 
limit by requiring the repetitive inspection to be performed whenever 
the high pressure turbine (HPT) stage 1 or stage 2 disks are 
disassembled from the HPT module. In addition, this supersedure allows 
the disks identified by serial number (S/N) that were retired by AD 98-
20-18 to be reintroduced into service following an initial ultrasonic 
inspection specified by this AD.

Comment Received

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. One favorable comment was received.

Conclusion

    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.

Cost Impact

    Since this AD only adjusts the timing of inspections already 
required, there is no additional adverse economic impact.

Regulatory Impact

    This rule does not have federalism implications, as defined in 
Executive Order No. 13132, because it does 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 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 removing amendment 39-10871 (63 FR 
63398, November 13, 1998) and amendment 39-11053 (64 FR 9910, March 1, 
1999) and by adding a new airworthiness directive to read as follows:

99-25-03  International Aero Engines AG: Amendment 39-11446. Docket 
No. 98-ANE-76-AD. Supersedes AD 98-20-18, Amendment 39-10871, and AD 
99-05-05, Amendment 39-11053.

    Applicability: International Aero Engines AG (IAE) V2500-A1 
series turbofan engines, installed on but not limited to Airbus 
Industrie A320 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 (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 high pressure turbine (HPT) disk fracture, which 
could result in an uncontained engine failure and damage to the 
airplane, accomplish the following:

[[Page 67710]]

Inspections

    (a) Perform initial and repetitive ultrasonic inspections of HPT 
stage 1 and 2 disks for subsurface anomalies, identified by serial 
numbers (S/Ns) in Table 1 of IAE Service Bulletin (SB) V2500-ENG-72-
0344, Revision 1, dated February 12, 1999, in accordance with the 
Accomplishment Instructions of IAE SB V2500-ENG-72-0344, dated 
December 18, 1998, or Revision 1, dated February 12,1999, as 
follows:
    (1) Initially inspect at the first opportunity when the engine 
is at a maintenance base after the effective date of this AD 
regardless of the planned maintenance or the reason for engine 
removal.
    (2) Thereafter, inspect whenever the HPT stage 1 or stage 2 
disks are disassembled from the HPT module.
    (3) Remove disks from service if a subsurface anomaly is found, 
and replace with serviceable parts.

Return to Service of Certain Disks

    (b) HPT stage 1 disks, part numbers (P/N's) 2A1801, S/N's 
P100421, P100430, P100618, and P100621, may return to service 
following a successful inspection in accordance with paragraph (a) 
of this AD.

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 (ECO). 
Operators shall submit their requests through an appropriate FAA 
Principal Maintenance Inspector, which 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.

Ferry Flights

    (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.

Incorporation by Reference

    (e) The actions required by this AD shall be done in accordance 
with International Aero Engines Service Bulletin V2500-ENG-72-0344, 
dated December 18,1998, or Revision 1, dated February 12, 1999. The 
incorporation by reference of IAE SB V2500-ENG-72-0344, dated 
December 18, 1998, was previously approved by the Director of the 
Federal Register as of April 30, 1999 (64 FR 9910, March 1, 1999). 
The incorporation by reference of IAE SB V2500-ENG-72-0344, Revision 
1, dated February 12, 1999, 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 Rolls-Royce Commercial Aero Engine 
Limited, P. O. Box 31, Derby, England, DE2488J, Attention: 
Publication Services ICL-TP; telephone +44-1-33-22-46553, fax +44-1-
33-22-46302. 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 January 7, 2000.

    Issued in Burlington, Massachusetts, on November 22, 1999.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 99-31070 Filed 12-2-99; 8:45 am]
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