[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 The first superseded AD, AD 98-20-18, currently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second superseded AD, AD 99-05-05, requires initial and repetitive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]
BILLING CODE 4910-13-U
