[Federal Register Volume 64, Number 39 (Monday, March 1, 1999)]
[Rules and Regulations]
[Pages 9910-9911]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-4793]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-ANE-76-AD; Amendment 39-11053; AD 99-05-05]
RIN 2120-AA64
Airworthiness Directives; International Aero Engines AG (IAE)
V2500-A1 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 International Aero Engines AG (IAE) V2500-A1 series
turbofan engines, that requires initial and repetitive inspections of
certain High Pressure Turbine (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 amendment is
prompted by the results of a stage 1 HPT disk fracture investigation
which has identified a population of HPT stage 1 and 2 disks that may
have subsurface anomalies formed as a result of the processes used to
manufacture the material. 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 April 30, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 30, 1999.
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. This
information may be examined at the Federal Aviation Administration
(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) to include an airworthiness
directive (AD) that is applicable to International Aero Engines AG
(IAE) V2500-A1 series turbofan engines was published in the Federal
Register on January 6, 1999 (64 FR 787). That action proposed to
require initial and repetitive inspections of certain High Pressure
Turbine (HPT) stage 1 and stage 2 disks utilizing an improved
ultrasonic method when the disks are exposed during a normal shop
visit. The action also proposed removal from service and replacement
with a serviceable part in accordance with IAE Service Bulletin (SB)
No. V2500-ENG-72-0344, dated December 18, 1998, if a subsurface anomaly
is found.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
One commenter supports the proposed actions contained in the notice
of proposed rulemaking (NPRM).
One commenter notes that its operators are not affected by the
proposed actions contained in the NPRM.
One commenter suggests changing some of the wording in the
discussion section of the NPRM to more accurately describe the process
by which a defect within the HPT stage 1 and stage 2 disks may have
occurred. The FAA concurs and has made an appropriate wording change in
the summary section.
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. The FAA has
determined that these changes will neither increase the economic burden
on any operator nor increase the scope of the AD.
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
[[Page 9911]]
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:
99-05-05 International Aero Engines: Amendment 39-11053. Docket 98-
ANE-76-AD.
Applicability: International Aero Engines AG (IAE) Models V2500-
A1 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 (d) 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 high pressure turbine (HPT) disk fracture, which
could result in an uncontained engine failure, and damage to the
airplane, accomplish the following:
(a) Ultrasonic inspect for subsurface anomalies those HPT stage
1 and stage 2 disks, with serial numbers listed in Tables 1, 2, 3,
and 4 of IAE Service Bulletin (SB) V2500-ENG-72-0344, dated December
18, 1998, at the first opportunity when the engine is disassembled
sufficiently to afford access to the High Pressure Turbine (HPT)
subassembly, or no later than 10,000 cycles in service (CIS) from
the effective date of this AD, whichever occurs first, in accordance
with Paragraphs F (1) and (2) of IAE SB V2500-ENG-72-0344, dated
December 18, 1998.
(b) Thereafter, repetitively ultrasonic inspect for subsurface
anomalies those HPT disks identified in paragraph (a) whenever the
engine is disassembled sufficiently to afford access to the HPT
subassembly, or no later than 12,000 CIS since last ultrasonic
inspection, whichever occurs first, in accordance with Paragraph F
(1) and (2) of IAE SB V2500-ENG-72-0344, dated December 18, 1998.
(c) Those HPT disks rejected at inspection may not be
reinstalled and must be replaced with a serviceable part.
(d) 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 shall submit their requests 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.
(e) 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.
(f) The inspections must be done in accordance with the
following International Aero Engines SB:
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Document No. Pages Revision Date
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V2500-ENG-72-0344....................... 1-8 Original................... Dec. 18, 1998.
Total pages: 8
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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 Rolls-Royce Commercial Aero Engine
Limited, P. O. Box 31, Derby, England, DE2488J, Attention:
Publication Services ICL-TP. 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.
(g) This amendment becomes effective on April 30, 1999.
Issued in Burlington, Massachusetts, on February 19, 1999.
Ronald L. Vavruska,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 99-4793 Filed 2-26-99; 8:45 am]
BILLING CODE 4910-13-P
