[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