[Federal Register Volume 64, Number 28 (Thursday, February 11, 1999)]
[Rules and Regulations]
[Pages 6786-6788]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-3037]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-ANE-08-AD; Amendment 39-11027; AD 99-04-03]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to International Aero Engines AG (IAE) V2500-A5/-D5 series 
turbofan engines, that requires the removal from service of certain 
high pressure compressor (HPC) stage 9-12 drums prior to reaching the 
new reduced cyclic life limits, and replacement with serviceable parts. 
This amendment is prompted by the reduction of the life limit for 
certain IAE V2500 HPC stage 9-12 drums due to higher stresses in this 
part than originally predicted. The actions specified by this AD are 
intended to prevent high pressure compressor (HPC) stage 9-12 drum 
failure, which could result in an uncontained engine failure and damage 
to the aircraft.

DATES: Effective date April 12, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 12, 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-A5/-D5 series turbofan engines was published in the Federal 
Register on September 28, 1998 (63 FR 51545). That action proposed to 
require removal from service of certain HPC stage 9-12 drums prior to 
reaching new, reduced cyclic life limits, and replacement with 
serviceable parts in accordance with IAE Service Bulletin (SB) No. 
V2500-ENG-72-0293, dated December 19, 1997.
    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 identifies a typographical error in paragraph (a) of 
the Compliance section and requests that ``Remove for service'' be 
changed to ``Remove from service.'' The FAA concurs. The typographical 
error has been corrected to ``Remove from service.''
    Two commenters express concern about the clarity and intent of 
paragraph (d) of the Compliance section. They believed that the second 
sentence of paragraph (d) suggested a life limit of all part number (P/
N) stage 9-12 drums are limited by the requirements of the proposed AD. 
They are concerned that this could be interpreted to mean that future 
stage 9-12 drums would have their life limits controlled by this 
proposed AD. The FAA concurs. Paragraph (d) has been changed to add 
``P/N 6A4156'' to the end of the sentence. The last sentence will now 
state ``Thereafter, except as provided in paragraph (e) of this AD, no 
alternative cyclic retirement life limits may be approved for HPC stage 
9-12 drum, P/N 6A4156.''
    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 with the changes described 
previously. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.
    There are approximately 400 International Aero Engines AG (IAE) 
V2500-A5/-D5 series turbofan engines of the affected design in the 
worldwide fleet. The FAA estimates that 162 engines installed on 
airplanes of U.S. registry will be affected by this AD and that it will 
take no additional work hours per engine to accomplish the required 
actions. Required parts, on a prorated basis, will cost approximately 
$49,000 per engine. Based on these figures, the total cost impact of 
the AD

[[Page 6787]]

on U.S. operators is estimated to be $7,900,000
    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 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:

99-04-03  International Aero Engines: Amendment 39-11027. Docket 98-
ANE-08-AD.

    Applicability: International Aero Engines AG (IAE) Models V2522-
A5, V2524-A5, V2527-A5, V2527E-A5, V2530-A5, V2533-A5, V2525-D5, 
V2528-D5 turbofan engines, installed on but not limited to Airbus 
Industrie A319, A320, A321 series and McDonnell Douglas MD-90 series 
aircraft.

    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 (e) 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 compressor (HPC) stage 9-12 drum 
failure, which could result in an uncontained engine failure and 
damage to the aircraft, accomplish the following:
    (a) Remove from service HPC stage 9-12 drums, part number (P/N) 
6A4156, operated in a single engine model at a single thrust rating 
prior to accumulating the new, reduced cyclic life limits, which are 
dependent upon the engine installation and thrust rating, as 
described in Table 1 of IAE Service Bulletin (SB) No. V2500-ENG-72-
0293, dated December 19, 1997, and replace with a serviceable part.
    (b) Remove from service HPC stage 9-12 drums, P/N 6A4156, 
installed in engines which operate at a mixture of thrust ratings, 
prior to accumulating the cyclic life limit of the highest thrust 
rating employed, as described in Table 1 of IAE SB No. V2500-ENG-72-
0293, dated December 19, 1997, and replace with a serviceable part. 
The use of an HPC stage 9-12 drum, P/N 6A4156, at a higher thrust 
rating for even a single flight invokes the cyclic life limit 
applicable for the higher thrust rating.
    (c) Remove from service HPC stage 9-12 drums, P/N 6A4156, 
removed from one engine model and installed into another engine 
model or operated at different thrust ratings prior to accumulating 
the applicable component cyclic life limit for the engine model with 
the highest thrust rating, as described in Table 1 of IAE SB No. 
V2500-ENG-72-0293, dated December 19, 1997, regardless of the cycles 
in service at this rating, and replace with a serviceable part.
    (d) This AD establishes new cyclic retirement life limits for 
HPC stage 9-12 drums, part number (P/N) 6A4156. Thereafter, except 
as provided in paragraph (e) of this AD, no alternative cyclic 
retirement life limits may be approved for HPC stage 9-12 drums, P/N 
6A4156.
    (e) 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.

    (f) 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.
    (g) The cyclic retirement life limits shall be determined in 
accordance with the following International Aero Engines SB:

----------------------------------------------------------------------------------------------------------------
             Document No.                 Pages             Revision                         Date
----------------------------------------------------------------------------------------------------------------
V2500-ENG-72-0293....................          1-7  Original................  December 19, 1997.
    Total pages: 7
----------------------------------------------------------------------------------------------------------------


[[Page 6788]]

    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.
    (h) This amendment becomes effective on April 12, 1999.

    Issued in Burlington, Massachusetts, on February 1, 1999.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 99-3037 Filed 2-10-99; 8:45 am]
BILLING CODE 4910-13-P