[Federal Register Volume 64, Number 114 (Tuesday, June 15, 1999)]
[Rules and Regulations]
[Pages 31967-31969]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-14933]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NE-37-AD; Amendment 39-11194; AD 99-13-01]
RIN 2120-AA64


Airworthiness Directives; International Aero Engines AG V2500-A1 
and V2500-A5 Series Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain International Aero Engines AG (IAE) V2500-A1 
and V2500-A5 series turbofan engines. This action requires determining 
the need for a special borescope inspection of the high pressure 
turbine (HPT) stage 1 inner rotating airseal (TOBI ID seal) for oil 
wetting after an in-flight shutdown (IFSD). It also requires, if 
necessary, the tear down and inspection of HPT hardware. This amendment 
is prompted by reports of overheat damage to the HPT hardware caused by 
ignition of oil that leaked into the HPT from the No. 4 bearing 
compartment during an IFSD. The actions specified in this AD are 
intended to prevent failure of the HPT hardware due to ignition of oil 
trapped by the HPT TOBI ID seal, which could result in an uncontained 
engine failure and damage to the airplane.

DATES: Effective June 25, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 25, 1999.
    Comments for inclusion in the Rules Docket must be received on or 
before August 16, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 99-NE-37-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may also be sent 
via the Internet using the following address: ``9-ane-
[email protected].'' Comments sent via the Internet must contain the 
docket number in the subject line.
    The service information referenced in this AD may be obtained from 
International Aero Engines, 400 Main Street, East Hartford, CT 06108; 
telephone (860) 565-5515; fax (860) 565-5510. 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: The Federal Aviation Administration (FAA) 
has received reports of overheat damage to the high pressure turbine 
(HPT) hardware from two International Aero Engines AG (IAE) V2500-A1 
series turbofan engines. The investigation of these engines revealed 
overheat damage to the HPT hardware was caused by ignition of oil that 
leaked from the No. 4 bearing compartment during an IFSD into the HPT 
and became trapped by the stage 1 inner rotating airseal (TOBI ID 
seal). The oil ignited during subsequent operation. The results of the 
investigation show that the probable cause of oil entering the TOBI ID 
seal is due to insufficient oil scavenging capability of the No. 4 
bearing compartment during windmilling. The investigation has also 
concluded that V2500 engines that incorporate a redesigned scavenge 
tube and a redesigned or reworked TOBI ID seal have sufficient No. 4 
bearing compartment oil scavenging capability and do not require any 
special actions following an IFSD. This condition, if not corrected, 
could result in failure of the HPT hardware due to ignition of oil 
trapped by the HPT TOBI ID seal, which could result in an uncontained 
engine failure and damage to the airplane.
    The FAA has reviewed and approved the technical contents of IAE All 
Operator Wire (AOW) 1046, Issue 2, dated May 21, 1999, that describes 
procedures for determining which actions must be accomplished within 
five cycles after the IFSD. The actions are determined in AOW 
Attachments I, II, and III by the engine model, engine serial number, 
and whether the scavenge tube and TOBI ID seal have been replaced by 
new or reworked designs. The FAA has also reviewed and approved the 
technical contents of IAE service bulletins (SB's) V2500-ENG-72-0120, 
revision 2, dated October 30, 1992 or revision 3, dated May 14, 1999, 
that describe the requirements for replacing the No. 4 bearing scavenge 
tube assembly; and V2500-ENG-72-0190, revision 2, dated September 26, 
1996, and V2500-ENG-72-0351, dated May

[[Page 31968]]

31, 1999, that describe requirements for replacing or reworking the 
TOBI ID seal.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other engines of the same type design, this AD is 
being issued to prevent failure of the HPT hardware due to ignition of 
oil trapped by the HPT TOBI ID seal, which could result in an 
uncontained engine failure and damage to the airplane. This AD requires 
determining the need for a special borescope inspection of the TOBI ID 
seal for oil wetting or overheat damage within five cycles after an 
IFSD, and if necessary, tear down and inspection of the HPT module. 
Because of the complex nature of the borescope inspection, only IAE is 
currently authorized to perform the borescope inspection. IAE will 
provide training to perform the borescope inspections for those 
operators who want to perform the borescope inspections themselves. In 
the event of HPT damage, this AD requires removing affected parts from 
service and replacing with serviceable parts. Accomplish the actions in 
accordance with the AOW and SB's described previously.
    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications should identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 99-NE-37-AD.'' The postcard will be date stamped and 
returned to the commenter.
    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.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and is not a ``significant regulatory action'' 
under Executive Order 12866. It has been determined further that this 
action involves an emergency regulation under DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979). If it is determined 
that this emergency regulation otherwise would be significant under DOT 
Regulatory Policies and Procedures, a final regulatory evaluation will 
be prepared and placed in the Rules Docket. A copy of it, if filed, 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:

99-13-01  International Aero Engines AG: Amendment 39-11194. Docket 
99-NE-37-AD.

    Applicability: International Aero Engines AG (IAE) V2500-A1 
turbofan engines, all serial numbers (S/Ns), and V2500-A5 turbofan 
engines, with S/Ns V10079 and below, installed on, but not limited 
to, Airbus Industries A319, A320, and A321 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 (h) 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 failure of the high pressure turbine (HPT) hardware 
due to ignition of oil trapped by the HPT stage 1 inner rotating 
airseal (TOBI ID seal), which could result in an uncontained engine 
failure and damage to the airplane, accomplish the following:
    (a) Within five cycles after an in-flight shutdown (IFSD), 
accomplish the actions specified in the following Attachments of IAE 
All Operators Wire (AOW) 1046, Issue 2, dated May 21, 1999:
    (1) For V2500-A1 engines with S/N's below V0313, accomplish the 
actions specified in Attachment III, V2500 No.4 Compartment Oil Loss 
Risk Elimination Flow Chart; or
    (2) For V2500-A1 engines with S/N's V0313 and above, accomplish 
the actions specified in Attachment II, V2500 No.4 Compartment Oil 
Loss Risk Elimination Flow Chart; or
    (3) For V2500-A5 engines with S/N's V10079 or below, accomplish 
the actions specified in Attachment I, V2500 No.4 Compartment Oil 
Loss Risk Elimination Flow Chart.
    (4) For the purpose of this AD, engines that have been restarted 
in flight using normal procedures following an IFSD have used 1 
cycle since the IFSD.
    (b) This AD has no further requirements if no special actions 
are identified in accordance with the instructions given in IAE AOW 
1046, Issue 2, dated May 21, 1999.
    (c) If a borescope inspection of the HPT TOBI ID seal is 
required, have IAE inspect in accordance with IAE AOW 1046, Issue 2, 
dated May 21, 1999.
    (d) If any evidence of oil wetness or overheat damage is seen 
with the borescope, disassemble the HPT module, remove from

[[Page 31969]]

service any part with overheat damage, and replace with a 
serviceable part.
    (e) For V2500-A1 engines with S/N's below V0313, incorporation 
of service bulletins (SB's) V2500-ENG-72-0120, revision 2, dated 
October 30, 1992 or revision 3, dated May 14, 1999, and V2500-ENG-
72-0351, dated May 31, 1999, constitute terminating action for the 
requirements specified in paragraph (a) and paragraph (c) of this 
AD.
    (f) For V2500-A1 engines with S/N's V0313 and above, 
incorporation of SB V2500-ENG-72-0351, dated May 31, 1999, 
constitutes terminating action for the requirements specified in 
paragraph (a) and paragraph (c) of this AD.
    (g) For V2500-A5 engines with S/N's V10079 and below, 
incorporation of SB V2500-ENG-72-0190, revision 2, dated September 
26, 1996, constitutes terminating action for the requirements 
specified in paragraph (a) and paragraph (c) of this AD.
    (h) 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.

    (i) 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 
inspection requirements of this AD can be accomplished.
    (j) The inspection and optional terminating actions must be done 
in accordance with the following International Aero Engines AG AOW 
and SB's:

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            Document No.                     Pages               Revision                     Date
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AOW 1046...........................  All.................  Issue 2............  May 21, 1999.
    Total pages: 6.
SB V2500-ENG-72-0120...............  All.................  2..................  October 30, 1992.
    Total pages: 10.
SB V2500-ENG-72-0120...............  1...................  3..................  May 14, 1999.
                                     2...................  2..................  October 30, 1992.
                                     3...................  3..................  May 14, 1999.
                                     4 to 7..............  2..................  October 30, 1992.
                                     8 to 9..............  3..................  May 14, 1999.
                                     10..................  2..................  October 30, 1992.
    Total pages: 10.
SB V2500-ENG-72-0190...............  1...................  2..................  September 26, 1996.
                                     2 to 18.............  1..................  April 30, 1994.
                                     19..................  2..................  September 26, 1996.
                                     20 to 21............  1..................  April 30, 1994.
    Total pages: 21.
SB V2500-ENG-72-0351...............  All.................  Original...........  May 31, 1999.
    Total pages: 14.
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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 International Aero Engines, 400 
Main Street, East Hartford, CT 06108; telephone (860) 565-5515; fax 
(860) 565-5510. 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.
    (k) This amendment becomes effective on June 25, 1999.

    Issued in Burlington, Massachusetts, on June 4, 1999.
Mark C. Fulmer,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 99-14933 Filed 6-14-99; 8:45 am]
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