[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: ``adcomment@faa.gov.'' 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]
BILLING CODE 4910-13-P
