Airworthiness Directives; International Aero Engines AG (IAE) V2500 Series Turbofan Engines, 40715-40719 [E8-15686]
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40715
Rules and Regulations
Federal Register
Vol. 73, No. 137
Wednesday, July 16, 2008
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
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REGISTER issue of each week.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28058; Directorate
Identifier 2007–NE–08–AD; Amendment 39–
15610; AD 2008–14–15]
Examining the AD Docket
RIN 2120–AA64
Airworthiness Directives; International
Aero Engines AG (IAE) V2500 Series
Turbofan Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
dwashington3 on PRODPC61 with RULES
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for IAE
V2500–A1, V2522–A5, V2524–A5,
V2527–A5, V2527E–A5, V2527M–A5,
V2530–A5, V2533–A5, V2525–D5, and
V2528–D5 turbofan engines. This AD
requires removing certain No. 4 bearing
oil system components from service at
the next shop visit or by an end date
determined by the engine model. This
AD results from instances of oil loss
from the No. 4 bearing compartment.
We are issuing this AD to prevent heat
damage to high-pressure turbine (HPT)
and low-pressure turbine (LPT) critical
life limited hardware such as the HPT
stage 1–2 airseal. Damage to the HPT
stage 1–2 airseal could cause
uncontained engine failure and damage
to the airplane.
DATES: This AD becomes effective
August 20, 2008.
ADDRESSES: The Docket Operations
office is located at Docket Management
Facility, U.S. Department of
Transportation, 1200 New Jersey
Avenue, SE., West Building Ground
Floor, Room W12–140, Washington, DC
20590–0001.
FOR FURTHER INFORMATION CONTACT:
Mark Riley, Aerospace Engineer, Engine
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15:04 Jul 15, 2008
Certification Office, FAA, Engine and
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
telephone (781) 238–7758; fax (781)
238–7199.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
a proposed AD. The proposed AD
applies to IAE V2500–A1, V2522–A5,
V2524–A5, V2527–A5, V2527E–A5,
V2527M–A5, V2530–A5, V2533–A5,
V2525–D5, and V2528–D5 turbofan
engines. We published the proposed AD
in the Federal Register on July 9, 2007
(72 FR 37126). That action proposed to
require removing certain No. 4 bearing
oil system components from service at
the next shop visit or by an end date
determined by the engine model.
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You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
(800) 647–5527) is provided in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Requests To Change Compliance
Schedule
Three commenters, Air Transport
Association, United Airlines, and Jet
Blue Airways ask that we change the
compliance:
• To require removing the parts only
when they access the No. 4 bearing
compartment, or
• For engines that don’t require
access to the No. 4 bearing compartment
at the next shop visit, to permit them to
defer removing the parts to the
subsequent shop visit, but not later than
June 30, 2011.
The commenters state that changing
the compliance times will avoid an
undue burden of forcing every engine
visit to access the No. 4 bearing
compartment and will avoid aircraft-on-
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ground situations due to lack of spare
parts.
We don’t agree. We developed the
compliance requirements to maintain an
acceptable level of safety for the entire
V2500 fleet. Revising the compliance
requirements will result in having to
accelerate the program in order to
maintain the same level of safety. That
will most likely have an adverse impact
on the fleet, due to forcing additional
engine removals. The engine
manufacturer, IAE, has also stated that
a sufficient supply of spare parts exists
to handle incorporation within the
compliance requirements of the AD,
including unexpected shop visit
situations. However, operators who
have special conditions may propose
alternate compliance schedules, if they
can show that the alternate compliance
schedules provide an acceptable level of
safety. We didn’t change the AD.
Request To Address Design Deficiencies
in the HPT Stage 1–2 Airseal
One commenter, Jet Blue Airways,
asks us to revise the AD to address
design deficiencies in the HPT Stage
1–2 airseal as a contributor to HPT
distress, rather than attributing the root
cause of all HPT Stage 1–2 airseal
distress to oil in the turbine. The
commenter states that one of the
reported ‘‘confirmed instances of oil
loss’’ in the turbine is inaccurate. One
investigation, which was categorized as
an ‘‘oil in turbine’’ event, revealed no
substantive evidence of oil loss in the
turbine, or thermal oil ignition that
could have caused the dimensional
defects in the HPT Stage 1–2 airseal. It
is not beyond reasonable speculation
that, of the remaining 23 events, some
percentage was incorrectly stated as
related to ‘‘No. 4 bearing compartment
oil loss.’’
We don’t agree. We have been
involved in the manufacturer’s
Engineering Investigations for each of
the subject ‘‘oil in turbine’’ (OIT) events,
and agree with the manufacturer’s
conclusions. Due to the operating
conditions surrounding the No. 4
bearing compartment, it can be
extremely difficult, following engine
operation, to detect either evidence of
oil loss, or thermo oil ignition. The
investigation concluded that the HPT
Stage 1–2 airseal distress experienced is
a result of thermo oil ignition and not
due to design deficiencies in the HPT
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Federal Register / Vol. 73, No. 137 / Wednesday, July 16, 2008 / Rules and Regulations
Stage 1–2 airseal. The investigation also
concluded that measurement of specific
HPT Stage 1–2 airseal dimensions is a
reliable method of determining if oil
ignition has occurred. We did not
change the AD.
Request To Eliminate the Requirement
To Incorporate ‘‘OIT Package 2’’
The same commenter, Jet Blue, asks
us to revise the AD to eliminate the
requirement to incorporate the ‘‘OIT
Package 2’’ for compliance. The ‘‘OIT
Package 2’’ includes mainly external
hardware revisions to eliminate ‘‘oil
traps’’ in the oil scavenge tubes for the
No. 4 bearing compartment that may
adversely impact oil scavenge
capability. The commenter states ‘‘To
our knowledge, no V2527–A5 engine
incorporating the modification
standards of ‘OIT Package’ have been
found with the reported defects or
suspected of No. 4 bearing compartment
loss.’’
We don’t agree. We have reviewed the
results of the Engineering Investigation
of the No. 4 bearing compartment oil
loss events, and agree with the
manufacturer’s conclusions that all
hardware identified in Tables 1, 2, and
3 of this AD contribute to the root cause
of insufficient oil scavenging from the
No. 4 bearing compartment. We didn’t
change the AD.
Request To Revise the NPRM To State
a Significant Economic Impact
The same commenter, Jet Blue, asks
us to revise the AD to state that the
proposed rule would have a significant
economic impact. The commenter states
that the modification would cost more
than $8,000,000 for its fleet.
We don’t agree. In order for us to
categorize an AD as a ‘‘significant
economic impact’’ to operators, the total
cost of the AD must exceed
$100,000,000 per year. We based our
economic assessment for this AD on
actual hardware replacement cost (using
the manufacturer’s spare parts pricing),
the estimated number of work-hours (at
$80 per hour) required to comply with
the AD, and the estimated number of
shop visits per year. Based on those
figures, we estimate the cost of the
proposed AD to U.S. operators to be
$45,037,165 per year, which is below
the $100,000,000 threshold criterion.
We didn’t change the AD.
Request To Incorporate IAE Service
Bulletin V2500–ENG–72–0541 Into the
AD
The same commenter, Jet Blue
Airways, requests that we revise the AD
to incorporate IAE Service Bulletin (SB)
V2500–ENG–72–0541 into the AD. The
commenter states that tracking all of the
individual parts listed in the AD,
especially from parts that are not
serialized, is cumbersome and beyond
reasonable and customary standards.
We don’t agree. Due to the complexity
of the various IAE SBs, we determined
that it would be clearer to list in the AD,
only the parts that operators must
remove from service. We list IAE SB
V2500–ENG–72–0541 in the Related
Information section of the AD. That SB
provides specific instructions and the
current replacement part information.
Listing only the parts that the operators
must remove from service also provides
operators with increased flexibility for
installing other approved parts not
listed in the IAE SB. However, we have
added a statement in the Compliance
section of the AD that states ‘‘If you
have accomplished IAE Service Bulletin
V2500–ENG–72–0541, Revision 4, dated
March 12, 2008, you have complied
with this AD.’’
Request To Correct Certain Information
in the AD
One commenter, IAE, asks us to
correct certain information in the
Compliance section of the AD.
We agree. We have:
• Corrected the part number (P/N) for
the Seal Assembly, No. 4 Bearing, Front,
in Table 2 of the AD, from P/N 2A0853
to P/N 2A2055.
• Deleted P/N 2A0830–01, Tube,
Scavenge, No. 4 Bearing Assy, from
Table 2 of the AD.
• Deleted P/N 2A1949–01, Tube,
Scavenge, No. 4 Bearing Assy, from
Table 2 of the AD.
• Deleted P/N 5R8111, Tube A/O Oil,
No. 4 Bearing Scav Dif Case to Bif Panel,
from Table 2 of the AD.
• Added paragraph (j) for V2525–D5
and V2528–D5 engines stating that with
HPT stage 1 rotor assembly, P/Ns
2A9521–002 and 2A9621–002, the stage
1 HPT hub metering plug, P/N 2A3182,
does not need to be removed.
• Replaced IAE Service Bulletin
V2500–ENG–72–0541, Revision 1, dated
February 26, 2007, in the Related
Information paragraph, with IAE Service
Bulletin V2500–ENG–72–0541, Revision
4, dated March 12, 2008.
Conclusion
We have carefully reviewed the
available data, including the comments
received, and determined that air safety
and the public interest require adopting
the AD with the changes described
previously. We have determined that
these changes will neither increase the
economic burden on any operator nor
increase the scope of the AD.
Costs of Compliance
We estimate that this AD will affect
686 engines installed on airplanes of
U.S. registry. Of those 686 engines, the
operators of nineteen V2500–A1
engines, thirty –A5 engines and twentyone –D5 engines have already complied
with the requirements in this AD.
COSTS OF COMPLIANCE PER YEAR BY ENGINE MODEL
Number of
engines per
year
Engine model
dwashington3 on PRODPC61 with RULES
V2500–A1 ......................................................................................................................
V2522–A5, V2524–A5, V2527–A5, V2527E–A5, V2527M–A5, V2530–A5, V2533–A5
V2525–D5, V2528–D5 ...................................................................................................
Based on these figures, we estimate
the total cost of this AD to U.S.
operators to be $45,037,165 per year.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
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Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in subtitle VII,
part A, subpart III, section 44701,
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Total labor
cost per
year
33
142
5
$355,080
1,368,880
15,400
Total parts
cost per year
$7,230,564
35,790,816
276,425
Total cost
per year
$7,585,644
37,159,696
291,825
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
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Federal Register / Vol. 73, No. 137 / Wednesday, July 16, 2008 / Rules and Regulations
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
List of Subjects in 14 CFR Part 39
Regulatory Findings
Adoption of the Amendment
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect 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.
For the reasons discussed above, I
certify that this AD:
(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.
We prepared a summary of the costs
to comply with this AD and placed it in
the AD Docket. You may get a copy of
this summary at the address listed
under ADDRESSES.
I
Air transportation, Aircraft, Aviation
safety, Safety.
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends 14 CFR part 39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
I
2008–14–15 International Aero Engines AG
(IAE): Amendment 39–15610. Docket
No. FAA–2007–28058; Directorate
Identifier 2007–NE–08–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective August 20, 2008.
Affected ADs
(b) None.
40717
Applicability
(c) This AD applies to IAE V2500–A1,
V2522–A5, V2524–A5, V2527–A5, V2527E–
A5, V2527M–A5, V2530–A5, V2533–A5,
V2525–D5, and V2528–D5 turbofan engines
with a part listed by part number (P/N) in
this AD installed. These engines are installed
on, but not limited to, Airbus A319, A320,
A321, and McDonnell Douglas MD–90
airplanes.
Unsafe Condition
(d) This AD results from instances of oil
loss from the No. 4 bearing compartment. We
are issuing this AD to prevent heat damage
to high-pressure turbine (HPT) and lowpressure turbine (LPT) critical life limited
hardware such as the HPT stage 1–2 airseal.
Damage to the HPT stage 1–2 airseal could
cause uncontained engine failure and damage
to the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified unless the
actions have already been done.
V2500–A1 Engines
(f) For V2500–A1 engines, remove the parts
listed by P/N in the following Table 1 of this
AD at the next shop visit after the effective
date of this AD but not later than November
30, 2008. The ATA chapter reference of the
IAE V2500–A1 engine manual (E–V2500–
1IA) contains information on removing the
parts.
TABLE 1.—V2500–A1 PARTS TO BE REMOVED
dwashington3 on PRODPC61 with RULES
ATA chapter reference
72–42–20
72–42–20
72–42–20
72–42–20
72–42–20
72–42–20
72–42–20
72–42–33
72–42–33
72–42–33
72–42–33
72–42–33
72–42–33
72–42–33
72–42–33
72–42–33
72–42–35
72–42–35
72–43–20
72–43–20
72–43–20
72–43–20
72–43–20
72–43–20
72–43–20
72–45–11
72–45–11
72–45–11
72–45–13
72–45–13
72–45–13
79–22–49
79–22–49
79–22–49
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P/N
Nomenclature
2A0367–01 ................................................
2A2873–01 ................................................
2A0830–01 ................................................
2A1949–01 ................................................
2A2028–01 ................................................
2A0830–001 ..............................................
2A2274–01 ................................................
2A0853 ......................................................
2A2055 ......................................................
2A2834 ......................................................
2A2930 ......................................................
2A3525 ......................................................
2A3538 ......................................................
2A0851 ......................................................
2A2833 ......................................................
2A3537 ......................................................
2A0892–01 ................................................
2A2257–01 ................................................
2A2056 ......................................................
2A2931 ......................................................
2A3526 ......................................................
2A0847 ......................................................
2A0891–01 ................................................
2A1205–01 ................................................
2A3078–01 ................................................
2A0594 ......................................................
2A1040 ......................................................
2A2181 ......................................................
2A0884 ......................................................
2A1203 ......................................................
2A0884–001 ..............................................
5R8111 ......................................................
5R8138 ......................................................
6A5367 ......................................................
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Tube Assy of, Weep, No. 4 Bearing Outer.
Tube Assy of, Weep, No. 4 Bearing Outer.
Tube, Scavenge, No. 4 Bearing Assy.
Tube, Scavenge, No. 4 Bearing Assy.
Tube, Scavenge, No. 4 Bearing Assy.
Tube, Scavenge, No. 4 Bearing Assy.
Tube, Scavenge, No. 4 Bearing Assy.
Seal Assy, No. 4 Bearing, Front.
Seal Assy, No. 4 Bearing, Front.
Seal Assy, No. 4 Bearing, Front.
Seal Assy, No. 4 Bearing, Front.
Seal Assy, No. 4 Bearing, Front.
Seal Assy, No. 4 Bearing, Front.
Support Assy, No. 4 Bearing Seal.
Support, No. 4 Bearing, Seal Assy.
Support, No. 4 Bearing Seal Assy.
Duct Assy, Cooling Air, No. 4 Bearing, Front.
Duct Assy, Cooling Air, No. 4 Bearing, Front.
Seal Assy, No. 4 Bearing, Rear.
Seal Assy, No. 4 Bearing, Rear.
Seal Assy, No. 4 Bearing, Rear.
Seal Ring Holder.
Duct Assy, Cooling Air, No. 4 Bearing, Rear.
Duct Assy, Cooling Air, No. 4 Bearing, Rear.
Duct Assy, Cooling Air, No. 4 Bearing, Rear.
Metering Plug, HPT Hub, Stage 1.
Metering Plug, HPT Hub, Stage 1.
Metering Plug, HPT Hub, Stage 1.
Seal Air, HPT Stage 1.
Seal Air, HPT Stage 1.
Seal Air, HPT Stage 1.
Tube A/O Oil—No. 4 Brg Scav Dif Case to Bif Panel.
Tube A/O Oil—No. 4 Brg Scav Dif Case to Bif Panel.
Tube A/O Oil—No. 4 Brg Scav Dif Case to Bif Panel.
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TABLE 1.—V2500–A1 PARTS TO BE REMOVED—Continued
ATA chapter reference
79–22–49
79–22–49
79–22–49
79–23–51
P/N
...................................................
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Nomenclature
5A9083 ......................................................
5A9084 ......................................................
5A8573 ......................................................
1648MK2 ...................................................
V2522–A5, V2524–A5, V2527–A5, V2527E–
A5, V2527M–A5, V2530–A5, and V2533–A5
Engines
(g) For V2522–A5, V2524–A5, V2527–A5,
V2527E–A5, V2527M–A5, V2530–A5, and
Tube A/O Oil—No. 4 Brg Discon to Discon.
Tube A/O Oil—No. 4 Brg Discon to Scav Valve.
Tube A/O Oil—Press ‘T’ To Pressure Transducer.
Scavenge Valve.
V2533–A5 engines, remove the parts listed
by P/N in the following Table 2 of this AD
at the next shop visit after the effective date
of this AD but not later than June 30, 2011.
The ATA chapter reference of the IAE
V2500–A5 engine manual (E–V2500–1IA)
contains information on removing the parts.
TABLE 2.—V2522–A5, V2524–A5, V2527–A5, V2527E–A5, V2527M–A5, V2530–A5, AND V2533–A5 PARTS TO BE
REMOVED
ATA chapter reference
72–42–20
72–42–20
72–42–33
72–42–33
72–42–33
72–42–33
72–42–33
72–42–33
72–42–33
72–42–33
72–42–35
72–42–35
72–43–20
72–43–20
72–43–20
72–43–20
72–43–20
72–43–20
72–43–20
72–45–11
72–45–11
72–45–11
72–45–11
72–45–13
72–45–13
79–22–49
79–22–49
79–22–49
79–22–49
79–22–49
P/N
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Nomenclature
2A0367–01 ................................................
2A2873–01 ................................................
2A2055 ......................................................
2A2834 ......................................................
2A2930 ......................................................
2A3525 ......................................................
2A3538 ......................................................
2A0851 ......................................................
2A2833 ......................................................
2A3537 ......................................................
2A0892–01 ................................................
2A2257–01 ................................................
2A2056 ......................................................
2A2931 ......................................................
2A3526 ......................................................
2A0847 ......................................................
2A0891–01 ................................................
2A1205–01 ................................................
2A3078–01 ................................................
2A0594 ......................................................
2A1040 ......................................................
2A2354 ......................................................
2A3182 ......................................................
2A1352 ......................................................
2A3032 ......................................................
5R8138 ......................................................
6A5367 ......................................................
5A9083 ......................................................
5A9084 ......................................................
5A8573 ......................................................
(h) For V2522–A5, V2524–A5, V2527–A5,
V2527E–A5, V2527M–A5, V2530–A5, and
V2533–A5 engines with HPT stage 1 rotor
assembly, P/Ns 2A9521–002 and 2A9621–
002, the stage 1 HPT hub metering plug,
P/N 2A3182, does not need to be removed.
Tube Assy of, Weep, No. 4 Bearing Outer.
Tube Assy of, Weep, No. 4 Bearing Outer.
Seal Assy, No. 4 Bearing, Front.
Seal Assy, No. 4 Bearing, Front.
Seal Assy, No. 4 Bearing, Front.
Seal Assy, No. 4 Bearing, Front.
Seal Assy, No. 4 Bearing, Front.
Support Assy, No. 4 Bearing Seal.
Support, No. 4 Bearing, Seal Assy.
Support, No. 4 Bearing Seal Assy.
Duct Assy, Cooling Air, No. 4 Bearing, Front.
Duct Assy, Cooling Air, No. 4 Bearing, Front.
Seal Assy, No. 4 Bearing, Rear.
Seal Assy, No. 4 Bearing, Rear.
Seal Assy, No. 4 Bearing, Rear.
Seal Ring Holder.
Duct Assy, Cooling Air, No. 4 Bearing, Rear.
Duct Assy, Cooling Air, No. 4 Bearing, Rear.
Duct Assy, Cooling Air, No. 4 Bearing, Rear.
Metering Plug, HPT Hub, Stage 1.
Metering Plug, HPT Hub, Stage 1.
Metering Plug, HPT Hub, Stage 1.
Metering Plug, HPT Hub, Stage 1.
Seal Air, HPT Stage 1.
Seal Air, HPT Stage 1.
Tube A/O Oil—No. 4 Brg Scav Dif Case to Bif Panel.
Tube A/O Oil—No. 4 Brg Scav Dif Case to Bif Panel.
Tube A/O Oil—No. 4 Brg Discon to Discon.
Tube A/O Oil—No. 4 Brg Discon to Scav Valve.
Tube A/O Oil—Press ‘T’ To Pressure Transducer.
V2525–D5 and V2528–D5 Engines
(i) For V2525–D5 and V2528–D5 engines,
remove the parts listed by P/N in the
following Table 3 of this AD at the next shop
visit after the effective date of this AD but not
later than June 30, 2011. The ATA chapter
reference of the IAE V2500–D5 engine
manual (E–V2500–3IA) contains information
on removing the parts.
TABLE 3.—V2525–D5 AND V2528–D5 PARTS TO BE REMOVED
dwashington3 on PRODPC61 with RULES
ATA chapter reference
72–42–20
72–42–20
72–42–33
72–42–33
72–42–33
72–42–33
72–42–33
72–42–33
72–42–33
72–42–35
P/N
.......................................................
.......................................................
.......................................................
.......................................................
.......................................................
.......................................................
.......................................................
.......................................................
.......................................................
.......................................................
VerDate Aug<31>2005
15:04 Jul 15, 2008
Jkt 214001
Nomenclature
2A0367–01 .....................................................
2A2873–01 .....................................................
2A0851 ...........................................................
2A2833 ...........................................................
2A3537 ...........................................................
2A2834 ...........................................................
2A2930 ...........................................................
2A3525 ...........................................................
2A3538 ...........................................................
2A2257–01 .....................................................
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
Tube Assy of, Weep, No. 4 Bearing Outer.
Tube Assy of, Weep, No. 4 Bearing Outer.
Support Assy, No. 4 Bearing Seal.
Support, No. 4 Bearing, Seal Assy.
Support, No. 4 Bearing Seal Assy.
Seal Assy, No. 4 Bearing, Front.
Seal Assy, No. 4 Bearing, Front.
Seal Assy, No. 4 Bearing, Front.
Seal Assy, No. 4 Bearing, Front.
Duct Assy, Cooling Air, No. 4 Bearing, Front.
E:\FR\FM\16JYR1.SGM
16JYR1
Federal Register / Vol. 73, No. 137 / Wednesday, July 16, 2008 / Rules and Regulations
40719
TABLE 3.—V2525–D5 AND V2528–D5 PARTS TO BE REMOVED—Continued
ATA chapter reference
72–43–20
72–43–20
72–43–20
72–43–20
72–43–20
72–43–20
72–45–11
72–45–11
72–45–13
72–45–13
P/N
.......................................................
.......................................................
.......................................................
.......................................................
.......................................................
.......................................................
.......................................................
.......................................................
.......................................................
.......................................................
Nomenclature
2A2056 ...........................................................
2A2931 ...........................................................
2A3526 ...........................................................
2A0847 ...........................................................
2A1205–01 .....................................................
2A3078–01 .....................................................
2A3182 ...........................................................
2A2354 ...........................................................
2A1352 ...........................................................
2A3032 ...........................................................
(j) For V2525–D5 and V2528–D5 engines
with HPT stage 1 rotor assembly, P/Ns
2A9521–002 and 2A9621–002, the stage 1
HPT hub metering plug, P/N 2A3182, does
not need to be removed.
DEPARTMENT OF TRANSPORTATION
Previous Credit
[Docket No. FAA–2007–0275; Airspace
Docket No. 07–AEA–15]
(k) If you have accomplished IAE Service
Bulletin V2500–ENG–72–0541, Revision 4,
dated March 12, 2008, you have complied
with this AD.
(l) After the effective date of this AD, do
not install any part that has a P/N listed in
this AD.
Alternative Methods of Compliance
(m) The Manager, Engine Certification
Office, has the authority to approve
alternative methods of compliance for this
AD if requested using the procedures found
in 14 CFR 39.19.
Related Information
(n) International Aero Engines Service
Bulletin No. V2500–ENG–72–0541, Revision
4, dated March 12, 2008, pertains to the
subject of this AD.
(o) Contact Mark Riley, Aerospace
Engineer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; telephone (781) 238–7758; fax (781)
238–7199, for more information about this
AD.
Material Incorporated by Reference
(p) None.
Issued in Burlington, Massachusetts, on
July 2, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E8–15686 Filed 7–15–08; 8:45 am]
BILLING CODE 4910–13–P
dwashington3 on PRODPC61 with RULES
Seal Assy, No. 4 Bearing, Rear.
Seal Assy, No. 4 Bearing, Rear.
Seal Assy, No. 4 Bearing, Rear.
Seal Ring Holder.
Duct Assy, Cooling Air, No. 4 Bearing, Rear.
Duct Assy, Cooling Air, No. 4 Bearing, Rear.
Metering Plug, HPT Hub, Stage 1.
Metering Plug, HPT Hub, Stage 1.
Seal Air, HPT Stage 1.
Seal Air, HPT Stage 1.
VerDate Aug<31>2005
15:04 Jul 15, 2008
Jkt 214001
Federal Aviation Administration
14 CFR Part 71
Establishment of Class E Airspace,
Emporium, PA
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; confirmation of
effective date, correction.
AGENCY:
SUMMARY: This action confirms the
effective date and corrects an error in
the airport name listed in a direct final
rule published in the Federal Register
January 30, 2008, that established Class
E controlled airspace at Emporium, PA
(73 FR 5432) Docket No. FAA–2007–
0275.
DATES: Effective 0901 UTC, July 16,
2008. The Director of the Federal
Register approves this incorporation by
reference action under Title 1, Code of
Federal Regulations, part 51, subject to
the annual revision of FAA Order
7400.9 and publication of conforming
amendments.
Confirmation of Effective Date
The FAA uses the direct final
rulemaking procedure for a
noncontroversial rule where the FAA
believes that there will be no adverse
public comment. This direct final rule
advised the public that no adverse
comments were anticipated, and that
unless a written adverse comment, or a
written notice of intent to submit such
an adverse comment were received
within the comment period, the
regulation would become effective on
April 10, 2008. No adverse comments
were received, and thus this notice also
confirms that effective date.
Correction
Accordingly, pursuant to the authority
delegated to me, the publication in the
Federal Register dated January 30, 2008
(73 FR 5432, Federal Register Docket
No. FAA–2007–0275, on page 5433,
column 3, line 42 and line 50), is
corrected to read:
Cameron County Junior/Senior High
School Heliport.
*
*
*
*
*
I
FOR FURTHER INFORMATION CONTACT:
Daryl Daniels, Airspace Specialist,
System Support, AJO2–E2B.12, FAA
Eastern Service Center, 1701 Columbia
Ave., College Park, GA 30337; telephone
(404) 305–5581; fax (404) 305–5572.
SUPPLEMENTARY INFORMATION:
Issued in College Park, GA, on April 25,
2008.
Mark A. Ward,
Manager, Operations Support Group, Eastern
Service Center, Air Traffic Organization.
[FR Doc. E8–15549 Filed 7–15–08; 8:45 am]
BILLING CODE 4910–13–M
History
The FAA published a direct final rule
with request for comments in the
Federal Register January 30, 2008, (73
FR 5432) Docket No. FAA–2007–0275.
In that rule, airspace was established to
serve a landing site at the local High
School, however, after publication, an
error was discovered in the name used
for the heliport. The correct name
should have read ‘‘Cameron County
Junior/Senior High School Heliport’’.
This action corrects this error.
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2008–0336; Airspace
Docket No. 08–ANM–4]
Establishment of Class E Airspace;
Fort Collins, CO
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
E:\FR\FM\16JYR1.SGM
16JYR1
]]>Agencies
[Federal Register Volume 73, Number 137 (Wednesday, July 16, 2008)]
[Rules and Regulations]
[Pages 40715-40719]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-15686]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
Federal Register / Vol. 73, No. 137 / Wednesday, July 16, 2008 /
Rules and Regulations
[[Page 40715]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28058; Directorate Identifier 2007-NE-08-AD;
Amendment 39-15610; AD 2008-14-15]
RIN 2120-AA64
Airworthiness Directives; International Aero Engines AG (IAE)
V2500 Series Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for IAE
V2500-A1, V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5,
V2533-A5, V2525-D5, and V2528-D5 turbofan engines. This AD requires
removing certain No. 4 bearing oil system components from service at
the next shop visit or by an end date determined by the engine model.
This AD results from instances of oil loss from the No. 4 bearing
compartment. We are issuing this AD to prevent heat damage to high-
pressure turbine (HPT) and low-pressure turbine (LPT) critical life
limited hardware such as the HPT stage 1-2 airseal. Damage to the HPT
stage 1-2 airseal could cause uncontained engine failure and damage to
the airplane.
DATES: This AD becomes effective August 20, 2008.
ADDRESSES: The Docket Operations office is located at Docket Management
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue,
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.
FOR FURTHER INFORMATION CONTACT: Mark Riley, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; telephone (781) 238-7758;
fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with a proposed AD. The proposed AD applies to IAE V2500-A1, V2522-A5,
V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, V2533-A5, V2525-D5,
and V2528-D5 turbofan engines. We published the proposed AD in the
Federal Register on July 9, 2007 (72 FR 37126). That action proposed to
require removing certain No. 4 bearing oil system components from
service at the next shop visit or by an end date determined by the
engine model.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (telephone (800) 647-5527) is provided in
the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Requests To Change Compliance Schedule
Three commenters, Air Transport Association, United Airlines, and
Jet Blue Airways ask that we change the compliance:
To require removing the parts only when they access the
No. 4 bearing compartment, or
For engines that don't require access to the No. 4 bearing
compartment at the next shop visit, to permit them to defer removing
the parts to the subsequent shop visit, but not later than June 30,
2011.
The commenters state that changing the compliance times will avoid
an undue burden of forcing every engine visit to access the No. 4
bearing compartment and will avoid aircraft-on-ground situations due to
lack of spare parts.
We don't agree. We developed the compliance requirements to
maintain an acceptable level of safety for the entire V2500 fleet.
Revising the compliance requirements will result in having to
accelerate the program in order to maintain the same level of safety.
That will most likely have an adverse impact on the fleet, due to
forcing additional engine removals. The engine manufacturer, IAE, has
also stated that a sufficient supply of spare parts exists to handle
incorporation within the compliance requirements of the AD, including
unexpected shop visit situations. However, operators who have special
conditions may propose alternate compliance schedules, if they can show
that the alternate compliance schedules provide an acceptable level of
safety. We didn't change the AD.
Request To Address Design Deficiencies in the HPT Stage 1-2 Airseal
One commenter, Jet Blue Airways, asks us to revise the AD to
address design deficiencies in the HPT Stage 1-2 airseal as a
contributor to HPT distress, rather than attributing the root cause of
all HPT Stage 1-2 airseal distress to oil in the turbine. The commenter
states that one of the reported ``confirmed instances of oil loss'' in
the turbine is inaccurate. One investigation, which was categorized as
an ``oil in turbine'' event, revealed no substantive evidence of oil
loss in the turbine, or thermal oil ignition that could have caused the
dimensional defects in the HPT Stage 1-2 airseal. It is not beyond
reasonable speculation that, of the remaining 23 events, some
percentage was incorrectly stated as related to ``No. 4 bearing
compartment oil loss.''
We don't agree. We have been involved in the manufacturer's
Engineering Investigations for each of the subject ``oil in turbine''
(OIT) events, and agree with the manufacturer's conclusions. Due to the
operating conditions surrounding the No. 4 bearing compartment, it can
be extremely difficult, following engine operation, to detect either
evidence of oil loss, or thermo oil ignition. The investigation
concluded that the HPT Stage 1-2 airseal distress experienced is a
result of thermo oil ignition and not due to design deficiencies in the
HPT
[[Page 40716]]
Stage 1-2 airseal. The investigation also concluded that measurement of
specific HPT Stage 1-2 airseal dimensions is a reliable method of
determining if oil ignition has occurred. We did not change the AD.
Request To Eliminate the Requirement To Incorporate ``OIT Package 2''
The same commenter, Jet Blue, asks us to revise the AD to eliminate
the requirement to incorporate the ``OIT Package 2'' for compliance.
The ``OIT Package 2'' includes mainly external hardware revisions to
eliminate ``oil traps'' in the oil scavenge tubes for the No. 4 bearing
compartment that may adversely impact oil scavenge capability. The
commenter states ``To our knowledge, no V2527-A5 engine incorporating
the modification standards of `OIT Package' have been found with the
reported defects or suspected of No. 4 bearing compartment loss.''
We don't agree. We have reviewed the results of the Engineering
Investigation of the No. 4 bearing compartment oil loss events, and
agree with the manufacturer's conclusions that all hardware identified
in Tables 1, 2, and 3 of this AD contribute to the root cause of
insufficient oil scavenging from the No. 4 bearing compartment. We
didn't change the AD.
Request To Revise the NPRM To State a Significant Economic Impact
The same commenter, Jet Blue, asks us to revise the AD to state
that the proposed rule would have a significant economic impact. The
commenter states that the modification would cost more than $8,000,000
for its fleet.
We don't agree. In order for us to categorize an AD as a
``significant economic impact'' to operators, the total cost of the AD
must exceed $100,000,000 per year. We based our economic assessment for
this AD on actual hardware replacement cost (using the manufacturer's
spare parts pricing), the estimated number of work-hours (at $80 per
hour) required to comply with the AD, and the estimated number of shop
visits per year. Based on those figures, we estimate the cost of the
proposed AD to U.S. operators to be $45,037,165 per year, which is
below the $100,000,000 threshold criterion. We didn't change the AD.
Request To Incorporate IAE Service Bulletin V2500-ENG-72-0541 Into the
AD
The same commenter, Jet Blue Airways, requests that we revise the
AD to incorporate IAE Service Bulletin (SB) V2500-ENG-72-0541 into the
AD. The commenter states that tracking all of the individual parts
listed in the AD, especially from parts that are not serialized, is
cumbersome and beyond reasonable and customary standards.
We don't agree. Due to the complexity of the various IAE SBs, we
determined that it would be clearer to list in the AD, only the parts
that operators must remove from service. We list IAE SB V2500-ENG-72-
0541 in the Related Information section of the AD. That SB provides
specific instructions and the current replacement part information.
Listing only the parts that the operators must remove from service also
provides operators with increased flexibility for installing other
approved parts not listed in the IAE SB. However, we have added a
statement in the Compliance section of the AD that states ``If you have
accomplished IAE Service Bulletin V2500-ENG-72-0541, Revision 4, dated
March 12, 2008, you have complied with this AD.''
Request To Correct Certain Information in the AD
One commenter, IAE, asks us to correct certain information in the
Compliance section of the AD.
We agree. We have:
Corrected the part number (P/N) for the Seal Assembly, No.
4 Bearing, Front, in Table 2 of the AD, from P/N 2A0853 to P/N 2A2055.
Deleted P/N 2A0830-01, Tube, Scavenge, No. 4 Bearing Assy,
from Table 2 of the AD.
Deleted P/N 2A1949-01, Tube, Scavenge, No. 4 Bearing Assy,
from Table 2 of the AD.
Deleted P/N 5R8111, Tube A/O Oil, No. 4 Bearing Scav Dif
Case to Bif Panel, from Table 2 of the AD.
Added paragraph (j) for V2525-D5 and V2528-D5 engines
stating that with HPT stage 1 rotor assembly, P/Ns 2A9521-002 and
2A9621-002, the stage 1 HPT hub metering plug, P/N 2A3182, does not
need to be removed.
Replaced IAE Service Bulletin V2500-ENG-72-0541, Revision
1, dated February 26, 2007, in the Related Information paragraph, with
IAE Service Bulletin V2500-ENG-72-0541, Revision 4, dated March 12,
2008.
Conclusion
We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
We estimate that this AD will affect 686 engines installed on
airplanes of U.S. registry. Of those 686 engines, the operators of
nineteen V2500-A1 engines, thirty -A5 engines and twenty-one -D5
engines have already complied with the requirements in this AD.
Costs of Compliance per Year by Engine Model
----------------------------------------------------------------------------------------------------------------
Number of Total labor Total parts
Engine model engines per cost per cost per Total cost
year year year per year
----------------------------------------------------------------------------------------------------------------
V2500-A1................................................... 33 $355,080 $7,230,564 $7,585,644
V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530- 142 1,368,880 35,790,816 37,159,696
A5, V2533-A5..............................................
V2525-D5, V2528-D5......................................... 5 15,400 276,425 291,825
----------------------------------------------------------------------------------------------------------------
Based on these figures, we estimate the total cost of this AD to
U.S. operators to be $45,037,165 per year.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority
[[Page 40717]]
because it addresses an unsafe condition that is likely to exist or
develop on products identified in this rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect 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.
For the reasons discussed above, I certify that this AD:
(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.
We prepared a summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary at the
address listed under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2008-14-15 International Aero Engines AG (IAE): Amendment 39-15610.
Docket No. FAA-2007-28058; Directorate Identifier 2007-NE-08-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective August
20, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to IAE V2500-A1, V2522-A5, V2524-A5, V2527-
A5, V2527E-A5, V2527M-A5, V2530-A5, V2533-A5, V2525-D5, and V2528-D5
turbofan engines with a part listed by part number (P/N) in this AD
installed. These engines are installed on, but not limited to,
Airbus A319, A320, A321, and McDonnell Douglas MD-90 airplanes.
Unsafe Condition
(d) This AD results from instances of oil loss from the No. 4
bearing compartment. We are issuing this AD to prevent heat damage
to high-pressure turbine (HPT) and low-pressure turbine (LPT)
critical life limited hardware such as the HPT stage 1-2 airseal.
Damage to the HPT stage 1-2 airseal could cause uncontained engine
failure and damage to the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified unless the
actions have already been done.
V2500-A1 Engines
(f) For V2500-A1 engines, remove the parts listed by P/N in the
following Table 1 of this AD at the next shop visit after the
effective date of this AD but not later than November 30, 2008. The
ATA chapter reference of the IAE V2500-A1 engine manual (E-V2500-
1IA) contains information on removing the parts.
Table 1.--V2500-A1 Parts To Be Removed
--------------------------------------------------------------------------------------------------------------------------------------------------------
ATA chapter reference P/N Nomenclature
--------------------------------------------------------------------------------------------------------------------------------------------------------
72-42-20................................. 2A0367-01................... Tube Assy of, Weep, No. 4 Bearing Outer.
72-42-20................................. 2A2873-01................... Tube Assy of, Weep, No. 4 Bearing Outer.
72-42-20................................. 2A0830-01................... Tube, Scavenge, No. 4 Bearing Assy.
72-42-20................................. 2A1949-01................... Tube, Scavenge, No. 4 Bearing Assy.
72-42-20................................. 2A2028-01................... Tube, Scavenge, No. 4 Bearing Assy.
72-42-20................................. 2A0830-001.................. Tube, Scavenge, No. 4 Bearing Assy.
72-42-20................................. 2A2274-01................... Tube, Scavenge, No. 4 Bearing Assy.
72-42-33................................. 2A0853...................... Seal Assy, No. 4 Bearing, Front.
72-42-33................................. 2A2055...................... Seal Assy, No. 4 Bearing, Front.
72-42-33................................. 2A2834...................... Seal Assy, No. 4 Bearing, Front.
72-42-33................................. 2A2930...................... Seal Assy, No. 4 Bearing, Front.
72-42-33................................. 2A3525...................... Seal Assy, No. 4 Bearing, Front.
72-42-33................................. 2A3538...................... Seal Assy, No. 4 Bearing, Front.
72-42-33................................. 2A0851...................... Support Assy, No. 4 Bearing Seal.
72-42-33................................. 2A2833...................... Support, No. 4 Bearing, Seal Assy.
72-42-33................................. 2A3537...................... Support, No. 4 Bearing Seal Assy.
72-42-35................................. 2A0892-01................... Duct Assy, Cooling Air, No. 4 Bearing, Front.
72-42-35................................. 2A2257-01................... Duct Assy, Cooling Air, No. 4 Bearing, Front.
72-43-20................................. 2A2056...................... Seal Assy, No. 4 Bearing, Rear.
72-43-20................................. 2A2931...................... Seal Assy, No. 4 Bearing, Rear.
72-43-20................................. 2A3526...................... Seal Assy, No. 4 Bearing, Rear.
72-43-20................................. 2A0847...................... Seal Ring Holder.
72-43-20................................. 2A0891-01................... Duct Assy, Cooling Air, No. 4 Bearing, Rear.
72-43-20................................. 2A1205-01................... Duct Assy, Cooling Air, No. 4 Bearing, Rear.
72-43-20................................. 2A3078-01................... Duct Assy, Cooling Air, No. 4 Bearing, Rear.
72-45-11................................. 2A0594...................... Metering Plug, HPT Hub, Stage 1.
72-45-11................................. 2A1040...................... Metering Plug, HPT Hub, Stage 1.
72-45-11................................. 2A2181...................... Metering Plug, HPT Hub, Stage 1.
72-45-13................................. 2A0884...................... Seal Air, HPT Stage 1.
72-45-13................................. 2A1203...................... Seal Air, HPT Stage 1.
72-45-13................................. 2A0884-001.................. Seal Air, HPT Stage 1.
79-22-49................................. 5R8111...................... Tube A/O Oil--No. 4 Brg Scav Dif Case to Bif Panel.
79-22-49................................. 5R8138...................... Tube A/O Oil--No. 4 Brg Scav Dif Case to Bif Panel.
79-22-49................................. 6A5367...................... Tube A/O Oil--No. 4 Brg Scav Dif Case to Bif Panel.
[[Page 40718]]
79-22-49................................. 5A9083...................... Tube A/O Oil--No. 4 Brg Discon to Discon.
79-22-49................................. 5A9084...................... Tube A/O Oil--No. 4 Brg Discon to Scav Valve.
79-22-49................................. 5A8573...................... Tube A/O Oil--Press `T' To Pressure Transducer.
79-23-51................................. 1648MK2..................... Scavenge Valve.
--------------------------------------------------------------------------------------------------------------------------------------------------------
V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, and
V2533-A5 Engines
(g) For V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5,
V2530-A5, and V2533-A5 engines, remove the parts listed by P/N in
the following Table 2 of this AD at the next shop visit after the
effective date of this AD but not later than June 30, 2011. The ATA
chapter reference of the IAE V2500-A5 engine manual (E-V2500-1IA)
contains information on removing the parts.
Table 2.--V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, and V2533-A5 Parts To Be Removed
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ATA chapter reference P/N Nomenclature
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72-42-20................................. 2A0367-01................... Tube Assy of, Weep, No. 4 Bearing Outer.
72-42-20................................. 2A2873-01................... Tube Assy of, Weep, No. 4 Bearing Outer.
72-42-33................................. 2A2055...................... Seal Assy, No. 4 Bearing, Front.
72-42-33................................. 2A2834...................... Seal Assy, No. 4 Bearing, Front.
72-42-33................................. 2A2930...................... Seal Assy, No. 4 Bearing, Front.
72-42-33................................. 2A3525...................... Seal Assy, No. 4 Bearing, Front.
72-42-33................................. 2A3538...................... Seal Assy, No. 4 Bearing, Front.
72-42-33................................. 2A0851...................... Support Assy, No. 4 Bearing Seal.
72-42-33................................. 2A2833...................... Support, No. 4 Bearing, Seal Assy.
72-42-33................................. 2A3537...................... Support, No. 4 Bearing Seal Assy.
72-42-35................................. 2A0892-01................... Duct Assy, Cooling Air, No. 4 Bearing, Front.
72-42-35................................. 2A2257-01................... Duct Assy, Cooling Air, No. 4 Bearing, Front.
72-43-20................................. 2A2056...................... Seal Assy, No. 4 Bearing, Rear.
72-43-20................................. 2A2931...................... Seal Assy, No. 4 Bearing, Rear.
72-43-20................................. 2A3526...................... Seal Assy, No. 4 Bearing, Rear.
72-43-20................................. 2A0847...................... Seal Ring Holder.
72-43-20................................. 2A0891-01................... Duct Assy, Cooling Air, No. 4 Bearing, Rear.
72-43-20................................. 2A1205-01................... Duct Assy, Cooling Air, No. 4 Bearing, Rear.
72-43-20................................. 2A3078-01................... Duct Assy, Cooling Air, No. 4 Bearing, Rear.
72-45-11................................. 2A0594...................... Metering Plug, HPT Hub, Stage 1.
72-45-11................................. 2A1040...................... Metering Plug, HPT Hub, Stage 1.
72-45-11................................. 2A2354...................... Metering Plug, HPT Hub, Stage 1.
72-45-11................................. 2A3182...................... Metering Plug, HPT Hub, Stage 1.
72-45-13................................. 2A1352...................... Seal Air, HPT Stage 1.
72-45-13................................. 2A3032...................... Seal Air, HPT Stage 1.
79-22-49................................. 5R8138...................... Tube A/O Oil--No. 4 Brg Scav Dif Case to Bif Panel.
79-22-49................................. 6A5367...................... Tube A/O Oil--No. 4 Brg Scav Dif Case to Bif Panel.
79-22-49................................. 5A9083...................... Tube A/O Oil--No. 4 Brg Discon to Discon.
79-22-49................................. 5A9084...................... Tube A/O Oil--No. 4 Brg Discon to Scav Valve.
79-22-49................................. 5A8573...................... Tube A/O Oil--Press `T' To Pressure Transducer.
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(h) For V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5,
V2530-A5, and V2533-A5 engines with HPT stage 1 rotor assembly, P/Ns
2A9521-002 and 2A9621-002, the stage 1 HPT hub metering plug, P/N
2A3182, does not need to be removed.
V2525-D5 and V2528-D5 Engines
(i) For V2525-D5 and V2528-D5 engines, remove the parts listed
by P/N in the following Table 3 of this AD at the next shop visit
after the effective date of this AD but not later than June 30,
2011. The ATA chapter reference of the IAE V2500-D5 engine manual
(E-V2500-3IA) contains information on removing the parts.
Table 3.--V2525-D5 and V2528-D5 Parts To Be Removed
----------------------------------------------------------------------------------------------------------------
ATA chapter reference P/N Nomenclature
----------------------------------------------------------------------------------------------------------------
72-42-20...................... 2A0367-01........ Tube Assy of, Weep, No. 4 Bearing Outer.
72-42-20...................... 2A2873-01........ Tube Assy of, Weep, No. 4 Bearing Outer.
72-42-33...................... 2A0851........... Support Assy, No. 4 Bearing Seal.
72-42-33...................... 2A2833........... Support, No. 4 Bearing, Seal Assy.
72-42-33...................... 2A3537........... Support, No. 4 Bearing Seal Assy.
72-42-33...................... 2A2834........... Seal Assy, No. 4 Bearing, Front.
72-42-33...................... 2A2930........... Seal Assy, No. 4 Bearing, Front.
72-42-33...................... 2A3525........... Seal Assy, No. 4 Bearing, Front.
72-42-33...................... 2A3538........... Seal Assy, No. 4 Bearing, Front.
72-42-35...................... 2A2257-01........ Duct Assy, Cooling Air, No. 4 Bearing, Front.
[[Page 40719]]
72-43-20...................... 2A2056........... Seal Assy, No. 4 Bearing, Rear.
72-43-20...................... 2A2931........... Seal Assy, No. 4 Bearing, Rear.
72-43-20...................... 2A3526........... Seal Assy, No. 4 Bearing, Rear.
72-43-20...................... 2A0847........... Seal Ring Holder.
72-43-20...................... 2A1205-01........ Duct Assy, Cooling Air, No. 4 Bearing, Rear.
72-43-20...................... 2A3078-01........ Duct Assy, Cooling Air, No. 4 Bearing, Rear.
72-45-11...................... 2A3182........... Metering Plug, HPT Hub, Stage 1.
72-45-11...................... 2A2354........... Metering Plug, HPT Hub, Stage 1.
72-45-13...................... 2A1352........... Seal Air, HPT Stage 1.
72-45-13...................... 2A3032........... Seal Air, HPT Stage 1.
----------------------------------------------------------------------------------------------------------------
(j) For V2525-D5 and V2528-D5 engines with HPT stage 1 rotor
assembly, P/Ns 2A9521-002 and 2A9621-002, the stage 1 HPT hub
metering plug, P/N 2A3182, does not need to be removed.
Previous Credit
(k) If you have accomplished IAE Service Bulletin V2500-ENG-72-
0541, Revision 4, dated March 12, 2008, you have complied with this
AD.
(l) After the effective date of this AD, do not install any part
that has a P/N listed in this AD.
Alternative Methods of Compliance
(m) The Manager, Engine Certification Office, has the authority
to approve alternative methods of compliance for this AD if
requested using the procedures found in 14 CFR 39.19.
Related Information
(n) International Aero Engines Service Bulletin No. V2500-ENG-
72-0541, Revision 4, dated March 12, 2008, pertains to the subject
of this AD.
(o) Contact Mark Riley, Aerospace Engineer, Engine Certification
Office, FAA, Engine and Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803; telephone (781) 238-7758; fax
(781) 238-7199, for more information about this AD.
Material Incorporated by Reference
(p) None.
Issued in Burlington, Massachusetts, on July 2, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E8-15686 Filed 7-15-08; 8:45 am]
BILLING CODE 4910-13-P
