Airworthiness Directives; International Aero Engines AG (IAE) V2500 Series Turbofan Engines, 37126-37130 [E7-13256]
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37126
Federal Register / Vol. 72, No. 130 / Monday, July 9, 2007 / Proposed Rules
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.
§ 39.13
FAA AD Differences
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
Pacific Aerospace Corporation, Ltd: Docket
No. FAA–2007–27865; Directorate
Identifier 2007-CE–039-AD.
Comments Due Date
(a) We must receive comments by August
8, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Model 750XL
airplanes, all serial numbers, certificated in
any category, that have not incorporated
Pacific Aerospace Limited Service Letter
PACSL/XL/07–1, dated April 18, 2007, with
Pacific Aerospace LTD Drawing, 11–03129,
Issue B or subsequent, in its entirety.
Subject
(d) Air Transport Association of America
(ATA) Code 56: Windows.
pwalker on PROD1PC71 with NOTICES2
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
To prevent the cockpit door windows
separating from their frames, * * * The
MCAI requires you to inspect the windscreen
and cockpit door windows for signs of
disbonding of the adhesive between the
transparency and the composite window
frame. If disbonding is evident, you must do
the required modification.
Actions and Compliance
(f) Unless already done, do the following
actions:
(1) Within the next 50 hours time-inservice (TIS) after the effective date of this
AD and thereafter at intervals not to exceed
50 hours TIS, inspect the windscreen and
cockpit door windows for signs of
disbonding of the adhesive between the
transparency and the composite window
frame following Pacific Aerospace
Corporation, Ltd Pacific Aerospace Limited
Mandatory Service Bulletin PACSB/XL/024
(embodiment of modification PAC/XL/0276),
dated April 18, 2007, and PAC Drawing No.
11–03137 (undated). If you find disbonding,
before further flight, modify the windscreen
and cockpit windows to incorporate
mechanical fasteners following Pacific
Aerospace Corporation, Ltd Pacific
Aerospace Limited Mandatory Service
Bulletin PACSB/XL/024 (embodiment of
modification PAC/XL/0276), dated April 18,
2007, and PAC Drawing No. 11–03137
(undated).
(2) Within the next 150 hours TIS after the
effective date of this AD or the next 6 months
after the effective date of this AD, whichever
occurs first, modify the windscreen and
cockpit windows to incorporate mechanical
VerDate Aug<31>2005
16:43 Jul 06, 2007
fasteners following Pacific Aerospace
Corporation, Ltd Pacific Aerospace Limited
Mandatory Service Bulletin PACSB/XL/024
(embodiment of modification PAC/XL/0276),
dated April 18, 2007, and PAC Drawing No.
11–03137 (undated).
Jkt 211001
Note: This AD differs from the MCAI and/
or service information as follows: No
differences.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Staff,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Karl Schletzbaum, Aerospace
Engineer, FAA, Small Airplane Directorate,
901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329–4146; fax: (816)
329–4090. Before using any approved AMOC
on any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et.seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to MCAI Civil Aviation Authority
of New Zealand AD DCA/750XL/10, dated
March 29, 2007; Pacific Aerospace
Corporation, Ltd Pacific Aerospace Limited
Mandatory Service Bulletin PACSB/XL/024
(embodiment of modification PAC/XL/0276),
dated April 18, 2007; PAC Drawing No. 11–
03137 (undated); and Pacific Aerospace
Limited Service Letter PACSL/XL/07–1,
dated April 18, 2007, with Pacific Aerospace
LTD Drawing, 11–03129, Issue B or
subsequent, for related information.
Issued in Kansas City, Missouri, on June
29, 2007.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E7–13247 Filed 7–6–07; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28058; Directorate
Identifier 2007-NE–08–AD]
RIN 2120–AA64
Airworthiness Directives; International
Aero Engines AG (IAE) V2500 Series
Turbofan Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt 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,
V2528–D5 turbofan engines. This
proposed AD would require removing
certain No. 4 bearing seal components
from service at the next shop visit or by
an end date determined by the engine
model. This proposed AD results from
instances of oil loss from the No. 4
bearing compartment. We are proposing
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: We must receive any comments
on this proposed AD by September 7,
2007.
ADDRESSES: Use one of the following
addresses to comment on this proposed
AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building, Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
• Fax: (202) 493–2251.
FOR FURTHER INFORMATION CONTACT:
Colleen M. D’Alessandro, Aerospace
Engineer, Engine Certification Office,
FAA, Engine and Propeller Directorate,
12 New England Executive Park,
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Federal Register / Vol. 72, No. 130 / Monday, July 9, 2007 / Proposed Rules
Burlington, MA 01803; telephone (781)
238–7133; fax (781) 238–7199.
19477–78) or you may visit https://
dms.dot.gov.
SUPPLEMENTARY INFORMATION:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://dms.dot.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 proposed
AD, the regulatory evaluation, any
comments received, and other
information. The street address for the
Docket Operations office (telephone
(800) 647–5527) is the same as the Mail
address provided in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
Comments Invited
We invite you to send us any written
relevant data, views, or arguments
regarding this proposal. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
2007–28058; Directorate Identifier
2007–NE–08–AD’’ in the subject line of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the proposed AD. We will
consider all comments received by the
closing date and may amend the
proposed AD in light of those
comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of the DOT
Web site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You may
review the DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
Discussion
Between March 1993 and October
2006, we received reports of 24
confirmed instances of oil loss from the
No. 4 bearing compartment. Each
instance resulted in the oil igniting and
caused heat distress damage to HPT and
LPT hardware.
International Aero Engines (IAE)
attributes the oil loss to two root causes,
fractures of the rear No. 4 carbon seal
and insufficient oil scavenging. The
fractures result from fracture of the HPT
stage 1 disk metering plug due to highcycle fatigue (HCF). Industry confirms
five instances of fractured metering
plugs between January 2001 and
October 2006. Regarding the insufficient
oil scavenging, Industry confirms 19
instances of distress of the HPT, the
37127
LPT, or both, caused by oil flooding the
No. 4 bearing compartment between
March 1993, and October 2006.
We have monitored industry’s
investigation, field actions, and service
experience with this problem. However,
we conclude that proposed corrective
actions are inadequate. These
conditions, if not corrected, could result
in heat damage to 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.
FAA’s Determination and Requirements
of the Proposed AD
We have evaluated all pertinent
information and identified an unsafe
condition that is likely to exist or
develop on other products of this same
type design. We are proposing this AD,
which would require removing the parts
specified in this proposed AD at the
next shop visit, but no later than
November 2008 for the V2500–A1
model or June 2011 for the—A5 and –D5
models.
Costs of Compliance
We estimate that this proposed AD
would 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 the proposed AD.
COSTS OF COMPLIANCE PER YEAR BY ENGINE MODEL
Number of engines per year
Engine Model
V2500–A1 ........................................................................................................
V2522–A5, V2524–A5, V2527–A5, V2527E–A5, V2527M–A5, V2530–A5,
V2533–A5 .....................................................................................................
V2525–D5, V2528–D5 .....................................................................................
pwalker on PROD1PC71 with NOTICES2
Based on these figures, we estimate
the total cost of the proposed 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
VerDate Aug<31>2005
16:43 Jul 06, 2007
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Total cost per
year
$355,080
$7,230,564
$7,585,644
142
5
1,368,880
15,400
35,790,816
276,425
37,159,696
291,825
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would 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
Frm 00006
Total parts
cost per year
33
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
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
PO 00000
Total labor
cost per year
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Would 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 regulatory evaluation
of the estimated costs to comply with
this proposed AD. You may get a copy
of this summary at the address listed
under ADDRESSES.
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37128
Federal Register / Vol. 72, No. 130 / Monday, July 9, 2007 / Proposed Rules
International Aero Engines AG (IAE): Docket
No. FAA–2007–28058; Directorate
Identifier 2007–NE–08–AD.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
Comments Due Date
(a) The Federal Aviation Administration
(FAA) must receive comments on this
airworthiness directive (AD) action by
September 7, 2007.
The Proposed Amendment
Under the authority delegated to me
by the Administrator, the Federal
Aviation Administration proposes to
amend 14 CFR part 39 as follows:
Affected ADs
(b) None.
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
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, 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
Boeing MD–90 airplanes.
Unsafe Condition
(d) This proposed 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
72–42–20
72–42–20
72–42–20
72–42–20
72–42–20
72–42–20
................
................
................
................
................
................
................
2A0367–01 ............
2A2873–01 ............
2A0830–01 ............
2A1949–01 ............
2A2028–01 ............
2A0830–001 ..........
2A2274–01 ............
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.
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
................
................
................
................
................
................
................
................
................
2A0853
2A2055
2A2834
2A2930
2A3525
2A3538
2A0851
2A2833
2A3537
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.
..................
..................
..................
..................
..................
..................
..................
..................
..................
2A0892–01 ............
2A2257–01 ............
Duct Assy, Cooling Air, No. 4 Bearing, Front.
Duct Assy, Cooling Air, No. 4 Bearing, Front.
72–43–20
72–43–20
72–43–20
72–43–20
72–43–20
72–43–20
72–43–20
................
................
................
................
................
................
................
2A2056 ..................
2A2931 ..................
2A3526 ..................
2A0847 ..................
2A0891–01 ............
2A1205–01 ............
2A3078–01 ............
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.
72–45–11 ................
72–45–11 ................
72–45–11 ................
2A0594 ..................
2A1040 ..................
2A2181 ..................
Metering Plug, HPT Hub, Stage 1.
Metering Plug, HPT Hub, Stage 1.
Metering Plug, HPT Hub, Stage 1.
72–45–13 ................
72–45–13 ................
72–45–13 ................
pwalker on PROD1PC71 with NOTICES2
72–42–35 ................
72–42–35 ................
2A0884 ..................
2A1203 ..................
2A0884–001 ..........
Seal Air, HPT Stage 1.
Seal Air, HPT Stage 1.
Seal Air, HPT Stage 1.
79–22–49
79–22–49
79–22–49
79–22–49
79–22–49
79–22–49
5R8111
5R8138
6A5367
5A9083
5A9084
5A8573
Tube
Tube
Tube
Tube
Tube
Tube
................
................
................
................
................
................
79–23–51 ................
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..................
..................
..................
..................
..................
1648MK2 ...............
16:43 Jul 06, 2007
Jkt 211001
A/O
A/O
A/O
A/O
A/O
A/O
Oil—No. 4 Brg Scav Dif Case to Bif Panel.
Oil—No. 4 Brg Scav Dif Case to Bif Panel.
Oil—No. 4 Brg Scav Dif Case to Bif Panel.
Oil—No. 4 Brg Discon to Discon.
Oil—No. 4 Brg Discon to Scav Valve.
Oil—Press ‘T’ To Pressurre Transducer.
Scavenge Valve.
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Federal Register / Vol. 72, No. 130 / Monday, July 9, 2007 / Proposed Rules
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
37129
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
P/N
Nomenclature
72–42–20
72–42–20
72–42–20
72–42–20
................
................
................
................
2A0367–01
2A2873–01
2A0830–01
2A1949–01
............
............
............
............
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
................
................
................
................
................
................
................
................
................
................
2A0853 ..................
2A2834 ..................
2A2930 ..................
2A3525 ..................
2A3538 ..................
2A0851 ..................
2A2833 ..................
2A3537 ..................
2A0892–01 ............
2A2257–01 ............
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.
72–43–20
72–43–20
72–43–20
72–43–20
72–43–20
72–43–20
72–43–20
................
................
................
................
................
................
................
2A2056 ..................
2A2931 ..................
2A3526 ..................
2A0847 ..................
2A0891–01 ............
2A1205–01 ............
2A3078–01 ............
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.
72–45–11
72–45–11
72–45–11
72–45–11
................
................
................
................
2A0594
2A1040
2A2354
2A3182
Metering
Metering
Metering
Metering
..................
..................
..................
..................
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.
Plug,
Plug,
Plug,
Plug,
HPT
HPT
HPT
HPT
Hub,
Hub,
Hub,
Hub,
72–45–13 ................
72–45–13 ................
2A1352 ..................
2A3032 ..................
5R8111
5R8138
6A5367
5A9083
5A9084
5A8573
Tube
Tube
Tube
Tube
Tube
Tube
1.
1.
1.
1.
Seal Air, HPT Stage 1.
Seal Air, HPT Stage 1.
79–22–49
79–22–49
79–22–49
79–22–49
79–22–49
79–22–49
Stage
Stage
Stage
Stage
................
................
................
................
................
................
..................
..................
..................
..................
..................
..................
(h) For V2522–A5, V2524–A5, V2527–A5,
V2527E–A5, V2527M–A5, V2530–A5, and
V2533–A5 engines with high pressure
turbine (HPT) stage 1 rotor assembly, P/Ns
2A9521–002 and 2A9621–002, the stage 1
A/O
A/O
A/O
A/O
A/O
A/O
Oil—No. 4 Brg Scav Dif Case to Bif Panel.
Oil—No. 4 Brg Scav Dif Case to Bif Panel.
Oil—No. 4 Brg Scav Dif Case to Bif Panel.
Oil—No. 4 Brg Discon to Discon.
Oil—No. 4 Brg Discon to Scav Valve.
Oil—Press ‘T’ To Pressure Transducer.
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
P/N
72–42–20 ................
72–42–20 ................
pwalker on PROD1PC71 with NOTICES2
ATA chapter
reference
2A0367–01 ............
2A2873–01 ............
Tube Assy of, Weep, No. 4 Bearing Outer.
Tube Assy of, Weep, No. 4 Bearing Outer.
72–42–33
72–42–33
72–42–33
72–42–33
72–42–33
72–42–33
72–42–33
72–42–35
2A0851 ..................
2A2833 ..................
2A3537 ..................
2A2834 ..................
2A2930 ..................
2A3525 ..................
2A3538 ..................
2A2257–01 ............
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.
................
................
................
................
................
................
................
................
VerDate Aug<31>2005
16:43 Jul 06, 2007
Jkt 211001
Nomenclature
PO 00000
Frm 00008
Fmt 4702
Sfmt 4702
E:\FR\FM\09JYP1.SGM
09JYP1
37130
Federal Register / Vol. 72, No. 130 / Monday, July 9, 2007 / Proposed Rules
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
P/N
Nomenclature
................
................
................
................
................
................
2A2056 ..................
2A2931 ..................
2A3526 ..................
2A0847 ..................
2A1205–01 ............
2A3078–01 ............
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.
72–45–11 ................
72–45–11 ................
2A3182 ..................
2A2354 ..................
Metering Plug, HPT Hub, Stage 1.
Metering Plug, HPT Hub, Stage 1.
72–45–13 ................
72–45–13 ................
2A1352 ..................
2A3032 ..................
Seal Air, HPT Stage 1.
Seal Air, HPT Stage 1.
All Engines
(j) 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
(k) 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
(l) International Aero Engines nonmodification Service Bulletin No. V2500ENG–72–0541, Revision 1, dated February
26, 2007, pertains to the subject of this AD.
Issued in Burlington, Massachusetts, on
July 2, 2007.
Peter A. White,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E7–13256 Filed 7–6–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28620; Directorate
Identifier 2007–NM–090–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747–100, 747–100B, 747–100B
SUD, 747–200B, 747–200C, 747–200F,
747–300, 747SR, and 747SP Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
pwalker on PROD1PC71 with NOTICES2
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Boeing Model 747–100, 747–
100B, 747–100B SUD, 747–200B, 747–
200C, 747–200F, 747–300, 747SR, and
VerDate Aug<31>2005
16:43 Jul 06, 2007
Jkt 211001
747SP series airplanes. This proposed
AD would require repetitive inspections
for cracking of the station (STA) 1241
bulkhead fittings just above the canted
pressure deck; a one-time determination
of the edge margin at seven fastener
positions on each side of the airplane;
and related investigative/corrective
actions if necessary. This proposed AD
results from a report that an operator
found a 1.65-inch crack on the STA
1241 bulkhead fitting on the left side of
a Boeing Model 747–200F series
airplane that had accumulated 17,332
total flight cycles. We are proposing this
AD to detect and correct cracking in the
STA 1241 bulkhead fittings, which
could result in reduced structural
integrity of the airplane.
DATES: We must receive comments on
this proposed AD by August 23, 2007.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room W12–140 on
the ground floor of the West Building,
1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for the service
information identified in this proposed
AD.
FOR FURTHER INFORMATION CONTACT: Ivan
Li, Aerospace Engineer, Airframe
PO 00000
Frm 00009
Fmt 4702
Sfmt 4702
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington
98057–3356; telephone (425) 917–6437;
fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed in the
ADDRESSES section. Include the docket
number ‘‘FAA–2007–28620; Directorate
Identifier 2007–NM–090–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of that Web
site, anyone can find and read the
comments in any of our dockets,
including the name of the individual
who sent the comment (or signed the
comment on behalf of an association,
business, labor union, etc.). You may
review DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you may visit https://
dms.dot.gov.
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The Docket
Operations office (telephone (800) 647–
E:\FR\FM\09JYP1.SGM
09JYP1
]]>Agencies
[Federal Register Volume 72, Number 130 (Monday, July 9, 2007)]
[Proposed Rules]
[Pages 37126-37130]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-13256]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28058; Directorate Identifier 2007-NE-08-AD]
RIN 2120-AA64
Airworthiness Directives; International Aero Engines AG (IAE)
V2500 Series Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt 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, V2528-D5 turbofan engines. This proposed
AD would require removing certain No. 4 bearing seal components from
service at the next shop visit or by an end date determined by the
engine model. This proposed AD results from instances of oil loss from
the No. 4 bearing compartment. We are proposing 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: We must receive any comments on this proposed AD by September 7,
2007.
ADDRESSES: Use one of the following addresses to comment on this
proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building, Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Fax: (202) 493-2251.
FOR FURTHER INFORMATION CONTACT: Colleen M. D'Alessandro, Aerospace
Engineer, Engine Certification Office, FAA, Engine and Propeller
Directorate, 12 New England Executive Park,
[[Page 37127]]
Burlington, MA 01803; telephone (781) 238-7133; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send us any written relevant data, views, or
arguments regarding this proposal. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2007-28058;
Directorate Identifier 2007-NE-08-AD'' in the subject line of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of the
DOT Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78) or you
may visit https://dms.dot.gov.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
dms.dot.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 proposed AD, the regulatory evaluation, any
comments received, and other information. The street address for the
Docket Operations office (telephone (800) 647-5527) is the same as the
Mail address provided in the ADDRESSES section. Comments will be
available in the AD docket shortly after receipt.
Discussion
Between March 1993 and October 2006, we received reports of 24
confirmed instances of oil loss from the No. 4 bearing compartment.
Each instance resulted in the oil igniting and caused heat distress
damage to HPT and LPT hardware.
International Aero Engines (IAE) attributes the oil loss to two
root causes, fractures of the rear No. 4 carbon seal and insufficient
oil scavenging. The fractures result from fracture of the HPT stage 1
disk metering plug due to high-cycle fatigue (HCF). Industry confirms
five instances of fractured metering plugs between January 2001 and
October 2006. Regarding the insufficient oil scavenging, Industry
confirms 19 instances of distress of the HPT, the LPT, or both, caused
by oil flooding the No. 4 bearing compartment between March 1993, and
October 2006.
We have monitored industry's investigation, field actions, and
service experience with this problem. However, we conclude that
proposed corrective actions are inadequate. These conditions, if not
corrected, could result in heat damage to 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.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other products
of this same type design. We are proposing this AD, which would require
removing the parts specified in this proposed AD at the next shop
visit, but no later than November 2008 for the V2500-A1 model or June
2011 for the--A5 and -D5 models.
Costs of Compliance
We estimate that this proposed AD would 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 the
proposed AD.
Costs of Compliance per year by Engine Model
----------------------------------------------------------------------------------------------------------------
Number of
Engine Model engines per Total labor Total parts Total cost per
year cost per year cost per year year
----------------------------------------------------------------------------------------------------------------
V2500-A1........................................ 33 $355,080 $7,230,564 $7,585,644
V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M- 142 1,368,880 35,790,816 37,159,696
A5, V2530-A5, V2533-A5.........................
V2525-D5, V2528-D5.............................. 5 15,400 276,425 291,825
----------------------------------------------------------------------------------------------------------------
Based on these figures, we estimate the total cost of the proposed
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 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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 the proposed AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Would 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 regulatory evaluation of the estimated costs to
comply with this proposed AD. You may get a copy of this summary at the
address listed under ADDRESSES.
[[Page 37128]]
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Under the authority delegated to me by the Administrator, the
Federal Aviation Administration proposes to amend 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. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive:
International Aero Engines AG (IAE): Docket No. FAA-2007-28058;
Directorate Identifier 2007-NE-08-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by September 7,
2007.
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, 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 Boeing MD-90 airplanes.
Unsafe Condition
(d) This proposed 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.
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 Pressurre
Transducer.
------------------------------------------------------------------------
79-23-51................ 1648MK2................. Scavenge Valve.
------------------------------------------------------------------------
[[Page 37129]]
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
------------------------------------------------------------------------
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.
------------------------------------------------------------------------
72-42-33................ 2A0853.................. 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................ 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.
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.
------------------------------------------------------------------------
(h) For V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5,
V2530-A5, and V2533-A5 engines with high pressure turbine (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 37130]]
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.
------------------------------------------------------------------------
All Engines
(j) 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
(k) 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
(l) International Aero Engines non-modification Service Bulletin
No. V2500-ENG-72-0541, Revision 1, dated February 26, 2007, pertains
to the subject of this AD.
Issued in Burlington, Massachusetts, on July 2, 2007.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E7-13256 Filed 7-6-07; 8:45 am]
BILLING CODE 4910-13-P
