[Federal Register: July 9, 2007 (Volume 72, Number 130)]
[Proposed Rules]
[Page 37126-37130]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr09jy07-10]
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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
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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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 http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://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 http://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 http://dms.dot.gov.
Examining the AD Docket
You may examine the AD docket on the Internet at http://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