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Airworthiness Directives; International Aero Engines AG (IAE) V2500 Series Turbofan Engines

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Information about this document as published in the Federal Register.

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Start Preamble Start Printed Page 40715

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.

Start Further Info

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.

End Further Info End Preamble Start Supplemental Information

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 http://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 Start Printed Page 40716Stage 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

Engine modelNumber of engines per yearTotal labor cost per yearTotal parts cost per yearTotal cost per year
V2500-A133$355,080$7,230,564$7,585,644
V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, V2533-A51421,368,88035,790,81637,159,696
V2525-D5, V2528-D5515,400276,425291,825

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 Start Printed Page 40717because 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.

Start List of Subjects

List of Subjects in 14 CFR Part 39

End List of Subjects

Adoption of the Amendment

Start Amendment Part

Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends

End Amendment Part Start Part

PART 39—AIRWORTHINESS DIRECTIVES

End Part Start Amendment Part

1. The authority citation for part 39 continues to read as follows:

End Amendment Part Start Authority

Authority: 49 U.S.C. 106(g), 40113, 44701.

End Authority
[Amended]
Start Amendment Part

2. The FAA amends § 39.13 by adding the following new airworthiness directive:

End Amendment Part

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 referenceP/NNomenclature
72-42-202A0367-01Tube Assy of, Weep, No. 4 Bearing Outer.
72-42-202A2873-01Tube Assy of, Weep, No. 4 Bearing Outer.
72-42-202A0830-01Tube, Scavenge, No. 4 Bearing Assy.
72-42-202A1949-01Tube, Scavenge, No. 4 Bearing Assy.
72-42-202A2028-01Tube, Scavenge, No. 4 Bearing Assy.
72-42-202A0830-001Tube, Scavenge, No. 4 Bearing Assy.
72-42-202A2274-01Tube, Scavenge, No. 4 Bearing Assy.
72-42-332A0853Seal Assy, No. 4 Bearing, Front.
72-42-332A2055Seal Assy, No. 4 Bearing, Front.
72-42-332A2834Seal Assy, No. 4 Bearing, Front.
72-42-332A2930Seal Assy, No. 4 Bearing, Front.
72-42-332A3525Seal Assy, No. 4 Bearing, Front.
72-42-332A3538Seal Assy, No. 4 Bearing, Front.
72-42-332A0851Support Assy, No. 4 Bearing Seal.
72-42-332A2833Support, No. 4 Bearing, Seal Assy.
72-42-332A3537Support, No. 4 Bearing Seal Assy.
72-42-352A0892-01Duct Assy, Cooling Air, No. 4 Bearing, Front.
72-42-352A2257-01Duct Assy, Cooling Air, No. 4 Bearing, Front.
72-43-202A2056Seal Assy, No. 4 Bearing, Rear.
72-43-202A2931Seal Assy, No. 4 Bearing, Rear.
72-43-202A3526Seal Assy, No. 4 Bearing, Rear.
72-43-202A0847Seal Ring Holder.
72-43-202A0891-01Duct Assy, Cooling Air, No. 4 Bearing, Rear.
72-43-202A1205-01Duct Assy, Cooling Air, No. 4 Bearing, Rear.
72-43-202A3078-01Duct Assy, Cooling Air, No. 4 Bearing, Rear.
72-45-112A0594Metering Plug, HPT Hub, Stage 1.
72-45-112A1040Metering Plug, HPT Hub, Stage 1.
72-45-112A2181Metering Plug, HPT Hub, Stage 1.
72-45-132A0884Seal Air, HPT Stage 1.
72-45-132A1203Seal Air, HPT Stage 1.
72-45-132A0884-001Seal Air, HPT Stage 1.
79-22-495R8111Tube A/O Oil—No. 4 Brg Scav Dif Case to Bif Panel.
79-22-495R8138Tube A/O Oil—No. 4 Brg Scav Dif Case to Bif Panel.
79-22-496A5367Tube A/O Oil—No. 4 Brg Scav Dif Case to Bif Panel.
Start Printed Page 40718
79-22-495A9083Tube A/O Oil—No. 4 Brg Discon to Discon.
79-22-495A9084Tube A/O Oil—No. 4 Brg Discon to Scav Valve.
79-22-495A8573Tube A/O Oil—Press ‘T' To Pressure Transducer.
79-23-511648MK2Scavenge 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

ATA chapter referenceP/NNomenclature
72-42-202A0367-01Tube Assy of, Weep, No. 4 Bearing Outer.
72-42-202A2873-01Tube Assy of, Weep, No. 4 Bearing Outer.
72-42-332A2055Seal Assy, No. 4 Bearing, Front.
72-42-332A2834Seal Assy, No. 4 Bearing, Front.
72-42-332A2930Seal Assy, No. 4 Bearing, Front.
72-42-332A3525Seal Assy, No. 4 Bearing, Front.
72-42-332A3538Seal Assy, No. 4 Bearing, Front.
72-42-332A0851Support Assy, No. 4 Bearing Seal.
72-42-332A2833Support, No. 4 Bearing, Seal Assy.
72-42-332A3537Support, No. 4 Bearing Seal Assy.
72-42-352A0892-01Duct Assy, Cooling Air, No. 4 Bearing, Front.
72-42-352A2257-01Duct Assy, Cooling Air, No. 4 Bearing, Front.
72-43-202A2056Seal Assy, No. 4 Bearing, Rear.
72-43-202A2931Seal Assy, No. 4 Bearing, Rear.
72-43-202A3526Seal Assy, No. 4 Bearing, Rear.
72-43-202A0847Seal Ring Holder.
72-43-202A0891-01Duct Assy, Cooling Air, No. 4 Bearing, Rear.
72-43-202A1205-01Duct Assy, Cooling Air, No. 4 Bearing, Rear.
72-43-202A3078-01Duct Assy, Cooling Air, No. 4 Bearing, Rear.
72-45-112A0594Metering Plug, HPT Hub, Stage 1.
72-45-112A1040Metering Plug, HPT Hub, Stage 1.
72-45-112A2354Metering Plug, HPT Hub, Stage 1.
72-45-112A3182Metering Plug, HPT Hub, Stage 1.
72-45-132A1352Seal Air, HPT Stage 1.
72-45-132A3032Seal Air, HPT Stage 1.
79-22-495R8138Tube A/O Oil—No. 4 Brg Scav Dif Case to Bif Panel.
79-22-496A5367Tube A/O Oil—No. 4 Brg Scav Dif Case to Bif Panel.
79-22-495A9083Tube A/O Oil—No. 4 Brg Discon to Discon.
79-22-495A9084Tube A/O Oil—No. 4 Brg Discon to Scav Valve.
79-22-495A8573Tube 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 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 referenceP/NNomenclature
72-42-202A0367-01Tube Assy of, Weep, No. 4 Bearing Outer.
72-42-202A2873-01Tube Assy of, Weep, No. 4 Bearing Outer.
72-42-332A0851Support Assy, No. 4 Bearing Seal.
72-42-332A2833Support, No. 4 Bearing, Seal Assy.
72-42-332A3537Support, No. 4 Bearing Seal Assy.
72-42-332A2834Seal Assy, No. 4 Bearing, Front.
72-42-332A2930Seal Assy, No. 4 Bearing, Front.
72-42-332A3525Seal Assy, No. 4 Bearing, Front.
72-42-332A3538Seal Assy, No. 4 Bearing, Front.
72-42-352A2257-01Duct Assy, Cooling Air, No. 4 Bearing, Front.
Start Printed Page 40719
72-43-202A2056Seal Assy, No. 4 Bearing, Rear.
72-43-202A2931Seal Assy, No. 4 Bearing, Rear.
72-43-202A3526Seal Assy, No. 4 Bearing, Rear.
72-43-202A0847Seal Ring Holder.
72-43-202A1205-01Duct Assy, Cooling Air, No. 4 Bearing, Rear.
72-43-202A3078-01Duct Assy, Cooling Air, No. 4 Bearing, Rear.
72-45-112A3182Metering Plug, HPT Hub, Stage 1.
72-45-112A2354Metering Plug, HPT Hub, Stage 1.
72-45-132A1352Seal Air, HPT Stage 1.
72-45-132A3032Seal 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.

Start Signature

Issued in Burlington, Massachusetts, on July 2, 2008.

Peter A. White,

Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service.

End Signature End Supplemental Information

[FR Doc. E8-15686 Filed 7-15-08; 8:45 am]

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