RE: [Docket No. FAA-2010-0494; Directorate Identifier 2010-NE-20-AD] 

Trino, Henry 

to: 

Carlos Fernandes 

01/17/2011 11:04 AM 

Cc: 

PowerplantEngineering 

Show Details 

History: This message has been replied to. 

Hi Carlos,

Further to my request below about BSI interval, our existing Jetblue (and maybe the rest of the industry is the same) BSI MPD for the 

combustion Chamber and Turbine section in is 2000 FH. If this BSI interval can let go to 2000 hours coinciding with our existing BSI interval 

it would be very beneficial and would lessen if not eliminate the burden to most operator.

Best Regards.

Henry J. Trino

Powerplant Engineer

JetBlue Airways

118-29 Queens Blvd.,

Forest Hills. NY 11375

Tel: 718-709-3450

Fax: 718-228-8042

E-mail: henry.trino@jetblue.com

From: Trino, Henry 

Sent: Tuesday, January 11, 2011 11:06 AM 

To: 'carlos.fernandes@faa.gov' 

Cc: PowerplantEngineering 

Subject: [Docket No. FAA-2010-0494; Directorate Identifier 2010-NE-20-AD]

 

Hi Carlos,

Per our telephone conversation this morning with regards to the below NPRM BSI compliance interval which is every 2A Check (1200 hrs). 

Just recently, Airbus together with our local FAA approved MPD extension to Jetblue Airways A check from 600 hrs to 750 hrs. Therefore 

JetBlue Airways 2A check is now 1500 hrs which won’t coincide with the 2A check (1200 hrs) NPRM BSI compliance interval. Would it be 

possible to change BSI interval from 2A Check (1200 hrs) to the recent Airbus MPD extension of 2A Check (1500 hrs) granted to Jetblue to 

relieve us from additional burden that this NPRM cause to us.

Best Regards,

Henry J. Trino

Powerplant Engineer

JetBlue Airways

118-29 Queens Blvd.,

Forest Hills. NY 11375

Tel: 718-709-3450

Fax: 718-228-8042

E-mail: henry.trino@jetblue.com

DEPARTMENT OF TRANSPORTATION

  

Federal Aviation Administration

  

14 CFR Part 39

  

[Docket No. FAA‐2010‐0494; Directorate Identifier 2010‐NE‐20‐AD]

5/3/2011 12:13:58 PM

Page 1 of 6
RIN 2120‐AA64

  

  

Airworthiness Directives; International Aero Engines V2500‐A1,  

V2522‐A5, V2524‐A5, V2525‐D5, V2527‐A5, V2527E‐A5, V2527M‐A5, V2528‐D5,  

V2530‐A5, and V2533‐A5 Turbofan Engines

  

AGENCY: Federal Aviation Administration (FAA), DOT.

  

ACTION: Notice of proposed rulemaking (NPRM).

  

‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐ 

  

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)  

for International Aero Engines (IAE) V2500‐A1, V2522‐A5, V2524‐A5,  

V2525‐D5, V2527‐A5, V2527E‐A5, V2527M‐A5, V2528‐D5, V2530‐A5, and  

V2533‐A5 turbofan engines. This proposed AD would require initial and  

repetitive 360[deg] borescope inspections of high‐pressure turbine  

(HPT) stage 1 blade outer air seal segments for evidence of certain  

distress conditions. This proposed AD would also require incorporation  

of improved durability stage 1 blade outer air seal segments at the  

next exposure to the HPT module subassembly, as terminating action to  

the repetitive inspections. This proposed AD results from three reports  

received of HPT case burn‐through events, numerous shop reports of loss  

of stage 1 blade outer air seal segments, and HPT case bulging. We are  

proposing this AD to prevent HPT case burn‐through, uncontrolled under‐ 

cowl engine fire, and damage to the airplane.

  

DATES: We must receive any comments on this proposed AD by January 24,  

2011.

  

ADDRESSES: Use one of the following addresses to comment on this  

proposed AD.

     Federal eRulemaking Portal: Go to http://

www.regulations.gov and follow the instructions for sending your  

comments electronically.

     Mail: Docket Management Facility, U.S. Department of  

Transportation, 1200 New Jersey Avenue, SE., West Building Ground  

Floor, Room W12‐140, Washington, DC 20590‐0001.

     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.

  

[[Page 71374]]

  

    Contact International Aero Engines AG, 400 Main Street, East  

Hartford, CT 06108; telephone: (860) 565‐5515; fax: (860) 565‐5510, for  

a copy of the service information identified in this proposed AD.

  

FOR FURTHER INFORMATION CONTACT: Carlos Fernandes, Aerospace Engineer,  

Engine Certification Office, FAA, Engine & Propeller Directorate, 12  

New England Executive Park, Burlington, MA 01803; e‐mail:  

carlos.fernandes@faa.gov; telephone (781) 238‐7189; 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‐2010‐0494; Directorate  

Identifier 2010‐NE‐20‐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://

www.regulations.gov, including any personal information you provide. We  

will also post a report summarizing each substantive verbal contact  

5/3/2011 12:13:58 PM

Page 2 of 6
with FAA personnel concerning this proposed AD. Using the search  

function of the Web site, anyone can find and read the comments in any  

of our dockets, including, if provided, 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).

  

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 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

  

    Since August 2006 we have received three reports of IAE V2500  

series engines experiencing HPT case burn‐through events. There have  

also been numerous shop reports of loss of stage 1 blade outer air seal  

segments, and reports of HPT case bulging. Investigation revealed the  

cause to be due to HPT stage 1 blade outer air seal distress. Distress  

initially starts with surface erosion and cracking of the blade outer  

air seal segments. Continued engine operation then leads to burn‐ 

through, radial bowing of the segments into the gas path, contact with  

the HPT stage 1 blades, and loss of the segments from the HPT case.  

This condition, if not corrected, could then result in HPT case burn‐ 

through, uncontrolled under‐cowl engine fire, and damage to the  

airplane.

  

Relevant Service Information

  

    We have reviewed and approved the technical contents of IAE Service  

Bulletin (SB) No. V2500‐ENG‐72‐0580, Revision 2, dated August 12, 2010,  

that describes procedures for initial and repetitive 360[deg] borescope  

inspections of stage 1 blade outer air seal segments for evidence of  

distress. We have also reviewed and approved IAE SB No. V2500‐ENG‐72‐ 

0483, Revision 3, dated January 7, 2009, and IAE SB No. V2500‐ENG‐72‐ 

0542, Revision 1, dated January 7, 2009, which incorporate improved  

durability stage 1 blade outer air seal segments.

  

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  

initial and repetitive 360[deg] borescope inspections of HPT stage 1  

blade outer air seal segments for evidence of distress. This proposed  

AD would also require incorporation of improved design stage 1 blade  

outer air seal segments at the next exposure to the HPT module  

subassembly. The proposed AD would require you to use the service  

information described previously to perform these actions.

  

Costs of Compliance

  

    We estimate that this proposed AD would affect 34 V2500 A1 series  

and 510 V2500 A5/D5 series engines installed on airplanes of U.S.  

registry. We also estimate that it would take about 3 work‐hours per  

engine to perform one proposed inspection, about 3 work‐hours per  

engine to install the improved durability stage 1 blade outer air seal  

segments, and that the average labor rate is $85 per work‐hour.  

Required parts would cost about $150,882 (V2500 A1 series) and $155,195  

(V2500 A5/D5 series), per engine. Based on these figures, we estimate  

the total cost of the proposed AD to U.S. operators to be $84,556,878.

  

5/3/2011 12:13:58 PM

Page 3 of 6
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.

  

List of Subjects in 14 CFR Part 39

  

    Air transportation, Aircraft, Aviation safety, Incorporation by  

reference, Safety.

  

[[Page 71375]]

  

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: Docket No. FAA‐2010‐0494; Directorate  

Identifier 2010‐NE‐20‐AD.

  

Comments Due Date

  

    (a) The Federal Aviation Administration (FAA) must receive  

comments on this airworthiness directive (AD) action by January 24,  

2011.

  

Affected ADs

5/3/2011 12:13:58 PM

Page 4 of 6
  

    (b) None.

  

Applicability

  

    (c) This AD applies to International Aero Engines (IAE) V2500‐ 

A1, V2522‐A5, V2524‐A5, V2525‐D5, V2527‐A5, V2527E‐A5, V2527M‐A5,  

V2528‐D5, V2530‐A5, and V2533‐A5 turbofan engines. 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 three reports received of high‐pressure  

turbine (HPT) case burn‐through events. There have also been  

numerous shop reports of loss of stage 1 blade outer air seal  

segments, and HPT case bulging. We are issuing this AD to prevent  

HPT case burn‐through, uncontrolled under‐cowl engine fire, 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.

    (f) For engines that have incorporated IAE Service Bulletin (SB)  

No. V2500‐ENG‐72‐0483, Revision 3 or earlier, or IAE SB No. V2500‐ 

ENG‐72‐0542, Revision 1 or earlier, no further action is required.

  

Borescope Inspections

  

    (g) Perform 360[deg] borescope inspections of the HPT stage 1  

blade outer air seal segments for evidence of the distress  

conditions listed in Appendix D of IAE SB No. V2500‐ENG‐72‐0580,  

Revision 2, dated August 12, 2010.

    (1) For V2525‐D5 and V2528‐D5 turbofan engines:

    (i) Inspect within 1,000 operating hours after the engine meets  

all criteria as defined in Table 1 of this AD, or within 600  

operating hours after the effective date of this AD, whichever is  

greater.

    (ii) Thereafter, re‐inspect within every 1,000 operating hours  

or as defined in Appendix D of IAE SB No. V2500‐ENG‐72‐0580,  

Revision 2, dated August 12, 2010, whichever is less.

    (iii) Use Accomplishment Instructions paragraphs 3.B.(1) through  

3.B.(3), and Appendices A through D of IAE SB No. V2500‐ENG‐72‐0580,  

Revision 2, dated August 12, 2010, to do these inspections.

    (2) For V2500‐A1, V2522‐A5, V2524‐A5, V2527‐A5, V2527E‐A5,  

V2527M‐A5, V2530‐A5, and V2533‐A5 turbofan engines:

    (i) Inspect within 1,200 operating hours after the engine meets  

all criteria as defined in Table 1 of this AD, or within 600  

operating hours after the effective date of this AD, whichever is  

greater.

    (ii) Thereafter, re‐inspect within every 1,200 operating hours  

or as defined in Appendix D of IAE SB No. V2500‐ENG‐72‐0580,  

Revision 2, dated August 12, 2010, whichever is less.

    (iii) Use Accomplishment Instructions paragraphs 3.A.(1) through  

3.A.(3), and Appendices A through D of IAE SB No. V2500‐ENG‐72‐0580,  

Revision 2, dated August 12, 2010, to do these inspections.

  

                  Table 1‐‐Stage 1 Blade Outer Air Seal Segment Inspection Compliance Criteria

‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐

                                                           Stage 1 blade      Stage 1 blade

                                                           outer air seal     outer air seal      Exhaust gas

                                                          segments hours‐    segments cycles‐     temperature

                      Engine model                          since‐new or       since‐new or      margin degrees

                                                         since‐last‐repair  since‐last‐repair    celsius (less

                                                           (greater than)     (greater than)         than)

‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐

A1.....................................................              6,000              3,800                 45

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A5.....................................................              6,000              3,500                 45

D5.....................................................              5,000              3,500                 45

‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐‐

  

     (h) Exhaust Gas Temperature Margin is defined as the expected  

margin during a sea‐level takeoff on a 30‐degree Celsius Outside Air  

Temperature Day.

  

Terminating Action

  

    (i) As terminating action to the repetitive 360[deg] borescope  

inspections required in paragraphs (g)(1)(ii) and (g)(2)(ii) above,  

install improved durability stage 1 blade outer air seal segments at  

the next HPT module subassembly exposure.

    (1) For V2500‐A1 turbofan engines, use paragraphs 1.B.,  

Concurrent Requirements, and paragraphs 3.(1) through 3.(2)(b) of  

the Accomplishment Instructions of IAE SB No. V2500‐ENG‐72‐0542,  

Revision 1, dated January 7, 2009, to do the installation.

    (2) For V2522‐A5, V2524‐A5, V2525‐D5, V2527‐A5, V2527E‐A5,  

V2527M‐A5, V2528‐D5, V2530‐A5, and V2533‐A5 turbofan engines, use  

paragraphs 1.B., Concurrent Requirements, and paragraphs 3.(1)  

through 3.(2)(b) of the Accomplishment Instructions of IAE SB No.  

V2500‐ENG‐72‐0483, Revision 3, dated January 7, 2009, to do the  

installation.

    (3) Both IAE SBs No. V2500‐ENG‐72‐0542, Revision 1, and SB No.  

V2500‐ENG‐72‐0483, Revision 3, require modification of the stage 1  

HPT support assembly before installing the new blade outer air seal  

segments. You must complete the modification using those SBs, as  

applicable to the appropriate engine model, to properly perform the  

mandatory terminating action of this AD.

  

Alternative Methods of Compliance

  

    (j) 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

  

    (k) Contact Carlos Fernandes, Aerospace Engineer, Engine  

Certification Office, FAA, Engine & Propeller Directorate, 12 New  

England Executive Park, Burlington, MA 01803; e‐mail:  

mark.riley@faa.gov; telephone (781) 238‐7189; fax (781) 238‐7199,  

for more information about this AD.

    (l) Contact International Aero Engines AG, 400 Main Street, East  

Hartford, CT 06108; telephone: (860) 565‐5515; fax: (860) 565‐5510,  

for a copy of the service information referenced in this AD.

  

    Issued in Burlington, Massachusetts, on November 16, 2010.

Peter A. White,

Assistant Manager, Engine and Propeller Directorate, Aircraft  

Certification Service.

[FR Doc. 2010‐29450 Filed 11‐22‐10; 8:45 am]

BILLING CODE 4910‐13‐P

Henry J. Trino

Powerplant Engineer

JetBlue Airways

118-29 Queens Blvd.,

Forest Hills. NY 11375

Tel: 718-709-3450

Fax: 718-228-8042

E-mail: henry.trino@jetblue.com

 

5/3/2011 12:13:58 PM

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