### RE: [Docket No. FAA-2010-0494; Dire ctorate 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 Jetb lue (and maybe the rest of the industry is the same) BSI MPD f or the

combustion Chamber and Turbine section in is 2000 FH. If this BS I interval can let go to 2000 hours coinciding with our existin g 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 wi th regards to the below NPRM BSI complianc e interval which is every 2A Check (120 0 hrs).

Just recently, Airbus together with our lo cal FAA approved MPD extension to Jetblue Ai rways A check from 600 hrs to 750 hrs. Th erefore

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

possible to change BSI interval from 2A Chec k (1200 hrs) to the recent Airbus MPD exte nsion of 2A Check (1500 hrs) granted to J etblue 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

Pa g e 1 of 6RIN 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

Pa g e 2 of 6with 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

Pa g e 3 of 6Authority 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

Pa g e 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 

## 5/3/2011 12:13:58 PM

Pa g e 5 of 6A5..................................................... 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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