Federal Register / Vol. 75, No. 225 / Tuesday, November 23, 2010 / Proposed Rules 71373 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA 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. 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Thielert Aircraft Engines GmbH: Docket No. 

FAA–2010–0820; Directorate Identifier 

2010–NE–31–AD. 

Comments Due Date 

(a) We must receive comments by January 

7, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Thielert Aircraft 

Engines GmbH models TAE 125–01, TAE 

125–02–99, and TAE 125–02–114 

reciprocating engines installed in, but not 

limited to, Cessna 172 and (Reims-built) F172 

series (European Aviation Safety Agency 

(EASA) STC No. EASA.A.S.01527); Piper 

PA–28 series (EASA STC No. EASA.A.S. 

01632); APEX (Robin) DR 400 series (EASA 

STC No. A.S.01380); and Diamond Aircraft 

Industries Models DA 40, DA 42, and DA 

42M NG airplanes. 

Reason 

(d) This AD results from mandatory 

continuing airworthiness information (MCAI) 

issued by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. We are 

issuing this AD to prevent engine in-flight 

shutdown or power loss, possibly resulting in 

reduced control of the airplane. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

(1) Within 110 flight hours after the 

effective date of the AD or during next 

maintenance, whichever occurs first, install 

full-authority digital electronic control 

(FADEC) software version 2.91. 

(2) Guidance on FADEC software 

installation can be found in the following: 

(i) For TAE 125–01 engines, Operation & 

Maintenance Manual OM–01–02, Issue 3, 

Revision 13. 

(ii) For TAE 125–02–99 and TAE 125–02– 

114 engines, Operation & Maintenance 

Manual OM–02–02, Issue 1, Revision 10. 

Prohibition of FADEC Software Earlier 

Versions 

(f) Once FADEC software version 2.91 is 

installed, do not install any earlier version of 

FADEC software. 

FAA AD Differences 

(g) EASA AD 2010–0137 permits 

installation of earlier FADEC software 

versions, once version 2.91 is installed. This 

AD does not. 

(h) EASA AD 2010–0137 requires 

compliance within 110 flight hours after the 

effective date of the AD or during next 

maintenance, whichever occurs first, but no 

later than 6 months after the effective date of 

the AD. This AD requires compliance within 

110 flight hours after the effective date of the 

AD or during next maintenance, whichever 

occurs first. 

Alternative Methods of Compliance 

(AMOCS) 

(i) The Manager, Engine Certification 

Office, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

Related Information 

(j) Refer to AD 2010–0137, dated June 30, 

2010, for related information. Contact 

Thielert Aircraft Engines GmbH, 

Platanenstrasse 14 D–09350, Lichtenstein, 

Germany, telephone: +49–37204–696–0; fax: 

+49–37204–696–2912; e-mail: 

info@centurion-engines.com, for a copy of 

the service information referenced in this 

AD. 

(k) Contact Alan Strom, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: alan.strom@faa.gov; telephone 

(781) 238–7143; fax (781) 238–7199, for more 

information about this AD. 

Issued in Burlington, Massachusetts, on 

November 16, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–29449 Filed 11–22–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0494; Directorate 

Identifier 2010–NE–20–AD] 

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° 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 burnthrough, 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. 


erowe on DSK5CLS3C1PROD with PROPOSALS-1
71374 Federal Register / Vol. 75, No. 225 / Tuesday, November 23, 2010 / Proposed Rules 

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 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 burnthrough 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 burnthrough, 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 undercowl 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° 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° 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. 

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. 


erowe on DSK5CLS3C1PROD with PROPOSALS-1
Federal Register / Vol. 75, No. 225 / Tuesday, November 23, 2010 / Proposed Rules 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. 

§ 39.13 [Amended] 

2. The FAA amends § 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 

(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 undercowl 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° 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

Engine model 

Stage 1 blade 

outer air seal 

segments hourssince-new or 

since-last-repair 

(greater than) 

Stage 1 blade 

outer air seal 

segments cyclessince-new or 

since-last-repair 

(greater than) 

Exhaust gas 

temperature 

margin degrees 

celsius (less than) 

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

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 sealevel takeoff on a 30-degree Celsius Outside 

Air Temperature Day. 

Terminating Action 

(i) As terminating action to the repetitive 

360° 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 


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