50874 Federal Register / Vol. 75, No. 159 / Wednesday, August 18, 2010 / Rules and Regulations 

TABLE 2—AIRBUS CREDIT SERVICE INFORMATION—Continued 

Airbus all operators telex— Revision— Dated— 

A340–34A4241 ............................................................................................................................................... Original ........ September 10, 2009. 

A340–34A4241 ............................................................................................................................................... 1 .................. September 21, 2009. 

A340–34A5074 ............................................................................................................................................... Original ........ September 10, 2009. 

A340–34A5074 ............................................................................................................................................... 1 .................. September 21, 2009. 

(4) As of the effective date of this AD, no 

person may install a pitot probe having 

Goodrich P/N 0851HL, serial numbers 

267328 through 270714 inclusive, on any 

airplane, unless the actions required by 

paragraph (g)(1) of this AD have been done; 

or an intact red torque check mark is visible 

on the interface of the pnuematic quick 

disconnect union and the union mount. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: 

Where the MCAI includes a compliance 

time of ‘‘5 days,’’ we have determined that a 

compliance time of ‘‘within 14 days after the 

effective date of the AD’’ is appropriate. The 

manufacturer and EASA agree with this 

expansion in compliance time. 

Other FAA AD Provisions 

(h) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, FAA, Transport Airplane 

Directorate, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. Send 

information to ATTN: Vladimir Ulyanov, 

Aerospace Engineer, International Branch, 

ANM–116, FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1138; fax (425) 227–1149. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

The AMOC approval letter must specifically 

reference this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(i) Refer to MCAI Airworthiness Directive 

2009–0202R1, dated April 15, 2010; and the 

service information specified in Table 1 of 

this AD; for related information. 

Material Incorporated by Reference 

(j) You must use the service information 

contained in Table 3 of this AD, as 

applicable, to do the actions required by this 

AD, unless the AD specifies otherwise. (The 

document number, revision level, and date of 

these documents are listed only on the first 

page of these documents; no other page of 

these documents contains this information.) 

TABLE 3—MATERIAL INCORPORATED BY REFERENCE

Airbus all operators telex— Revision— Dated— 

A330–34A3235 ........................................................................................................................................................ 02 ................ March 1, 2010. 

A340–34A4241 ........................................................................................................................................................ 02 ................ March 1, 2010. 

A340–34A5074 ........................................................................................................................................................ 02 ................ March 1, 2010. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; e-mail 

airworthiness.A330–A340@airbus.com; 

Internet http://www.airbus.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on July 30, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–19701 Filed 8–17–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0782; Directorate 

Identifier 2010–SW–053–AD; Amendment 

39–16396; AD 2010–11–51] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France (Eurocopter) Model AS350B, 

BA, B1, B2, C, D, and D1 Helicopters 

and Model AS355E, F, F1, F2, and N 

Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This document publishes in 

the Federal Register an amendment 

adopting Airworthiness Directive (AD) 

2010–11–51, which was sent previously 

to all known U.S. owners and operators 


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of the specified Eurocopter model 

helicopters by individual letters. This 

AD requires visually inspecting the tail 

gearbox (TGB) control lever for a crack. 

If a crack is found, this AD also requires 

replacing the cracked TGB control lever 

with an airworthy TGB control lever. 

Optional terminating actions for the 

inspection requirements of this AD can 

be done by either replacing a TGB 

control lever with an airworthy TGB 

control lever that is marked with an ‘‘X’’ 

near the part number or stripping the 

rework area and dye-penetrant 

inspecting that area for a crack, and if 

no crack is found, reworking and 

marking the TGB control lever. If a crack 

is found, removing and replacing the 

cracked TGB control lever with an 

airworthy TGB control lever is required. 

This AD is prompted by several reports 

of cracking in a TGB control lever. The 

actions specified by this AD are 

intended to prevent failure of the TGB 

control lever, loss of tail rotor control, 

and subsequent loss of control of the 

helicopter. 

DATES: Effective September 2, 2010, to 

all persons except those persons to 

whom it was made immediately 

effective by Emergency AD 2010–11–51, 

issued on May 11, 2010, which 

contained the requirements of this 

amendment. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of September 

2, 2010. 

Comments for inclusion in the Rules 

Docket must be received on or before 

October 18, 2010. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• 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: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue, SE., Washington, DC 20590, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

You may get the service information 

identified in this AD from American 

Eurocopter Corporation, 2701 Forum 

Drive, Grand Prairie, Texas 75053–4005, 

telephone (800) 232–0323, fax (972) 

641–3710, or at http:// 

www.Eurocopter.com. 

Examining the Docket: You may 

examine the docket that contains the 

AD, any comments, and other 

information 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 Docket 

Operations office (telephone (800) 647– 

5527) is located in Room W12–140 on 

the ground floor of the West Building at 

the street address stated in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: J.R. 

Holton, Jr., Aviation Safety Engineer, 

FAA, Rotorcraft Directorate, Safety 

Management Group, 2601 Meacham 

Blvd., Fort Worth, Texas 76137, 

telephone (817) 222–4964, fax (817) 

222–5961. 

SUPPLEMENTARY INFORMATION: On May 

11, 2010, the FAA issued Emergency AD 

2010–11–51 for the specified Eurocopter 

model helicopters, which requires 

visually inspecting the TGB control 

lever for a crack. If a crack is found, the 

AD requires replacing the cracked TGB 

control lever with an airworthy TGB 

control lever. Optional terminating 

actions for the inspection requirements 

of the AD can be done by either 

replacing a TGB control lever with an 

airworthy TGB control lever that is 

marked with an ‘‘X’’ near the part 

number or stripping the rework area and 

dye-penetrant inspecting that area for a 

crack, and if no crack is found, 

reworking and marking the TGB control 

lever. If a crack is found, the AD 

requires removing and replacing the 

cracked TGB control lever with an 

airworthy TGB control lever. The AD 

was prompted by several reports of 

cracking in a TGB control lever, 

including an accident involving a 

Eurocopter Model AS350B2 helicopter. 

An investigation revealed that a few 

surface anomalies may lead to a crack in 

the TGB control lever. This condition, if 

not corrected, could result in failure of 

the TGB control lever, loss of tail rotor 

control, and subsequent loss of control 

of the helicopter. 

We have reviewed Eurocopter 

Emergency Alert Service Bulletin 

(EASB) No. 05.00.62, for Model AS350 

helicopters and EASB No. 05.00.57 for 

Model AS355 helicopters. Both EASBs 

are Revision 1, dated April 23, 2010, 

and both describe procedures for a 

visual inspection of the TGB control 

lever for a crack that must be performed 

after the last flight of each day and prior 

to exceeding 10 flying hours for each 

inspection. The EASBs also describe a 

rework procedure for affected TGB 

control levers, which must be 

accomplished within 660 flying hours 

or no later than June 30, 2011, or before 

installing an affected TGB control lever 

on a helicopter. The one Eurocopter 

EASB contains four different service 

bulletin numbers (Nos. 05.00.62, 

05.00.57, 05.00.38, and 05.00.35) 

applicable to four different Eurocopter 

model helicopters. EASB No. 05.00.38 

relates to Eurocopter Model AS550 

helicopters, and EASB No. 05.00.35 

relates to Eurocopter Model AS555 

helicopters. Eurocopter Model AS550 

and AS555 helicopters are military 

models and are not type-certificated in 

the United States. This AD does not 

incorporate EASB No. 05.00.38 nor 

EASB No. 05.00.35. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for France, notified the FAA that an 

unsafe condition may exist on these 

helicopter models. EASA advises of a 

crack discovered in a TGB control lever, 

which could lead to a loss of tail rotor 

control and subsequent loss of control of 

the helicopter. EASA classified the 

service bulletin as mandatory and 

issued EASA Emergency AD No. 2010– 

0082–E, dated April 27, 2010, to ensure 

the continued airworthiness of these 

helicopters. The AD differs from EASA 

Emergency AD No. 2010–0082–E as 

follows: 

• We include the Eurocopter Model 

AS350C and AS350D1 helicopters that 

may contain the affected TGB control 

lever; 

• We use the term ‘‘hours time-inservice’’ rather than ‘‘flight hours’’; 

• We do not require replacing the 

TGB control lever within 660 hours TIS 

or 14 months, but instead offer optional 

terminating actions for the repetitive 

inspection requirements; and 

• We do not require you to contact 

Eurocopter if a crack is found during 

any inspection. 

These helicopter models are type 

certificated for operation in the United 

States under the provisions of 14 CFR 

21.29 and the applicable bilateral 

agreement. Pursuant to the applicable 

bilateral agreement, EASA has kept the 

FAA informed of the situation 

described. The FAA has examined the 

findings of EASA, reviewed all available 

information, and determined that AD 

action is necessary for products of these 

type designs that are certificated for 

operation in the United States. 

Since the unsafe condition described 

is likely to exist or develop on other 

Eurocopter model helicopters of these 

same type designs, the FAA issued 

Emergency AD 2010–11–51 to prevent 

failure of the TGB control lever, loss of 

tail rotor control, and subsequent loss of 


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50876 Federal Register / Vol. 75, No. 159 / Wednesday, August 18, 2010 / Rules and Regulations 

control of the helicopter. The AD 

requires within 10 hours time-in-service 

(TIS) and thereafter at intervals not to 

exceed 10 hours TIS, visually inspecting 

the TGB control lever for a crack. If a 

crack is found, the AD requires 

replacing the cracked TGB control lever 

with an airworthy TGB control lever 

before further flight. Optional 

terminating actions for the inspection 

requirements of the AD can be 

accomplished by either replacing a TGB 

control lever with an airworthy TGB 

control lever that is marked with an ‘‘X’’ 

near the part number or stripping the 

rework area and dye-penetrant 

inspecting that area for a crack, and if 

no crack is found, reworking and 

marking the TGB control lever before 

further flight. If a crack is found, 

removing and replacing the cracked 

TGB control lever with an airworthy 

TGB control lever is required before 

further flight. The actions must be done 

by following the specified portions of 

the service bulletin described 

previously. 

The short compliance time involved 

is required because the previously 

described critical unsafe condition can 

adversely affect the controllability and 

structural integrity of the helicopter. 

Therefore, visually inspecting the TGB 

control lever for a crack is required 

within 10 hours TIS replacing any 

cracked TGB is required before further 

flight, and this AD must be issued 

immediately. 

Since it was found that immediate 

corrective action was required, notice 

and opportunity for prior public 

comment thereon were impracticable 

and contrary to the public interest, and 

good cause existed to make the AD 

effective immediately by individual 

letters issued on May 11, 2010, to all 

known U.S. owners and operators of the 

specified Eurocopter model helicopters. 

These conditions still exist, and the AD 

is hereby published in the Federal 

Register as an amendment to 14 CFR 

39.13 to make it effective to all persons. 

The FAA estimates that this AD will 

affect 791 helicopters of U.S. registry. 

The initial and repetitive inspections for 

a crack in the TGB control lever will 

take a minimal amount of time. The 

average labor rate is $85 per work hour. 

Replacing a control lever, will take 

about 3 work hours, and the required 

parts will cost about $2,103 per 

helicopter. Based on these figures, we 

estimate the total cost of the AD on U.S. 

operators to be $1,865,178, assuming the 

control lever is replaced on the entire 

fleet. If you choose to dye-penetrant 

inspect, remove, rework, and replace the 

lever, it will take about 5 work hours, 

and the parts will cost about $20 per 

helicopter. Based on these figures, we 

estimate the total cost of the AD on U.S. 

operators to be $351,995, assuming no 

control levers are found cracked. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

written data, views, or arguments 

regarding this AD. Send your comments 

to an address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2010–0782; 

Directorate Identifier 2010–SW–053– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the AD. We will consider all comments 

received by the closing date and may 

amend the 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 AD. Using the 

search function of our docket Web site, 

you can find and read the comments to 

any of our dockets, including the name 

of the individual who sent the 

comment. You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78). 

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 the regulation: 

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. 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 an economic evaluation 

of the estimated costs to comply with 

this AD. See the AD docket to examine 

the economic evaluation. 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (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. Section 39.13 is amended by adding 

a new airworthiness directive to read as 

follows: 

2010–11–51 Eurocopter France: 

Amendment 39–16396. Docket No. 

FAA–2010–0782; Directorate Identifier 

2010–SW–053–AD. 

Applicability: Model AS350B, BA, B1, B2, 

C, D, and D1 helicopters and Model AS355E, 

F, F1, F2, and N helicopters, with a tail 

gearbox (TGB) control lever, part number (P/ 

N) 350A33–1058–00, P/N 350A33–1058–01, 

P/N 350A33–1058–02, or P/N 350A33–1058– 

03, that is not marked with an ‘‘X’’ near the 

P/N, installed, certificated in any category. 

Compliance: Required as indicated. 

To detect cracking in a TGB control lever 

and prevent failure of the TGB control lever, 

loss of tail rotor control, and subsequent loss 

of control of the helicopter, accomplish the 

following: 

(a) Within 10 hours time-in-service (TIS), 

unless accomplished previously, and 

thereafter at intervals not to exceed 10 hours 

TIS, visually inspect the affected TGB control 


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Federal Register / Vol. 75, No. 159 / Wednesday, August 18, 2010 / Rules and Regulations 50877 

lever for cracking in accordance with the 

Accomplishment Instructions, paragraph 

2.B.1.a., in Eurocopter Emergency Alert 

Service Bulletin (EASB) No. 05.00.62, 

Revision 1, dated April 23, 2010, for Model 

AS350 helicopters or EASB No. 05.00.57, 

Revision 1, dated April 23, 2010, for Model 

AS355 helicopters. 

(b) If a crack is found, before further flight, 

remove and replace the cracked TGB control 

lever with an airworthy TGB control lever in 

accordance with the Accomplishment 

Instructions, paragraph 2.B.2., in the EASB 

appropriate for your model helicopter. 

(c) Either of the following options 

constitutes a terminating action for the 

inspection requirements of this AD: 

(1) Replace a TGB control lever with an 

airworthy TGB control lever that is marked 

with an ‘‘X’’ near the P/N; or 

(2) Strip the rework area ‘‘B’’ as shown in 

Figure 4 of each EASB and perform a dyepenetrant inspection on that area for a crack. 

If no crack is found, rework and mark the 

TGB control lever in accordance with 

paragraph 2.B.3.b. of the EASB appropriate 

for your model helicopter, except you are not 

required to contact Eurocopter France. If a 

crack is found, before further flight, remove 

and replace the cracked TGB control lever 

with an airworthy TGB control lever in 

accordance with the Accomplishment 

Instructions, paragraph 2.B.2., in the EASB. 

Note 1: One Eurocopter EASB contains 

four different service bulletin numbers but 

only portions of 2 EASBs are being 

incorporated. 

Note 2: Installing a reinforced TGB control 

lever, P/N 350A33–1524–00 or P/N 350A33– 

1526–00, that does not need to be marked 

with an ‘‘X’’ constitutes compliance with 

paragraph (c) of this AD. 

(d) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact the Manager, Safety 

Management Group, FAA, ATTN: J.R. 

Holton, Jr., Aviation Safety Engineer, ASW– 

112, 2601 Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–4964, fax (817) 

222–5961, for information about previously 

approved alternative methods of compliance. 

(e) Special flight permits may be issued in 

accordance with 14 CFR 21.197 and 21.199 

to operate the helicopter to a location where 

the inspection requirements of paragraph (a) 

of this AD can be accomplished. 

(f) The Joint Aircraft System/Component 

(JASC) Code is 6720: Tail Rotor Control 

System. 

(g) Inspecting, replacing the control lever 

or removing, reworking, and replacing the 

control lever shall be done in accordance 

with the specified portions of Eurocopter 

Emergency Alert Service Bulletin (EASB) No. 

05.00.62, Revision 1, dated April 23, 2010, 

for Model AS350 helicopters or EASB No. 

05.00.57, Revision 1, dated April 23, 2010, 

for Model AS355 helicopters. The Director of 

the Federal Register approved this 

incorporation by reference in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Copies may be obtained from American 

Eurocopter Corporation, 2701 Forum Drive, 

Grand Prairie, Texas 75053–4005, telephone 

(800) 232–0323, fax (972) 641–3710, or at 

http://www.Eurocopter.com. Copies may be 

inspected at the FAA, Office of the Regional 

Counsel, Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas, or at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

(h) This amendment becomes effective on 

September 2, 2010, to all persons except 

those persons to whom it was made 

immediately effective by Emergency AD 

2010–11–51, issued May 11, 2010, which 

contained the requirements of this 

amendment. 

Note 3: The subject of this AD is addressed 

in European Aviation Safety Agency (France) 

Emergency AD No. 2010–0082–E, dated April 

27, 2010. 

Issued in Fort Worth, Texas, on August 2, 

2010. 

Scott A. Horn, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–19818 Filed 8–17–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0521; Directorate 

Identifier 2009–NE–21–AD; Amendment 39– 

16405; AD 2010–17–13] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc RB211–524C2 Series Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. 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. The MCAI describes the unsafe 

condition as: 

A number of LPT casings have been found 

cracked during engine shop visit. Cracking of 

the LPT casing reduces the capability of the 

casing to contain debris in the event of an 

LPT stage 1 blade failure. Therefore, blade 

failure in an engine featuring a cracked LPT 

casing may result in release of uncontained 

high energy debris. 

For the reason described above, this AD 

requires repetitive inspections and corrective 

actions, depending on findings. 

We are issuing this AD to detect cracks 

in the low-pressure turbine (LPT) 

casings, which could result in the 

release of uncontained high-energy 

debris in the event of a stage 1 blade 

failure. Uncontained high-energy debris 

could result in damage to the airplane. 

DATES: This AD becomes effective 

September 22, 2010. 

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. 

FOR FURTHER INFORMATION 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. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on May 19, 2010 (75 FR 27973). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

A number of LPT casings have been found 

cracked during engine shop visit. Cracking of 

the LPT casing reduces the capability of the 

casing to contain debris in the event of an 

LPT stage 1 blade failure. Therefore, blade 

failure in an engine featuring a cracked LPT 

casing may result in release of uncontained 

high energy debris. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. The 

commenter supports the NPRM. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

Based on the service information, we 

estimate that this AD will affect about 

10 products of U.S. registry. We also 

estimate that it will take about 10 workhours per product to comply with this 

AD. The average labor rate is $85 per 

work-hour. Required parts will cost 

about $25,000 per product. Based on 

these figures, we estimate the cost of the 

AD on U.S. operators to be $258,500. 


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