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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50878 Federal Register / Vol. 75, No. 159 / Wednesday, August 18, 2010 / Rules and Regulations 

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 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 this 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. 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 regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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 (phone 

(800) 647–5527) is provided in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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 AD: 

2010–17–13 Rolls-Royce plc (Formerly 

Rolls-Royce Limited): Amendment 39– 

16405. Docket No. FAA–2010–0521; 

Directorate Identifier 2009–NE–21–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective September 22, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Rolls-Royce plc (RR) 

model RB211–524C2–19 and RB211–524C2– 

B–19 turbofan engines. These engines are 

installed on, but not limited to, Boeing 747 

series airplanes. 

Reason 

(d) 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 with a 

cracked LPT casing may result in release of 

uncontained high-energy debris. 

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 highenergy debris could result in damage to the 

airplane. 

Actions and Compliance 

(e) Unless already done, do the following 

actions: 

Initial Inspection Requirements 

(1) Perform a fluorescent penetrant 

inspection (FPI) before the life of the LPT 

casing has reached 4,500 cycles-since-new 

(CSN) or within 4,500 cycles-since-last 

inspection (CSLI) or within 500 cycles after 

the effective date of this AD, whichever 

occurs later. You can find guidance on 

performing the FPI in RR Alert Service 

Bulletin (ASB) RB.211–72–AG076, dated 

November 13, 2008. 

Repetitive Inspection Requirements 

(2) Thereafter, perform an FPI at intervals 

not exceeding 4,500 CSLI. You can find 

guidance on performing the FPI in RollsRoyce plc ASB RB.211–72–AG076, dated 

November 13, 2008. 

Remove Parts With Cracks 

(3) Remove cracked LPT casings, found 

using paragraphs (e)(1) or (e)(2) of this AD, 

from service before further flight. 

Alternative Methods of Compliance 

(AMOCs) 

(f) 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 

(g) Refer to MCAI EASA AD 2009–0083, 

dated April 16, 2009, and Rolls-Royce plc 

ASB No. RB.211–72–AG076, dated November 

13, 2008, for related information. Contact 

Rolls-Royce plc, P.O. Box 31, Derby, DE24 

8BJ, United Kingdom; telephone 011 44 1332 

242424; fax 011 44 1332 249936, for a copy 

of this service information. 

(h) 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. 

Material Incorporated by Reference 

(i) None. 

Issued in Burlington, Massachusetts, on 

August 6, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–20353 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–2010–0433; Directorate 

Identifier 2009–NM–117–AD; Amendment 

39–16388; AD 2010–16–11] 

RIN 2120–AA64 

Airworthiness Directives; McDonnell 

Douglas Corporation Model MD–90–30 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Model MD–90–30 airplanes. This AD 

requires inspecting for corrosion of the 

retract cylinder support fitting for the 

main landing gear (MLG) and the mating 

bore for the support fitting in the MLG 

trunnion fitting, performing corrective 

actions if necessary, and replacing 

cadmium-plated retract cylinder 


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