Federal Register / Vol. 75, No. 186 / Monday, September 27, 2010 / Rules and Regulations 59065 

(1) If the crack is 0.30 inch or more: 

Replace the bracket before further flight. 

(2) If the crack is less than 0.30 inch: 

Continued flight for a maximum of 10 flight 

hours for repositioning of the airplane and 

replacement of the bracket is allowed, within 

the restricted flight envelope included in the 

attachment to Cessna Alert Service Letter 

ASL750–27–21, dated October 13, 2006, 

titled ‘‘Flight Restrictions.’’ 

Special Flight Permits 

(i) Special flight permits, as described in 

Section 39.23 of the Federal Aviation 

Regulations (14 CFR 39.23), are allowed with 

the limitations required by paragraph (h)(2) 

of this AD. 

No Reporting or Return of Parts to 

Manufacturer 

(j) Cessna Alert Service Letter ASL750–27– 

21, dated October 13, 2006, specifies 

submitting a sheet related to inspection 

results to the manufacturer; this AD does not 

include that requirement. The service letter 

also specifies sending the elevator assembly 

to the manufacturer for replacement of the 

inboard-hinge bracket if a crack is found that 

is 0.30 inch or more; however, this AD 

requires corrective actions be done using a 

method approved by us. 

New Requirements of This AD 

(k) Within 60 months after the effective 

date of this AD, do the applicable actions 

required by paragraphs (k)(1), (k)(2), (k)(3), 

and (k)(4) of this AD, in accordance with the 

Accomplishment Instructions of Cessna 

Service Bulletin SB750–27–62, Revision 3, 

dated August 21, 2009. Accomplishing the 

actions required by paragraph (k) of this AD 

terminates the requirements of paragraphs (g) 

through (j) of this AD. 

(1) For all airplanes except those having 

S/Ns 288 through 305 inclusive: Do an eddy 

current inspection for cracks of the bracket of 

the inboard horizontal stabilizer. Before 

further flight, replace any cracked bracket of 

the inboard horizontal stabilizer with a 

serviceable bracket. 

(2) For all airplanes except those having 

S/Ns 288 through 305 inclusive: Measure the 

lug thickness of the horizontal stabilizer 

hinges. If the lug thickness is not within the 

acceptable tolerance range, as identified in 

Cessna Service Bulletin SB750–27–62, 

Revision 3, dated August 21, 2009, before 

further flight, replace the bearing plate with 

a serviceable bearing plate. 

(3) For all airplanes except those having 

S/Ns 288 through 305 inclusive: Modify the 

left and right horizontal stabilizer; and add 

the modification part number of the 

horizontal stabilizer to the modification 

section of the MS27253–1 identification 

plate. 

(4) For all airplanes: Replace the existing 

elevator assemblies with new elevator 

assemblies having part numbers 6734000–17 

(for the left side) and 6734000–18 (for the 

right side). 

Credit for Actions Done Using the Previous 

Service Information 

(l) Actions accomplished before the 

effective date of this AD in accordance with 

the service bulletins identified in Table 1 of 

this AD are considered acceptable for 

compliance with the corresponding 

requirements of paragraphs (k)(1), (k)(2), and 

(k)(3) of this AD. 

TABLE 1—CREDIT FOR PREVIOUS SERVICE BULLETINS

Service Bulletin Revision 

level Date 

Cessna Service Bulletin SB750–27–62 ............................................................................................................... (1) October 13, 2008. 

Cessna Service Bulletin SB750–27–62 ............................................................................................................... 1 October 22, 2008. 

Cessna Service Bulletin SB750–27–62 ............................................................................................................... 2 December 17, 2008. 

1Original. 

Alternative Methods of Compliance 

(AMOCs) 

(m)(1) The Manager, Wichita ACO, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. Send information to ATTN: 

T.N. Baktha, Aerospace Engineer, Airframe 

Branch, ACE–118W, FAA, Wichita ACO, 

1801 Airport Road, Room 100, Mid-Continent 

Airport, Wichita, Kansas 67209; telephone 

(316) 946–4155; fax (316) 946–4107. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. 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. 

Material Incorporated by Reference 

(n) You must use Cessna Alert Service 

Letter ASL750–27–21, excluding the 

attachment titled ‘‘Inspection Results Form’’ 

and including the attachment titled ‘‘Flight 

Restrictions,’’ dated October 13, 2006; and 

Cessna Service Bulletin SB750–27–62, 

Revision 3, dated August 21, 2009, including 

Service Bulletin Supplemental Data, Revision 

D, dated September 18, 2009; as applicable; 

to do the actions required by this AD, unless 

the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Cessna Service Bulletin SB750–27–62, 

Revision 3, dated August 21, 2009, including 

Service Bulletin Supplemental Data, Revision 

D, dated September 18, 2009, under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of Cessna Alert Service Letter 

ASL750–27–21, excluding the attachment 

titled ‘‘Inspection Results Form’’ and 

including the attachment titled ‘‘Flight 

Restrictions,’’ dated October 13, 2006, on 

November 22, 2006 (71 FR 65047, November 

7, 2006). 

(3) For service information identified in 

this AD, contact Cessna Aircraft Co., P.O. Box 

7706, Wichita, Kansas 67277; telephone 316– 

517–6215; fax 316–517–5802; e-mail 

citationpubs@cessna.textron.com; Internet 

https://www.cessnasupport.com/ 

newlogin.html. 

(4) 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. 

(5) 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 

September 15, 2010. 

Robert D. Breneman, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–23834 Filed 9–24–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–28077; Directorate 

Identifier 2007–NE–20–AD; Amendment 

39–16445; AD 2009–09–03R1] 

RIN 2120–AA64 

Airworthiness Directives; Turbome ́ca 

S.A. Arriel 2B and 2B1 Turboshaft 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are revising an existing 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

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59066 Federal Register / Vol. 75, No. 186 / Monday, September 27, 2010 / Rules and Regulations 

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: 

Since issuance of AD 2007–0109, 

Turbome ́ca has released modification TU166 

which consists in inserting HP blade 

dampers between the HP disc and the HP 

blade platform. Introduction of these 

dampers has demonstrated to limit axial 

displacement of the HP blade relative to the 

disk in case of blade lock rupture or opening, 

therefore eliminating the need for inspection 

and replacement. 

We are issuing this AD to prevent an 

uncommanded in-flight engine 

shutdown which could result in an 

emergency autorotation landing or an 

accident. 

DATES: This AD becomes effective 

November 1, 2010. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD as of 

November 1, 2010. The Director of the 

Federal Register approved the 

incorporation by reference of 

Turbome ́ca S.A. Mandatory Service 

Bulletin No. 292 72 2825, dated April 5, 

2007, listed in this AD as of June 1, 2009 

(74 FR 18981, April 27, 2009). 

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: 

Richard Woldan, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803–5299; telephone (781) 238–7136; 

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 12, 2010 (75 FR 26681). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states that: 

Since issuance of AD 2007–0109, 

Turbome ́ca has released modification TU166 

which consists in inserting HP blade 

dampers between the HP disc and the HP 

blade platform. Introduction of these 

dampers has demonstrated to limit axial 

displacement of the HP blade relative to the 

disk in case of blade lock rupture or opening, 

therefore eliminating the need for inspection 

and replacement. 

Therefore, this AD revises AD 2007–0109 

by retaining the same requirements of AD 

2007–0109 except that applicability is 

limited to ARRIEL 2B, 2B1 and 2B1A engines 

which do not incorporate modification 

TU166. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we required different actions in this AD 

from those in the MCAI in order to 

follow FAA policies. Any such 

differences are described in a separate 

paragraph of the AD. These 

requirements take precedence over the 

actions copied from the MCAI. 

Costs of Compliance 

Based on the service information, we 

estimate that this AD would affect about 

248 products of U.S. registry. We also 

estimate that it would take about 2 

work-hours per product to comply with 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

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

operators to be $42,160. 

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, Incorporation by reference, 

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 

removing Amendment 39–15889 (74 FR 

18981), and adding a new airworthiness 

directive, Amendment 39–16445, to 

read as follows: 

2009–09–03R1 Turbome ́ca S.A.: 

Amendment 39–16445. Docket No. 

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Federal Register / Vol. 75, No. 186 / Monday, September 27, 2010 / Rules and Regulations 59067 

FAA–2007–28077; Directorate Identifier 

2007–NE–20–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective November 1, 2010. 

Affected ADs 

(b) This AD revises AD 2009–09–03, 

Amendment 39–15889. 

Applicability 

(c) This AD applies to Turbome ́ca S.A. 

ARRIEL 2B and 2B1 turboshaft engines that 

don’t incorporate modification TU166. These 

engines are installed on, but not limited to, 

Eurocopter AS 350 B3 and EC 130 B4 

helicopters. 

Reason 

(d) This AD results from: 

Since issuance of AD 2007–0109, 

Turbome ́ca has released modification TU166 

which consists in inserting HP blade 

dampers between the HP disc and the HP 

blade platform. Introduction of these 

dampers has demonstrated to limit axial 

displacement of the HP blade relative to the 

disk in case of blade lock rupture or opening, 

therefore eliminating the need for inspection 

and replacement. 

We are issuing this AD to prevent an 

uncommanded in-flight engine shutdown 

which could result in an emergency 

autorotation landing or an accident. 

Actions and Compliance 

(e) Unless already done, do the following 

actions: 

Initial Inspection 

(1) Perform an initial high-pressure (HP) 

turbine borescope inspection according to 

Turbome ́ca S.A. Mandatory Service Bulletin 

(MSB) No. 292 72 2825, Version B, dated 

September 21, 2009, or earlier version as 

follows: 

(i) For engines with fewer than 500 hours 

and 450 cycles since new or since the last HP 

turbine borescope inspection, inspect before 

reaching 600 hours or 500 cycles whichever 

occurs first. Replace HP turbine modules 

with rearward turbine blade displacement 

greater than 0.5 mm. 

(ii) For the remaining engines, inspect 

within the next 100 hours. Replace HP 

turbine modules with rearward turbine blade 

displacement greater than 0.5 mm. 

Repetitive Inspections 

(2) Perform repetitive HP turbine borescope 

inspections according to Turbome ́ca S.A. 

MSB No. 292 72 2825, Version B, dated 

September 21, 2009 or earlier version: 

(i) Within 600 hours or 500 cycles from the 

previous inspection, whichever occurs first, 

if the rearward displacement of the turbine 

blades was less than 0.2 mm. Replace HP 

turbine modules with rearward turbine blade 

displacement greater than 0.5 mm. 

(ii) Within 100 hours of the previous 

inspection if the rearward displacement of 

the turbine blades was between 0.2 mm and 

0.5 mm. Replace HP turbine modules with 

rearward turbine blade displacement greater 

than 0.5 mm. 

Optional Terminating Action 

(f) Incorporating modification TU166 

terminates the repetitive inspection 

requirements of paragraphs (e)(2)(i) and 

(e)(2)(ii) of this AD. 

FAA AD Differences 

(g) For clarification, we restructured the 

actions and compliance wording of this AD. 

(h) We deleted the Turbome ́ca reporting 

requirement from the AD. 

(i) Although EASA Airworthiness Directive 

2007–0109R1, dated November 9, 2009, 

applies to the ARRIEL 2B1A engine, this AD 

does not apply to that model because it has 

no U.S. type certificate. 

Alternative Methods of Compliance 

(AMOCs) 

(j) 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 

(k) Refer to EASA Airworthiness Directive 

2007–0109R1, dated November 9, 2009, and 

Turbome ́ca S.A. MSB No. 292 72 2825, 

Version B, dated September 21, 2009, or 

earlier version, for related information. 

(l) Contact Richard Woldan, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803–5299; telephone (781) 238–7136; fax 

(781) 238–7199, for more information about 

this AD. 

Material Incorporated by Reference 

(m) You must use Turbome ́ca S.A. 

Mandatory Service Bulletin No. 292 72 2825, 

Version B, dated September 21, 2009, to do 

the actions required by this AD, unless the 

AD specifies otherwise. 

(1) The Director of the Federal Register 

previously approved the incorporation by 

reference of Turbome ́ca S.A. Mandatory 

Service Bulletin No. 292 72 2825, dated April 

5, 2007, on June 1, 2009 (74 FR 18981, April 

27, 2009). 

(2) For service information identified in 

this AD, contact Turbome ́ca, 40220 Tarnos, 

France; telephone 33 05 59 74 40 00, fax 33 

05 59 74 45 15. 

(3) You may review copies at the FAA, 

New England Region, 12 New England 

Executive Park, Burlington, MA; 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/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

September 17, 2010. 

Robert J. Ganley, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–23833 Filed 9–24–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1100; Directorate 

Identifier 2009–NE–37–AD; Amendment 39– 

16441; AD 2010–20–07] 

RIN 2120–AA64 

Airworthiness Directives; International 

Aero Engines AG 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: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

International Aero Engines AG (IAE) 

V2500–A1, V2525–D5 and V2528–D5 

turbofan engines and certain serial 

numbers (S/Ns) of IAE V2522–A5, 

V2524–A5, V2527–A5, V2527E–A5, 

V2527M–A5, V2530–A5, and V2533–A5 

turbofan engines. For certain S/Ns of 

V2500–A1, V2522–A5, V2524–A5, 

V2527–A5, V2527E–A5, V2527M–A5, 

V2530–A5, and V2533–A5 series 

turbofan engines, this AD requires 

initial and repetitive on-wing ultrasonic 

inspections of the high-pressure 

compressor (HPC) stage 3 to 8 drum for 

cracks. As mandatory terminating action 

to the repetitive inspections, this AD 

requires removal from service of the 

fully silver plated nuts attaching the 

HPC stage 3 to 8 drum to the HPC stage 

9 to 12 drum, removal of silver residue 

from the HPC stage 3 to 8 drum, and 

fluorescent penetrant inspection (FPI) of 

the stage 3 to 8 drum within a specified 

time. For all other engines, this AD 

requires removal from service of the 

fully silver plated nuts attaching the 

HPC stage 3 to 8 drum to the HPC stage 

9 to 12 drum, removal of silver residue 

from the HPC stage 3 to 8 drum, and FPI 

of the HPC stage 3 to 8 drum at the next 

drum piece-part exposure. This AD 

results from reports of 39 HPC stage 3 

to 8 drums found cracked since March 

2009. We are issuing this AD to prevent 

uncontained failure of the HPC stage 3 

to 8 drum, which could result in 

damage to the airplane. 

DATES: This AD becomes effective 

November 1, 2010. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulations as 

of November 1, 2010. 

ADDRESSES: You can get the service 

information identified in this AD from 

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