59062 Federal Register / Vol. 75, No. 186 / Monday, September 27, 2010 / Rules and Regulations 

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 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 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 summary of the costs 

to comply with this AD and placed it in 

the AD Docket. 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. 

Adoption of the Amendment 

■ Under 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. The FAA amends § 39.13 by 

removing Amendment 39–15028 (72 FR 

19110, April 17, 2007), and by adding 

a new airworthiness directive, 

Amendment 39–16439, to read as 

follows: 

2010–20–05 Turbome ́ca S.A.: Amendment 

39–16439. Docket No. FAA–2005–21624; 

Directorate Identifier 2005–NE–17–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective October 12, 2010. 

Affected ADs 

(b) This AD supersedes AD 2005–13–25R1, 

Amendment 39–15028. 

Applicability 

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

ARRIEL 2B turboshaft engines that do not 

have Modification TU 149 incorporated. 

These engines are installed on, but not 

limited to, Eurocopter AS350B3 helicopters. 

Unsafe Condition 

(d) This AD results from reports of engines 

with modification TU 132 incorporated 

experiencing stuck acceleration control axles 

in the hydromechanical unit (HMU) metering 

valve body. We are issuing this AD to prevent 

loss of control of engine fuel flow in manual 

control mode or mixed control mode, which 

can lead to engine overspeed, and in-flight 

engine shutdown resulting in a forced 

autorotation landing or accident. 

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. 

HMUs Without Modification TU 149 

(f) Within 20 operating hours of the 

effective date of this AD, check the fuel 

metering system and perform maintenance 

procedures in accordance with Paragraph 2 

of Turbome ́ca MSB A292 73 2814, Version D, 

dated October 16, 2009. 

(g) Repeat the maintenance procedures of 

paragraph (f) of this AD within every 210 

operating hours. 

Optional Terminating Action 

(h) Modifying the HMU to Modification TU 

149 terminates the repetitive inspection 

requirements specified in paragraph (g) of 

this AD. You can find guidance on modifying 

the HMU to Modification TU 149 in 

Turbome ́ca Service Bulletin 292 73 2149, 

Version C, dated August 10, 2009. 

Previous Credit 

(i) Maintenance performed prior to the 

effective date of this AD using Turbome ́ca 

MSB A292 73 2814, Version C, dated 

December 19, 2006, or an earlier version of 

this MSB, satisfies the maintenance 

requirements of paragraph (f) 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) EASA airworthiness directive 2009– 

00246, dated November 10, 2009, also 

addresses the subject of this AD. 

(l) Contact Kevin Dickert, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: kevin.dickert@faa.gov; 

telephone (781) 238–7117, fax (781) 238– 

7199, for more information about this AD. 

Material Incorporated by Reference 

(m) You must use Turbome ́ca Mandatory 

Service Bulletin (MSB) A292 73 2814, 

Version D, dated October 16, 2009, to 

perform the actions required by this AD. The 

Director of the Federal Register approved the 

incorporation by reference of MSB A292 73 

2814, Version D, dated October 16, 2009, in 

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

part 51. Contact Turbome ́ca S.A., 40220 

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

fax 33 05 59 74 45 15, for a copy of this 

service information. You may review copies 

at the FAA, New England Region, Office of 

the Regional Counsel, 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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Burlington, Massachusetts, on 

September 15, 2010. 

Thomas A. Boudreau, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–23581 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–2010–0380; Directorate 

Identifier 2009–NM–009–AD; Amendment 

39–16444; AD 2010–20–10] 

RIN 2120–AA64 

Airworthiness Directives; The Cessna 

Aircraft Company Model 750 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to all Model 750 

airplanes. That AD currently requires 

inspecting the inboard-hinge brackets of 

the left and right elevators for cracking 

and doing related investigative and 

corrective actions if necessary. For 

certain airplanes, this new AD requires 

inspecting for cracks of the bracket of 

the inboard horizontal stabilizer and 

measuring the lug thickness of the 

horizontal stabilizer hinges; doing 

corrective actions if necessary; and 

modifying the left and right elevators 

and left and right horizontal stabilizer. 

For all airplanes, this new AD requires 

replacing the existing elevator 

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Federal Register / Vol. 75, No. 186 / Monday, September 27, 2010 / Rules and Regulations 59063 

assemblies with new elevator 

assemblies, which terminates the 

requirements of the existing AD. This 

new AD also revises the applicability to 

remove certain airplanes. This AD 

results from a report of cracking found 

on the elevator inboard-hinge brackets 

and the horizontal stabilizer hinges. We 

are issuing this AD to prevent such 

cracking of the elevator inboard-hinge 

brackets and the horizontal stabilizer 

hinges, which could result in structural 

failure of the elevators and consequent 

loss of control of the airplane. 

DATES: This AD becomes effective 

November 1, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of November 1, 2010. 

On November 22, 2006 (71 FR 65047, 

November 7, 2006), the Director of the 

Federal Register approved the 

incorporation by reference of a certain 

other publication listed in the AD. 

ADDRESSES: 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility 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 address for the 

Docket Office (telephone 800–647–5527) 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: T.N. 

Baktha, Aerospace Engineer, Airframe 

Branch, ACE–118W, FAA, Wichita 

Aircraft Certification Office, 1801 

Airport Road, Room 100, Mid-Continent 

Airport, Wichita, Kansas 67209; 

telephone (316) 946–4155; fax (316) 

946–4107. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2006–23–05, amendment 

39–14817 (71 FR 65047, November 7, 

2006). The existing AD applies to all 

Model 750 airplanes. That NPRM was 

published in the Federal Register on 

April 8, 2010 (75 FR 17879). That NPRM 

proposed to continue to require 

inspecting the inboard-hinge brackets of 

the left and right elevators for cracking 

and doing related investigative and 

corrective actions if necessary. For 

certain airplanes that NPRM proposed 

to require an inspection for cracks and 

corrosion of the bracket of the inboard 

horizontal stabilizer and measuring the 

lug thickness of the horizontal stabilizer 

hinges; doing corrective actions if 

necessary; and modifying the left and 

right elevators and left and right 

horizontal stabilizer. For all airplanes, 

that NPRM proposed to require 

replacing the existing elevator 

assemblies with new elevator 

assemblies, which would terminate the 

requirements of the existing AD. That 

NPRM also proposed to revise the 

applicability to remove certain 

airplanes. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments that have 

been received on the NPRM. 

Request To Remove References to 

Corrosion 

Cessna Aircraft Company requests 

that in the ‘‘Differences Between the 

Proposed AD and Service Bulletin’’ 

section of the NPRM the sentence, ‘‘This 

proposed AD would also require an 

inspection for corrosion and 

replacement of any corroded brackets,’’ 

be removed. Cessna states that corrosion 

of the brackets has not been an issue, 

and current maintenance practices are 

sufficient. Cessna states that the 

requirement to inspect the horizontal 

hinge brackets for corrosion will 

complicate compliance for operators 

that have already complied with 

previous revisions of Cessna Service 

Bulletin SB750–27–62. Cessna states 

that the addition of an inspection for 

corrosion of the horizontal inboard 

hinge in paragraph (k)(1) of the NPRM 

is not specified in Cessna Service 

Bulletin SB750–27–62, Revision 3, 

dated August 21, 2009. 

We agree with Cessna’s request. Since 

the NPRM was issued, we have received 

sufficient technical information to 

support the request. We have changed 

the AD to remove references to 

corrosion. 

Request To Clarify Table 1 of the NPRM 

Cessna states that it is unclear which 

requirements of paragraph (k) of the 

NPRM are covered by previous revisions 

of Cessna Service Bulletin SB750–27– 

62. Cessna requests that we amend 

Table 1 of the NPRM to reference 

paragraphs (k)(1), (k)(2), and (k)(3) of the 

NPRM. 

We partially agree with Cessna’s 

request. In lieu of revising Table 1 of 

this AD, we have changed paragraph (l) 

of this AD to show that 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.’’ 

Request To Clarify the Effect of 

Previous Compliance 

JATEC requests that we explain how 

the NPRM affects airplanes that have 

already complied with Cessna Service 

Bulletin SB750–27–62, Revision 3, 

dated August 21, 2009. JATEC asks if 

anything further is required once 

Revision 3 has been incorporated. 

As specified in paragraph (f) of this 

AD, you are responsible for having the 

actions required by this AD performed 

within the compliance time specified, 

unless the actions have already been 

done. In addition, as specified in 

paragraph (k) of this AD, once the 

actions required by that paragraph are 

accomplished, the requirements of 

paragraphs (g) through (j) of this AD are 

terminated; no further action is 

required. No changes to this AD are 

necessary in this regard. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

that have been received, and determined 

that air safety and the public interest 

require adopting the AD with the 

changes described previously. We have 

determined that these changes will 

neither increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD. 

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59064 Federal Register / Vol. 75, No. 186 / Monday, September 27, 2010 / Rules and Regulations 

ESTIMATED COSTS

Action Work 

hours 

Average 

labor rate 

per hour 

Parts Cost per 

airplane 

Number 

of U.S.- 

registered 

airplanes 

Fleet cost 

Inspection (required by AD 

2006–23–05).

2 ............... $85 $0 ........................................... $170 ................. 253 $43,010. 

Modification and Replacement 

(new actions).

Up to 200 85 The manufacturer states that 

it will supply parts to the 

operators at no cost.

Up to $17,000 .. 253 Up to $4,301,000. 

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 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 this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

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. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

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 Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–14817 (71 

FR 65047, November 7, 2006) and by 

adding the following new airworthiness 

directive (AD): 

2010–20–10 The Cessna Aircraft Company: 

Amendment 39–16444. Docket No. 

FAA–2010–0380; Directorate Identifier 

2009–NM–009–AD. 

Effective Date 

(a) This AD becomes effective November 1, 

2010. 

Affected ADs 

(b) This AD supersedes AD 2006–23–05, 

Amendment 39–14817. 

Applicability 

(c) This AD applies to The Cessna Aircraft 

Company Model 750 airplanes, certificated in 

any category, as identified in Cessna Service 

Bulletin SB750–27–62, Revision 3, dated 

August 21, 2009. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 27: Flight Controls. 

Unsafe Condition 

(e) This AD results from a report of 

cracking found on the elevator inboard-hinge 

brackets and the horizontal stabilizer hinges. 

The Federal Aviation Administration is 

issuing this AD to prevent cracking of the 

elevator inboard-hinge brackets and the 

horizontal stabilizer hinges, which could 

result in structural failure of the elevators 

and consequent loss of control of the 

airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Restatement of Requirements of AD 2006– 

23–05, With No Changes 

Inspection 

(g) After the airplane accumulates 2,500 

total flight hours: Perform a general visual 

inspection for cracking of the inboard-hinge 

brackets of the left and right elevators in 

accordance with the Accomplishment 

Instructions of Cessna Alert Service Letter 

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

the inspection before the airplane 

accumulates 3,000 total flight hours, or 

within 10 flight hours after November 22, 

2006 (the effective date of AD 2006–23–05), 

whichever is later. 

Note 1: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to enhance visual access to 

all exposed surfaces in the inspection area. 

This level of inspection is made under 

normally available lighting conditions such 

as daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’ 

Related Investigative and Corrective Actions 

(h) If any crack is found during the 

inspection required by paragraph (g) of this 

AD: Before further flight, perform an eddy 

current inspection of the inboard-hinge 

brackets to determine the crack length, in 

accordance with the Accomplishment 

Instructions of Cessna Alert Service Letter 

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

do the actions specified in paragraph (h)(1) 

or (h)(2) of this AD, as applicable, at the time 

specified. All corrective actions must be done 

using a method approved by the Manager, 

Wichita Aircraft Certification Office (ACO), 

FAA. For a replacement method to be 

approved by the Manager, Wichita ACO, as 

required by this paragraph, the Manager’s 

approval letter must specifically refer to this 

AD. 

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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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