34354 Federal Register / Vol. 75, No. 116 / Thursday, June 17, 2010 / Rules and Regulations 

TABLE 6—MATERIAL INCORPORATED BY REFERENCE

AFM/POM name AFM effective pages list 

MU–2B–25 Airplane Flight Manual K Model, Document Number MR– 

0156–1, MU–2B–25; MU–2B–25 Pilot’s Operating Manual, Document 

Number MR–0157–1, revised July 15, 2004.

all revised pages up to and including revision 11, dated March 10, 

2009, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in the 

AFM. 

MU–2B–26 Airplane Flight Manual M Model, Document Number MR– 

0160–1; MU–2B–26 Pilot’s Operating Manual, Document Number 

MR–0161–1, revised July 15, 2004.

all revised pages up to and including revision 11, dated March 10, 

2009, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in the 

AFM. 

MU–2B–26A Airplane Flight Manual P Model, Document Number MR– 

0194–1; MU–2B–26A Pilot’s Operating Manual, Document Number 

MR–0195–1, revised July 15, 2004.

all revised pages up to and including revision 13, dated March 10, 

2009, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in the 

AFM. 

MU–2B–36A Airplane Flight Manual N Model, Document Number MR– 

0196–1; MU–2B–36A Pilot’s Operating Manual, Document Number 

MR–0197–1, revised July 15, 2004.

all revised pages up to and including revision 15, dated March 10, 

2009, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in the 

AFM. 

MU–2B–40 Airplane Flight Manual SOLITAIRE Model, Document Number MR–0271–1; MU–2B–40 Pilot’s Operating Manual, Document 

Number MR–0335–1, revised July 15, 2004.

all revised pages up to and including revision 13, dated March 10, 

2009, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in the 

AFM. 

MU–2B–60 Airplane Flight Manual MARQUISE Model, Document Number MR–0273–1; MU–2B–60 Pilot’s Operating Manual, Document 

Number MR–0338–1, revised July 15, 2004.

all revised pages up to and including revision 15, dated March 10, 

2009, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in the 

AFM. 

MU–2B Airplane Flight Manual, YET 67026A; MU–2B Pilot’s Operating 

Manual, Document Number YET 67025A, revised September 10, 

1997.

all revised pages up to and including revision 13, dated November 29, 

2007, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in the 

AFM. 

MU–2B–10 Airplane Flight Manual, YET 86400; MU–2B–10 Pilot’s Operating Manual, Document Number YET 87236, revised September 

10, 1997.

all revised pages up to and including revision 13, dated November 29, 

2007, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in the 

AFM. 

MU–2B–15 Airplane Flight Manual, YET 68038A; MU–2B–15 Pilot’s 

Operating Manual, Document Number YET 87237, revised September 10, 1997.

all revised pages up to and including revision 13, dated November 29, 

2007, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in the 

AFM. 

MU–2B–20 Airplane Flight Manual, YET 68034A; MU–2B–20 Pilot’s 

Operating Manual, Document Number YET 68134A, revised February 20, 1998.

all revised pages up to and including revision 13, dated November 29, 

2007, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in the 

AFM. 

MU–2B–25 Airplane Flight Manual, YET 71367A; MU–2B–25 Pilot’s 

Operating Manual, Document Number YET 72067A, revised September 10, 1997.

all revised pages up to and including revision 13, dated November 29, 

2007, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in the 

AFM. 

MU–2B–26 Airplane Flight Manual, YET 74129A; MU–2B–26 Pilot’s 

Operating Manual, Document Number YET 74130A, revised September 10, 1997.

all revised pages up to and including revision 13, dated November 29, 

2007, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in the 

AFM. 

MU–2B–30 Airplane Flight Manual, YET 69013A; MU–2B–30 Pilot’s 

Operating Manual, Document Number YET 69224A, revised September 10, 1997.

all revised pages up to and including revision 14, dated November 29, 

2007, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in the 

AFM. 

MU–2B–35 Airplane Flight Manual, YET 70186A; MU–2B–10 Pilot’s 

Operating Manual, Document Number YET 70187A, revised September 10, 1997.

all revised pages up to and including revision 14, dated November 29, 

2007, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in the 

AFM. 

MU–2B–36 Airplane Flight Manual, YET 74122A; MU–2B–36 Pilot’s 

Operating Manual, Document Number YET 74123A, revised September 10, 1997.

all revised pages up to and including revision 13, dated November 29, 

2007, as listed on page 1 and page 2 of the ‘‘Effective Pages’’ in the 

AFM. 

Issued in Kansas City, Missouri on May 4, 

2010. 

Wes Ryan, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–11034 Filed 6–16–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0327; Directorate 

Identifier 2010–CE–012–AD; Amendment 

39–16321; AD 2010–12–01] 

RIN 2120–AA64 

Airworthiness Directives; Cessna 

Aircraft Company Model 525A 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) to 

supersede AD 2009–24–13, which 

applies to certain Cessna Aircraft 

Company (Cessna) Model 525A 

airplanes. AD 2009–24–13 currently 

requires you to repetitively inspect the 

thrust attenuator paddle assemblies for 

loose and damaged fasteners and for 

cracks. AD 2009–24–13 also requires 

you to replace loose or damaged 

fasteners and replace cracked thrust 

attenuator paddles found during any 

inspection. Since we issued AD 2009– 

24–13, Cessna has developed new 

design thrust attenuator paddles and 

universal head rivets as terminating 

action for the repetitive inspections. 

Consequently, this AD would retain the 

requirements of AD 2009–24–13 until 

replacement of both thrust attenuator 

paddles and the eight countersunk 

fasteners with new design thrust 

attenuator paddles and universal head 


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Federal Register / Vol. 75, No. 116 / Thursday, June 17, 2010 / Rules and Regulations 34355 

rivets. We are issuing this AD to detect 

and correct loose and damaged fasteners 

and cracks in the thrust attenuator 

paddles, which could result in in-flight 

departure of the thrust attenuator 

paddles. This failure could lead to 

rudder and elevator damage and result 

in loss of control. 

DATES: This AD becomes effective on 

July 22, 2010. 

On July 22, 2010, the Director of the 

Federal Register approved the 

incorporation by reference of Cessna 

Citation Service Bulletin SB525A–78– 

02, Revision 1, dated February 5, 2010, 

listed in this AD. 

As of December 15, 2009 (74 FR 

62479, November 30, 2009), the Director 

of the Federal Register approved the 

incorporation by reference of Cessna 

Citation Alert Service Letter ASL525A– 

78–01, Revision 1, dated October 27, 

2009, listed in this AD. 

ADDRESSES: For service information 

identified in this AD, contact Cessna 

Aircraft Company, Product Support, 

P.O. Box 7706, Wichita, KS 67277; 

telephone: (316) 517–6000; fax: (316) 

517–8500; Internet: http:// 

www.cessna.com. 

To view the AD docket, go to U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590, or on the Internet at http:// 

www.regulations.gov. The docket 

number is FAA–2010–0327; Directorate 

Identifier 2010–CE–012–AD. 

FOR FURTHER INFORMATION CONTACT: T.N. 

Baktha, Aerospace Engineer, Wichita 

Aircraft Certification Office (ACO), 1801 

Airport Road, Room 100, Wichita, 

Kansas 67209; telephone: (316) 946– 

4155; fax: (316) 946–4107. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On March 23, 2010, we issued a 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) to 

include an AD that would apply to 

certain Cessna Model 525A airplanes. 

This proposal was published in the 

Federal Register as a notice of proposed 

rulemaking (NPRM) on March 30, 2010 

(75 FR 15629). The NPRM proposed to 

supersede AD 2009–24–13 with a new 

AD that would retain the requirements 

of AD 2009–24–13 until replacement of 

both thrust attenuator paddles and the 

eight countersunk fasteners with new 

design thrust attenuator paddles and 

universal head rivets. 

Comments 

We provided the public the 

opportunity to participate in developing 

this AD. We received no comments on 

the proposal or on the determination of 

the cost to the public. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD as proposed except for 

minor editorial corrections. We have 

determined that these minor 

corrections: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Costs of Compliance 

We estimate that this AD affects 136 

airplanes in the U.S. registry. 

We estimate the following costs to do 

the inspection (retained from AD 2009– 

24–13): 

Labor cost Parts cost Total cost per 

airplane 

Total cost on 

U.S. operators 

1 work-hour × $85 per hour = $85 ............................................................ Not Applicable ................................. $85 $11,560 

We estimate the following costs to do 

any necessary installation (retained 

from AD 2009–24–13) of missing/ 

damaged fasteners that will be required 

based on the results of the inspection. 

We have no way of determining the 

number of airplanes that may need this 

replacement: 

Labor cost Parts cost for 

two fasteners 

Total cost per 

airplane 

2 work-hours × $85 per hour = $170 .............................................................................................................. $99.90 $269.90 

We estimate the following costs to do 

any necessary replacement (retained 

from AD 2009–24–13) of a cracked 

thrust attenuator paddle that will be 

required based on the results of the 

inspection. We have no way of 

determining the number of airplanes 

that may need this replacement: 

Labor cost Parts cost 

(per paddle) 

Total cost per 

airplane 

3 work-hours × $85 per hour = $255 .............................................................................................................. $1,200 $1,455 

We estimate the following costs to do 

the replacement of both thrust 

attenuator paddles and the eight 

countersunk fasteners with new design 

thrust attenuator paddles and universal 

head rivets: 

Labor cost Parts cost Total cost per 

airplane 

Total cost on 

U.S. operators 

5 work-hours × $85 per hour = $425 .......................................................................................... $3,464 $3,889 $528,904 


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34356 Federal Register / Vol. 75, No. 116 / Thursday, June 17, 2010 / Rules and Regulations 

As determined by the manufacturer, 

eligible airplanes may qualify for 

warranty coverage of parts and labor. 

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 AD. 

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 other 

information as included in the 

Regulatory Evaluation) and placed it in 

the AD Docket. You may get a copy of 

this summary by sending a request to us 

at the address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2010–0327; 

Directorate Identifier 2010–CE–012–AD’’ 

in your request. 

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 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 Airworthiness Directive (AD) 

2009–24–13, Amendment 39–16105 (74 

FR 62479, November 30, 2009), and 

adding the following new AD: 

2010–12–01 Cessna Aircraft Company: 

Amendment 39–16321; Docket No. 

FAA–2010–0327; Directorate Identifier 

2010–CE–012–AD. 

Effective Date 

(a) This AD becomes effective on July 22, 

2010. 

Affected ADs 

(b) This AD supersedes AD 2009–24–13, 

Amendment 39–16105. 

Applicability 

(c) This AD applies to Model 525A 

airplanes, serial numbers 0001 through 0244, 

that are certificated in any category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 72: Engine. 

Unsafe Condition 

(e) This AD results from reports of fatigue 

cracks found in thrust attenuator paddles on 

Cessna Model 525A airplanes. We are issuing 

this AD to detect and correct loose and 

damaged fasteners and cracks in the thrust 

attenuator paddles, which could result in inflight departure of the thrust attenuator 

paddles. This failure could lead to rudder 

and elevator damage and result in loss of 

control. 

Compliance 

(f) To address this problem, you must do 

the following, unless already done: 

Actions Compliance Procedures 

(1) Visually inspect the left and right thrust attenuator paddle assemblies to determine if 

there are any missing, loose, or damaged 

fasteners and to determine if there are any 

cracks in the paddle.

Within the next 60 days after December 15, 

2009 (the effective date retained from AD 

2009–24–13) or within the next 30 hours 

time-in-service (TIS) after December 15, 

2009 (the effective date retained from AD 

2009–24–13), whichever occurs first. Repetitively thereafter inspect at intervals not 

to exceed 150 hours TIS.

Follow Cessna Citation Alert Service Letter 

ASL525A–78–01, Revision 1, dated October 27, 2009. 

(2) If you do not find any cracks in the thrust attenuator paddles during any inspection required in paragraph (f)(1) of this AD, install 

any missing fasteners, and replace any loose 

or damaged fasteners.

Before further flight after the inspection required in paragraph (f)(1) of this AD. Continue with the repetitive inspections specified in paragraph (f)(1) of this AD.Follow Cessna Citation Alert Service Letter 

ASL525A–78–01, Revision 1, dated October 27, 2009. 

(3) If cracks are found during any inspection required in paragraph (f)(1) of this AD, do a 

surface eddy current inspection of the thrust 

attenuator paddles and the fastener hole(s) 

to determine the length of the cracks(s).

Before further flight after the inspection required in paragraph (f)(1) of this AD in 

which cracks are found.

Follow Cessna Citation Alert Service Letter 

ASL525A–78–01, Revision 1, dated October 27, 2009. 


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Actions Compliance Procedures 

(4) If the cracks identified in paragraph (f)(3) of 

this AD meet or exceed the limits specified in 

paragraph 3 of Cessna Citation Alert Service 

Letter ASL525A–78–01, Revision 1, dated 

October 27, 2009, replace the thrust attenuator paddle and attachment hardware, as applicable.

(i) If the conditions of paragraph 3.A.(1) of 

Cessna Citation Alert Service Letter 

ASL525A–78–01, Revision 1, dated October 27, 2009, are met, replace before further flight after the inspection required in 

paragraph (f)(3) of this AD. After the replacement, continue with the repetitive inspections specified in paragraph (f)(1) of 

this AD.

(ii) If the conditions of paragraph 3.A.(2) of 

Cessna Citation Alert Service Letter 

ASL525A–78–01, Revision 1, dated October 27, 2009, are met, replace within the 

next 150 hours TIS after the inspection required in paragraph (f)(3) of this AD. After 

the replacement, continue with the repetitive inspections specified in paragraph 

(f)(1) of this AD.

Follow Cessna Citation Alert Service Letter 

ASL525A–78–01, Revision 1, dated October 27, 2009. 

(5) Replace both thrust attenuator paddles ....... Within the next 300 hours TIS after July 22, 

2010 (the effective date of this AD), or within 1 year after July 22, 2010 (the effective 

date of this AD), whichever occurs first.

Follow Cessna Citation Service Bulletin 

SB525A–78–02, Revision 1, dated February 

5, 2010. 

(g) The replacement required in paragraph 

(f)(5) of this AD terminates the repetitive 

inspection requirement of this AD. This 

replacement may be done at anytime, but 

must be done no later than 300 hours TIS 

after July 22, 2010 (the effective date of this 

AD), or within 1 year after July 22, 2010 (the 

effective date of this AD), whichever occurs 

first. 

(h) If, before July 22, 2010 (the effective 

date of this AD), you have done all the 

actions in the original issue of Cessna 

Citation Service Bulletin SB525A–78–02, 

dated November 13, 2009, then no further 

action is required by this AD. This is 

considered ‘‘unless already done’’ credit for 

this AD action. 

Alternative Methods of Compliance 

(AMOCs) 

(i) The Manager, Wichita Aircraft 

Certification Office (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, Wichita ACO, 

1801 Airport Road, Room 100, Wichita, 

Kansas 67209; telephone: (316) 946–4155; 

fax: (316) 946–4107. Before using any 

approved AMOC on any airplane to which 

the AMOC applies, notify your appropriate 

principal inspector (PI) in the FAA Flight 

Standards District Office (FSDO), or lacking 

a PI, your local FSDO. 

(j) AMOCs approved for AD 2009–24–13 

are approved for this AD. 

Material Incorporated by Reference 

(l) You must use Cessna Citation Alert 

Service Letter ASL525A–78–01, Revision 1, 

dated October 27, 2009, and Cessna Citation 

Service Bulletin SB525A–78–02, Revision 1, 

dated February 5, 2010, 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 Citation Service Bulletin SB525A–78– 

02, Revision 1, dated February 5, 2010, under 

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

(2) On December 15, 2009 (74 FR 62479, 

November 30, 2009), the Director of the 

Federal Register approved the incorporation 

by reference of Cessna Citation Alert Service 

Letter ASL525A–78–01, Revision 1, dated 

October 27, 2009. 

(3) For service information identified in 

this AD, contact Cessna Aircraft Company, 

Product Support, P.O. Box 7706, Wichita, KS 

67277; telephone: (316) 517–6000; fax: (316) 

517–8500; Internet: http://www.cessna.com. 

(4) You may review copies of the service 

information incorporated by reference for 

this AD at the FAA, Central Region, Office of 

the Regional Counsel, 901 Locust, Kansas 

City, Missouri 64106. For information on the 

availability of this material at the Central 

Region, call (816) 329–3768. 

(5) You may also review copies of the 

service information incorporated by reference 

for this AD 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 Kansas City, Missouri, on May 

26, 2010. 

Steven W. Thompson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–13139 Filed 6–16–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0170; Directorate 

Identifier 2009–NM–127–AD; Amendment 

39–16328; AD 2010–12–07] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) Model EMB–135ER, 

–135KE, –135KL, and –135LR 

Airplanes; and EMBRAER Model 

EMB–145, –145ER, –145MR, –145LR, 

–145XR, –145MP, and –145EP 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (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) 

originated 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: 

Reassessment of the damage tolerance 

analysis resulted in threshold reduction for 

some Structure Significant Items (SSI) of the 

Maintenance Review Board Report (MRBR) 

Airworthiness Limitations Items (ALI). 

Failure to inspect these structural 

components, according to the new threshold, 

could prevent a timely detection of fatigue 

cracking. These cracks, if not properly 


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