9796 Federal Register / Vol. 78, No. 29 / Tuesday, February 12, 2013 / Rules and Regulations 

TABLE 1 TO PARAGRAPH (A)—Continued 

Helicopter models Fitting P/Ns Fitting S/Ns 

204B, 205A and 205A–1 ......................... 204–012–102–005 .................................. All. 

204B, 205A and 205A–1 ......................... 204–012–102–009 .................................. All, except S/Ns 7500 or larger with a prefix of ‘‘A’’. 

212 .......................................................... 212–010–103–005 .................................. All. 

212 .......................................................... 212–010–103–007 .................................. All, except S/Ns 140 or larger with a prefix of ‘‘SH’’ and except S/Ns 11021 or larger with a prefix of ‘‘A’’. 

205A–1, 205B and 210 ........................... 212–010–103–101 .................................. All, except S/Ns 486 or larger with a prefix of ‘‘SH,’’ and 

except S/Ns 10997 or larger with a prefix of ‘‘A’’. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in the fitting and the determination that 

additional part-numbered fittings may not 

have been manufactured in accordance with 

approved manufacturing processes and 

controls. This condition could result in 

failure of a fitting, loss of a main rotor blade, 

and loss of helicopter control. 

(c) Affected ADs 

This AD supersedes AD 2011–08–01, 

Docket No. FAA–2011–0323, Amendment 

39–16651 (76 FR 18865, April 6, 2011), 

Directorate Identifier 2011–SW–005–AD. 

(d) Effective Date 

This AD becomes effective February 27, 

2013. 

(e) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(f) Required Actions 

(1) Within 25 hours time-in-service or 15 

days, whichever occurs first, perform a 

magnetic particle inspection (MPI) of each 

fitting for a crack. If an MPI was already 

performed on a fitting resulting in reidentifying the fitting with ‘‘FM’’ at the end 

of the P/N or at the end of the P/N on the 

fitting’s component history card or 

equivalent record, then the requirements of 

this AD have been met. 

(2) If a fitting is cracked, before further 

flight, replace it with an airworthy fitting. 

(3) If a fitting is not cracked, before further 

flight, re-identify the fitting by adding ‘‘FM’’ 

at the end of the P/N using a vibrating stylus. 

The depth of the ‘‘FM’’ must not exceed 

0.005 inches or extend within 0.10 inch of 

the part’s edge. Also, add ‘‘FM’’ at the end 

of the P/N on the fitting’s component history 

card or equivalent record. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Rotorcraft Certification 

Office, FAA, may approve AMOCs for this 

AD. Send your proposal to: Michael Kohner, 

Aerospace Engineer, FAA, Rotorcraft 

Directorate, Rotorcraft Certification Office, 

2601 Meacham Blvd., Fort Worth, Texas, 

76137, phone: (817) 222–5170; fax: (817) 

222–5783; email: mike.kohner@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(h) Additional Information 

Bell Alert Service Bulletin (ASB) No. 212– 

10–141, Revision A, dated November 18, 

2010; and ASBs No. 204–11–66, No. 205–11– 

107, No. 205B–11–58, No. 210–11–08; and 

No. 212–10–142 Revision B, all dated May 

31, 2011, which are not incorporated by 

reference, contain additional information 

about the subject of this AD. For this service 

information, contact Bell Helicopter Textron, 

Inc., P.O. Box 482, Fort Worth, TX 76101, 

telephone (817) 280–3391, fax (817) 280– 

6466, or at http://www.bellcustomer.com/ 

files/. You may review this service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6220, Main Rotor Head. 

Issued in Fort Worth, Texas, on January 28, 

2013. 

Lance T. Gant, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–02899 Filed 2–11–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1273; Directorate 

Identifier 2012–CE–045–AD; Amendment 

39–17350; AD 2013–03–15] 

RIN 2120–AA64 

Airworthiness Directives; Cessna 

Aircraft Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Cessna Aircraft Company Models 172R 

and 172S airplanes. This AD was 

prompted by reports of chafing of a new 

configuration of the fuel return line 

assembly, which was caused by the fuel 

return line assembly rubbing against the 

right steering tube assembly during 

rudder pedal actuation. This AD 

requires you to install the forward and 

aft fuel return line support clamps and 

brackets; inspect for a minimum 

clearance between the fuel return line 

assembly and the steering tube assembly 

and clearance between the fuel return 

line assembly and the airplane 

structure; and, if any damage is found, 

replace the fuel return line assembly. 

We are issuing this AD to correct the 

unsafe condition on these products. 

DATES: This AD is effective March 19, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of March 19, 2013. 

ADDRESSES: For service information 

identified in this AD, contact Cessna 

Aircraft Company, Customer service, 

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

telephone: (316) 517–5800; fax: (316) 

517–7271; email: 

customercare@cessna.textron.com; 

Internet: http:// 

www.cessnasupport.com. You may 

review copies of the referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

MO 64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. 

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 (phone: 800–647–5527) is 

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: Jeff 

Janusz, Aerospace Engineer, Wichita 


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Federal Register / Vol. 78, No. 29 / Tuesday, February 12, 2013 / Rules and Regulations 9797 

Aircraft Certification Office, FAA, 1801 

S. Airport Road, Room 100, Wichita, 

Kansas 67209; phone: (316) 946–4148; 

fax: (316) 946–4107; email: 

jeff.janusz@faa.gov. 

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 published in the Federal 

Register on December 5, 2012 (77 FR 

72250). That NPRM proposed to require 

you to install the forward and aft fuel 

return line support clamps and brackets; 

inspect for a minimum clearance 

between the fuel return line assembly 

and the steering tube assembly and 

clearance between the fuel return line 

assembly and the airplane structure; 

and, if any damage is found, replace the 

fuel return line assembly. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (77 

FR 72250, December 5, 2012) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

72250, December 5, 2012) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 72250, 

December 5, 2012). 

Costs of Compliance 

We estimate that this AD affects 80 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Installation of brackets and clamps and inspection of 

the fuel return line assembly for chafing and clearance.

2 work-hours × $85 per hour = $170 $78 $248 $19,840 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

proposed inspection. We have no way of 

determining the number of aircraft that 

might need this replacement: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement of the fuel return line assembly and adjustment of 

the clearance between the fuel return line assembly and the 

steering tube assembly and the airplane structure.

2 work-hours × $85 per hour = $170 .......... $53 $223 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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 

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), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) 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. 

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 adding 

the following new airworthiness 

directive (AD): 

2013–03–15 Cessna Aircraft Company: 

Amendment 39–17350; Docket No. 


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9798 Federal Register / Vol. 78, No. 29 / Tuesday, February 12, 2013 / Rules and Regulations 

FAA–2012–1273; Directorate Identifier 

2012–CE–045–AD. 

(a) Effective Date 

This AD is effective March 19, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the following Cessna 

Aircraft Company (Cessna) airplanes, 

certificated in any category: 

(1) Model 172R, serial numbers (S/N) 

17281573 through 17281616; and 

(2) Model 172S, S/N l72S11074 through 

172S11193. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 2820, Aircraft Fuel Distribution System. 

(e) Unsafe Condition 

This AD was prompted by reports of 

chafing of a new configuration of the fuel 

return line assembly, which was caused by 

the fuel return line assembly rubbing against 

the right steering tube assembly during 

rudder pedal actuation. We are issuing this 

AD to correct the unsafe condition on these 

products. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspect the Fuel Return Line Assembly 

At whichever of the following compliance 

times that occurs later, inspect the fuel return 

line assembly (Cessna part number (P/N) 

0516031–1) for damage following the 

Accomplishment Instructions section of 

Cessna Aircraft Company Service Bulletin 

SEB–28–01, dated September 21, 2012. 

(1) At the next annual inspection after 

March 19, 2013 (the effective date of this 

AD); 

(2) Within the next 100 hours time-inservice (TIS) after March 19, 2013 (the 

effective date of this AD); or 

(3) Within the next 12 calendar months 

after March 19, 2013 (the effective date of 

this AD). 

(h) Replace the Fuel Return Line Assembly 

If you find evidence of damage of the fuel 

return line assembly (Cessna P/N 0516031– 

1) as a result of the inspection required by 

paragraph (g) of this AD, before further flight, 

replace the fuel return line assembly (Cessna 

P/N 0516031–1) following the 

Accomplishment Instructions section of 

Cessna Aircraft Company Service Bulletin 

SEB–28–01, dated September 21, 2012. 

(i) Install the Fuel Return Line Assembly 

If you find no evidence of damage of the 

fuel return line assembly (Cessna P/N 

0516031–1) as a result of the inspection 

required by paragraph (g) of this AD, before 

further flight, reinstall the fuel return line 

assembly (Cessna P/N 0516031–1) following 

the Accomplishment Instructions section of 

Cessna Aircraft Company Service Bulletin 

SEB–28–01, dated September 21, 2012. 

(j) Install Forward and Aft Fuel Return Line 

Support Clamps and Brackets 

After installing the fuel return line 

assembly as required by replacement in 

paragraph (h) of this AD or installation in 

paragraph (i) of this AD, before further flight, 

install the forward and aft fuel return line 

support clamps and brackets following the 

Accomplishment Instructions section of 

Cessna Aircraft Company Service Bulletin 

SEB–28–01, dated September 21, 2012. 

(k) Inspect for a Minimum Clearance 

Between Certain Parts 

After the installation required by paragraph 

(j) of this AD, before further flight, inspect for 

a minimum clearance between the following 

parts throughout the range of copilot pedal 

travel. The requirements of this AD take 

precedence over the actions required in the 

Accomplishment Instructions section of 

Cessna Aircraft Company Service Bulletin 

SEB–28–01, dated September 21, 2012: 

(1) A minimum clearance of 0.5 inch 

between the fuel return line assembly 

(Cessna P/N 0516031–1) and the steering 

tube assembly (Cessna P/N MC0543022–2C); 

and 

(2) Visible positive clearance between the 

fuel return line assembly (Cessna P/N 

0516031–1) and the airplane structure. 

(l) Adjust Clearance for Fuel Return Line 

Assembly 

If you find any clearance less than the 

minimum clearance required by paragraph 

(k) of this AD, before further flight, adjust to 

the minimum clearance required by 

paragraph (k) of this AD. 

(m) Alternative Methods of Compliance 

(AMOCs) 

(1) 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. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(l) Related Information 

For more information about this AD, 

contact Jeff Janusz, Aerospace Engineer, 

Wichita ACO, FAA, 1801 S. Airport Road, 

Room 100, Wichita, Kansas 67209; phone: 

(316) 946–4148; fax: (316) 946–4107; email: 

jeff.janusz@faa.gov. 

(m) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Cessna Aircraft Company Service 

Bulletin SEB–28–01, dated September 21, 

2012. 

(ii) Reserved. 

(3) For Cessna Aircraft Company service 

information identified in this AD, contact 

Cessna Aircraft Company, Customer service, 

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

(316) 517–5800; fax: (316) 517–7271; 

customercare@cessna.textron.com; Internet: 

http://www.cessnasupport.com. 

(4) You may view this service information 

at FAA, Small Airplane Directorate, 901 

Locust, Kansas City, MO 64106. For 

information on the availability of this 

material at the FAA, call (816) 329–4148. 

(5) You may view this 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/cfr/ibrlocations.html. 

Issued in Kansas City, Missouri, on 

February 4, 2013. 

John Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–02897 Filed 2–11–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1037; Directorate 

Identifier 2012–NM–008–AD; Amendment 

39–17347; AD 2013–03–12] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Aviation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Dassault Aviation Model MystereFalcon 50 airplanes. This AD was 

prompted by a manufacturer revision to 

the airplane maintenance manual 

(AMM) that introduces new or more 

restrictive maintenance requirements 

and airworthiness limitations. This AD 

requires revising the maintenance 

program to incorporate new or revised 

maintenance requirements and 

airworthiness limitations. We are 

issuing this AD to prevent reduced 

structural integrity of the airplane. 

DATES: This AD becomes effective 

March 19, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 19, 2013. 


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