56148 Federal Register / Vol. 78, No. 177 / Thursday, September 12, 2013 / Rules and Regulations 

Director may initiate action to revoke 

and/or deny the respondent’s 

applications for Airport Improvement 

Program grants issued under 49 U.S.C. 

47114(c)–(e) and 47115. 

(e) On appeal from a hearing officer’s 

initial decision, the Associate 

Administrator will consider the 

following questions: 

(1) Are the findings of fact each 

supported by a preponderance of 

reliable, probative and substantial 

evidence? 

(2) Are conclusions made in 

accordance with law, precedent and 

policy? 

(3) Are the questions on appeal 

substantial? 

(4) Have any prejudicial errors 

occurred? 

(f) Any new issues or evidence 

presented in an appeal or reply will not 

be allowed unless accompanied by a 

certified petition and good cause found 

as to why the new matter was not 

presented to the Director. Such a 

petition must: 

(1) Set forth the new issues or 

evidence; 

(2) Contain affidavits of prospective 

witnesses, authenticated documents, or 

both, or an explanation of why such 

substantiation is unavailable; and 

(3) Contain a statement explaining 

why such new matter could not have 

been discovered in the exercise of due 

diligence prior to the date on which the 

evidentiary record closed. 

(g) A Final Agency Decision may be 

appealed in accordance with subpart G 

of this part. 

Subparts H and I [Redesignated as 

Subparts G and H] 

■ 33. Redesignate subpart H, consisting 

of § 16.247, and subpart I, consisting of 

§§ 16.301, 16.303, 16.305, and 16.307, as 

subparts G and H, respectively. 

■ 34. In § 16.247, revise paragraphs (a), 

(b)(2), and (b)(4) to read as follows: 

§ 16.247 Judicial review of a final decision 

and order. 

(a) A person may seek judicial review, 

in a United States Court of Appeals, of 

a final decision and order of the 

Associate Administrator, and of an 

order of dismissal with prejudice issued 

by the Director, as provided in 49 U.S.C. 

46110 or 49 U.S.C. 47106(d) and 

47111(d). A party seeking judicial 

review shall file a petition for review 

with the Court not later than 60 days 

after the order has been served on the 

party or within 60 days after the entry 

of an order under 49 U.S.C. 46110. 

(b) * * * 

(2) A Director’s Determination; 

* * * * * 

(4) A Director’s Determination or an 

initial decision of a hearing officer 

becomes the final decision of the 

Associate Administrator because it was 

not appealed within the applicable time 

periods provided under §§ 16.33(c) and 

16.241(b). 

§ 16.301 [Removed] 

■ 35. Remove § 16.301 from newly 

redesignated subpart H. 

§§ 16.303, 16.305, and 16.307 

[Redesignated as §§ 16.301, 16.303, and 

16.305] 

■ 36. In newly redesignated subpart H, 

redesignate §§ 16.303, 16.305, and 

16.307 as §§ 16.301, 16.303, and 16.305, 

respectively. 

Issued under authority provided by 49 

U.S.C. 106(f), 46101, 46104, and 47122 in 

Washington, DC, on August 23, 2013. 

Michael P. Huerta, 

Administrator. 

[FR Doc. 2013–22130 Filed 9–11–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0400; Directorate 

Identifier 2009–SW–48–AD; Amendment 39– 

17579; AD 2013–18–06] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Limited 

(Bell) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Bell 

Model 206A, 206B, 206L, 206L–1, 

206L–3, 206L–4, 222, 222B, 222U, 230, 

407, 427, and 430 helicopters. This AD 

requires inspecting each bearing to 

determine if it has been properly staked 

and replacing the bearing or assembly if 

it has not been properly staked. This AD 

was prompted by bearings not being 

properly staked and migrating out of 

their proper position, which may limit 

the functionality of the affected part. 

The actions of this AD are intended to 

prevent failure of a bearing and the 

assembly in which it is installed and 

subsequent loss of control of the 

helicopter. 

DATES: This AD is effective October 17, 

2013. 

ADDRESSES: For service information 

identified in this AD, contact Bell 

Helicopter Textron Canada Limited, 

12,800 Rue de l’Avenir, Mirabel, Quebec 

J7J1R4, telephone (450) 437–2862 or 

(800) 363–8023, fax (450) 433–0272, or 

at http://www.bellcustomer.com/files/. 

You may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

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 foreign 

authority’s AD, the economic 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations Office (phone: 

800–647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Sharon Miles, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

sharon.y.miles@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On May 13, 2013, at 78 FR 27869, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 to 

include an AD that would apply to Bell 

Model 206A, 206B, 206L, 206L–1, 

206L–3, 206L–4, 222, 222B, 222U, 230, 

407, 427, and 430 helicopters. The 

NPRM proposed using a 10X or higher 

power magnifying glass or a boroscope 

to inspect each bearing in each affected 

part to determine if each bearing had 

been properly staked. For a part that 

could not be accessed to determine if 

the bearing is properly staked, the 

NPRM proposed removing the part from 

the helicopter to inspect it. The NPRM 

proposed replacing the bearing or 

assembly if it was not properly staked. 

The proposed requirements were 

intended to prevent failure of a bearing 

and the assembly in which it is installed 

and subsequent loss of control of the 

helicopter. 

The NPRM was prompted by AD No. 

CF–2009–32, dated July 24, 2009, issued 

by Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, to correct an unsafe 

condition for the specified Bell model 


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Federal Register / Vol. 78, No. 177 / Thursday, September 12, 2013 / Rules and Regulations 56149 

helicopters. TCCA advises that some 

bearings may not have been staked as 

required, which may limit the proper 

functioning of the affected part. Bell, the 

helicopter manufacturer, received two 

reports stating that a bearing migrated 

out of a flight control lever. 

Investigation revealed that, although the 

inspection witness mark was applied to 

the part, the bearing had not been staked 

during manufacturing. Affected parts 

were associated with a single Bell 

supplier. Review of the supplier’s 

manufacturing and quality process 

indicates inspection of additional parts 

is necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM (78 FR 27869, May 13, 2013). 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Canada and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with Canada, TCCA has 

notified us of the unsafe condition 

described in its AD. We are issuing this 

AD because we evaluated all 

information provided by TCCA and 

determined the unsafe condition exists 

and is likely to exist or develop on other 

helicopters of these same type designs 

and that air safety and the public 

interest require adopting the AD 

requirements as proposed. 

Related Service Information 

Bell has issued Alert Service Bulletin 

(ASB) No. 206–09–122 for Model 206A/ 

B series; No. 206L–09–156 for Model 

206L series; No. 222–09–107 for Model 

222 and 222B; No. 222U–09–78 for 

Model 222U; No. 230–09–39 for Model 

230; No. 407–09–88 for Model 407; No. 

427–09–25 for Model 427; and No. 430– 

09–42, for Model 430, all dated April 7, 

2009. The ASBs specify inspecting for 

parts that contain bearings that have not 

been staked. 

Costs of Compliance 

We estimate that this AD will affect 

2,601 helicopters of U.S. registry. Based 

on an average labor rate of $85 per 

work-hour, we estimate that operators 

may incur the following costs in order 

to comply with this AD. It will take 

about 1 to 5 work-hours per helicopter, 

depending on the model, to inspect for 

properly staked bearings. Replacing a 

bearing will require about 2 work-hours 

and will cost $3,306 for required parts. 

Based on an average inspection time of 

2 work-hours, we estimate the cost of 

this AD to inspect the helicopters will 

be $170 per helicopter and $442,170 for 

the U.S. operator fleet. Replacing a 

bearing will cost $3,476 per helicopter. 

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 

helicopters 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 to the extent that it justifies 

making a regulatory distinction; 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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): 

2013–18–06 Bell Helicopter Textron 

Canada Limited: Amendment 39–17579; 

Docket No. FAA–2013–0400; Directorate 

Identifier 2009–SW–48–AD. 

(a) Applicability 

This AD applies to Model 206A, 206B, 

206L, 206L–1, 206L–3, 206L–4, 222, 222B, 

222U, 230, 407, 427, and 430 helicopters as 

follows, certificated in any category. 

(1) Model 206A, Model 206B helicopters 

converted from Model 206A, and Model 

206B with Bellcrank Assembly, part-number 

(P/N) 206–001–526–001 or 206–001–538– 

009; Idler Link Assembly, P/N 206–010–336– 

109; or Link Assembly, P/N 206–031–589– 

001, installed. 

(2) Model 206L, Model 206L–1, Model 

206L–3, and Model 206L–4 with Idler 

Assembly, P/N 206–001–549–101; Bellcrank 

Assembly, P/N 206–001–552–001; or Link 

Assembly, P/N 206–010–336–109, installed. 

(3) Model 222 and Model 222B with 

(i) Cyclic Link Assembly, P/N 222–010– 

419–110; or 

(ii) Bellcrank Assembly Directional 

Controls, P/N 222–001–734–001 or 222–001– 

736–005, installed. 

(4) Model 222U with 

(i) Cyclic Link Assembly, P/N 222–010– 

419–110; or 

(ii) Bellcrank Assembly Directional 

Controls, P/N 222–001–734–001 or 222–001– 

736–005, installed. 

(5) Model 230 with 

(i) Fitting Assembly Engine Bipod Mount, 

P/N 230–060–113–101, 230–060–113–102, 

230–060–114–101, or 230–060–114–102; 

Cyclic Link Assembly P/N 222–010–419–110; 

or 

(ii) Bellcrank Assembly Directional 

Controls, P/N 222–001–734–001, or 222– 

001–736–005, installed. 

(6) Model 407 with 

(i) Bearing and Liner Assembly, P/N 406– 

010–417–101; Cyclic Mixer Follower 

Assembly, P/N 407–001–325–101; Bellcrank 

Assembly, P/N 407–001–524–105, 407–001– 

524–109, 407–001–526–105, 407–001–526– 

109, 407–001–528–101, or 407–001–528–105; 

or 

(ii) Beam Assembly, P/N 407–001–723– 

101, installed. 

(7) Model 427 with Swashplate Lateral 

Link Assembly (upper and lower bearing), 

P/N 427–001–021–101; Swashplate 

Longitudinal Link Assembly (upper and 

lower bearing), P/N 427–001–022–101; 

Transmission Mounted Longitudinal 

Bellcrank Assembly (pivot bearing), P/N 427– 

001–521–105/–109; Transmission Mounted 

Lateral Bellcrank Assembly (pivot bearing), 

P/N 427–001–520–109/–113; or Bearing and 


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56150 Federal Register / Vol. 78, No. 177 / Thursday, September 12, 2013 / Rules and Regulations 

Liner (lower drive link bearing), P/N 406– 

010–417–109, installed. 

(8) Model 427 with Tail Rotor Actuator 

Output Idler, P/N 427–001–723–101, 

installed. 

(9) Model 430 with 

(i) Fitting Assembly Engine Bipod Mount, 

P/N 230–060–113–101, 230–060–113–102, 

230–060–114–101, or 230–060–114–102; 

Bearing Assembly M/R Rotating Controls, P/ 

N 430–010–449–101; Rod End Assembly Lift 

link, P/N 430–010–204–101 or 430–010–204– 

103, or 

(ii) Bellcrank Assembly Directional 

Controls, P/N 222–001–734–001, or 222– 

001–736–005, installed. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

bearings that may not have been staked as 

required and may migrate out of their proper 

position and limit the functionality of the 

affected part. This condition could result in 

failure of a bearing and the lever assembly in 

which it is installed and subsequent loss of 

control of the helicopter. 

(c) Effective Date 

This AD becomes effective October 17, 

2013. 

(d) 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. 

(e) Required Actions 

(1) Perform each action required by this AD 

within the compliance time for each part 

listed in the applicability paragraph of this 

AD as follows: (a)(1), (a)(2), (a)(6)(i), (a)(7), 

and (a)(8), within 10 hours time-in-service 

(TIS) or 30 days, whichever occurs first; 

(a)(3)(i), (a)(4)(i), (a)(5)(i), and (a)(9)(i), within 

5 hours TIS or 30 days, whichever occurs 

first; (a)(3)(ii), (a)(4)(ii), (a)(5)(ii), and (a)(9)(ii) 

within 150 hours TIS or 12 months, 

whichever occurs first; and (a)(6)(ii) within 

300 hours TIS or 12 months, whichever 

occurs first. 

(2) Using a 10X or higher power 

magnifying glass or using a boroscope, 

inspect each bearing and determine if the 

bearing has been properly staked for each 

part that contains a part serial number with 

a prefix of either ‘‘TI’’ or ‘‘TIFS.’’ 

(i) If a part does not contain a serial 

number, inspect the bearing of that part even 

if that part contains a supplier marking. 

(ii) If you cannot access the bearing while 

the part is installed on the helicopter to make 

a determination as to whether the bearing in 

the part is properly staked, remove the part 

and inspect the bearing using a 10X or higher 

power magnifying glass or using a boroscope. 

(iii) If you find a part that is not properly 

staked, replace the bearing or the assembly 

with an airworthy bearing or assembly before 

further flight. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to Sharon Miles, 

ASW–111, Aviation Safety Engineer, 

Rotorcraft Directorate, Regulations and 

Guidance Group, 2601 Meacham Blvd., Fort 

Worth, Texas 76137, telephone (817) 222– 

5110, email sharon.y.miles@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. 

(g) Additional Information 

(1) Bell Alert Service Bulletin (ASB) No. 

206–09–122 for Models 206A and 206B; No. 

206L–09–156 for Models 206L, 206L–1, 

206L–3, and 206L–4; No. 222–09–107 for 

Models 222 and 222B; No. 222U–09–78 for 

Model 222U; No. 230–09–39 for Model 230; 

No. 407–09–88 for Model 407; No. 427–09– 

25 for Model 427; and No. 430–09–42 for 

Model 430, all dated April 7, 2009, which are 

not incorporated by reference, contain 

additional information about the subject of 

this AD. For service information identified in 

this AD, contact Bell Helicopter Textron 

Canada Limited, 12,800 Rue de l’Avenir, 

Mirabel, Quebec J7J1R4, telephone (450) 

437–2862 or (800) 363–8023, fax (450) 433– 

0272, or at http://www.bellcustomer.com/

files/. You may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(2) The subject of this AD is addressed in 

Transport Canada Civil Aviation AD No. CF– 

2009–32, dated July 24, 2009, which may be 

reviewed in the AD docket on the Internet at 

http://www.regulations.gov. 

(h) Subject 

Joint Aircraft System/Component (JASC) 

Code: 6700 Rotorcraft Flight Controls and 

6710 Main Rotor Control. 

Issued in Fort Worth, Texas, on August 27, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–21716 Filed 9–11–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0535; Directorate 

Identifier 2013–CE–018–AD; Amendment 

39–17489; AD 2013–13–01] 

RIN 2120–AA64 

Airworthiness Directives; Piper 

Aircraft, Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; correction. 

SUMMARY: The FAA is correcting an 

airworthiness directive (AD) that 

published in the Federal Register. AD 

2013–13–01 applies to certain Piper 

Aircraft, Inc. Models PA–46–310P, PA– 

46–350P, PA–46R–350T, and PA–46– 

500TP airplanes. There is an incorrect 

reference to a paragraph designation, 

four instances of an incorrect reference 

to the paragraph in the service bulletin 

that references an airworthiness 

limitation, and an incomplete email 

address for the person to contact in the 

Related Information section. This 

document corrects those errors. In all 

other respects, the original document 

remains the same. 

DATES: This final rule is effective 

September 12, 2013. The effective date 

for AD 2013–13–01 (78 FR 41277, July 

10, 2013) remains July 10, 2013. 

ADDRESSES: 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: Gary 

Wechsler, Aerospace Engineer, Atlanta 

Aircraft Certification Office, FAA, 1701 

Columbia Avenue, College Park, Georgia 

30337; telephone: (404) 474–5575; fax: 

(404) 474–5606; email: gary.wechsler@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Airworthiness Directive 2013–13–01, 

Amendment 39–17489 (78 FR 41277, 

July 10, 2013), currently requires 

inspecting the fuel vent valves to 

identify if the nitrile parts are installed 

and modifying and eventually replacing 

the fuel vent valves if the nitrile parts 

are installed for certain Piper Aircraft, 

Inc. Models PA–46–310P, PA–46–350P, 

PA–46R–350T, and PA–46–500TP 

airplanes. 

As published, there is an incomplete 

email address in the For Further 

Information Contact section of the 

preamble. There is an incorrect 

reference to a paragraph designation, 

four instances of an incorrect reference 

to the paragraph in the service bulletin 

that references an airworthiness 

limitation, and an incomplete email 

address for the person to contact in the 

regulatory information. 


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