Federal Register / Vol. 78, No. 178 / Friday, September 13, 2013 / Rules and Regulations 56589 

3(m)(1) of the Act (12 U.S.C. 1813(m)(1)) 

and this part. 

* * * * * 

■ 3. In § 330.3, revise paragraph (e) to 

read as follows: 

§ 330.3 General principles. 

* * * * * 

(e) Deposits payable outside of the 

United States and certain other 

locations. (1) Any obligation of an 

insured depository institution which is 

payable solely at an office of that 

institution located outside any State, as 

the term ‘‘State’’ is defined in section 

3(a)(3) of the Act (12 U.S.C. 1813(a)(3)), 

is not a deposit for the purposes of this 

part. 

(2) Except as provided in paragraph 

(e)(3) of this section, any obligation of 

an insured depository institution which 

is carried on the books and records of 

an office of that institution located 

outside any State, as referred to in 

paragraph (e)(1) of this section, shall not 

be an insured deposit for purposes of 

this part, or any other provision of this 

part, notwithstanding that the obligation 

may also be payable at an office of that 

institution located within any State. 

(3) Rule of construction. For purposes 

of this paragraph (e), Overseas Military 

Banking Facilities operated under 

Department of Defense regulations, 32 

CFR Parts 230 and 231, are not 

considered to be offices located outside 

any State, as referred to in paragraph 

(e)(1) of this section. 

* * * * * 

Dated at Washington, DC, this 10th day of 

September, 2013. 

By order of the Board of Directors. 

Federal Deposit Insurance Corporation. 

Robert E. Feldman, 

Executive Secretary. 

[FR Doc. 2013–22340 Filed 9–12–13; 8:45 am] 

BILLING CODE 6714–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0527; Directorate 

Identifier 2013–CE–014–AD; Amendment 

39–17577; AD 2013–18–04] 

RIN 2120–AA64 

Airworthiness Directives; PIAGGIO 

AERO INDUSTRIES S.p.A Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

PIAGGIO AERO INDUSTRIES S.p.A 

Model P–180 airplanes. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as cracks at the joint between 

the hinge pin sub-assembly and the lock 

pin of the main landing gear lever hinge 

fitting. We are issuing this AD to require 

actions to address the unsafe condition 

on these products. 

DATES: This AD is effective October 18, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of October 18, 2013. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov or in person at 

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 service information identified in 

this AD, contact Piaggio Aero Industries 

S.p.A—Airworthiness Office, Via Luigi 

Cibrario, 4–16154 Genova-Italy; phone: 

+39 010 6481353; fax: +39 010 6481881; 

email: airworthiness@piaggioaero.it; 

Internet: http://www.piaggioaero.com/#/ 

en/aftersales/service-support; and 

Messier-Dowty Limited, Cheltenham 

Road, Gloucester, GL2 9QH, England; 

phone: +44(0)1452 712424; fax: 

+44(0)1452 713821; email: 

americatassc@safranmbd.com; Internet: 

www.safranmbd.com. You may review 

copies of the referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. 

FOR FURTHER INFORMATION CONTACT: 

Mike Kiesov, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4144; fax: (816) 

329–4090; email: mike.kiesov@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. The 

NPRM was published in the Federal 

Register on June 19, 2013 (78 FR 36691). 

The NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

During scheduled maintenance, cracks 

have been detected at the joint between the 

hinge pin sub-assembly and the lock pin of 

the main landing gear (MLG) lever hinge 

fitting (LHF) of a Piaggio P.180 aeroplane. 

The results of the subsequent investigation 

revealed that the cracks were initiated by an 

unforeseen friction in the MLG wheel lever 

sub-assembly. 

This condition, if not detected and 

corrected, could lead to a structural failure of 

the MLG, possibly resulting in loss of control 

of the aeroplane during take-off or landing 

runs. 

To address this potential unsafe condition, 

Piaggio Aero Industries (PAI) issued Service 

Bulletin (SB) 80–0345 to provide instructions 

for early identification of cracks in the MLG 

LHF and, in case of identification of the 

crack, replacement of the MLG. 

For the reasons described above, this AD 

required inspections of the MLG LHF and, 

depending on findings, replacement of the 

MLG. 

This AD is considered to be an interim 

action, and based on gathered experience, 

further AD action may follow. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

Request To Change Compliance Time 

From Hours Time-in-Service (TIS) to 

Landings 

Carlo Cardu of PIAGGIO AERO 

INDUSTRIES S.p.A requested the 

compliance time be changed from hours 

TIS to landing, as recommended in the 

related service bulletin, to take into 

account actual landing gear usage. 

We partially agreed with the 

commenter to include landings as a 

measure for the compliance of this AD 

because the unsafe condition addressed 

in this AD is a function of cycles on the 

landing gear. We disagreed with only 

using landings because this class of 

airplane does not require landings to be 

recorded. If an operator does document 

landings, this is an acceptable measure. 

However, if an operator does not record 

landings, TIS is also an acceptable 

measure for compliance. 

We have changed the final rule AD 

action based on this comment. 

Request To Change the Requirement To 

Replace the Main Landing Gear (MLG) 

Lever Hinge Fitting (LHF) 

Carlo Cardu of PIAGGIO AERO 

INDUSTRIES S.p.A requested we 

change the corrective action from 

replacing the MLG LHF with a 


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56590 Federal Register / Vol. 78, No. 178 / Friday, September 13, 2013 / Rules and Regulations 

serviceable part to replacing the MLG 

with a serviceable part based on the 

description of a serviceable part in the 

related service bulletin. 

The commenter also requested we 

change the language from MLG LHF to 

MLG when referring to the inspections 

required after replacement of the MLG. 

We agreed with the commenter. Based 

on the description of a serviceable part 

in the service bulletin, the operator has 

options to meet the intent of a 

serviceable part that do not increase the 

burden on the owners/operators of the 

affected airplanes. We have changed the 

final rule AD action based on this 

comment. 

Request To Clarify Inspection 

Requirements for Newly Installed MLG 

Carlo Cardu of PIAGGIO AERO 

INDUSTRIES S.p.A requested changing 

all repetitive inspection language for 

newly installed MLG. The commenter 

suggested changing this AD to specify 

that a newly installed MLG is subject to 

specific inspection reqirements. 

We agreed with the commenter and 

have changed the final rule AD action 

based on this comment. 

Request To Expand Criteria for 

Determining a ‘‘Serviceable’’ MLG 

Carlo Cardu of PIAGGIO AERO 

INDUSTRIES S.p.A requested additional 

language be added to clarify the 

definition of a ‘‘serviceable’’ MLG. 

We agreed with the commenter and 

have changed the final rule AD action 

based on this comment. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously. 

We have determined that these minor 

changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

36691, June 19, 2013) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 36691, 

June 19, 2013). 

We also determined that these changes 

will not increase the economic burden 

on any operator or increase the scope of 

this AD. 

Interim Action 

We consider this AD interim action. 

We are requiring inspection(s) of the left 

and right MLG LHF with a report to the 

manufacturer of the results if cracks are 

found. We will work with the type 

certificate holder to evaluate the report 

results to determine repetitive 

inspection intervals and subsequent 

terminating action. Based on this 

evaluation, we may initiate further 

rulemaking action to address the unsafe 

condition identified in this AD. 

Costs of Compliance 

We estimate that this AD will affect 

109 products of U.S. registry. We also 

estimate that it will take about 11 total 

work-hours, which is 2 work-hours for 

the initial visual inspection; 2 workhours for the detailed visual inspection; 

and 7 work-hours for the fluorescent 

penetrant inspection, per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. 

Based on these figures, we estimate 

the cost of this AD on U.S. operators to 

be $101,915, or $935 per product. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 7 work-hours and require parts 

costing $21,540 to replace a left-hand 

LHF, for a cost of $22,153, and $20,662 

to replace a right-hand LHF, for a cost 

of $21,257. 

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 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(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. 

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 the NPRM, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(telephone (800) 647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2013–18–04 PIAGGIO AERO INDUSTRIES 

S.p.A: Amendment 39–17577; Docket 

No. FAA–2012–0962; Directorate 

Identifier 2012–CE–033–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective October 18, 2013. 

(b) Affected ADs 

None. 


emcdonald on DSK67QTVN1PROD with RULES
Federal Register / Vol. 78, No. 178 / Friday, September 13, 2013 / Rules and Regulations 56591 

(c) Applicability 

This AD applies to PIAGGIO AERO 

INDUSTRIES S.p.A Model P–180 airplanes, 

all serial numbers, certificated in any 

category. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 32: Landing Gear. 

(e) Reason 

This AD was prompted by 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 cracks at the joint between the 

hinge pin sub-assembly and the lock pin of 

the main landing gear (MLG) lever hinge 

fitting (LHF). We are issuing this AD to 

prevent structural failure of the MLG LHF, 

which could result in loss of control during 

take-off or landing runs. 

(f) Actions and Compliance 

Unless already done, do the following 

actions in paragraphs (f)(1) through (f)(8), 

including all subparagraphs, of this AD: 

(1) Within the next 200 landings after 

October 18, 2013 (the effective date of this 

AD), or within the next 3 months after 

October 18, 2013 (the effective date of this 

AD), whichever occurs first, and before 

further flight after each MLG replacement, 

visually inspect each MLG LHF for cracks 

and verify freedom of rotation of the MLG 

wheel lever subassemblies. Do the inspection 

following Part 1 of the Accomplishment 

Instructions in PIAGGIO AERO INDUSTRIES 

S.p.A. Mandatory Service Bulletin No. 80– 

0345, dated September 20, 2012; and 

Paragraph A of the Accomplishment 

Instructions in Appendix A of PIAGGIO 

AERO INDUSTRIES S.p.A. Mandatory 

Service Bulletin No. 80–0345, dated 

September 20, 2012, which includes MessierDowty Service Bulletin No. P180–32–32, 

dated September 10, 2012. The compliance 

times for the entire AD are presented in 

landings; however, it is not mandatory to 

track landings for this class of airplane. If an 

operator does not track landings, 1 hour timein-service (TIS) corresponds to 1 landing for 

compliance with this AD. 

(2) If, during the inspection required in 

paragraph (f)(1) of this AD, freedom of 

rotation of the MLG wheel lever subassembly 

is not assured, before further flight, mark the 

LHF on the affected MLG as ‘‘inspect as per 

SB–80–0345’’ with an indelible pen, and 

replace the MLG with a serviceable part as 

defined in paragraph (f)(7) of this AD. Do the 

replacement following Part 1 of the 

Accomplishment Instructions in PIAGGIO 

AERO INDUSTRIES S.p.A. Mandatory 

Service Bulletin No. 80–0345, dated 

September 20, 2012. The newly installed 

MLG is subject to the inspection requirement 

specified in paragraph (f)(1) of this AD and 

all repetitive inspection requirements 

specified in paragraphs (f)(3) and (f)(4) of this 

AD. 

(3) Within the compliance times specified 

in paragraphs (f)(3)(i), (f)(3)(ii), and (f)(3)(iii) 

of this AD, and repetitively thereafter at 

intervals not to exceed 200 landings, do a 

detailed visual inspection of each MLG LHF 

for cracks. Do the inspection following Part 

2 of the Accomplishment Instructions in 

PIAGGIO AERO INDUSTRIES S.p.A. 

Mandatory Service Bulletin No. 80–0345, 

dated September 20, 2012; and Paragraph B 

of the Accomplishment Instructions in 

Appendix A of PIAGGIO AERO INDUSTRIES 

S.p.A. Mandatory Service Bulletin No. 80– 

0345, dated September 20, 2012, which 

includes Messier-Dowty Service Bulletin No. 

P180–32–32, dated September 10, 2012. 

(i) As of October 18, 2013 (the effective 

date of this AD), if the MLG LHF has 

accumulated 2,300 landings or less since 

new, inspect before exceeding 2,500 landings 

since new. 

(ii) As of October 18, 2013 (the effective 

date of this AD), if the MLG LHF has 

accumulated more than 2,300 landings since 

new, but less than 2,500 landings since new, 

inspect within the next 200 landings after 

October 18, 2013 (the effective date of this 

AD). 

(iii) As of October 18, 2013 (the effective 

date of this AD), if the MLG LHF has 

accumulated 2,500 landings or more since 

new, inspect within the next 200 landings 

after October 18, 2013 (the effective date of 

this AD), or within the next 3 months after 

October 18, 2013 (the effective date of this 

AD), whichever occurs first. 

(4) Within the compliance times specified 

in paragraphs (f)(3)(i), (f)(3)(ii), and (f)(3)(iii) 

of this AD and repetitively thereafter at 

intervals not to exceed 750 landings, do a 

fluorescent penetrant inspection on each 

MLG LHF for cracks. Do the inspection 

following Part 3 of the Accomplishment 

Instructions in PIAGGIO AERO INDUSTRIES 

S.p.A. Mandatory Service Bulletin No. 80– 

0345, dated September 20, 2012; and 

Paragraph C in Appendix A of PIAGGIO 

AERO INDUSTRIES S.p.A. Mandatory 

Service Bulletin No. 80–0345, dated 

September 20, 2012, which includes MessierDowty Service Bulletin No. P180–32–32, 

dated September 10, 2012. 

(5) If, during any inspection required by 

paragraphs (f)(1), (f)(3), (f)(4), (f)(7), and (f)(8) 

of this AD, including all subparagraphs, any 

crack is found, before further flight, replace 

the MLG with a serviceable part as defined 

in paragraph (f)(7) of this AD. Do the 

replacement following the Accomplishment 

Instructions in PIAGGIO AERO INDUSTRIES 

S.p.A. Mandatory Service Bulletin No. 80– 

0345, dated September 20, 2012. The newly 

installed MLG is subject to the inspection 

requirement specified in paragraph (f)(1) of 

this AD and all repetitive inspection 

requirements specified in paragraphs (f)(3) 

and (f)(4) of this AD. 

(6) Within 30 days after each MLG 

replacement, submit an inspection result 

report to PIAGGIO AERO INDUSTRIES S.p.A 

at the address specified in paragraph (h) of 

this AD using the Confirmation Slip attached 

to PIAGGIO AERO INDUSTRIES S.p.A. 

Mandatory Service Bulletin No. 80–0345, 

dated September 20, 2012. 

(7) For the purpose of this AD, a 

‘‘serviceable’’ MLG is defined as an airworthy 

MLG that has had the freedom of rotation 

verified before installation and that has been 

inspected following paragraphs (f)(3), (f)(4), 

and (f)(8) (paragraph (f)(8) only applies if the 

LHF on the MLG has been marked ‘‘inspect 

as per SB–80–0345’’ as specified in 

paragraph (f)(2) of this AD) of this AD, 

including all subparagraphs, and is found 

free of cracks. If status of detailed visual 

inspections intervals, fluorescent penetrant 

inspections intervals, or landings since new 

cannot be determined from the Authorized 

Release Certificate of the MLG to be installed, 

before next flight after installation, inspect 

the MLG LHF as specified in paragraphs 

(f)(1), (f)(3), and (f)(4) of this AD. For the 

purpose of this AD, a serviceable MLG 

replacement is defined in paragraphs (f)(7)(i), 

(f)(7)(ii), and (f)(7)(iii) of this AD. All newly 

installed MLG LHF is subject to the 

inspections required in paragraphs (f)(1), 

(f)(3), and (f)(4) of this AD. 

(i) Remove the unserviceable MLG and 

replace it with a different serviceable MLG. 

(ii) Rework the unserviceable MLG 

following Part 2 and Part 3 of the 

Accomplishment Instructions in PIAGGIO 

AERO INDUSTRIES S.p.A. Mandatory 

Service Bulletin No. 80–0345, dated 

September 20, 2012, until it passes the check 

for freedom of rotation and no cracks are 

found. 

(iii) Replace the cracked LHF in the 

unserviceable MLG with a new LHF and, 

after LHF replacement, check the MLG for 

freedom of rotation. 

(8) As of October 18, 2013 (the effective 

date of this AD), any MLG with LHF marked 

‘‘inspect as per SB 80–0345’’ that was 

removed as specified in paragraph (f)(2) of 

this AD may be reinstalled provided that 

before installation, freedom of rotation has 

been restored. Before further flight after 

installation, the MLG LHF must be inspected 

as specified in paragraphs (f)(1), (f)(3), and 

(f)(4) of this AD. Continue thereafter with the 

repetitive inspections at the intervals 

specified in paragraphs (f)(3) and (f)(4) of this 

AD. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

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: Mike Kiesov, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4144; fax: (816) 329– 

4090; email: mike.kiesov@faa.gov. 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. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 


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56592 Federal Register / Vol. 78, No. 178 / Friday, September 13, 2013 / Rules and Regulations 

(h) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) AD No. 2013–0084, dated 

April 5, 2013, which can be found in the AD 

docket on the Internet at http://

www.regulations.gov; Messier-Dowty PCS– 

2700 Paint Stripping document, dated 

January 2011; Messier-Dowty PCS–2622 Cold 

Degreasing (Solvent) document, Issue 2, 

dated May 12, 2008; and Messier-Dowty Ltd 

201034005 and 201034006 Component 

Maintenance Manual, page 2, dated May 1, 

2004, and page 1020, dated March 17, 2006, 

which can be found on the Internet at: 

http://www.safranmbd.com, for related 

information. 

(i) 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) PIAGGIO AERO INDUSTRIES S.p.A. 

Mandatory Service Bulletin No. 80–0345, 

dated September 20, 2012. 

(ii) PIAGGIO AERO INDUSTRIES S.p.A. 

Mandatory Service Bulletin No. 80–0345, 

Appendix A, dated September 20, 2012, 

which includes Messier-Dowty Service 

Bulletin No. P180–32–32, dated September 

10, 2012. 

(3) For PIAGGIO AERO INDUSTRIES 

S.p.A. service information identified in this 

AD, contact Piaggio Aero Industries S.p.A— 

Airworthiness Office, Via Luigi Cibrario, 4– 

16154 Genova-Italy; phone: +39 010 6481353; 

fax: +39 010 6481881; email: airworthiness@

piaggioaero.it; Internet: http://

www.piaggioaero.com/#/en/aftersales/

service-support; and Messier-Dowty Limited, 

Cheltenham Road, Gloucester, GL2 9QH, 

England; phone: +44(0)1452 712424; fax: 

+44(0)1452 713821; email: americatassc@

safranmbd.com; Internet: 

www.safranmbd.com. 

(4) You may view this service information 

at FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 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 August 

29, 2013. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013–22203 Filed 9–12–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0379; Directorate 

Identifier 2009–SW–26–AD; Amendment 39– 

17580; AD 2013–18–07] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron, Inc. (Bell) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding revised 

Airworthiness Directive (AD) 76–12–07 

for all Bell Model 204B and certain 

serial-numbered Model 205A–1 

helicopters with a certain tail rotor pitch 

control chain (chain) installed. AD 76– 

12–07 required visually inspecting the 

chain to detect a crack in the link 

segments and, for affected Model 205A– 

1 helicopters, replacing the chain and 

cable control system with a push-pull 

control system. This new AD requires, 

for Bell Model 204B, inspecting certain 

chains at specified intervals, revising 

the inspection procedures, installing a 

tail rotor cable and chain damper kit 

(damper kit), and revising the 

maintenance manual or Instructions for 

Continued Airworthiness (ICAs) to 

include the inspection intervals. This 

new AD also requires, for certain Bell 

Model 205A–1 helicopters, replacing 

the chain and cable control system with 

an airworthy tail rotor push-pull control 

system kit. This AD was prompted by 

the rapid growth of a crack leading to 

premature chain failure. The actions are 

intended to prevent failure of the chain, 

loss of tail rotor blade pitch control, and 

subsequent loss of control of the 

helicopter. 

DATES: This AD is effective October 18, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 18, 2013. 

ADDRESSES: For service information 

identified in this AD, 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 a copy of 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, any incorporated-byreference service information, 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: 

Michael Kohner, Aviation Safety 

Engineer, Rotorcraft Certification Office, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5170; email 

7-AVS-ASW-170@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On June 3, 1976, we issued AD 76– 

12–07, Amendment 39–2640 (41 FR 

23939, June 14, 1976), Docket No. 76– 

SW–19, which required repetitive 

inspections at specified intervals for a 

certain part-numbered chain installed 

on Model 204B and 205A–1 helicopters. 

AD 76–12–07 also required, before 

further flight, replacing chains with 

cracked or broken links or segments. 

On September 12, 1979, we revised 

AD 76–12–07 by issuing Amendment 

39–3569 (44 FR 55555, September 27, 

1979). The revised AD 76–12–07 limited 

the applicability for the Model 205A–1 

helicopter to certain serial numbers; 

decreased the inspection interval of the 

chain; and required replacing the 

existing chain and cable control system 

with a push-pull control system. 

Both amendments were prompted by 

several chain failures occurring in flight 

and reports of cracked chain links on 

Model 205A–1 helicopters. Those 

actions were intended to detect cracks 

in the chain link segments to prevent 

failure of a chain and subsequent loss of 

directional control of the helicopter. 

On April 25, 2013, at 78 FR 24368, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 to 

include an AD that would supersede 

original and revised AD 76–12–07. The 

NPRM proposed to expand the 

applicability of AD 76–12–07 to a 

newly-produced, similarly-designed 

chain; reduce the inspection interval for 

the Model 204B; and require installing 


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