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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Federal Register / Vol. 78, No. 178 / Friday, September 13, 2013 / Rules and Regulations 56593 

a push-pull control system on Model 

205A–1 helicopters. Specifically, the 

NPRM proposed to apply to Model 204B 

helicopters with a chain, part number 

(P/N) 204–001–739–003 or –105, 

installed, and Model 205A–1 

helicopters with a serial number 30001 

through 30228. The NPRM proposed to 

require, for certain Model 205A–1 

helicopters, before further flight, 

replacing the chain and cable control 

system by installing an improved tail 

rotor hub and blade assembly kit and 

then installing a certain push/pull antitorque retrofit kit. The NPRM also 

proposed, for Model 204B helicopters, 

visually inspecting certain partnumbered chains at specified intervals 

using a 10-power or higher magnifying 

glass and a light; revising the inspection 

procedures; installing a damper kit; and 

revising the maintenance manual or 

ICAs to include the inspection intervals. 

The proposed requirements were 

intended to prevent failure of the chain, 

loss of tail rotor blade pitch control, and 

subsequent loss of control of the 

helicopter. 

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 24368, April 25, 2013). 

FAA’s Determination 

We have reviewed the relevant 

information and determined that an 

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 

The FAA has reviewed Bell Alert 

Service Bulletin (ASB) No. 204–75–4, 

dated December 16, 1975, for the Model 

204B helicopter, which specifies 

visually inspecting the chain using a 10- 

power magnifying glass every 10 flight 

hours. The inspection intervals for a 

chain were reduced because of several 

field reports of cracked and broken 

links. We have also reviewed Bell ASB 

204–79–7, dated August 21, 1979, 

which specifies installing a damper kit. 

A field evaluation has shown 

considerable improvement in the 

reliability of the chain when a damper 

kit is installed. 

Further, we have reviewed Bell ASB 

No. 205–78–5, dated May 16, 1978, for 

Model 205A–1 helicopters, serial 

number 30001 through 30228, which 

specifies removing the chain and cable 

control system and installing a pushpull control system kit, P/N 205–704– 

057–001 or 205–704–057–101. The tail 

rotor push-pull control system is 

installed in accordance with Service 

Instructions (SI) No. 205–38, ‘‘changed’’ 

March 28, 1990, for an improved tail 

rotor hub and blade assembly kit, P/N 

205–704–040–001 and 205–704–040– 

003, and SI No. 205–46, revised March 

7, 1980, for installing a push/pull antitorque retrofit kit. 

Costs of Compliance 

We estimate that this AD will affect 

13 Model 204B and 52 Model 205A–1 

helicopters of U.S. registry, and 

operators may incur the following costs: 

• Visual inspection of the link 

segments in a chain on a Model 204B 

helicopter will require .25 work hour for 

each inspection, 60 per year, at an 

average labor rate of $85 per work hour 

for a cost per helicopter of $1,275 and 

fleet cost of $16,575; 

• Replacement of a chain having a 

cracked or broken link or segment on a 

Model 204B helicopter will require .5 

work hour and a parts cost of $4,922, for 

a cost per helicopter of $4,965 and a 

total cost of $9,930 (assuming 2 are 

replaced); 

• Installation of a damper kit on a 

Model 204B helicopter will require 3 

work hours and a parts cost of $14,925, 

for a cost per helicopter of $15,180 and 

a total cost of $30,360 (assuming 2 are 

installed); and 

• Installation of a tail rotor push-pull 

control system on an affected Model 

205A–1 helicopter will require 225 

work hours and a parts cost of $152,214, 

for a cost per helicopter of $171,339. 

Therefore, we estimate the total cost 

impact of this AD on U.S. operators to 

be $228,204. 

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 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 

removing Airworthiness Directive (AD) 

76–12–07 Amendment 39–3569 (44 FR 

55555, September 27, 1979), which 

amended Amendment 39–2640 (41 FR 

23939; June 14, 1976), and by adding 

the following new AD: 

2013–18–07 BELL HELICOPTER TEXTRON 

(BELL): Amendment 39–17580; Docket 

No. FAA–2013–0379; Directorate 

Identifier 2009–SW–26–AD. 

(a) Applicability 

This AD applies to Model 204B helicopters 

with a tail rotor pitch control chain (chain), 

part number (P/N) 204–001–739–003 or –105, 

installed, and Model 205A–1 helicopters 

with a serial number (S/N) 30001 through 

30228, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in a chain, which can grow quickly 


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because of oscillatory loads and lead to 

premature failure of the chain, loss of the tail 

rotor blade pitch control, and subsequent loss 

of control of the helicopter. 

(c) Affected ADs 

This AD supersedes AD 76–12–07, 

Amendment 39–2640 (41 FR 23939, June 14, 

1976) as revised by Amendment 39–3569 (44 

FR 55555, September 27, 1979). 

(d) Effective Date 

This AD becomes effective October 18, 

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) For Model 205A–1 helicopters, before 

further flight, replace the tail rotor chain and 

cable control system with an airworthy tail 

rotor push-pull control system by installing 

an improved tail rotor hub and blade 

assembly kit, P/N 205–704–040–001 or 205– 

704–040–103, and then installing a push/pull 

anti-torque retrofit kit, P/N 205–704–057–001 

or 205–704–057–101. 

(2) For Model 204B helicopters: 

(i) Within 10 hours time-in-service (TIS) 

and thereafter at intervals not to exceed 10 

hours TIS, using a 10-power or higher 

magnifying glass and a light, visually inspect 

each of the link segments in the chain for a 

crack. Also, slowly operate the cockpit antitorque control pedals during the inspection 

so that the entire surface area of the chain in 

contact with the control quill sprocket 

(sprocket) is visibly accessible and can be 

inspected. Pay particular attention to the 

portion of the chain that travels over the 

sprocket and extends 6 inches to each side 

of the sprocket. 

(A) If there is no cracked or broken link 

segment, lubricate the chain with a light 

preservative oil (C–125) or wipe with a cloth 

dampened in lubricating oil (C–010). 

(B) If there is a cracked or broken link 

segment, before further flight, replace the 

chain with an airworthy chain. 

(ii) Within 50 hours TIS, install a tail rotor 

cable and chain damper kit, P/N 204–706– 

130–101, as depicted in Figures 1 through 3, 

and by following the Accomplishment 

Instructions, paragraphs 2. through 9., of Bell 

Alert Service Bulletin (ASB) No. 204–79–7, 

dated August 21, 1979. 

(g) Alternative Methods of Compliance 

(AMOC) 

(1) The Manager, Rotorcraft Certification 

Office, FAA, may approve AMOCs for this 

AD. Send your proposal to Michael Kohner, 

ASW–170, Aviation Safety Engineer, 

Rotorcraft Directorate, 2601 Meacham Blvd., 

Fort Worth, Texas 76137, telephone (817) 

222–5170, fax (817) 222–5783, email 

mike.kohner @faa.gov. 

(2) For operations conducted under 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 

(1) Bell ASB No. 204–75–4, dated 

December 16, 1975; Bell ASB No. 205–78–5, 

dated May 16, 1978; Service Instructions (SI) 

No. 205–38, ‘‘changed’’ March 28, 1990; and 

SI No. 205–46, revised March 7, 1980, 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 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. 

(2) The subject of this AD is addressed in 

Transport Canada Civil Aviation (TCCA) AD 

CF–1990–06R1, issued January 7, 2008. You 

may view the TCAA AD in the AD docket on 

the Internet at http://www.regulations.gov. 

(i) Subject 

The Joint Aircraft System Component Code 

is 6720: Tail Rotor Control System. 

(j) 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) Bell Alert Service Bulletin No. 204–79– 

7, dated August 21, 1979. 

(ii) Reserved. 

(3) For Bell Helicopter Textron, Inc. 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/. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(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 Fort Worth, Texas, on August 27, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–22188 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–2013–0186; Directorate 

Identifier 2013–NE–11–AD; Amendment 39– 

17571; AD 2013–17–07] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

General Electric Company (GE) GE90– 

76B, –85B, –90B, –94B, –110B1, and 

–115B turbofan engines. This AD was 

prompted by multiple reports of distress 

of certain stage 1 high-pressure turbine 

(HPT) stator shrouds due to accelerated 

corrosion and oxidation, including one 

engine in-flight shutdown (IFSD) caused 

by failure of the HPT stator shrouds. 

This AD requires initial and repetitive 

on-wing 360-degree borescope 

inspections (BSIs) for corrosion and 

oxidation of stage 1 HPT stator shrouds. 

If a shroud is found to be distressed, this 

AD requires reinspection at a reduced 

interval or removal from service before 

further flight. We are issuing this AD to 

prevent failure of stage 1 HPT stator 

shrouds, resulting in an IFSD of one or 

more engines, loss of thrust control, and 

damage to the airplane. 

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: For service information 

identified in this AD, contact General 

Electric Company, One Neumann Way, 

MD Y–75, Cincinnati, OH; phone: 513– 

552–2913; email: geae.aoc@ge.com; Web 

site: www.GE.com. You may view this 

service information at the FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

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 


emcdonald on DSK67QTVN1PROD with RULES