Federal Register / Vol. 78, No. 161 / Tuesday, August 20, 2013 / Proposed Rules 51123 

39–1312 (36 FR 19572, October 8, 1971). We 

are issuing this AD to detect and correct 

defective fuel valve covers, which could 

result in fuel selector handle binding leading 

to fuel flow interruption resulting in engine 

stoppage. 

(f) Compliance 

Unless already done, within the next 100 

hours time-in-service (TIS) after the effective 

date of this AD or within the next 12 months 

after the effective date of this AD, whichever 

occurs first, do the following actions as 

applicable in paragraphs (g) through (h) of 

this AD, including all subparagraphs. 

(g) Inspection 

Inspect to verify if the appropriate kit, 

Piper part number (P/N) 760–545V or P/N 

760–546V, has been installed on the 

applicable airplanes, using one of two 

methods defined in paragraphs (g)(1), (g)(2), 

or (g)(3) of this AD: 

(1) Review the prior logbook entries of the 

airplanes identified in table 2 to paragraph 

(g) of this AD for documentation of Piper 

Mandatory Service Bulletin (MSB) 840, dated 

June 19, 1986, or Piper Service Letter (SL) 

588, dated September 3, 1971, compliance; or 

kit, Piper P/N 760–545V installation. 

TABLE 2 TO PARAGRAPH (G) OF THIS AD—KIT, PIPER P/N 760–545V, APPLICABILITY

Model Serial Nos. 

PA–28–140 ......................... 28–7125001 through 28–7125666. 

PA–28–180 ......................... 28–7105001 through 28–7105259. 

PA–28R–180 ...................... 28R–7130001 through 28R–7130038. 

PA–28R–200 ...................... 28R–7135001 through 28R–7135254. 

(2) Review the prior logbook entries of the 

airplanes identified in table 3 to paragraph 

(g) of this AD for documentation of Piper 

Mandatory Service Bulletin (MSB) 840, dated 

June 19, 1986, or Piper Service Letter (SL) 

588, dated September 3, 1971 compliance; or 

kit, Piper P/N 760–546V installation. 

TABLE 3 TO PARAGRAPH (G) OF THIS AD—KIT, PIPER P/N 760–546V, APPLICABILITY

Model Serial Nos. 

PA–28–140 ......................... 28–20000 through 28–26946. 

PA–28–150/160/180 ........... 28–01 through 28–5859. 

PA–28R–180 ...................... 28R–30000 through 28R–31270. 

PA–28R–200 ...................... 28R–35001 through 28R–35820. 

(3) Visually examine the fuel selector cover 

installed on the applicable airplanes 

referenced in table 1 to paragraph (c) of this 

AD. Airplanes that have installed the kit, 

Piper P/N 760–545V or 760–546V, will 

have a fuel selector cover with a silver-gray, 

spring loaded, metal stop located at the 5 

o’clock position, approximately 1.75 inches 

from the center of the fuel selector cover. 

(h) Replacement 

If after doing the inspections required in 

paragraph (g)(1), (g)(2), and (g)(3) of this AD 

you do not find fuel selector valve kit, Piper 

P/N 760–545V or P/N 760–546V, installed on 

the airplane, replace the fuel selector valve 

as specified in paragraphs (h)(1) and (h)(2) of 

this AD: 

(1) For Model PA–28–140 airplanes, serial 

numbers (S/Ns) 28–7125001 through 28– 

7125666; Model PA–28–180 airplanes, S/Ns 

28–7105001 through 28–7105259; Model PA– 

28R–180 airplanes, S/Ns 28R–7130001 

through 28R–7130038; and Model PA–28R– 

200 airplanes, S/Ns 28R–7135001 through 

28R–7135254: Replace with FuelSelector 

Valve Cover Replacement Kit, Piper P/N 760– 

545V; and Air Vent Flange Kit, Piper P/N 

65735–219. Do the replacement following the 

instructions referenced in Piper MSB No. 

840, dated June 19, 1986. 

(2) For Model PA–28–140 airplanes, S/Ns 

28–20000 through 28–26946; Model PA–28– 

150/160/180 airplanes, S/Ns 28–01 through 

28–5859; Model PA–28R–180 airplanes, S/Ns 

28R–30000 through 28R–31270; and Model 

PA–28R–200 airplanes, S/Ns 28R–35001 

through 28R–35820: Replace with Fuel 

Selector Valve Cover Replacement Kit, Piper 

P/N 760–546V. Do the replacement following 

the instructions referenced in Piper MSB No. 

840, dated June 19, 1986. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta 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. 

(j) Related Information 

(1) For more information about this AD, 

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. 

(2) For service information identified in 

this AD, contact Piper Aircraft, Inc., 2926 

Piper Drive, Vero Beach, Florida 32960; 

telephone: (772) 567–4361; fax: (772) 978– 

6573; email: customer.service@piper.com; 

Internet: www.piper.com/home/pages/

Publications.cfm. 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. 

Issued in Kansas City, Missouri, on August 

14, 2013. 

John Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–20328 Filed 8–19–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0734; Directorate 

Identifier 2012–SW–080–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) for 

Bell Helicopter Textron (Bell) Model 

222, 222B, 222U, 230, and 430 

helicopters. The existing AD currently 

requires inspecting parts of the main 

rotor hydraulic servo actuator (servo 

actuator) for certain conditions and 


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51124 Federal Register / Vol. 78, No. 161 / Tuesday, August 20, 2013 / Proposed Rules 

replacing any unairworthy parts before 

further flight. Since we issued the AD, 

a new stainless steel piston rod has been 

manufactured. We propose requiring the 

installation of a servo actuator assembly 

with this piston rod and setting an 

interval for the next overhaul at 10,000 

hours time-in-service (TIS) or 10 years, 

whichever comes first. The proposed 

actions are intended to detect pitting or 

penetration of the base metal of the 

piston rod that could lead to the piston 

rod’s failure, the servo actuator’s failure, 

and the loss of helicopter control. 

DATES: We must receive comments on 

this proposed AD by October 21, 2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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 proposed AD, the 

foreign authority’s AD, the economic 

evaluation, any comments received and 

other information. The street address for 

the Docket Operations Office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

For service information identified in 

this proposed AD, contact Bell 

Helicopter Textron, 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 service information at the FAA, 

Office of the Regional Counsel, 

Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas 

76137. 

FOR FURTHER INFORMATION CONTACT: Matt 

Wilbanks, Aviation Safety Engineer, 

Rotorcraft Certification Office, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

matt.wilbanks@faa.gov. 

SUPPLEMENTARY INFORMATION:

Comments Invited 

We invite you to participate in this 

rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

On November 24, 2010, we published 

AD 2010–19–51, Amendment 39–16523 

(75 FR 71540), for Bell Model 222, 222B, 

222U, 230, and 430 helicopters. AD 

2010–19–51 requires inspecting parts of 

the servo actuator for certain conditions 

and replacing any unairworthy parts 

before further flight. AD 2010–19–51 

was prompted by a collective servo 

actuator malfunction. A subsequent 

investigation revealed that the output 

piston rod assembly had fractured at the 

threaded end because of corrosion 

cracking. The investigation also showed 

a nonconforming grind relief on a 

separate piston rod. The actions of AD 

2010–19–51 were intended to detect 

corrosion or a nonconforming piston rod 

that, if not corrected, could result in the 

failure of the piston rod, failure of the 

servo actuator, and subsequent loss of 

the helicopter. 

Actions Since Existing AD Was Issued 

Since we issued AD 2010–19–51 (75 

FR 71540, November 24, 2010), 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, issued Canadian AD No. 

CF–2010–29R1, dated July 26, 2012, to 

correct an unsafe condition for Bell 

Model 222, 222B, 222U, 230, and 430 

helicopters with servo actuator part 

number (P/N) 222–382–001–107. TCCA 

AD No. CF–2010–29R1 supersedes AD 

No. CF–2010–29, dated August 26, 

2010. The original TCCA AD required a 

one-time inspection of the servo 

actuator for corrosion or a crack, and if 

needed, repair of the servo actuator. AD 

No. CF–2010–29 also set intervals for a 

required overhaul of the servo actuator, 

depending on the primer or plating on 

the piston rod. 

TCCA’s subsequent AD No. CF–2010– 

29R1 requires an inspection of the servo 

actuator and either overhauling or 

replacing the piston rod with a stainless 

steel piston rod. Replacement of the 

piston rod extends the overhaul interval 

of the servo actuator to 10,000 hours TIS 

or 10 years, whichever comes first. AD 

No. CF–2010–29R1 allows different 

compliance times for overhaul or 

replacement of the piston rod, 

depending on the condition of the 

piston rod when inspected. 

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, its 

technical representative, has notified us 

of the unsafe condition described in its 

AD. We are proposing this AD because 

we evaluated all known relevant 

information and determined that an 

unsafe condition is likely to exist or 

develop on other products of the same 

type design. 

Related Service Information 

We reviewed Bell Alert Service 

Bulletin (ASB) 222–11–111 for Model 

222 and 222B helicopters, ASB 222U– 

11–82 for Model 222U helicopters, ASB 

230–11–43 for Model 230 helicopters, 

and ASB 430–11–46 for Model 430 

helicopters, all Revision A and all dated 

June 22, 2012. The ASBs contain, and 

require compliance with, Woodward 

HRT Service Bulletin 141600–67–03, 

dated February 14, 2012, to upgrade the 

servo actuator by replacing the piston 

rod and then re-identifying the servo 

actuator dash number with ‘‘–111FM.’’ 

The compliance time for upgrading the 

servo actuator varies depending on the 

color and amount of corrosion found 

and type of plating on the piston rod. 

The Bell ASBs also provide an 

alternative inspection and procedure for 

servo actuator P/N 222–382–001–107 

which have not reached certain hours 

TIS and where the servo actuator cannot 

be upgraded. 

TCCA classified these ASBs as 

mandatory and issued AD No. CF– 

2010–29R1, dated July 26, 2012, to 


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Federal Register / Vol. 78, No. 161 / Tuesday, August 20, 2013 / Proposed Rules 51125 

ensure the continued airworthiness of 

these helicopters. 

Proposed AD Requirements 

This proposed AD would supersede 

AD 2010–19–51, Amendment 39–16523 

(75 FR 71540, November 24, 2010) and 

would require within 5 hours time-inservice (TIS), inspecting servo actuator, 

P/N 222–382–001–107, using a 10X or 

higher power magnifying glass to 

determine whether the piston rod has 

any pitting or penetration of the base 

metal. 

If the piston rod has pitting or 

penetration of the base metal, the 

proposed AD would require, before 

further flight, replacing the servo 

actuator with servo actuator P/N 222– 

382–001–111 or P/N 222–382–001– 

111FM. Thereafter, the proposed AD 

would require overhauling servo 

actuator P/N 222–382–001–111 or P/N 

222–382–001–111FM at intervals not to 

exceed 10 years or 10,000 hours TIS, 

whichever comes first. 

Differences Between the Proposed AD 

and the TCCA AD 

This proposed AD differs from the 

TCCA AD as follows: 

The TCCA AD sets three different 

timelines or time-in-service 

requirements for the overhaul or 

upgrade of the applicable servo 

actuators, depending on the damage and 

type of material applied to protect the 

piston rod. 

We would require replacing, before 

further flight, the piston rod if it has 

pitting or any penetration of the base 

metal. 

The TCCA AD requires returning 

parts to the manufacturer, and this 

proposed AD would not. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 146 helicopters of U.S. 

Registry and that labor costs average $85 

an hour. Based on these estimates, we 

expect the following costs: 

• Inspecting the servo actuators 

would require 4 work-hours for a labor 

cost of $340 per helicopter, and $49,640 

for the U.S. fleet. 

• Overhauling the servo actuators 

would require 8 work-hours for a labor 

cost of $680. Parts would cost $11,900 

for a total cost of $12,580 per helicopter. 

• Replacing the servo actuators would 

require 8 hours work-hours for a labor 

cost of $680. Parts would cost $35,700 

for a total cost of $36,380 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 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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, I certify 

this proposed regulation: 

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 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 proposed 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 Amendment 39–16523, 75 FR 

71540, and adding the following new 

airworthiness directive (AD): 

Bell Helicopter Textron: Docket No. FAA– 

2013–0734; Directorate Identifier 2012–SW– 

080–AD. 

(a) Applicability 

This AD applies to Bell Helicopter Textron 

Canada (Bell) Model 222, 222B, 222U, 230, 

and 430 helicopters, with a main rotor 

hydraulic servo actuator (servo actuator), part 

number (P/N) 222–382–001–107, installed, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

pitting or any other penetration of the base 

metal on the output piston rod assembly. 

This condition could lead to failure of the 

piston rod, failure of the servo actuator, and 

subsequent loss of helicopter control. 

(c) Affected ADs 

This AD supersedes AD 2010–19–51, 

Amendment 39–16523 (75 FR 71540, 

November 24, 2010). 

(d) Comments Due Date 

We must receive comments by October 21, 

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 5 hours time-in-service (TIS), 

inspect servo actuator, P/N 222–382–001– 

107, using a 10X or higher power magnifying 

glass to determine whether the piston rod has 

any pitting or penetration of the base metal. 

(2) If the piston rod has pitting or any 

penetration of the base metal, replace with 

servo actuator P/N 222–382–001–111 or P/N 

222–382–001–111FM, before further flight. 

Thereafter, overhaul servo actuator P/N 222– 

382–001–111 or P/N 222–382–001–111FM at 

intervals not to exceed 10 years or 10,000 

hours TIS, whichever comes first. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Matt Wilbanks, 

Aviation Safety Engineer, Rotorcraft 

Certification Office, Rotorcraft Directorate, 

FAA, 2601 Meacham Blvd., Fort Worth, 

Texas 76137; telephone (817) 222–5110; 

email matt.wilbanks@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. 


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51126 Federal Register / Vol. 78, No. 161 / Tuesday, August 20, 2013 / Proposed Rules 

(h) Additional Information 

(1) The subject of this AD is addressed in 

Transport Canada Civil Aviation AD No. CF– 

2010–29R1, dated July 26, 2012. A copy of 

this document is available for review in 

Docket No. FAA–2013–0734 on the Internet 

at http://www.regulations.gov. 

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

222–11–111 for Model 222 and 222B 

helicopters, ASB No. 222U–11–82 for Model 

222U helicopters, ASB No. 230–11–43 for 

Model 230 helicopters, and ASB No. 430–11– 

46 for Model 430 helicopters, all Revision A 

and all dated June 22, 2012, contain 

information to replace and overhaul the servo 

actuator. You may review 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: 6730, Rotorcraft Servo System. 

Issued in Fort Worth, Texas, on August 12, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–20309 Filed 8–19–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0735; Directorate 

Identifier 2013–SW–014–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron, Inc. (Bell) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for Bell 

Model 204B helicopters. This proposed 

AD would require inspecting the tail 

rotor (T/R) cable assembly for an 

incorrectly machined body. This 

proposed AD is prompted by a report 

from Bell that a defective body on the 

cable prevents the barrel assembly from 

fully engaging in the body cavity. The 

proposed actions are intended to 

prevent disengagement of the cable from 

the barrel, failure of the T/R pitch 

control, and subsequent loss of control 

of the helicopter. 

DATES: We must receive comments on 

this proposed AD by October 21, 2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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 proposed AD, the 

economic evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

Office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

For service information identified in 

this proposed 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 the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

FOR FURTHER INFORMATION CONTACT: 

Helene Gandy, Aviation Safety 

Engineer, Rotorcraft Certification Office, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5413; email 

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

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to participate in this 

rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

We received a report from Bell that a 

number of cable assemblies, part 

number (P/N) 205–001–720–001, were 

manufactured with a defective body, P/ 

N 205–001–742–001. Bell states the 

bodies were incorrectly machined with 

a ‘‘false cut,’’ preventing the barrel 

assembly, P/N 0301245, from fully 

engaging with the body cavity. This 

condition, combined with a failure of 

the lockwire securing the barrel and the 

cable, could result in disengagement of 

the cable, T/R pitch control failure in a 

fixed position, and subsequent loss of 

control of the helicopter. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all known relevant 

information and determined that an 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

the same type design. 

Related Service Information 

We reviewed Bell Alert Service 

Bulletin (ASB) No. 204B–12–68, dated 

October 10, 2012, which describes 

procedures for inspecting the barrel 

assembly to determine if an incorrectly 

machined body is installed. If an 

incorrectly machined body is installed, 

the ASB specifies replacing the cable 

assembly. The ASB further specifies 

inspecting the barrel assembly and cable 

connection daily until the cable 

assembly is replaced. 

Proposed AD Requirements 

This proposed AD would require 

inspecting each cable assembly, within 

25 hours time-in-service (TIS), to 

determine if an incorrectly machined 

body is installed. If an incorrectly 

machined body is installed, the 

proposed AD would require replacing 

the cable assembly within 100 hours 

TIS. Until the cable assembly is 

replaced, this proposed AD would 

require inspecting the assembly for 

separation daily. 


sroberts on DSK5SPTVN1PROD with PROPOSALS