34332 Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Proposed Rules 

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 adding 

the following new airworthiness 

directive (AD): 

B/E Aerospace: Docket No. FAA–2015–2134; 

Directorate Identifier 2015–CE–012–AD. 

(a) Comments Due Date 

We must receive comments by July 31, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to B/E Aerospace 

Protective Breathing Equipment (PBE), part 

number 119003–11, that is installed on 

airplanes. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 35; Oxygen. 

(e) Unsafe Condition 

This AD was prompted by reports of a 

compromise in the vacuum seal of the pouch 

that contains the PBE. We are issuing this AD 

to correct the unsafe condition on these 

products. 

(f) Compliance 

Unless already done, comply with 

paragraphs (g) through (h) of this AD. 

(g) Inspection 

(1) Within 3 months after the effective date 

of this AD, while still in the stowage box, 

physically inspect the PBE pouch to 

determine if it has an intact vacuum seal. 

Repetitively thereafter, inspect every 12 

months. Do these inspections following 

paragraph III.A.1. of the Accomplishment 

Instructions in B/E Aerospace Service 

Bulletin No. 119003–35–011. Rev. 000, dated 

February 4, 2015. 

(2) Within 36 months after the first 

inspection required in paragraph (g)(1) of this 

AD, remove the PBE pouch from the stowage 

box and physically inspect the PBE pouch to 

determine if it has an intact vacuum seal. 

Repetitively thereafter, inspect every 36 

months. Do these inspections following 

paragraph III.A.2. of the Accomplishment 

Instructions in B/E Aerospace Service 

Bulletin No. 119003–35–011, Rev. 000, dated 

February 4, 2015. 

(h) Replacement 

If a PBE pouch is found that does not have 

an intact vacuum seal during any inspection 

required in paragraphs (g)(1) and (g)(2) of this 

AD, before further flight, replace the PBE 

with an FAA-approved PBE contained in a 

vacuum sealed pouch. After the replacement, 

continue with the inspections required in 

paragraphs (g)(1) and (g)(2) of this AD. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Wichita Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (j)(1) 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 David Enns, Aerospace Engineer, 

Wichita ACO, FAA, 1801 S. Airport Road, 

Room 100, Wichita, Kansas 67209; phone: 

(316) 946–4147; fax: (316) 946–4107; email: 

david.enns@faa.gov. 

(2) For service information identified in 

this AD, contact B/E Aerospace, Inc., 10800 

Pflumm Road, Commercial Aircraft Products 

Group, Lenexa, Kansas 66215; telephone: 

(913) 338–9800; fax: (913) 338–8419; 

Internet: www.beaerospace.com. You may 

review this 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. 

Issued in Kansas City, Missouri, on June 5, 

2015. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2015–14286 Filed 6–15–15; 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 Canada Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (SNPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for Bell Helicopter Textron Canada 

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

430 helicopters, which proposed to 

require replacing certain servo actuators 

before further flight. The NPRM was 

prompted by a collective servo actuator 

malfunction. This action revises the 

NPRM by adding new actions. Since 

these actions impose an additional 

burden over that proposed in the NPRM, 

we are reopening the comment period to 

allow the public the chance to comment 

on these proposed changes. 

DATES: We must receive comments on 

this SNPRM by August 17, 2015. 

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 

Transport Canada Civil Aviation (TCCA) 

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 Woodward HRT and Bell service 

information identified in this proposed 

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. 

FOR FURTHER INFORMATION CONTACT: Matt 

Wilbanks, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

matt.wilbanks@faa.gov. 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
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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 issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to remove AD 2010–19–51, 

Amendment 39–16523 (75 FR 71540, 

November 24, 2010) and add a new AD. 

AD 2010–19–51 applies to Bell Model 

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

helicopters and 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 

due to a nonconforming grind relief on 

a separate piston rod and corrosion 

cracking at the threaded end of the 

output piston rod assembly. 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 helicopter control. 

The NPRM was published in the 

Federal Register on August 20, 2013 (78 

FR 51123). The NPRM proposed 

inspecting servo actuator, part number 

(P/N) 222–382–001–107, for pitting or 

penetration of the base metal of the 

piston rod. If the piston rod has pitting 

or any penetration of the base metal, the 

NPRM proposed replacing the servo 

actuator with servo actuator P/N 222– 

382–001–111 or P/N 222–382–001– 

111FM, before further flight. Thereafter, 

the NPRM proposed requiring 

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. 

Comments 

After our NPRM (78 FR 51123, August 

20, 2013) was published, we received 

comments from one commenter. 

Request 

Bell noted that the AD does not 

mandate replacement of servo actuator 

P/N 222–382–001–107 with servo 

actuator part number P/N 222–382–001– 

111 if no pitting or penetration of the 

base metal is found during the 

inspection, and requested that we 

include the replacement provisions in 

Part 1 of Bell Alert Service Bulletin 

(ASB) 430–11–46, Revision A, dated 

June 22, 2012. 

We agree. In light of Bell’s comment, 

we have determined that our AD should 

retain all of the inspection requirements 

of AD 2010–19–51 (75 FR 71540, 

November 24, 2010) and also include 

compliance times for replacing servo 

actuator P/N 222–382–001–107 with 

servo actuator part number P/N 222– 

382–001–111 or –111FM based upon the 

results of the inspection, as specified in 

Revision A of the ASB. We have 

changed the Required Actions 

accordingly and are consequently 

proposing this SNPRM. 

FAA’s Determination 

We are proposing this SNPRM 

because we evaluated all known 

relevant information and determined 

that an unsafe condition is likely to 

exist or develop on other products of 

these same type designs. Certain 

changes described above expand the 

scope of the original NPRM. As a result, 

we have determined that it is necessary 

to reopen the comment period to 

provide additional opportunity for the 

public to comment on this SNPRM. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Woodward HRT Service 

Bulletin 141600–67–02, dated August 

18, 2010, which provides instructions 

for disassembling the servo actuator and 

for cleaning and inspecting the piston 

rod and nut. This service information is 

reasonably available because the 

interested parties have access to it 

through their normal course of business 

or by the means identified in the 

ADDRESSES section of this SNPRM. 

Other Related Service Information 

We also reviewed Bell 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 reidentifying the servo actuator dash 

number with ‘‘–111FM.’’ The 

compliance time for upgrading the servo 

actuator varies depending on the results 

of the inspections required by 

Woodward HRT Service Bulletin 

141600–67–02, dated August 18, 2010. 

The Bell ASBs also provide an 

alternative inspection procedure for 

servo actuator P/N 222–382–001–107 

that has 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 

ensure the continued airworthiness of 

these helicopters. 

Proposed Requirements of the SNPRM 

This proposed AD would require 

before further flight: 

• Disassembling each servo actuator. 

• Cleaning the piston rod and nut, 

and inspecting the grind relief 

configuration for the piston rod and nut. 

If the grind relief is unacceptable, 

replacing the piston rod and nut. 

• Using a 10× or higher magnifying 

glass, visually inspecting the nut for any 

corrosion or any damage to the threads, 

and replacing the nut if you find any 

corrosion or any damage to the threads. 

• Using a 10× or higher magnifying 

glass, visually inspecting the piston rod 

for any corrosion, lack of cadmium 

plate, or damage. 

• If there is any corrosion or lack of 

cadmium plate or damage in certain 

critical areas, replacing the servo 

actuator with P/N 222–382–001–111 or 

P/N 222–382–001–111FM before further 

flight. 

• If there is any corrosion or lack of 

cadmium plate in areas that are not 

critical areas, reworking the piston rod, 

inspecting for bare base metal, and 

reassembling the servo actuator. 

Replacing the servo actuator with P/N 

222–382–001–111 or P/N 222–382–001– 

111FM would be required within 1,200 

hours time-in-service (TIS) or 1 year, 

whichever occurs first. 

• If there is any corrosion that is red 

or orange in color, magnetic particle 

inspecting the piston rod for a crack, 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
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and replacing the servo actuator with P/ 

N 222–382–001–111 or P/N 222–382– 

001–111FM before further flight if there 

is a crack or within 2,400 hours TIS or 

2 years, whichever occurs first, if there 

is no crack. 

• If there is no corrosion, lack of 

cadmium plate, or damage, inspecting 

for bare base metal, and reassembling 

the servo actuator. Replacing the servo 

actuator with P/N 222–382–001–111 or 

P/N 222–382–001–111FM would be 

required within 3,000 hours TIS or 4 

years, whichever occurs first. 

• 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 

occurs first. 

Differences Between the Proposed AD 

and the TCCA AD 

The TCCA AD requires inspecting 

each servo actuator to determine the 

condition of the piston rod assembly no 

later than 5 hours upon receiving the 

original issue of its AD. This proposed 

AD would require inspecting each servo 

actuator to determine the condition of 

the piston rod assembly before further 

flight. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 146 helicopters of U.S. 

Registry and that labor costs average $85 

a work-hour. Based on these estimates, 

we expect the following costs: 

• Inspecting a servo actuator would 

require 4 work-hours per actuator for a 

labor cost of $340. No parts would be 

needed for a total cost of $1,020 per 

helicopter and $148,920 for the U.S. 

fleet given 3 actuators per helicopter. 

• Replacing a servo actuator would 

require 8 work-hours for a labor cost of 

$680. Parts would cost $35,700 for a 

total cost of $36,380 per actuator. 

• Overhauling the servo actuator 

would require 8 work-hours for a labor 

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

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

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 adding 

the following new airworthiness 

directive (AD): 

Bell Helicopter Textron Canada: 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 

corrosion or a nonconforming grind relief on 

the output piston rod assembly (piston rod). 

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 August 17, 

2015. 

(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 

Before further flight: 

(1) Disassemble each servo actuator to gain 

access to the piston rod as shown in Figures 

1 through 5 and by following the 

Accomplishment Instructions, paragraph 

3.A., Part I., of Woodward HRT Alert Service 

Bulletin No. 141600–67–02, Revision 0, 

dated August 18, 2010 (Woodward ASB). 

(2) Clean the entire piston rod and nut 

using acetone and a nylon bristle brush 

removing all contaminates to allow for 

inspection. Inspect the grind relief 

configuration for the piston rod and nut as 

shown in Figure 6 of the Woodward ASB. If 

the grind relief is unacceptable as shown in 

Figure 6, replace the piston rod and the nut 

with airworthy parts. 

(3) Using a 10× or higher magnifying glass, 

visually inspect the nut for any corrosion or 

any damage to the threads. If you find any 

corrosion or any damage to the threads, 

replace the nut with an airworthy nut. 

(4) Using a 10× or higher magnifying glass, 

visually inspect the piston rod as shown in 

Figure 7 of the Woodward ASB for any 

corrosion, visible lack of cadmium plate 

(gold or gray color), or damage to the piston 

rod. For the purposes of this AD, damage to 

the piston rod is defined as pitting, a visible 

scratch, a crack, or a visible abrasion. 

(i) If there is any corrosion or visible lack 

of cadmium plate or any damage to the 

piston rod in the Critical Areas as shown in 

Figure 7 of the Woodward ASB, replace the 

servo actuator with servo actuator P/N 222– 

382–001–111 or P/N 222–382–001–111FM 

before further flight. 

(ii) If there is any corrosion or visible lack 

of cadmium plate on the piston rod in areas 

that are not considered Critical Areas as 

shown in Figure 7 of the Woodward ASB, 

rework the piston rod by removing any 

surface corrosion that has not penetrated into 

the base material by lightly buffing. Clean the 

part using acetone and a nylon bristle brush 

to remove any residue. Comply with 

paragraphs (f)(5) through (f)(7) of this AD. 

Within 1,200 hours time-in-service (TIS) or 1 

year, whichever occurs first, replace the 


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Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Proposed Rules 34335 

servo actuator with servo actuator P/N 222– 

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

(iii) If there is any corrosion that is red or 

orange in color, magnetic particle inspect the 

piston rod for a crack. 

(A) If there is a crack, replace the servo 

actuator with servo actuator, P/N 222–382– 

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

further flight. 

(B) If there is no crack, comply with 

paragraphs (f)(5) through (f)(7) of this AD. 

Within 2,400 hours TIS or 2 years, whichever 

occurs first, replace the servo actuator with 

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

222–382–001–111FM. 

(iv) If there is no corrosion, visible lack of 

cadmium plate, or damage to the piston rod, 

comply with paragraphs (f)(5) through and 

(f)(7) of this AD. Within 3,000 hours TIS or 

4 years, whichever occurs first, replace the 

servo actuator with servo actuator P/N 222– 

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

(5) Inspect the portion of the piston rod for 

any absence of cadmium plating (bare base 

metal), as shown in Figure 7 of the 

Woodward ASB. If there is any bare base 

metal on the piston rod in this area, apply 

brush cadmium plating to all bare and 

reworked areas using SPS5070 or equivalent 

0.0002 to 0.0005 inch thick and rework the 

piston rod by following the Accomplishment 

Instructions, paragraph C., Part III, C.1.1.1. 

through C.1.1.3., of the Woodward ASB. 

(6) Reassemble the servo actuator by 

following the Accomplishment Instructions, 

paragraph C, Part III, 1.1.4. through 3.3.4. of 

the Woodward ASB. 

(7) 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 occurs first. 

(g) Credit for Actions Previously Completed 

Compliance with the Woodward ASB or 

with AD 2010–19–51 (75 FR 71540, 

November 24, 2010) before the effective date 

of this AD is considered acceptable for 

compliance with the corresponding 

inspections specified in paragraph (f) of this 

AD. If you replaced the piston rod pursuant 

to the Woodward ASB or paragraph (d)(1) or 

(d)(3) of AD 2010–19–51, apply the 

requirements of paragraph (f)(4)(iv) of this 

AD. 

(h) 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, Regulations and 

Policy Group, 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. 

(i) Additional Information 

(1) 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, which are not 

incorporated by reference, contain additional 

information about the subject of this AD. For 

Woodward HRT and Bell 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 a copy of the 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 

the Transport Canada Civil Aviation (TCCA) 

AD No. CF–2010–29R1, dated July 26, 2012. 

You may view the TCCA AD on the Internet 

at http://www.regulations.gov in Docket No. 

FAA–2013–0734. 

(j) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6730, Rotorcraft Servo System. 

Issued in Fort Worth, Texas, on May 29, 

2015. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–14278 Filed 6–15–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0105; Directorate 

Identifier 2008–SW–58–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (Previously Eurocopter 

France) (Airbus Helicopters) 

Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This document proposes 

superseding Airworthiness Directives 

(AD) 2000–05–17 and AD 2001–04–12, 

which apply to Eurocopter France (now 

Airbus Helicopters) Model EC120B 

helicopters. AD 2000–05–17 and AD 

2001–04–12 require repetitive visual 

checks of the engine-to-main gearbox 

(MGB) coupling tube assembly 

(coupling tube) for a crack and replacing 

any cracked tube with an airworthy 

tube. This proposed AD would require 

removing certain engine mount parts 

from service, measuring the height of 

the engine mounting base for certain 

helicopters, replacing the engine mount 

if a certain height is exceeded, 

inspecting the flared coupling on certain 

helicopters for a crack, and replacing 

the coupling if it is cracked. Since we 

issued AD 2000–05–17 and AD 2001– 

04–12, there have been reports of 

additional cracks in coupling tubes. The 

proposed actions are intended to 

prevent coupling tube failure, loss of 

engine drive, and a subsequent forced 

landing of the helicopter. 

DATES: We must receive comments on 

this proposed AD by August 17, 2015. 

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 

Direction Generale de L’Aviation Civile 

(DGAC) 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 Airbus 

Helicopters, Inc., 2701 N. Forum Drive, 

Grand Prairie, Texas 75052; telephone 

(972) 641–0000 or (800) 232–0323; fax 

(972) 641–3775; or at http://

www.airbushelicopters.com/techpub. 

You may review the 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: 

James Blyn, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS