This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

38797 

Vol. 72, No. 135 

Monday, July 16, 2007 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–28688; Directorate 

Identifier 2005–SW–21–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Model 430 

Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This document proposes 

adopting a new airworthiness directive 

(AD) for Bell Helicopter Textron Canada 

(BHTC) Model 430 helicopters. This 

proposal would require replacing a 

certain servo actuator-to-actuator 

support attachment bolt (bolt) with an 

airworthy bolt. This proposal would 

also require establishing a retirement 

life for certain bolts and recording the 

retirement life on a component history 

card or equivalent record. This proposal 

is prompted by further evaluation of 

certain fatigue-critical parts, resulting in 

establishing a life limit of 5000 hours for 

the affected bolts. The actions specified 

by this proposed AD are intended to 

prevent fatigue failure of the bolt and 

subsequent loss of control of the 

helicopter. 

DATES: Comments must be received on 

or before September 14, 2007. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed AD: 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically; 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically; 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590; 

• Fax: 202–493–2251, or 

• Hand Delivery: West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

You may get the service information 

identified in this proposed AD from 

American Eurocopter Corporation, 2701 

Forum Drive, Grand Prairie, Texas 

75053–4005, telephone (972) 641–3460, 

fax (972) 641–3527. 

You may examine the comments to 

this proposed AD in the AD docket on 

the Internet at http://dms.dot.gov. 

FOR FURTHER INFORMATION CONTACT: 

Sharon Miles, Aviation Safety Engineer, 

FAA, Rotorcraft Directorate, Regulations 

and Guidance Group, Fort Worth, Texas 

76193–0111, telephone (817) 222–5122, 

fax (817) 222–5961. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to submit any written 

data, views, or arguments regarding this 

proposed AD. Send your comments to 

the address listed under the caption 

ADDRESSES. Include the docket number 

‘‘FAA–2007–28688, Directorate 

Identifier 2005–SW–21–AD’’ at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the proposed AD. We will consider all 

comments received by the closing date 

and may amend the proposed AD in 

light of those comments. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this proposed 

rulemaking. Using the search function 

of our docket Web site, you can find and 

read the comments to any of our 

dockets, including the name of the 

individual who sent or signed the 

comment. You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78), or you may visit 

http://dms.dot.gov. 

Examining the Docket 

You may examine the docket that 

contains the proposed AD, any 

comments, and other information in 

person at the Docket Management 

System (DMS) Docket Office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The 

Docket Office (telephone 1–800–647– 

5527) is located at the West Building 

Ground Floor, Room WL–140 at 1200 

New Jersey Avenue, SE., Washington, 

DC. Comments will be available in the 

AD docket shortly after the DMS 

receives them. 

Discussion 

Transport Canada, the airworthiness 

authority for Canada, notified the FAA 

that an unsafe condition may exist on 

BHTC Model 430 helicopters, serial 

numbers 49001 through 49106. 

Transport Canada advises of the need to 

establish a new airworthiness life 

limitation of 5000 hours for the three 

servo actuator support attachment bolts 

and to replace the three affected bolts. 

Bell Helicopter Textron has issued 

Alert Service Bulletin No. 430–05–33, 

dated February 16, 2005 (ASB). The 

ASB introduces a retirement life of 5000 

hours for the bolts. The ASB states that 

since these bolts have not been listed in 

the Helicopter Component Replace 

record, it is difficult to determine with 

accuracy the actual number of hours 

accumulated on fielded bolts. Also, the 

ASB states that Bell has elected to 

replace all the fielded bolts, part 

number (P/N) 50–047C8–31. Transport 

Canada classified this ASB as 

mandatory and issued AD No. CF– 

2005–09, dated April 14, 2005, to ensure 

the continued airworthiness of these 

helicopters in Canada. 

This helicopter model is 

manufactured in Canada and is type 

certificated for operation in the United 

States under the provisions of 14 CFR 

21.29 and the applicable bilateral 

agreement. Pursuant to the applicable 

bilateral agreement, Transport Canada 

has kept us informed of the situation 

described above. The upper three bolts 

of the servo attaching to the collective 

and cyclic levers have a retirement life 

of 5000 hours. However, three identical 

bolts at the lower end of the servos 

attaching to the actuator support do not 

have an established life limit. These 

three bolts may be subject to premature 

failure due to fatigue causing failure of 

the actuators and subsequent loss of 

control of the helicopter. We have 

examined the findings of Transport 


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38798 Federal Register / Vol. 72, No. 135 / Monday, July 16, 2007 / Proposed Rules 

Canada, reviewed all available 

information, and determined that AD 

action is necessary for products of this 

type design that are certificated for 

operation in the United States. 

This previously described unsafe 

condition is likely to exist or develop on 

other helicopters of the same type 

design registered in the United States. 

Further evaluation of certain fatiguecritical parts resulted in establishing a 

life limit of 5000 hours for the affected 

bolts which is intended to prevent 

fatigue failure of the bolt and 

subsequent loss of control of the 

helicopter. Therefore, the proposed AD 

would require the following: 

• Within 150 hours time-in-service 

(TIS), replace all three bolts, P/N 50–

047C8–31, with airworthy, zero-time 

bolts, P/N 50–047C8–31. 

• Revise the Airworthiness 

Limitations section of the maintenance 

manual by establishing a retirement life 

of 5000 hours TIS for each bolt. 

• Record a 5000-hour TIS life limit 

for each bolt on the component history 

card or equivalent record. 

We estimate that this proposed AD 

would affect 54 helicopters of U.S. 

registry. The proposed actions would 

take about 2 work hours per helicopter 

to replace 3 bolts at an average labor rate 

of $80 per work hour. Required parts 

would cost about $243 for each bolt. 

Based on these figures, we estimate the 

total cost impact of the proposed AD on 

U.S. operators to be $48,006, assuming 

that the recordkeeping cost would be 

negligible. 

Regulatory Findings 

We have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. Additionally, 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 above, I 

certify that the 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); and 

3. 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 a draft economic 

evaluation of the estimated costs to 

comply with this proposed AD. See the 

DMS to examine the draft economic 

evaluation. 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

The Proposed Amendment 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the Federal Aviation 

Administration proposes to amend part 

39 of the Federal Aviation Regulations 

(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. Section 39.13 is amended by 

adding a new airworthiness directive to 

read as follows: 

Bell Helicopter Textron Canada: Docket No. 

FAA–2007–28688; Directorate Identifier 

2005–SW–21–AD. 

Applicability 

Model 430 helicopters, serial numbers 

49001 through 49106, with a servo actuatorto-actuator support attachment bolt (bolt), 

part number (P/N) 50–047C8–31, installed, 

which attaches the lower two cyclic servo 

actuators and the lower collective servo 

actuator to the three lower actuator supports, 

certificated in any category. 

Compliance 

Required as indicated, unless 

accomplished previously. 

To prevent fatigue failure of the bolt and 

subsequent loss of control of the helicopter, 

do the following: 

(a) Within 150 hours time-in-service (TIS), 

replace all three affected bolts, as depicted 

for one of these bolts in Figure 1 of this AD, 

with airworthy, zero-time bolts, P/N 50–

047C8–31. 

BILLING CODE 4910–13–P 


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Federal Register / Vol. 72, No. 135 / Monday, July 16, 2007 / Proposed Rules 38799 

(b) This AD revises the Airworthiness 

Limitations section of the maintenance 

manual by establishing a retirement life of 

5000 hours TIS for each bolt. 

(c) Record a 5000-hour TIS life limit for 

each bolt on the component history card or 

equivalent record. 

(d) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact the Safety Management Group, 

FAA, ATTN: Sharon Miles, Aviation Safety 

Engineer, Rotorcraft Directorate, Regulations 

and Guidance Group, Fort Worth, Texas 


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38800 Federal Register / Vol. 72, No. 135 / Monday, July 16, 2007 / Proposed Rules 

76193–0111, telephone (817) 222–5122, fax 

(817) 222–5961 for information about 

previously approved alternative methods of 

compliance. 

Note: The subject of this AD is addressed 

in Transport Canada (Canada) AD No. CF 

2005–09, dated April 14, 2005. 

Issued in Fort Worth, Texas, on July 5, 

2007. 

David A. Downey, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 07–3434 Filed 7–13–07; 8:45 am] 

BILLING CODE 4910–13–C 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27975; Directorate 

Identifier 2007–CE–041–AD] 

RIN 2120–AA64 

Airworthiness Directives; PIAGGIO 

AERO INDUSTRIES S.p.A. Model P–180 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD 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: 

Several aircraft, at the factory, presented 

some debris in the hydraulic fluid of the 

steering system. Investigations revealed that 

some components of the steering system can 

be responsible for the fluid contamination 

because of an initial pollution on their 

manufacturing. 

If not corrected, a contaminated fluid could 

cause malfunction and a possible jamming of 

the steering system. 

The proposed AD would require actions 

that are intended to address the unsafe 

condition described in the MCAI. 

DATES: 

We must receive comments on this 

proposed AD by August 15, 2007. 

ADDRESSES: You may send comments by 

any of the following methods: 

• DOT Docket Web Site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M–

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M–

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.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 

proposed AD, 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. 

FOR FURTHER INFORMATION CONTACT: 

Sarjapur Nagarajan, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329–

4145; fax: (816) 329–4090. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2007–27975; Directorate Identifier 

2007–CE–041–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued Emergency 

Airworthiness Directive EAD No: 2007–

0147–E, dated May 22, 2007 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Several aircraft, at the factory, presented 

some debris in the hydraulic fluid of the 

steering system. Investigations revealed that 

some components of the steering system can 

be responsible for the fluid contamination 

because of an initial pollution on their 

manufacturing. 

If not corrected, a contaminated fluid could 

cause malfunction and a possible jamming of 

the steering system. 

The superseded Airworthiness Directive 

(AD) 2007–0088–E was previously issued to 

address the unsafe condition. 

The present Airworthiness Directive 

expands applicability of this AD to all P.180 

‘Avanti’ series aircraft and the list of 

defective components as listed in revision 1 

of Piaggio Aero Industries Mandatory Service 

Bulletin No 80–0236. This AD also requires 

Temporary Changes to the respective 

Airplane Flight Manual (AFM) and Aircraft 

Maintenance Manual (AMM) and introduces 

procedures to recondition defective units. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Piaggio Aero Industries S.p.A. has 

issued Service Bulletin (Mandatory) N.: 

80–0236 Rev. 1, dated May 15, 2007. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of the Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with this State of 

Design Authority, they have notified us 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This Proposed AD 

and the MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have proposed 

different actions in this AD from those 


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