Federal Register / Vol. 77, No. 23 / Friday, February 3, 2012 / Proposed Rules 5425 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0084; Directorate 

Identifier 2010–SW–089–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Limited 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the Bell 

Helicopter Textron Canada Limited 

(BHTC) Model 427 helicopters. This 

proposed AD is prompted by a review 

of the tailboom attachment installation, 

which revealed that the torque value of 

the bolts specified in the BHTC Model 

427 Maintenance Manual and applied 

during manufacturing was incorrect and 

exceeded the torque range 

recommended for the bolts. The 

proposed actions are intended to 

prevent an over-torque of the tailboom 

attachment bolt (bolt), bolt failure, loss 

of the tailboom, and subsequent loss of 

control of the helicopter. 

DATES: We must receive comments on 

this proposed AD by April 3, 2012. 

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 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 copies of 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: 

Sharon Miles, Aerospace Engineer, 

FAA, Regulations and Policy Group, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone: (817) 222–5122; email 

sharon.y.miles@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 

Transport Canada (TC), which is the 

aviation authority for Canada, has 

issued AD CF–2010–32, dated 

September 30, 2010 (AD CF–2010–32), 

to correct an unsafe condition for the 

BHTC Model 427 helicopters, serial 

numbers (S/Ns) 56001 through 56084, 

and S/Ns 58001 and 58002. TC advises 

that a review of the tailboom attachment 

installation determined that the torque 

value of the bolts specified in the BHTC 

Model 427 Maintenance Manual and 

applied during manufacturing exceeded 

the torque range recommended for the 

bolts. They state that this situation, if 

not corrected, could lead to a bolt 

failure, detachment of the tailboom, and 

loss of control of the helicopter. 

FAA’s Determination 

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 bilateral 

agreement, TC has kept the FAA 

informed of the situation described 

above. We are issuing this AD because 

we evaluated all information provided 

by TC and determined the unsafe 

condition is likely to exist or develop on 

other helicopters of these same type 

designs. 

Related Service Information 

BHTC has issued Alert Service 

Bulletin No. 427–10–31, dated March 1, 

2010 (ASB), which specifies installing 

new attachment hardware with a 

reduced torque value. This ASB 

specifies determining the torque of the 

newly installed bolts and nuts every 1 

to 5 flight hours until torque stabilizes 

at all locations, and thereafter at 

intervals not to exceed 300 flight hours. 

TC classified this ASB as mandatory 

and issued AD CF–2010–32 to ensure 

the continued airworthiness of these 

helicopters. 

Proposed AD Requirements 

This proposed AD would require, 

within 150 hours time-in-service (TIS) 

or 90 days, whichever occurs first, the 

following actions: 

• Remove the left upper bolt, 

washers, and nut. Install the new bolt, 

part number (P/N) NAS627–27; 

washers, P/N 140–007–29S25E6 and 

P/N NAS1149G0732P; and new nut, 

P/N 42FLW–720. Run the nut onto the 

threads of the mating bolt with a torque 

wrench and measure the existing tare. 

Any bolt and nut used must have a 

minimum tare of 14 inch/lbs. Torque 

the nut and coat the bolt head, nut, and 

washers with appropriate corrosion 

preventive compound to seal the joint. 

Repeat these actions at the three 

remaining bolt locations. 

• After installation of the new 

attachment hardware, at intervals of no 

less than 1 hour TIS but not exceeding 

5 hours TIS, determine the torque of 

each nut until torque stabilizes at each 

attachment location. Thereafter, 

determine the torque of each nut at 

intervals not to exceed 300 hours TIS. 

The actions would be required to be 

accomplished by following specified 

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5426 Federal Register / Vol. 77, No. 23 / Friday, February 3, 2012 / Proposed Rules 

portions of the service bulletin 

described previously. 

Differences Between This Proposed AD 

and the TC AD 

The differences between this 

proposed AD and the TC AD are as 

follows: 

• The TC AD applies to the BHTC 

Model 427 helicopter, serial numbers 

58001 and 58002; however, this 

proposed AD is not applicable to the 

BHTC Model 427 helicopters with these 

serial numbers because they are not 

eligible for an FAA Certificate of 

Airworthiness. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 28 helicopters of U.S. 

registry. We estimate it would take 

about 2.0 work-hours per helicopter to 

replace the hardware, and 1.0 workhour per helicopter to determine the 

recurring torque value at an average 

labor rate of $85 per work hour. 

Required parts would cost about $488 

per helicopter. Based on these figures, 

we estimate for the first year the total 

cost per helicopter to be $913, and the 

total cost impact on U.S. operators to be 

$25,564. This estimated total cost 

assumes attachment hardware will be 

replaced on all affected helicopters, the 

torque will be considered stabilized 

after one torquing, and the recurring 300 

hour TIS torque determination will be 

accomplished twice a year. 

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 Limited 

(BHTC): Docket No. FAA–2012–0084; 

Directorate Identifier 2010–SW–089–AD. 

(a) Applicability. This AD applies to model 

427 helicopters, serial numbers 56001 

through 56084, certificated in any category. 

(b) Unsafe Condition. This AD defines the 

unsafe condition as an over torque of the 

tailboom attachment bolt (bolt). This 

condition could result in bolt failure, loss of 

the tailboom, and subsequent loss of control 

of the helicopter. 

(c) 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. 

(d) Required Actions. 

(1) Within 150 hours time-in-service (TIS) 

or 90 days, whichever occurs first, replace 

the tailboom attachment hardware 

(attachment hardware) as follows: 

(i) Remove the left upper bolt, washers, 

and nut. 

(ii) Install a new bolt, part number (P/N) 

NAS627–27; washer, P/N 140–007–29S25E6; 

washer(s), P/N NAS1149G0732P; and new 

nut, P/N 42FLW–720 in accordance with 

paragraphs 5.a) through 5.d) of the 

Accomplishment Instructions in BHTC Alert 

Service Bulletin No. 427–10–31, dated March 

1, 2010 (ASB). 

(iii) Run the nut onto the threads of the 

mating bolt with a torque wrench and 

measure the existing tare torque. Any bolt 

and nut used must have a minimum tare 

torque value of 14 inch/lbs. 

(iv) Torque the nut in accordance with 

paragraphs 5.f) and 5.g) of the ASB. 

(v) Coat the bolt head, nut, and washers 

with appropriate corrosion preventive 

compound to seal the joint. 

(vi) At each remaining attachment location, 

remove the bolt, washers, and nut, and install 

the attachment hardware in accordance with 

paragraphs (d)(1)(ii) through (d)(1)(v) of this 

AD. 

(2) After installation of the new attachment 

hardware, at intervals of not less than 1 hour 

TIS but not exceeding 5 hours TIS, determine 

the torque of each nut until the torque 

stabilizes at each attachment location. 

Thereafter, at intervals not to exceed 300 

hours TIS, determine the torque of each nut. 

When determining the torque, it is acceptable 

to use the minimum tare torque of 14 inch/ 

lbs (1.58 Nm) added to the minimum torque 

range of 550–560 inch/lbs (62.1 to 63.3 Nm). 

If you remove corrosion preventative 

compound during the torquing, recoat the 

bolt head, nut, and washers with appropriate 

corrosion preventive compound to seal the 

joint. 

(e) Alternative Methods of Compliance 

(AMOC). 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Sharon Miles, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone: (817) 222–5122; fax: (817) 

222–5961, email sharon.y.miles@faa.gov. 

(2) For operations conducted under a Part 

119 operating certificate or under 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. 

(f) Additional Information. The subject of 

this AD is addressed in Transport Canada AD 

CF–2010–32, dated September 30, 2010. 

(g) Subject. Joint Aircraft Service 

Component (JASC) Code: 5302: Rotorcraft 

Tailboom. 

Issued in Fort Worth, Texas, on January 23, 

2012. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–2422 Filed 2–2–12; 8:45 am] 

BILLING CODE 4910–13–P 

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