31172 Federal Register / Vol. 77, No. 102 / Friday, May 25, 2012 / Rules and Regulations 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal-register/

cfr/ibr_locations.html. 

Issued in Kansas City, Missouri, on May 

14, 2012. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–12092 Filed 5–24–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0084; Directorate 

Identifier 2010–SW–089–AD; Amendment 

39–17050; AD 2012–10–01] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Limited 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Bell 

Helicopter Textron Canada Limited 

(BHTC) Model 427 helicopters which 

requires replacing certain tailboom 

attachment hardware and at certain 

intervals thereafter, determining the 

torque of that tailboom attachment 

hardware. This AD was 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 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: This AD is effective June 29, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of June 29, 2012. 

ADDRESSES: For 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 the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

Examining the AD Docket: You may 

examine the AD docket on the Internet 

at http://www.regulations.gov or in 

person at the Docket Operations Office 

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

through Friday, except Federal holidays. 

The AD docket contains this AD, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Sharon Miles, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

sharon.y.miles@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On February 3, 2012, at 77 FR 5425, 

the Federal Register published our 

Notice of Proposed Rulemaking 

(NPRM), which proposed to amend 14 

CFR part 39 to include an AD that 

would apply to BHTC Model 427 

helicopters, serial numbers 56001 

through 56084. That NPRM proposed to 

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 

torque. Any bolt and nut used must 

have a minimum tare torque value 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 not 

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 proposed requirements were 

intended to prevent an over-torque of 

the bolt, bolt failure, loss of the 

tailboom, and subsequent loss of control 

of the helicopter. 

Transport Canada (TC), which is the 

aviation authority for Canada, issued 

Canadian 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. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM. 

FAA’s Determination 

This helicopter model has been 

approved by the aviation authority of 

Canada and is approved for operation in 

the United States. Pursuant to our 

bilateral agreement with Canada, TC, its 

technical representative, has notified us 

of the unsafe condition described in the 

TC AD. We are issuing this AD because 

we evaluated all information provided 

by TC and determined the unsafe 

condition exists and is likely to exist or 

develop on other helicopters of this 

same type design and that air safety and 

the public interest require adopting the 

AD requirements as proposed. 

Differences Between This AD and the 

TC AD 

The differences between this 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 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. 

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 


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Federal Register / Vol. 77, No. 102 / Friday, May 25, 2012 / Rules and Regulations 31173 

the continued airworthiness of these 

helicopters. 

Costs of Compliance 

We estimate that this AD will affect 

28 helicopters of U.S. Registry. 

We estimate that operators may incur 

the following costs in order to comply 

with this AD. It will take about 2.0 

work-hours per helicopter to replace the 

hardware and 1.0 work-hour per 

helicopter to determine the recurring 

torque value at an average labor rate of 

$85 per work-hour. Required parts will 

cost about $488 per helicopter. Based on 

these figures, we estimate the first year 

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 

helicopters identified in this rulemaking 

action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

(3) Will not affect intrastate aviation 

in Alaska to the extent that it justifies 

making a regulatory distinction; and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2012–10–01 Bell Helicopter Textron 

Canada Limited (BHTC): Amendment 

39–17050; 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) Effective Date 

This AD becomes effective June 29, 2012. 

(d) 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. 

(e) 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 (e)(1)(ii) through (e)(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. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Sharon Miles, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

sharon.y.miles@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. 

(g) Additional Information 

The subject of this AD is addressed in 

Transport Canada AD CF–2010–32, dated 

September 30, 2010. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5302, Rotorcraft Tailboom. 

(i) Material Incorporated by Reference 

(1) You must use the specified portions of 

BHTC Alert Service Bulletin No. 427–10–31, 

dated March 1, 2010, to do the specified 

actions required by this AD. The Director of 

the Federal Register approved the 

incorporation by reference of this service 

information under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) For 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– 


wreier-aviles on DSK5TPTVN1PROD with RULES
31174 Federal Register / Vol. 77, No. 102 / Friday, May 25, 2012 / Rules and Regulations 

0272; or at http://www.bellcustomer.com/ 

files/. 

(3) You may review a copy of the 

referenced service information at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137 or at the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at NARA, call (202) 741– 

6030, or go to: http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Fort Worth, Texas, on May 10, 

2012. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–12399 Filed 5–24–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1416; Directorate 

Identifier 2011–NM–156–AD; Amendment 

39–17056; AD 2012–10–07] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model CL–600–2C10 

(Regional Jet Series 700, 701, & 702); 

CL–600–2D15 (Regional Jet Series 705); 

CL–600–2D24 (Regional Jet Series 900); 

and CL–600–2E25 (Regional Jet Series 

1000) airplanes. This AD was prompted 

by reports of deformation of the 

pressure regulator on the oxygen 

cylinder, which was attributed to 

batches of raw material that did not 

meet required tensile strength. This AD 

requires an inspection to determine if 

certain oxygen pressure regulators are 

installed, and replacement of oxygen 

cylinder and regulator assemblies 

(CRAs) containing pressure regulators 

that do not meet required material 

properties. We are issuing this AD to 

prevent elongation of the pressure 

regulator neck, which could result in 

rupture of the oxygen cylinder, and in 

the case of cabin depressurization, 

oxygen would not be available when 

required. 

DATES: This AD becomes effective June 

29, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 29, 2012. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office (ACO), 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7318; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on January 19, 2012 (77 FR 

2662). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

During a routine inspection, deformation 

was found at the neck of the pressure 

regulator body on the oxygen Cylinder and 

Regulator Assemblies (CRA) of a BD–700– 

1A11 aeroplane. 

An investigation by the vendor, Avox 

Systems Inc., revealed that the deformation 

was attributed to two (2) batches of raw 

material that did not meet the required 

tensile strength. This may cause elongation of 

the pressure regulator neck, which could 

result in rupture of the oxygen cylinder, and 

in the case of cabin depressurization, oxygen 

would not be available when required. 

Although there have been no reported 

failures to date on any CL–600–2C10, CL– 

600–2D15, CL–600–2D24 or CL–600–2E25 

aeroplanes, similar oxygen pressure 

regulators, Part Number (P/N) 806370–06, 

could also be installed on the aeroplanes 

listed in the Applicability section of this 

[Transport Canada Civil Aviation (TCCA)] 

directive. 

This [TCCA] directive mandates [an 

inspection for certain serial numbers, and if 

necessary, replacement of the affected oxygen 

CRA in accordance with the accomplishment 

instructions of Bombardier Service Bulletin 

670BA–35–011, dated July 5, 2011; and] the 

replacement of oxygen CRAs containing 

pressure regulators that do not meet the 

required material properties. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (77 

FR 2662, January 19, 2012) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed, except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 2662, 

January 19, 2012) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 2662, 

January 19, 2012). 

Costs of Compliance 

We estimate that this AD will affect 

263 products of U.S. registry. We also 

estimate that it will take about 2 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD to the U.S. operators to 

be $44,710, or $170 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 1 work-hour and require parts 

costing $0, for a cost of $85 per product. 

We have no way of determining the 

number of products that may need these 

actions. 

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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 


wreier-aviles on DSK5TPTVN1PROD with RULES