Federal Register / Vol. 77, No. 180 / Monday, September 17, 2012 / Rules and Regulations 57005 

(e) Reason 

This AD was prompted by a report of 

a torn out aspirator due to the aspirator 

interfering with the extrusion lip of the 

OWS enclosure during the initial stage 

of the deployment sequence. We are 

issuing this AD to prevent both off-wing 

exits from being inoperative, which, 

during an emergency, would impair the 

safe evacuation of occupants, possibly 

resulting in personal injuries. 

(f) Compliance 

You are responsible for having the 

actions required by this AD performed 

within the compliance times specified, 

unless the actions have already been 

done. 

(g) Modification 

Within 36 months after the effective 

date of this AD, modify both left-hand 

and right-hand OWS enclosures, in 

accordance with the instructions in 

Airbus Service Bulletin A320–25–1649, 

dated February 16, 2010. 

(h) Parts Installation Prohibition 

After accomplishing the modification 

required by paragraph (g) of this AD, no 

person may install an OWS having P/N 

D31865–109, P/N D31865–110, P/N 

D31865–209, or P/N D31865–210 on 

that airplane. 

(i) Other FAA AD Provisions 

The following provisions also apply 

to this AD: 

(1) Alternative Methods of 

Compliance (AMOCs): The Manager, 

International Branch, ANM–116, 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 International Branch, 

send it to ATTN: Sanjay Ralhan, 

Aerospace Engineer, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, 1601 Lind Avenue 

SW., Renton, Washington 98057–3356; 

telephone 425–227–1405; fax 425–227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

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. The AMOC 

approval letter must specifically 

reference this AD. 

(2) Airworthy Product: For any 

requirement in this AD to obtain 

corrective actions from a manufacturer 

or other source, use these actions if they 

are FAA-approved. Corrective actions 

are considered FAA-approved if they 

are approved by the State of Design 

Authority (or their delegated agent). You 

are required to assure the product is 

airworthy before it is returned to 

service. 

(j) Related Information 

Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 

2010–0210, dated October 21, 2010 

(corrected October 27, 2010); and Airbus 

Service Bulletin A320–25–1649, dated 

February 16, 2010; for related 

information. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal 

Register approved the incorporation by 

reference (IBR) of the service 

information listed in this paragraph 

under 5 U.S.C. 552(a) and 1 CFR part 51. 

(2) You must use this service 

information as applicable to do the 

actions required by this AD, unless the 

AD specifies otherwise. 

(i) Airbus Service Bulletin A320–25– 

1649, dated February 16, 2010. 

(ii) Reserved. 

(3) For service information identified 

in this AD, contact Airbus, 

Airworthiness Office—EAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. 

(4) You may review copies of the 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(5) You may view this service 

information that is incorporated by 

reference 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/cfr/index.html. http://

www.archives.gov/federal-register/cfr/

ibr-locations.html. 

Issued in Renton, Washington, on August 

31, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–22041 Filed 9–14–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0337; Directorate 

Identifier 2010–SW–090–AD; Amendment 

39–17185; AD 2012–18–09] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the Bell 

Helicopter Textron Canada Limited 

(BHTC) Model 407 helicopters. This AD 

requires you to replace tailboomattachment hardware (attachment 

hardware), and perform initial and 

recurring determinations of the torque 

on the nuts of the tailboom-attachment 

bolts (bolts) at all four attachment 

locations. 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 407 Maintenance Manual 

and applied during manufacturing was 

incorrect and exceeded the torque range 

recommended for the bolts. The actions 

required by this AD are intended to 

prevent an over-torque of a bolt, bolt 

failure, loss of the tailboom, and 

subsequent loss of control of the 

helicopter. 

DATES: This AD is effective October 22, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of October 22, 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 


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57006 Federal Register / Vol. 77, No. 180 / Monday, September 17, 2012 / Rules and Regulations 

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, Aerospace Engineer, 

FAA, Regulations and Policy Group, 

2601 Meacham Blvd., Fort Worth, Texas 

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

(817) 222–5961; email: 

sharon.y.miles@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On March 29, 2012, at 77 FR 18970, 

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 407 helicopters. That 

NPRM proposed to require replacing 

attachment hardware and performing 

initial and recurring determinations of 

the torque on the nuts of the tailboomattachment bolts at all four attachment 

locations. The proposed requirements 

were intended to prevent an over-torque 

of a bolt, bolt failure, loss of the 

tailboom, and subsequent loss of control 

of the helicopter. 

Transport Canada, which is the 

aviation authority for Canada, has 

issued Canadian AD No. CF–2010–33, 

dated September 30, 2010, to correct an 

unsafe condition for the BHTC Model 

407 helicopters, serial numbers (S/N) 

53000 through 53990. Transport Canada 

advises that a review of the tailboomattachment installation determined that 

the torque value of the bolts specified in 

the BHTC Model 407 Maintenance 

Manual and applied during 

manufacturing, exceeded the torque 

range recommended for the bolts. 

Transport Canada states that this 

situation, if not corrected, could lead to 

a bolt failure, detachment of the 

tailboom, and subsequent 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 

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, Transport 

Canada, its technical representative, has 

notified us of the unsafe condition 

described in the Transport Canada AD. 

We are issuing this AD because we 

evaluated all information provided by 

Transport Canada and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

the same type designs and that air safety 

and the public interest require adopting 

the AD requirements as proposed. 

Differences Between This AD and the 

Transport Canada AD 

The differences between this AD and 

the Transport Canada AD are as follows: 

• This AD uses the term ‘‘hours timein-service’’ to describe compliance 

times, and Transport Canada AD uses 

the term ‘‘air time’’; 

• For helicopters with 7000 hours or 

less TIS, the Transport Canada AD 

requires accomplishing the actions in 

the AD at the next scheduled 600-hour 

inspection or by December 31, 2010, 

whichever occurs first. This AD requires 

accomplishing the actions at the next 

scheduled 600-hour inspection or 90 

days, whichever occurs first. 

• This AD uses the term ‘‘determine 

the torque’’ when referring to the torque 

on a nut, and the Transport Canada AD 

uses the term ‘‘perform a torque check.’’ 

Related Service Information 

BHTC has issued Alert Service 

Bulletin No. 407–10–93, Revision A, 

dated August 30, 2010 (ASB), which 

specifies installing new attachment 

hardware with a reduced torque value. 

This ASB specifies performing a torque 

check of the newly installed bolts and 

nuts every one to five flight hours until 

the torque stabilizes at all locations, and 

thereafter at intervals not to exceed 300 

flight hours. Transport Canada classified 

this ASB as mandatory and issued AD 

CF–2010–33 to ensure the continued 

airworthiness of these helicopters. 

Costs of Compliance 

We estimate that this AD will affect 

552 helicopters of U.S. registry. We 

estimate it will take about two workhours per helicopter to replace the 

hardware and one 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 $498 per helicopter. Based on 

these figures, we estimate for the first 

year the total cost per helicopter to be 

$923, and the total cost impact on U.S. 

operators to be $509,496. This estimated 

total cost assumes attachment hardware 

will be replaced on all affected 

helicopters, the torque will be 

considered stabilized after determining 

the torque value once, and the 300-hour 

TIS recurring 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: 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 77, No. 180 / Monday, September 17, 2012 / Rules and Regulations 57007 

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): 

2012–18–09 Bell Helicopter Textron 

Canada (BHTC): Amendment 39–17185; 

Docket No. FAA–2012–0337; Directorate 

Identifier 2010–SW–090–AD. 

(a) Applicability 

This AD applies to BHTC Model 407 

helicopters, serial numbers 53000 through 

53990, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as an 

incorrect torque value of the tailboom 

attachment bolt (bolt) specified in the BHTC 

Model 407 Maintenance Manual and applied 

during manufacturing, which exceeds the 

torque range recommended for the bolts. This 

condition could result in an over-torque of 

the bolt, bolt failure, loss of the tailboom, and 

subsequent loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective October 22, 

2012. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless 

accomplished previously. 

(e) Required Actions 

(1) For helicopters with 7000 hours or less 

time-in-service (TIS), at the next 600 hours 

scheduled inspection, or 90 days, whichever 

comes first; and for helicopters with more 

than 7000 hours TIS, within 150 hours TIS 

or 90 days, whichever comes 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) 

NAS627–30; washer, P/N 140–007–29S25E6; 

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

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

paragraphs 2.a) through paragraph 3.e) of the 

‘‘Accomplishment Instructions: Replacement 

of tailboom attachment bolts and nuts’’ 

section and Figure 2 in the BHTC Alert 

Service Bulletin No. 407–10–93, Revision A, 

dated August 30, 2010 (ASB). 

(iii) Remove the opposite right upper bolt, 

washers, and nut, and accomplish the 

requirements in paragraph (e)(1)(ii) of this 

AD. 

(iv) Remove the left lower bolt, washers, 

and nut. 

(v) Install a new bolt, (P/N) NAS626–26; 

washer, P/N 140–007–25S22E6; washer(s), P/ 

N NAS1149G0663P; and new nut, P/N 

42FLW–624 in accordance with paragraphs 

6.a) through 7.e) of the ‘‘Accomplishment 

Instructions: Replacement of tailboom 

attachment bolts and nuts’’ section and 

Figure 2 in the ASB. 

(vi) Remove the right lower bolt, washers, 

and nut, and accomplish the requirements in 

paragraph (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, 

referring to Figure 2 of the ASB. Apply the 

minimum specified torque of the range, plus 

the minimum acceptable tare torque of 14 

inch/lbs (1.58 Nm) for the upper nuts, and 

9.5 inch/lbs (1.07 Nm) for the lower nuts. 

(3) At intervals not to exceed 300 hours 

TIS, determine the torque of each of the four 

attachment nuts, referring to Figure 2 of the 

ASB. Apply the minimum specified torque of 

the range plus the minimum acceptable tare 

torque of 14 inch/lbs (1.58 Nm) for the upper 

nuts, and 9.5 inch/lbs (1.07 Nm) for the lower 

nuts. If the proper torque has not been 

retained since the last torque determination, 

remove and inspect the tailboom assembly 

for damage, corrosion, improper assembly, 

and condition. If the tailboom assembly is 

airworthy, replace the attachment hardware 

in accordance with the requirements in 

paragraphs (e)(1)(i) through (e)(1)(vi) and 

determine that the torque has stabilized in 

accordance with paragraph (e)(2) of this AD. 

Replace any unairworthy tailboom assembly 

with an airworthy tailboom assembly. 

(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, 

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 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 the 

Transport Canada Civil Aviation (TCCA) AD 

CF–2010–33, dated September 30, 2010. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: Rotorcraft tailboom. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Bell Helicopter Textron Canada Limited 

Alert Service Bulletin No. 407–10–93, 

Revision A, dated August 30, 2010. 

(ii) Reserved. 

(3) 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/. 

(4) You may review a copy of this service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. For information on the 

availability of this material at the FAA, call 

(817) 222–5110. 

(5) You may view this service information 

that is incorporated by reference 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/cfr/ibrlocations.html. 

Issued in Fort Worth, Texas, on August 30, 

2012. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–22038 Filed 9–14–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0217; Directorate 

Identifier 2009–NE–23–AD; Amendment 39– 

17194; AD 2012–18–17] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Division Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

all Pratt & Whitney Division (Pratt & 

Whitney) PW4052, PW4056, PW4060, 

PW4062, PW4062A, PW4074, PW4077, 

PW4077D, PW4084D, PW4090, 

PW4090–3, PW4152, PW4156A, 

PW4158, PW4164, PW4168, PW4168A, 

PW4460, and PW4462 turbofan engines. 

That AD currently requires initial and 

repetitive fluorescent penetrant 

inspections (FPI) for cracks in the blade 

loading and locking slots of the highpressure compressor (HPC) drum rotor 

disk assembly rear drum. This new AD 

requires the same actions, requires 

replacement of the 13th, 14th, and 15th 

stage HPC seals with redesigned HPC 

seals as an additional action, and adds 

an optional terminating action to the 

repetitive inspection requirements by 

allowing replacement of the entire HPC 

drum rotor disk assembly with a 

redesigned HPC drum rotor disk 

assembly. This AD was prompted by 

Pratt & Whitney developing a 

redesigned HPC drum rotor disk 

assembly for certain affected engine 

models. We are issuing this AD to 

prevent failure of the HPC drum rotor 

disk assembly, which could lead to an 


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