42956 Federal Register / Vol. 77, No. 141 / Monday, July 23, 2012 / Rules and Regulations 

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): 

2012–14–10 Boeing Vertol (Type Certificate 

Currently Held by Columbia 

Helicopters, Inc.) and Kawasaki Heavy 

Industries, Limited Helicopters: 

Amendment 39–17124; Docket No. 

FAA–2012–0730; Directorate Identifier 

2012–SW–048–AD. 

(a) Applicability 

This AD applies to Boeing Vertol (type 

certificate currently held by Columbia 

Helicopters, Inc. (CHI)) Model 107–II and 

Kawasaki Heavy Industries, Limited Model 

KV107–II and KV107–IIA helicopters with an 

upper collective pitch control assembly, part 

number (P/N) 107CK003–2 or 107CK002–2, 

installed, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

failure of an upper collective pitch control 

yoke bolt (bolt). This condition could result 

in excessive vibration, migration of the 

shafts, and subsequent loss of control of the 

helicopter. 

(c) Effective Date 

This AD becomes effective August 7, 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 

Before further flight, replace bolts, P/N 

107C2733–1 and P/N 107C2733–2, with 

airworthy bolts, P/N C07C2700–1. Torque 

each nut to 450–500 in-lbs. Do not install a 

washer, P/N A02C3112–13 with a bolt, P/N 

C07C2700–1. Do not install bolts, P/N 

107C2733–1 and P/N 107C2733–2, on any 

helicopter. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Send your proposal to: 

Kathleen Arrigotti, Aviation Safety Engineer, 

Seattle Aircraft Certification Office, 

Transport Airplane Directorate, FAA, 1601 

Lind Avenue SW., Renton, Washington 

98057; telephone (425) 917–6426; email 9- 

ANM-Seattle-ACO-AMOC-Requests@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 

EAD through an AMOC. 

(g) Additional Information 

CHI Service Bulletin No. 107–27–0005 

(SB), Revision 0, dated April 26, 2012, which 

is not incorporated by reference, contains 

additional information about the subject of 

this AD. For service information identified in 

this AD, contact Columbia Helicopters, Inc.; 

14452 Arndt Road NE., Aurora, OR 97002; 

telephone (503) 678–1222; email 

ContactEngineering@colheli.com; or at 

www.ColHeli.com. 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. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6230 Main Rotor Mast/Swashplate. 

Issued in Fort Worth, Texas, on July 5, 

2012. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–17278 Filed 7–20–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0271; Directorate 

Identifier 2011–NM–196–AD; Amendment 

39–17118; AD 2012–14–04] 

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 DHC–8–100, 

DHC–8–200, and DHC–8–300 series 

airplanes. This AD was prompted by 

reports of hydraulic accumulator screw 

cap or end cap failure. This AD requires 

replacing the affected parking brake 

accumulator. We are issuing this AD to 

prevent failure of the parking brake 

accumulator screw caps or end caps, 

which could result in loss of the number 

2 hydraulic system and damage to 

airplane structures, and could 

potentially have an adverse effect on the 

controllability of the airplane. 

DATES: This AD becomes effective 

August 27, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 27, 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, 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 March 21, 2012 (77 FR 

16488). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Seven cases of on-ground hydraulic 

accumulator screw cap or end cap failure 

have been experienced on CL–600–2B19 

(CRJ) aeroplanes, resulting in loss of the 

associated hydraulic system and high-energy 

impact damage to adjacent systems and 

structure. To date, the lowest number of 

flight cycles accumulated at the time of 

failure has been 6991. 

Although there have been no failures to 

date on any DHC–8 aeroplanes, similar 

accumulators to those installed on the CL– 

600–2B19, Part Numbers (P/N)0860162001 

and 0860162002 (Parking Brake 

Accumulator), are installed on the aeroplanes 

listed in the Applicability section of this 

[TCCA] directive. 

A detailed analysis of the systems and 

structure in the potential line of trajectory of 

a failed screw cap/end cap for the 

accumulator has been conducted. It has 

identified that the worst-case scenarios 

would be the loss of number 2 hydraulic 

system, and damage to aeroplane structures. 

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Federal Register / Vol. 77, No. 141 / Monday, July 23, 2012 / Rules and Regulations 42957 

This [TCCA] directive gives instructions to 

determine the part number and serial number 

of the existing parking brake accumulator, 

and where applicable, replace the 

accumulator. 

Failure of the parking brake 

accumulator screw caps and/or end caps 

could result in loss of the number 2 

hydraulic system, and damage to 

airplane structures, and could 

potentially have an adverse effect on the 

controllability of the airplane. 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 16488, March 21, 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 

16488, March 21, 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 16488, 

March 21, 2012). 

Costs of Compliance 

We estimate that this AD will affect 

about 129 products of U.S. registry. We 

also estimate that it will take about 2 

work-hours 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 $21,930, or $170 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 3 work-hours and require parts 

costing $1,625, for a cost of $1,880 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, 

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 the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; 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 a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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 the NPRM (77 FR 16488, 

March 21, 2012), the regulatory 

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. 

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 AD: 

2012–14–04 Bombardier, Inc.: Amendment 

39–17118. Docket No. FAA–2012–0271; 

Directorate Identifier 2011–NM–196–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective August 27, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

DHC–8–101, –102, –103, –106, –201, –202, 

–301, –311, and –315 airplanes, certificated 

in any category, serial numbers 003 and 

subsequent. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32: Landing gear. 

(e) Reason 

This AD was prompted by reports of 

hydraulic accumulator screw cap or end cap 

failure. We are issuing this AD to prevent 

failure of the parking brake accumulator 

screw caps or end caps, which could result 

in loss of the number 2 hydraulic system and 

damage to airplane structures, and could 

potentially have an adverse effect on the 

controllability of the airplane. 

(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) Inspection and Replacement 

Within 2,000 flight hours or 12 months 

after the effective date of this AD, whichever 

occurs first: Inspect to determine the part 

number (P/N) and serial number of the 

parking brake hydraulic accumulator, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–32–170, dated February 25, 2011. A review 

of airplane maintenance records is acceptable 

in lieu of this inspection if the part number 

and serial number of the parking brake 

hydraulic accumulator can be conclusively 

determined from that review. 

(1) For accumulators not having P/N 

0860162001 or 0860162002: No further 

action is required by this paragraph. 

(2) For accumulators having P/N 

0860162001 or 0860162002: Before further 

flight, do the applicable actions specified in 

paragraphs (g)(2)(i) and (g)(2)(ii) of this AD. 

(i) If the serial number is listed in the table 

in paragraph 3.B.(2) of Bombardier Service 

Bulletin 8–32–170, dated February 25, 2011: 

No further action is required by this 

paragraph. 

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42958 Federal Register / Vol. 77, No. 141 / Monday, July 23, 2012 / Rules and Regulations 

(ii) If the serial number is not listed in the 

table in paragraph 3.B.(2) of Bombardier 

Service Bulletin 8–32–170, dated February 

25, 2011: Within 2,000 flight hours or 12 

months after the effective date of this AD, 

whichever occurs first, replace the 

accumulator with a new non-suspect 

accumulator, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–32–172, dated March 15, 

2011. 

(h) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install a parking brake 

accumulator, P/N 0860162001 or 0860162002 

with a serial number that is not listed in the 

table in paragraph 3.B.(2) of Bombardier 

Service Bulletin 8–32–170, dated February 

25, 2011, on any airplane. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, 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 ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone 516–228–7300; fax 516– 

794–5531. 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 Canadian Airworthiness 

Directive CF–2011–29, dated August 2, 2011, 

and the service information identified in 

paragraphs (j)(1) and (j)(2) of this AD, for 

related information. 

(1) Bombardier Service Bulletin 8–32–170, 

dated February 25, 2011. 

(2) Bombardier Service Bulletin 8–32–172, 

dated March 15, 2011. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the following service information 

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

(2) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. 

(i) Bombardier Service Bulletin 8–32–170, 

dated February 25, 2011. 

(ii) Bombardier Service Bulletin 8–32–172, 

dated March 15, 2011. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., Q-Series 

Technical Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone 416–375–4000; fax 416–375–4539; 

email thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.com. 

(4) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(5) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call 202–741– 

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

federal_register/code_of_federal_regulations/

ibr_locations.html. 

Issued in Renton, Washington, on June 28, 

2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–16967 Filed 7–20–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0704; Directorate 

Identifier 2012–SW–040–AD; Amendment 

39–17113; AD 2012–13–11] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

Deutschland GmbH Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Eurocopter Deutschland GmbH (ECD) 

Model MBB–BK 117 (all versions) and 

BO–105LS A–3 helicopters. This AD 

requires inspecting the tail rotor pitch 

link spherical bearing for proper 

swaging. This AD is prompted by a 

report of a tail rotor pitch link with a 

spherical bearing that had migrated out 

of the bearing bore. The actions 

specified by this AD are intended to 

prevent failure of the tail rotor pitch 

link and subsequent loss of control of 

the helicopter. 

DATES: This AD becomes effective 

August 7, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents August 7, 2012. 

We must receive comments on this 

AD by September 21, 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 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 AD, contact Able Engineering and 

Support Services, 2920 East Chambers 

Street, Phoenix, AZ 85040; telephone 

(602) 304–1227; fax (602) 304–1277; 

email info@ableengineering.com. 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. 

FOR FURTHER INFORMATION CONTACT: 

Sharon Miles, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, TX 76137; 

telephone (817) 222–5110; email 

sharon.y.miles@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments prior to it becoming effective. 

However, 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 

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