42954 Federal Register / Vol. 77, No. 141 / Monday, July 23, 2012 / Rules and Regulations 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1218, Revision 01, including Appendices 

01 and 02, dated June 17, 2010. If any 

cracking is found, before further flight, repair 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1218, Revision 01, including Appendices 

01 and 02, dated June 17, 2010. 

(h) Reporting 

Submit a report of the findings of the 

inspection required by paragraph (g) of this 

AD to Airbus in accordance with Appendix 

01 of Airbus Service Bulletin A320–53–1218, 

Revision 01, including Appendices 01 and 

02, dated June 17, 2010, at the applicable 

time specified in paragraph (h)(1) or (h)(2) of 

this AD. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 90 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 90 days after the effective date of this 

AD. 

(i) Credit for Previous Actions 

This paragraph provides credit for 

inspections and replacements required by 

paragraph (g) of this AD, if those actions were 

performed before the effective date of this AD 

using Airbus Service Bulletin A320–53–1218, 

including Appendices 01 and 02, dated 

February 8, 2010. 

(j) 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; phone: 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. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(k) Related Information 

Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2011– 

0120R1, dated July 13, 2011; and Airbus 

Service Bulletin A320–53–1218, Revision 01, 

including Appendices 01 and 02, dated June 

17, 2010; for related information. 

(l) 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) Airbus Service Bulletin A320–53–1218, 

Revision 01, including Appendices 01 and 

02, dated June 17, 2010. 

(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, 

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 July 5, 

2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–17389 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–2012–0730; Directorate 

Identifier 2012–SW–048–AD; Amendment 

39–17124; AD 2012–14–10] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Vertol (Type Certificate Currently Held 

by Columbia Helicopters, Inc. (CHI)) 

and Kawasaki Heavy Industries, 

Limited Helicopters (Kawasaki) 

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 CHI 

Model 107–II and Kawasaki Model 

KV107–II and KV107–IIA helicopters. 

This AD requires, before further flight, 

replacing certain upper collective pitch 

control yoke bolts. This AD is prompted 

by three failures of the affected bolts. 

These actions are intended to prevent 

failure of an upper collective pitch 

control yoke bolt (bolt), excessive 

vibration, migration of the shafts, and 

subsequent loss of control of the 

helicopter. 

DATES: This AD becomes effective 

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 

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Federal Register / Vol. 77, No. 141 / Monday, July 23, 2012 / Rules and Regulations 42955 

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 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. 

FOR FURTHER INFORMATION CONTACT: 

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 

kathleen.arrigotti@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 

federalism impacts that resulted from 

adopting this AD. The most helpful 

comments reference a specific portion of 

the AD, 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 them 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 

rulemaking during the comment period. 

We will consider all the comments we 

receive and may conduct additional 

rulemaking based on those comments. 

Discussion 

We are adopting a new AD for CHI 

Model 107–II and Kawasaki Model 

KV107–II and KV107–IIA helicopters. 

This AD requires replacing certain partnumbered bolts. The bolts are located in 

the forward and aft rotor upper 

collective pitch control assemblies. 

Upon failure, the yoke bolt head shears 

off, allowing shafts around the bolt to 

migrate out of place. If the shaft 

migrates fully out of place, the rotor 

pitch cannot be controlled. This AD is 

prompted by multiple failures of the 

affected bolts at low flight hours. These 

actions are intended to prevent failure 

of a bolt, excessive vibration, migration 

of the shafts, and subsequent loss of 

control of the helicopter. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other helicopters of the same 

type designs. 

Related Service Information 

CHI issued Service Bulletin No. 107– 

27–0005 (SB), Revision 0, dated April 

26, 2012. The SB specifies replacing all 

bolts, part number (P/N) 107C2733–1 

and P/N 107C2733–2, with bolts, P/N 

C07C2700–1. The SB also specifies 

modifying spare assemblies, daily 

inspections of the yoke bolt retaining 

nut, and recurring 35-hour inspections 

of the bolt. 

AD Requirements 

This AD requires, before further flight, 

replacing all affected bolts with 

airworthy bolts, P/N C07C2700–1, and 

torquing the nut to 450–500 in-lbs. This 

AD also prohibits installing washer P/N 

A02C3112–13 with bolt P/N C07C2700– 

1, and installing bolt P/N 107C2733–1 

and P/N 107C2733–2 on any helicopter. 

Differences Between This AD and the 

Service Information 

The CHI SB requires a repetitive daily 

inspection of the yoke bolt retaining 

nut, and a repetitive 35-hour inspection 

of the bolts after replacement. This AD 

does not require those inspections. The 

SB also specifies modifying spare 

assemblies. This AD does not address 

parts that are not installed. 

Costs of Compliance 

We estimate that this AD will affect 

12 helicopters of U.S. Registry. We 

estimate that operators may incur the 

following costs in order to comply with 

this AD: Replacing the bolts will take 4 

hours at an average labor rate of $85 per 

work hour. Required parts will cost 

$2,000. The total cost per helicopter is 

$2,340 and the total cost for the entire 

U.S. fleet is $28,080. 

FAA’s Justification and Determination 

of the Effective Date 

Providing an opportunity for public 

comments before adopting these AD 

requirements would delay 

implementing the safety actions needed 

to correct a previously described known 

critical unsafe condition, which can 

adversely affect the structural integrity 

and controllability of the helicopter. 

Therefore, we find that the risk to the 

flying public justifies waiving notice 

and comment prior to the adoption of 

this rule because the required corrective 

actions must be accomplished before 

further flight. 

Since an unsafe condition exists that 

requires the immediate adoption of this 

AD, we determined that notice and 

opportunity for public comment before 

issuing this AD are impracticable and 

that good cause exists for making this 

amendment effective in less than 30 

days. 

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, 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. 

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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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