Federal Register / Vol. 78, No. 58 / Tuesday, March 26, 2013 / Proposed Rules 18257 

phone: 847–294–7377; fax: 847–294–7384; 

email: mark.grace@faa.gov. 

(2) For service information identified in 

this AD, contact Hartzell Propeller Inc., 1 

Propeller Place, Piqua, OH 45356–2634; 

phone: 937–778–4379; fax: 937–778–4391; 

email: techsupport@hartzellprop.com. You 

may view this service information at the 

FAA, 12 New England Executive Park, 

Burlington, MA. For information on the 

availability of this material at the FAA, call 

781–238–7125. 

Issued in Burlington, Massachusetts, on 

March 19, 2013. 

Colleen M. D’Alessandro, 

Assistant Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–06843 Filed 3–25–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0209; Directorate 

Identifier 2012–NM–127–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to certain Bombardier, Inc. 

Model DHC–8–100, -200, and -300 

series airplanes. The existing AD 

currently requires replacing certain 

parking brake accumulators. Since we 

issued that AD, we have determined 

that it is necessary to protect the 

hydraulic system and airplane structure 

from possible damage by any faulty 

screw cap or end cap of any 

accumulator. This proposed AD would 

require installing restraint devices 

around the parking brake accumulator 

end caps. We are proposing this AD to 

prevent failure of the parking brake 

accumulator screw cap or end cap 

resulting in loss of the number 2 

hydraulic system and damage to 

airplane structures, which could 

adversely affect the controllability of the 

airplane. 

DATES: Send comments on or before 

April 25, 2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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. 

You may review copies of the 

referenced 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. 

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 

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. 

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:

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2013–0209; Directorate Identifier 

2012–NM–127–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On June 28, 2012, we issued AD 

2012–14–04, Amendment 39–17118 (77 

FR 42956, July 23, 2012). That AD 

required actions intended to address an 

unsafe condition on certain Model 

DHC–8–100, –200, and –300 series 

airplanes. 

Since we issued AD 2012–14–04, 

Amendment 39–17118 (77 FR 42956, 

July 23, 2012), we have determined that 

it is necessary to protect the hydraulic 

system and airplane structure from 

possible damage by any faulty screw cap 

or end cap of any accumulator. 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2011–29R1, 

dated May 24, 2012 (referred to after 

this as ‘‘the MCAI’’), 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. 

This [original TCCA] directive [which 

corresponds to FAA AD 2012–14–04, 

Amendment 39–17118 (77 FR 42956, July 23, 

2012)] gives instructions to determine the 

part number and serial number of the 

existing parking brake accumulator, and 

where applicable, replace the accumulator. 

Revision 1 of this [TCCA] AD mandates the 

installation of restraint devices around [all] 

the parking brake accumulator end caps to 

hold them in place in the event of an end cap 

failure. 

Uncontained 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 adversely 


tkelley on DSK3SPTVN1PROD with PROPOSALS
18258 Federal Register / Vol. 78, No. 58 / Tuesday, March 26, 2013 / Proposed Rules 

affect the controllability of the airplane. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Bombardier, Inc. has issued Service 

Bulletin 8–32–169, Revision A, dated 

December 16, 2011. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 129 products of U.S. 

registry. 

The actions that are required by AD 

2012–14–04, Amendment 39–17118 (77 

FR 42956, July 23, 2012), and retained 

in this proposed AD take about 2 workhours per product, at an average labor 

rate of $85 per work hour. Based on 

these figures, the estimated cost of the 

currently required actions is $170 per 

product. 

We estimate that it would take about 

15 work-hours per product to comply 

with the new basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Required parts cost 

$5,302 per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these parts. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$848,433, or $6,577 per product. 

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 above, 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; 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 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 

removing airworthiness directive (AD) 

2012–14–04, Amendment 39–17118 (77 

FR July 23, 2012), and adding the 

following new AD: 

Bombardier, Inc.: Docket No. FAA–2013– 

0209; Directorate Identifier 2012–NM– 

127–AD. 

(a) Comments Due Date 

We must receive comments by May 10, 

2013. 

(b) Affected ADs 

This AD supersedes AD 2012–14–04, 

Amendment 39–17118 (77 FR 42956, July 23, 

2012). 

(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 resulting in loss of 

the number 2 hydraulic system and damage 

to airplane structures, which could adversely 

affect 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) Retained Inspection and Replacement 

This paragraph restates the requirements of 

paragraph (g) of AD 2012–14–04, 

Amendment 39–17118 (77 FR 42956, July 23, 

2012), with no changes. Within 2,000 flight 

hours or 12 months after August 27, 2012 

(the effective date of AD 2012–14–04), 

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. 

(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 August 27, 2012 (the effective 

date of AD 2012–14–04, Amendment 39– 

17118 (77 FR 42956, July 23, 2012)), 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 58 / Tuesday, March 26, 2013 / Proposed Rules 18259 

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) Retained Parts Installation Prohibition 

This paragraph restates the requirements of 

paragraph (h) of AD 2012–14–04, 

Amendment 39–17118 (77 FR 42956, July 23, 

2012), with no changes. As of August 27, 

2012 (the effective date of AD 2012–14–04), 

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) New Requirement of this AD: Install 

Restraint Devices on All Airplanes 

Within 6,000 flight hours or 36 months 

after the effective date of this AD, whichever 

occurs first: Install restraint devices around 

the parking brake hydraulic accumulator end 

caps by incorporating Bombardier ModSum 

8Q101901, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–32–169, Revision A, dated 

December 16, 2011. 

(j) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (i) of this AD, if those 

actions were performed before the effective 

date of this AD using Bombardier Service 

Bulletin 8–32–169, dated November 25, 2011, 

which is not incorporated by reference in this 

AD. 

(k) 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, NY 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. 

(l) Related Information 

(1) Refer to MCAI Canadian Airworthiness 

Directive CF–2011–29R1, dated May 24, 

2012; and the service information identified 

in paragraphs (m)(1)(i) through (m)(1)(v) of 

this AD; for related information. 

(i) Bombardier Service Bulletin 8–32–169, 

Revision A, dated December 16, 2011. 

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

dated February 25, 2011. 

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

dated March 15, 2011. 

(2) 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. You 

may review copies of the referenced 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. 

Issued in Renton, Washington, on March 5, 

2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–05813 Filed 3–25–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2012–1345; Airspace 

Docket No. 12–ANM–31] 

Proposed Modification of Class D and 

Class E Airspace and Establishment of 

Class E Airspace; Pasco, WA 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

establish Class E surface airspace at TriCities Airport, Pasco, WA. Controlled 

airspace is necessary to accommodate 

aircraft using Area Navigation (RNAV) 

Global Positioning System (GPS) 

standard instrument approach 

procedures at Tri-Cities Airport, Pasco, 

WA. This action also would modify the 

Class D airspace and Class E airspace by 

adjusting the geographic coordinates of 

Tri-Cities Airport and Kennewick, Vista 

Field Airport. This will also correct the 

airport name from Vista Airport, 

Kennewick, WA to Kennewick, Vista 

Field Airport, WA. The FAA is 

proposing this action to enhance the 

safety and management of aircraft 

operations at Tri-Cities Airport, Pasco, 

WA. 

DATES: Comments must be received on 

or before May 10, 2013. 

ADDRESSES: Send comments on this 

proposal 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; telephone (202) 

366–9826. You must identify FAA 

Docket No. FAA–2012–1345; Airspace 

Docket No. 12–ANM–31, at the 

beginning of your comments. You may 

also submit comments through the 

Internet at http://www.regulations.gov. 

FOR FURTHER INFORMATION CONTACT: 

Eldon Taylor, Federal Aviation 

Administration, Operations Support 

Group, Western Service Center, 1601 

Lind Avenue SW., Renton, WA 98057; 

telephone (425) 203–4537. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

Interested parties are invited to 

participate in this proposed rulemaking 

by submitting such written data, views, 

or arguments, as they may desire. 

Comments that provide the factual basis 

supporting the views and suggestions 

presented are particularly helpful in 

developing reasoned regulatory 

decisions on the proposal. Comments 

are specifically invited on the overall 

regulatory, aeronautical, economic, 

environmental, and energy-related 

aspects of the proposal. 

Communications should identify both 

docket numbers (FAA Docket No. FAA 

2012–1345 and Airspace Docket No. 12– 

ANM–31) and be submitted in triplicate 

to the Docket Management System (see 

ADDRESSES section for address and 

phone number). You may also submit 

comments through the Internet at http:// 

www.regulations.gov. 

Commenters wishing the FAA to 

acknowledge receipt of their comments 

on this action must submit with those 

comments a self-addressed stamped 

postcard on which the following 

statement is made: ‘‘Comments to FAA 

Docket No. FAA–2012–1345 and 

Airspace Docket No. 12–ANM–31’’. The 

postcard will be date/time stamped and 

returned to the commenter. 

All communications received on or 

before the specified closing date for 

comments will be considered before 

taking action on the proposed rule. The 

proposal contained in this action may 

be changed in light of comments 

received. All comments submitted will 

be available for examination in the 

public docket both before and after the 

closing date for comments. A report 

summarizing each substantive public 

contact with FAA personnel concerned 


tkelley on DSK3SPTVN1PROD with PROPOSALS