Federal Register / Vol. 77, No. 210 / Tuesday, October 30, 2012 / Rules and Regulations 65617 

(g) Inspection and Replacement of Oxygen 

CRA, CL–604 Variant 

For CL–604 Variant airplanes with serial 

numbers 5701 through 5802 inclusive, 5804 

through 5808 inclusive, 5810 through 5816 

inclusive, 5819, 5822, and 5823: Within 750 

flight hours after the effective date of this AD, 

but no later than 6 months after the effective 

date of this AD, inspect the serial number of 

oxygen pressure regulators having part 

number (P/N) 806370–12, in accordance with 

the Accomplishment Instructions, paragraph 

2.B.(3), of Bombardier Service Bulletin 605– 

35–001, Revision 01, dated February 28, 

2011. A review of airplane maintenance 

records is acceptable in lieu of this 

inspection if the part number of the oxygen 

pressure regulator can be conclusively 

determined from that review. 

(1) If any serial number is found that is 

listed in table 2 of Section 2.B. of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 605–35–001, Revision 01, 

dated February 28, 2011, before further flight, 

replace the affected oxygen CRA, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

605–35–001, Revision 01, dated February 28, 

2011. 

(2) If any serial number is found that is not 

listed in table 2 of Section 2.B. of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 605–35–001, Revision 01, 

dated February 28, 2011, no further action is 

required by this paragraph. 

(h) Inspection and Corrective Action of the 

Oxygen CRA Wiring Harness, CL–604 

Variant 

For CL–604 Variant airplanes with serial 

numbers 5701 through 5778 inclusive, 5780 

through 5796 inclusive, 5798, 5800 through 

5802 inclusive, 5804, 5805, 5808, 5811, and 

5813: At the applicable compliance time 

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

AD, do a detailed inspection for damaged 

wiring (i.e., signs of damaged insulation, 

abrasion, or chafing) of the electrical wiring 

harness for the oxygen CRA, and protect the 

electrical wiring harness, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 605–24–005, 

dated January 31, 2011. If any damaged 

wiring is found, before further flight, repair 

or replace any damaged wiring, in 

accordance with a method approved by the 

Manager, New York Aircraft Certification 

Office (ACO), FAA; or Transport Canada 

Civil Aviation (TCCA) (or its delegated 

agent). 

(1) For airplanes on which the oxygen CRA 

must be replaced, as required by paragraph 

(g)(1) of this AD: At the time the oxygen CRA 

is replaced. 

(2) For airplanes other than those 

identified in paragraph (h)(1) of this AD: 

Within 800 flight hours after the effective 

date of this AD. 

(i) Credit for Previous Actions 

This paragraph provides credit for actions 

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

actions were performed before the effective 

date of this AD using Bombardier Service 

Bulletin 605–35–001, dated January 31, 2011. 

(j) Parts Installation Limitation, All 

Airplanes 

For all airplanes (CL–601–3A, CL–601–3R, 

and CL–604 Variants): As of the effective date 

of this AD, no person may install an oxygen 

pressure regulator (P/N 806370–12) having 

any serial number listed in table 2 of Section 

2.B. of the Accomplishment Instructions of 

Bombardier Service Bulletin 605–35–001, 

Revision 01, dated February 28, 2011, on any 

airplane, unless a suffix ‘‘-A’’ is beside the 

serial number. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York 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. 

(l) Related Information 

Refer to MCAI Canadian Airworthiness 

Directive CF–2011–11, dated May 25, 2011, 

and the service bulletins identified in 

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

related information. 

(1) Bombardier Service Bulletin 605–24– 

005, dated January 31, 2011. 

(2) Bombardier Service Bulletin 605–35– 

001, Revision 01, dated February 28, 2011. 

(m) 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 605–24– 

005, dated January 31, 2011. 

(ii) Bombardier Service Bulletin 605–35– 

001, Revision 01, dated February 28, 2011. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email 

thd.crj@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/cfr/ibr-locations.html. 

Issued in Renton, Washington, on October 

11, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–26075 Filed 10–29–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0726; Directorate 

Identifier 2012–NM–023–AD; Amendment 

39–17228; AD 2012–21–12] 

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–8–400 

series airplanes. This AD was prompted 

by cases of on-ground failure of the 

screw cap or end cap of hydraulic 

accumulators on other airplane models, 

resulting in high-energy impact damage 

to adjacent systems and structure. This 

AD requires inspecting for a part 

number and replacing the affected 

parking brake hydraulic accumulator, 

and relocating the parking brake 

accumulator, on the subject airplanes. 

We are issuing this AD to prevent 

failure of the screw caps and/or end 

caps of the parking brake hydraulic 

accumulator, which could result in 

damage to the airplane’s primary 

structures, with potential adverse effect 

on the airplane’s controllability. 

DATES: This AD becomes effective 

December 4, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 4, 2012. 


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65618 Federal Register / Vol. 77, No. 210 / Tuesday, October 30, 2012 / Rules and Regulations 

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; email 

Cesar.Gomez@faa.gov. 

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 August 2, 2012 (77 FR 

45981). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The Mandatory Continuing 

Airworthiness Information (MCAI) 

states: 

Seven cases of on-ground hydraulic 

accumulator/screw cap/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 Number (P/N) 08–60197–001 

(Parking Brake Accumulator), are installed on 

the aeroplanes listed in the Applicability 

section of this [Canadian] Airworthiness 

Directive (AD). It was also found that some 

of these accumulators may be affected by 

manufacturing non-conformances. 

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 been 

identified that the worst-case scenarios 

would be the damage to the aeroplane’s 

primary structures, which could have an 

adverse effect on the controllability of the 

aeroplane. 

This [Canadian] AD mandates the 

[inspection for part and serial numbers and] 

replacement of the affected hydraulic 

accumulators and the relocation of the 

parking brake accumulator. 

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 45981, August 2, 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 

45981, August 2, 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 45981, 

August 2, 2012). 

Costs of Compliance 

We estimate that this AD will affect 

about 83 products of U.S. registry. We 

also estimate that it will take about 17 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $5,205 

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 

this AD to the U.S. operators to be 

$551,950, or $6,650 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 3 work-hours and require parts 

costing $4,643, for a cost of $4,898 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 45981, 

August 2, 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: 


wreier-aviles on DSK7SPTVN1PROD with RULES
Federal Register / Vol. 77, No. 210 / Tuesday, October 30, 2012 / Rules and Regulations 65619 

2012–21–12 Bombardier, Inc.: Amendment 

39–17228. Docket No. FAA–2012–0726; 

Directorate Identifier 2012–NM–023–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective December 4, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

DHC–8–400, –401, and –402 airplanes, 

certificated in any category, serial numbers 

4001 through 4346 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32: Landing gear. 

(e) Reason 

This AD was prompted by cases of onground hydraulic accumulator/screw cap/ 

end cap failure, resulting in high-energy 

impact damage to adjacent systems and 

structure. We are issuing this AD to prevent 

failure of the screw caps and/or end caps of 

the hydraulic and parking brake 

accumulators, which could result in damage 

to the airplane’s primary structures, with 

potential adverse effect on the airplane’s 

controllability. 

(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/Replacement of the Parking 

Brake Hydraulic Accumulator 

For airplanes having serial numbers 4001 

through 4337 inclusive: Within 1,200 flight 

hours or 6 months after the effective date of 

this AD, whichever comes first, inspect the 

parking brake hydraulic accumulator to 

determine the part number and serial 

number, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–32–88, dated February 

16, 2011. 

(1) If the part number of the parking brake 

hydraulic accumulator can be determined by 

the inspection required by paragraph (g) of 

this AD, and is not identified in paragraph 

1., Effectivity, of Goodrich Service Bulletin 

08 60197 001–32–70 R2, dated February 1, 

2011: No further action is required by this 

paragraph. 

(2) If the part number and serial number of 

the parking brake hydraulic accumulator 

cannot be determined by the inspection 

required by paragraph (g) of this AD, or is 

identified in paragraph 1. Effectivity, of 

Goodrich Service Bulletin 08 60197 001–32– 

70 R2, dated February 1, 2011: Before further 

flight, replace the parking brake hydraulic 

accumulator, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–32–88, dated February 

16, 2011. 

(h) Relocation of the Parking Brake 

Hydraulic Accumulator 

(1) For airplanes having serial numbers 

4001 through 4068 inclusive, 4070 through 

4214 inclusive, 4216, 4219 through 4261 

inclusive, and 4263 through 4346 inclusive: 

Within 6,000 flight hours after the effective 

date of this AD, relocate the parking brake 

hydraulic accumulator, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 84–32–87, 

Revision B, dated November 22, 2011. 

(2) Accomplishing the actions specified in 

paragraph (h)(1) of this AD in accordance 

with previous revisions of Bombardier 

Service Bulletin 84–32–87 does not meet the 

requirements of paragraph (h)(1) of this AD. 

(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), 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–2012–04, dated January 13, 

2012, and the service information identified 

in paragraphs (j)(1) through (j)(3) of this AD, 

for related information. 

(1) Bombardier Service Bulletin 84–32–87, 

Revision B, dated November 22, 2011. 

(2) Bombardier Service Bulletin 84–32–88, 

dated February 16, 2011. 

(3) Goodrich Service Bulletin 08 60197 

001–32–70 R2, dated February 1, 2011. 

(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) Bombardier Service Bulletin 84–32–87, 

Revision B, dated November 22, 2011. 

(ii) Bombardier Service Bulletin 84–32–88, 

dated February 16, 2011. 

(iii) Goodrich Service Bulletin 08 60197 

001–32–70 R2, dated February 1, 2011. 

(3) For Bombardier, Inc., 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. For Goodrich 

service information identified in this AD, 

contact Goodrich Corporation, Landing Gear, 

1400 South Service Road, West Oakville L6L 

5Y7, Ontario, Canada; telephone 905–825– 

1568; email jean.breed@goodrich.com; 

Internet http://www.goodrich.com/TechPubs. 

(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/ibrlocations.html. 

Issued in Renton, Washington, on October 

11, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–26077 Filed 10–29–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HOMELAND 

SECURITY 

Coast Guard 

33 CFR Part 117 

[Docket No. USCG–2012–0895] 

Drawbridge Operation Regulations; 

Taunton River, MA 

AGENCY: Coast Guard, DHS. 

ACTION: Notice of deviation from 

drawbridge regulation; request for 

comments. 

SUMMARY: The Coast Guard has issued a 

temporary deviation from the operating 

schedule that governs the Veterans 

Memorial Bridge across the Taunton 

River, mile 2.1, between Fall River and 

Somerset, Massachusetts. This deviation 

will test a change to the drawbridge 

operation schedule to determine 

whether a permanent change to the 

schedule is needed. This deviation will 

allow us to test an operating schedule to 

help determine the hours the bridge 

should be crewed. It is expected that 

this test will help determine the best 

operating schedule that will meet the 

present and future needs of navigation. 

DATES: This deviation is effective from 

December 1, 2012, through May 29, 

2013. 


wreier-aviles on DSK7SPTVN1PROD with RULES