Federal Register / Vol. 77, No. 210 / Tuesday, October 30, 2012 / Rules and Regulations 65615 

Instructions of Boeing Alert Service Bulletin 

777–27A0109, dated December 1, 2011. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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 manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle ACO 

to make those findings. For a repair method 

to be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(k) Related Information 

For more information about this AD, 

contact Kenneth Frey, Aerospace Engineer, 

Systems and Equipment Branch, ANM–130S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: (425) 917–6468; fax: (425) 917– 

6590; email: Kenneth.frey@faa.gov. 

(l) 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) Boeing Alert Service Bulletin 777– 

27A0109, dated December 1, 2011. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(4) You may view this service information 

at 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 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. 2012–26074 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–2012–0146; Directorate 

Identifier 2011–NM–115–AD; Amendment 

39–17227; AD 2012–21–11] 

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 CL–600–2B16 

(CL–601–3A, CL–601–3R, and CL–604 

Variants) airplanes. This AD was 

prompted by reports of deformation at 

the neck of the pressure regulator body 

on the oxygen cylinder and regulator 

assemblies (CRAs), and an electrical 

wiring harness in the area of the oxygen 

cylinder with no protective conduit 

sleeving. This AD requires inspecting to 

determine if certain oxygen pressure 

regulators are installed and replacing 

oxygen CRAs containing pressure 

regulators that do not meet the required 

material properties. This AD also 

requires inspecting for damaged wiring, 

and repairing or replacing wiring if 

necessary. We are issuing this AD to 

prevent rupture of the oxygen cylinder, 

which in the case of cabin 

depressurization, would lead to oxygen 

not being available when required; and 

to detect and correct unprotected wiring 

that could chafe against the oxygen 

system components or surrounding 

structure in the area, and lead to 

electrical arcing and an oxygen-fed fire. 

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. 

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 (ACO), 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 February 22, 2012 (77 FR 

10413). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

During a routine inspection, deformation 

was found at the neck of the pressure 

regulator body on the oxygen Cylinder and 

Regulator Assemblies (CRA) of a BD–700– 

1A11 aeroplane. 

An investigation by the vendor, Avox 

Systems Inc., revealed that the deformation 

was attributed to two (2) batches of raw 

material that did not meet the required 

tensile strength. This may cause elongation of 

the pressure regulator neck, which could 

result in rupture of the oxygen cylinder, and 

in the case of cabin depressurization, oxygen 

would not be available when required. 

Although there have been no reported 

failures to date on any CL–600–2B16 

aeroplanes, oxygen pressure regulators, Part 

Numbers (P/N) 806370–12, could be part of 

the affected batches. 

It has also been found that the electrical 

wiring harness in the area of the oxygen 

cylinder has been installed without 

protection. Unprotected wiring could chafe 

against the oxygen system components or 

surrounding structure in the area, which 

could lead to electrical arcing and an oxygen 

fed fire. 

This [Transport Canada Civil Aviation 

(TCCA)] directive mandates [an inspection to 

determine if a certain oxygen CRA is 

installed and] the replacement of oxygen 

CRAs containing pressure regulators that do 

not meet the required material properties and 

to [do a general visual inspection of] and 

protect the affected wiring. 

Corrective actions include repairing 

or replacing any damaged wiring. 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 

considered the comment received. 

Request To Limit Applicability 

Bombardier requested that we remove 

the CL–601–3A and –3R Variants of 

Model CL–600–2B16 airplanes from the 


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65616 Federal Register / Vol. 77, No. 210 / Tuesday, October 30, 2012 / Rules and Regulations 

applicability of the NPRM (77 FR 10413, 

February 22, 2012), because the serial 

numbers identified in the MCAI include 

only the CL–604 Variant of Model CL– 

600–2B16 airplanes. 

We do not agree to remove the CL– 

601–3A and –3R Variants of Model CL– 

600–2B16 airplanes from the 

applicability of this AD. The commenter 

is correct that the serial number range 

captures only the CL–604 Variant. 

However, we included the other 

variants in the applicability of this AD 

to prevent someone from installing the 

affected parts on those other variants in 

the future. We have coordinated this 

difference with TCCA. 

To make this intent more visible, we 

have added ‘‘CL–604 Variant’’ to the 

heading and first sentence of paragraphs 

(g) and (h) of this AD, and ‘‘All 

Airplanes’’ and ‘‘CL–601–3A, CL–601– 

3R, and CL–604 Variants’’ to the 

heading and first sentence respectively 

of paragraph (j) of this AD. 

Explanation of Additional Change 

Made to This AD 

We have revised the heading for and 

the wording in paragraph (i) of this AD; 

this change has not affected the intent 

of that paragraph. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We have determined that these changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

10413, February 22, 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 10413, 

February 22, 2012). 

Costs of Compliance 

We estimate that this AD will affect 

about 72 products of U.S. registry. We 

also estimate that it will take about 1 

work-hour 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 $6,120, or $85 per product. 

In addition, we estimate that certain 

follow-on actions (wiring protection) 

would take about 2 work-hours and 

require parts costing $0, for a cost of 

$170 per product. We have no way of 

determining the number of products 

that may need these actions. 

We have received no definitive data 

that would enable us to provide cost 

estimates for certain other on-condition 

actions (repairing or replacing damaged 

wiring) specified in this AD. 

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 10413, 

February 22, 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: 

2012–21–11 Bombardier, Inc.: Amendment 

39–17227. Docket No. FAA–2012–0146; 

Directorate Identifier 2011–NM–115–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 

CL–600–2B16 (CL–601–3A, CL–601–3R, and 

CL–604 Variants) airplanes, certificated in 

any category; serial numbers 5701 through 

5802 inclusive, 5804 through 5808 inclusive, 

5810 through 5816 inclusive, 5819, 5822, and 

5823 and subsequent. 

(d) Subject 

Air Transport Association (ATA) of 

America Codes 24, Electrical power; and 35, 

Oxygen. 

(e) Reason 

This AD was prompted by reports of 

deformation at the neck of the pressure 

regulator body on the oxygen cylinder and 

regulator assemblies (CRAs), and an electrical 

wiring harness in the area of the oxygen 

cylinder with no protective conduit sleeving. 

We are issuing this AD to prevent rupture of 

the oxygen cylinder, which in the case of 

cabin depressurization, would lead to oxygen 

not being available when required; and to 

detect and correct unprotected wiring that 

could chafe against the oxygen system 

components or surrounding structure in the 

area, and lead to electrical arcing and an 

oxygen-fed fire. 

(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. 


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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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