Federal Register / Vol. 77, No. 54 / Tuesday, March 20, 2012 / Proposed Rules 16191 

‘‘Compliance,’’ of Boeing Service Bulletin 

737–55–1090, dated March 30, 2011, do 

HFEC and ultrasonic inspections for cracking 

of the forward and aft sides of the 

termination fitting, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–55–1090, dated March 

30, 2011. If any crack is found in any 

termination fitting: Before further flight, 

repair in accordance with the procedures 

specified in paragraph (l) of this AD. Repeat 

the HFEC and ultrasonic inspections 

thereafter at intervals not to exceed 3,500 

flight cycles. 

(i) Exception to Compliance Time 

Where Boeing Service Bulletin 737–55– 

1090, dated March 30, 2011, specifies a 

compliance time ‘‘after the original issue date 

on the service bulletin,’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(j) Exception to Service Bulletin 

Where Figure 1 of Boeing Service Bulletin 

737–55–1090, dated March 30, 2011, points 

to the location of a part number rather than 

the serial number, this AD requires an 

inspection for an identification plate with a 

serial number that starts with the letters 

‘‘SAIC.’’ 

(k) Exceptions to Corrective Actions 

If, during any inspection required by 

paragraphs (g) and (h) of this AD, any bolts 

other than P/N BACB30US14K() or 

BACB30US16K(), as applicable, are found: 

Before further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (l) of this AD. 

(l) 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. 

(m) Related Information 

(1) For more information about this AD, 

contact Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–917–6440; fax: 425–917– 

6590; email: nancy.marsh@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

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

5680; email me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You may 

review copies of the referenced 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. 

Issued in Renton, Washington, on March 8, 

2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–6628 Filed 3–19–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0267; Directorate 

Identifier 2011–NM–174–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 adopt a new 

airworthiness directive (AD) for certain 

Bombardier Inc. Model DHC–8–400 

series airplanes. This proposed AD was 

prompted by reports that the automatic 

de-icing mode became unavailable due 

to a failure of the timer and monitor unit 

(TMU). This proposed AD would 

require replacing the TMU. We are 

proposing this AD to prevent loss of the 

automatic de-icing mode and 

consequent increased workload for the 

flight crew, which, depending on 

additional failures, could lead to loss of 

control of the airplane. 

DATES: We must receive comments on 

this proposed AD by May 4, 2012. 

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, 

Washington. 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–2012–0267; Directorate Identifier 

2011–NM–174–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 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
16192 Federal Register / Vol. 77, No. 54 / Tuesday, March 20, 2012 / Proposed Rules 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2011–34, 

dated August 16, 2011 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

There have been multiple reports of inservice incidents where the automatic 

deicing mode became unavailable due to a 

failure of the Timer and Monitor Unit (TMU). 

Investigation has revealed that the failures 

were attributed to overstressed capacitors 

installed in the circuit board of the TMU 

‘‘Module 300’’ power supply. The failure of 

the capacitors leads to failure of the TMU 

‘‘Module 300’’ power supply and subsequent 

loss of the automatic deicing mode. 

This [TCCA] directive mandates the 

replacement of the TMU, part number (P/N) 

4100S018–06, with a new improved unit, 

P/N 4100S018–07. 

The unsafe condition is loss of the 

automatic de-icing mode and 

consequent increased workload for the 

flight crew, which, depending on 

additional failures, could lead to loss of 

control 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 84–30–14, dated May 20, 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 81 products of U.S. registry. 

We also estimate that it would take 

about 3 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $0 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 $20,655, or $255 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 adding 

the following new AD: 

Bombardier, Inc.: Docket No. FAA–2012– 

0267; Directorate Identifier 2011–NM– 

174–AD. 

(a) Comments Due Date 

We must receive comments by May 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 and subsequent, equipped with Aerazur 

timer and monitor unit, part number (P/N) 

4100S018–06. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 30: Ice and rain protection. 

(e) Reason 

This AD was prompted by reports that the 

automatic de-icing mode became unavailable 

due to a failure of the timer and monitor unit 

(TMU). We are issuing this AD to prevent 

loss of the automatic de-icing mode and 

consequent increased workload for the flight 

crew, which, depending on additional 

failures, could lead to loss of control 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) Replace the TMU 

Within 3,000 flight hours or 18 months 

after the effective date of this AD, whichever 

occurs first: Replace TMU P/N 4100S018–06 

with new TMU P/N 4100S018–07, by 

incorporating Bombardier ModSum 4– 

126525, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–30–14, dated May 20, 

2011. 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 54 / Tuesday, March 20, 2012 / Proposed Rules 16193 

(h) Parts Installation 

As of the effective date of this AD, no 

person may install a TMU, P/N 4100S018–06, 

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–2011–34, dated August 16, 

2011; and Bombardier Service Bulletin 84– 

30–14, dated May 20, 2011; for related 

information. 

Issued in Renton, Washington, on March 7, 

2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–6626 Filed 3–19–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0142; Directorate 

Identifier 2010–NM–275–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 adopt a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model CL–600–2C10 

(Regional Jet Series 700, 701, & 702), 

CL–600–2D15 (Regional Jet Series 705), 

and CL–600–2D24 (Regional Jet Series 

900) airplanes. This proposed AD was 

prompted by reports of failures of a 

hydraulic accumulator’s screw-cap/end 

cap while on the ground that resulted in 

loss of use of that hydraulic system and 

in high-energy impact damage to 

adjacent systems and structures. This 

proposed AD would require an 

inspection for part numbers; repetitive 

inspections for any cracking of certain 

hydraulic system accumulators, and 

replacement, if necessary; and revising 

the maintenance program to include a 

life limit for certain hydraulic system 

accumulators. We are proposing this AD 

to prevent loss of use of a hydraulic 

system, which could result in reduced 

controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by May 4, 2012. 

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., 400 Coˆte-Vertu 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. You may 

review copies of the referenced 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. 

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–2012–0142; Directorate Identifier 

2010–NM–275–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 

The Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2010–35R1, 

dated June 28, 2011 (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/end cap failure have 

been experienced on CL–600–2B19 

aeroplanes resulting in loss of the associated 

hydraulic system and high-energy impact 

damage to adjacent systems and structure. 

The lowest number of flight cycles 

accumulated at the time of failure, to date, 

has been 6,991 flight cycles. 

Although there have been no failures to 

date on any CL–600–2C10, CL–600–2D15 or 

CL–600–2D24 aeroplanes, similar 

accumulators to those installed on the CL– 

600–2B19, are installed. The part numbers 

(P/Ns) of the accumulators installed on CL– 

600–2C10, CL–600–2D15 and CL–600–2D24 

aeroplanes are 900096–1 (Hydraulic System 

No. 1 and Hydraulic System No. 2 

accumulators), 900097–1 (Hydraulic System 

No. 3 accumulator) and 08–60204–001 

(Inboard Brake and Outboard Brake 

accumulators). 

A detailed analysis of the calculated line 

of trajectory of a failed screw cap/end cap for 

each of the accumulators has been 

conducted, resulting in the identification of 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS