Federal Register / Vol. 77, No. 59 / Tuesday, March 27, 2012 / Proposed Rules 18135 

covered financial company’s support of 

such obligations or liabilities. 

(d) Notice of Transfer of Support or 

Provision of Adequate Protection. 

If the Corporation as receiver for a 

covered financial company transfers any 

support and related assets and liabilities 

of the covered financial company in 

accordance with paragraph (a)(2)(i) of 

this section or provides adequate 

protection in accordance with paragraph 

(a)(2)(ii) of this section, it shall 

promptly take steps to notify contract 

counterparties of such transfer or 

provision of adequate protection. Notice 

shall be given in a manner reasonably 

calculated to provide notification in a 

timely manner, including, but not 

limited to, notice posted on the Web site 

of the Corporation, the covered financial 

company or the subsidiary or affiliate, 

notice via electronic media, or notice by 

publication. Neither the failure to 

provide actual notice to any party nor 

the lack of actual knowledge on the part 

of any party shall affect the authority of 

the Corporation or a qualified transferee 

to enforce any contract or exercise any 

rights or powers under this section. 

Dated at Washington, DC, this 20th day of 

March 2012. 

By order of the Board of Directors. 

Federal Deposit Insurance Corporation. 

Robert E. Feldman, 

Executive Secretary. 

[FR Doc. 2012–7051 Filed 3–26–12; 8:45 am] 

BILLING CODE 6714–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0298; Directorate 

Identifier 2011–NM–072–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, 

–401, and –402 airplanes. This proposed 

AD was prompted by reports of cracking 

of certain fuel access panels of the outer 

wing. This proposed AD would require 

an external inspection, and if necessary 

an internal inspection, to determine if 

certain fuel access panels are installed, 

and replacement if necessary; optional 

repetitive inspections for cracking of the 

fuel access panels, and replacement if 

necessary, would defer the internal 

inspection; and eventual replacement of 

affected fuel access panels with new 

panels. We are proposing this AD to 

prevent cracking of fuel access panels, 

which could result in arcing and 

ignition of fuel vapor in the outer wing 

fuel tank during a lightning strike. 

DATES: We must receive comments on 

this proposed AD by May 11, 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: Aziz 

Ahmed, Aerospace Engineer, Airframe 

and Mechanical Systems Branch, ANE– 

171, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue. Westbury, NY 11590; 

telephone (516) 228–7329; 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–2012–0298; Directorate Identifier 

2011–NM–072–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 

Transport Canada Civil Aviation 

(TCCA), which is the airworthiness 

authority for Canada, has issued 

Canadian Airworthiness Directive CF– 

2011–04, dated March 8, 2011 (referred 

to after this as ‘‘the MCAI’’), to correct 

an unsafe condition for the specified 

products. The MCAI states: 

[Canadian] Airworthiness Directive (AD) 

CF–2005–37 was issued on 11 October 2005 

to address cracking of the outer wing fuel 

access panel, Part Number (P/N) 85714230– 

001. Similar cracking on an outer wing fuel 

access panel, P/N 85714231–001, has been 

reported. Further investigation revealed that 

certain fuel access panels may have seal 

grooves manufactured with non-conforming 

fillet radii which could lead to cracking. 

Cracking of the fuel access panel, if not 

corrected, could result in arcing and ignition 

of fuel vapor in the outer wing fuel tank 

during a lightning strike. 

This [TCCA] directive mandates the 

inspection and replacement of the affected 

fuel access panels. 

Required actions include an external 

detailed inspection of the outer wing 

access panels for rivets of the 

identification plate, and an internal 

inspection of panels without rivets to 

determine if the identification plate is 

installed, and replacing the fuel access 

panel if necessary. As an option, this 

proposed AD would allow repetitive 

external detailed inspections for 

cracking of the fuel access panels and, 

replacing if necessary, until the internal 

inspection is done. This proposed AD 

would also require eventually replacing 

the affected fuel access panels with new 

fuel access panels. You may obtain 

further information by examining the 

MCAI in the AD docket. 

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18136 Federal Register / Vol. 77, No. 59 / Tuesday, March 27, 2012 / Proposed Rules 

Relevant Service Information 

Bombardier has issued Service 

Bulletin 84–57–22, Revision B, dated 

February 16, 2011; and Service Bulletin 

84–57–23, Revision B, dated February 

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 74 products of U.S. registry. 

We also estimate that it would take 

about 36 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 $33,632 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 

$2,715,208, or $36,692 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– 

0298; Directorate Identifier 2011–NM– 

072–AD. 

(a) Comments Due Date 

We must receive comments by May 11, 

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 4003 through 4106 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57: Wings. 

(e) Reason 

This proposed AD was prompted by 

reports of cracking of certain fuel access 

panels of the outer wing. We are issuing this 

AD to prevent cracking of fuel access panels, 

which could result in arcing and ignition of 

fuel vapor in the outer wing fuel tank during 

a lightning strike. 

(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 and Replacement of Part 

Number (P/N) 85714231–001 

Within 600 flight hours after the effective 

date of this AD, do an external detailed 

inspection of the outer wing access panels 

having P/N 85714231–001 to locate the rivets 

of the identification plates, in accordance 

with the Accomplishment Instructions of 

Bombardier Service Bulletin 84–57–22, 

Revision B, dated February 16, 2011. If the 

rivets of the identification plate are found, no 

further action is required by this paragraph 

for that fuel access panel. If the rivets of the 

identification plate cannot be found: Before 

further flight, do the actions specified in 

paragraph (g)(1) or (g)(2) of this AD. 

(1) Remove fuel access panels having part 

number (P/N) 85714231–001 and inspect the 

panels to determine if the identification plate 

is installed, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–57–22, Revision B, dated 

February 16, 2011. If the identification plate 

is found: No further action is required by 

paragraph (g) of this AD for that fuel access 

panel. 

(i) If the identification plate cannot be 

found, and the job detail number stamped on 

the underside of the access panel does not 

match any of those listed in table 1 of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–57–22, Revision B, dated 

February 16, 2011: No further action is 

required for paragraph (g) of this AD for that 

fuel access panel. 

(ii) If the identification plate cannot be 

found, and the job detail number stamped on 

the underside of the fuel access panel does 

match any of those specified in table 1 of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–57–22, Revision B, dated 

February 16, 2011: Before further flight, 

replace the fuel access panel with a new fuel 

access panel having P/N 85714231–003, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–57–22, Revision B, dated February 16, 

2011. 

(2) Do an external detailed inspection on 

fuel access panels having P/N 85714231–001 

for cracking, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–57–22, Revision B, dated 

February 16, 2011. If no cracking is found: 

Repeat the inspection thereafter at intervals 

not to exceed 600 flight hours until the 

replacement specified in paragraph (g)(2)(i) 

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Federal Register / Vol. 77, No. 59 / Tuesday, March 27, 2012 / Proposed Rules 18137 

of this AD, or the inspection specified in 

paragraph (g)(1) of this AD, is done. 

(i) If the fuel access panel is found cracked 

during any inspection required by this AD: 

Before further flight, replace the fuel access 

panel with a new fuel access panel having P/ 

N 85714231–003, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–57–22, Revision B, dated 

February 16, 2011. 

(ii) Within 6,000 flight hours after the 

initial inspection required by paragraph (g)(2) 

of this AD, do the actions required in 

paragraph (g)(1) of this AD, unless the 

replacement required by paragraph (g)(2)(i) of 

this AD is done. 

(h) Inspection and Replacement of P/N 

85714232–001 

Within 1,200 flight hours after the effective 

date of this AD, do an external detailed 

inspection of the outer wing access panels 

having P/N 85714232–001 to locate the rivets 

of the identification plates, in accordance 

with the Accomplishment Instructions of 

Bombardier Service Bulletin 84–57–23, 

Revision B, dated February 16, 2011. If the 

rivets of the identification plate are found: 

No further action is required by this 

paragraph for that fuel access panel. If the 

rivets of the identification plate cannot be 

found: Before further flight, do the actions in 

paragraph (h)(1) or (h)(2) of this AD. 

(1) Remove fuel access panels having P/N 

85714232–001 and inspect the panels to 

determine if the identification plate is 

installed, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–57–23, Revision B, dated 

February 16, 2011. If the identification plate 

is found: No further action is required by 

paragraph (h) of this AD for that fuel access 

panel. 

(i) If the identification plate cannot be 

found, and the job detail number stamped on 

the underside of the access panel does not 

match any of those specified in table 1 of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–57–23, Revision B, dated 

February 16, 2011: No further action is 

required by paragraph (h) of this AD for that 

fuel access panel. 

(ii) If the identification plate cannot be 

found, and the job detail number stamped on 

the underside of the fuel access panel does 

match any of those specified in table 1 of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–57–23, Revision B, dated 

February 16, 2011: Before further flight, 

replace the fuel access panel with a new fuel 

access panel having P/N 85714232–003, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–57–23, Revision B, dated February 16, 

2011. 

(2) Do an external detailed inspection on 

fuel access panels having P/N 85714232–001 

for cracking, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–57–23, Revision B, dated 

February 16, 2011. If no cracking is found: 

Repeat the inspection thereafter at intervals 

not to exceed 1,200 flight hours until the 

replacement specified in paragraph (h)(2)(i) 

of this AD, or the inspection specified by 

paragraph (h)(1) of this AD is done. 

(i) If the fuel access panel is found cracked 

during any inspection required by this AD: 

Before further flight, replace the fuel access 

panel with a new fuel access panel having 

P/N 85714232–003, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–57–23, Revision B, dated 

February 16, 2011. 

(ii) Within 12,000 flight hours after the 

initial inspection required by paragraph 

(h)(2) of this AD, do the actions required by 

paragraph (h)(1) of this AD, unless the 

replacement required by paragraph (h)(2)(i) 

of this AD is done. 

(i) Parts Installation 

As of the effective date of this AD, no 

person may install a fuel access panel having 

P/N 85714231–001 and a job detail number 

listed in table 1 of the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–57–22, Revision B, dated February 16, 

2011; or having P/N 85714232–001 and a job 

detail number listed in table 1 of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–57–23, Revision B, dated 

February 16, 2011; on any airplane. 

(j) Credit for Previous Actions 

This paragraph provides credit for 

inspections and fuel access panel 

replacements required by this AD, if those 

actions were performed before the effective 

date of this AD using Bombardier Service 

Bulletin 84–57–22, Revision A, dated 

December 9, 2010; or Bombardier Service 

Bulletin 84–57–23, Revision A, dated 

December 9, 2010. 

(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–2011–04, dated March 8, 2011, 

and the following service information, for 

related information. 

(1) Bombardier Service Bulletin 84–57–22, 

Revision B, dated February 16, 2011. 

(2) Bombardier Service Bulletin 84–57–23, 

Revision B, dated February 16, 2011. 

Issued in Renton, Washington on March 

16, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–7357 Filed 3–26–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0299; Directorate 

Identifier 2011–NM–029–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Boeing Model 747–100, 747–200B, 747– 

200C, 747–200F, 747–300, 747–400, 

747–400F, and 747SR series airplanes. 

This proposed AD was prompted by 

reports of broken and damaged latch pin 

retention bolts of the main deck side 

cargo door (MDSCD), latch pin 

migration, and broken latch pin fittings. 

This proposed AD would require 

various repetitive inspections of the 

MDSCD latch pin fittings, measuring the 

latch pin, and related investigative and 

corrective actions if necessary; and 

modifying the latch pin fittings and 

installing new latch pins and latch pin 

fasteners. We are proposing this AD to 

prevent loss of the cargo door and rapid 

depressurization of the airplane. 

DATES: We must receive comments on 

this proposed AD by May 11, 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: Deliver to Mail 

address above between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS