34872 Federal Register / Vol. 77, No. 113 / Tuesday, June 12, 2012 / Proposed Rules 

compliance times specified, unless the 

actions have already been done. 

(g) Inspection of Main Landing Gear SideBrace Fitting Shaft and Replacement 

(1) At the applicable times specified in 

paragraphs (g)(1)(i), (g)(1)(ii), (g)(1)(iii), and 

(g)(1)(iv) of this AD, do a detailed inspection 

for corrosion and damage of each side-brace 

fitting shaft of the MLG, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 601R–57–052, 

dated July 28, 2011. Repeat the inspections 

at the applicable times specified in 

paragraphs (g)(1)(i), (g)(1)(ii), (g)(1)(iii), and 

(g)(1)(iv) of this AD. 

(i) For airplanes that average greater than 

900 flight hours per year and have side-brace 

shafts part number (P/N) 601R10237–1 

installed in either the left- or right-hand 

MLG, or if the side brace shaft part number 

cannot be identified without removal: Within 

1,000 flight hours after the effective date of 

this AD, do the inspection. Repeat the 

inspections thereafter at intervals not to 

exceed 1,000 flight hours until the 

replacement specified in paragraph (g)(2) or 

(h) of this AD is done. 

(ii) For airplanes that average 900 flight 

hours or less per year and have side-brace 

shafts P/N 601R10237–1 installed on either 

the left- or right-hand MLG, or if the side 

brace shaft part number cannot be identified 

without removal: Within 18 months after the 

effective date of this AD, do the inspection. 

Repeat the inspections thereafter at intervals 

not to exceed 18 months until the 

replacement specified in paragraph (g)(2) or 

(h) of this AD is done. 

(iii) For airplanes that average greater than 

900 flight hours per year and have side-brace 

shafts P/N 601R10237–3 installed on either 

the left- or right-hand MLG: Within 36 

months after the effective date of this AD, do 

the inspection. Repeat the inspections 

thereafter at intervals not to exceed 36 

months until the replacement specified in 

paragraph (g)(2) or (h) of this AD is done. 

(iv) For airplanes that average 900 flight 

hours or less per year and have side brace 

shafts P/N 601R10237–3 installed on either 

the left- or right-hand MLG: Within 60 

months after the effective date of this AD, do 

the inspection. Repeat the inspections 

thereafter at intervals not to exceed 60 

months until the replacement specified in 

paragraph (g)(2) or (h) of this AD is done. 

(2) If any corrosion or damage is found 

during any inspection required by paragraph 

(g) of this AD: Before further flight, replace 

the side-brace fitting shaft with a new shaft 

P/N 601R10247–3, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 601R–57–052, dated July 28, 

2011. Doing this replacement terminates the 

inspection requirements of paragraph (g) of 

this AD. 

(h) Replacement 

Do the replacement at the applicable time 

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

(1) For any airplanes that have side-brace 

shafts P/N 601R10237–1 installed or if the 

side-brace shaft part number cannot be 

identified without removal: Within 27 

months after the effective date of this AD, 

replace the side-brace fitting shaft of the MLG 

with a new shaft having P/N 601R10247–3, 

in accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

601R–57–052, dated July 28, 2011. Doing this 

replacement terminates the inspection 

requirements of paragraph (g) of this AD. 

(2) For airplanes that have side-brace shafts 

P/N 601R10237–3 installed: Within 117 

months after the effective date of this AD, 

replace the side-brace fitting shaft of the MLG 

with a new shaft P/N 601R10247–3, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

601R–57–052, dated July 28, 2011. Doing this 

replacement terminates the inspection 

requirements of paragraph (g) 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), 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–2011–39, dated October 25, 

2011; and Bombardier Service Bulletin 601R– 

57–052, dated July 28, 2011; for related 

information. 

Issued in Renton, Washington, on May 31, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–14208 Filed 6–11–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0593; Directorate 

Identifier 2011–NM–238–AD] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. 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 

Fokker Services B.V. Model F.28 Mark 

0070 and 0100 airplanes. This proposed 

AD was prompted by reports of burned 

contacts in a certain production break 

plug and its corresponding receptacle. 

This proposed AD would require 

modifying galley power supply wiring 

by disconnecting it from the affected 

plug/receptacle and reconnecting the 

power supply wiring through splices. 

We are proposing this AD to prevent a 

high electrical load which may lead to 

overheating of the galley power supply 

wiring and/or the electrical connector 

and consequent smoke or fire in the 

galley area, which could result in 

damage to the airplane and injury to 

occupants. 

DATES: We must receive comments on 

this proposed AD by July 27, 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 Fokker 

Services B.V., Technical Services Dept., 

P.O. Box 231, 2150 AE Nieuw-Vennep, 

the Netherlands; telephone +31 (0)252– 

627–350; fax +31 (0)252–627–211; 

email: technicalservices.fokkerservices@

stork.com; Internet http:// 

www.myfokkerfleet.com. You may 

review copies of the referenced service 

information at the FAA, Transport 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 77, No. 113 / Tuesday, June 12, 2012 / Proposed Rules 34873 

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: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: (425) 227–1137; 

fax: (425) 425–227–1149; email: 

tom.rodriguez@faa.gov. 

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–2012–0593; Directorate Identifier 

2011–NM–238–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 European Aviation Safety Agency 

(EASA), which is the aviation authority 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2011–0183, 

dated September 23, 2011 (referred to 

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

unsafe condition for the specified 

products. The MCAI states: 

Reports have been received about burned 

contacts in production break plug P4259B 

and corresponding receptacle J 4259A. After 

investigation, it was concluded that the high 

electrical load on the contacts M, L and X, 

in combination with the electrical loads on 

the adjacent connections, may have resulted 

in these occurrences. 

This condition, if not detected and corrected, 

can lead to overheating of the galley power 

supply wiring and/or the electrical connector 

and consequent smoke or fire in the galley 

area, possibly resulting in damage to the 

aeroplane and injury to occupants. 

For the reasons described above, this [EASA] 

AD requires modification of the galley power 

supply wiring by disconnecting it from the 

affected plug/receptacle and reconnecting the 

power supply wiring through splices. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Fokker Services B.V has issued 

Fokker Service Bulletin SBF100–24– 

044, dated July 14, 2011, which 

includes the following attachment: 

• Fokker Manual Change 

Notification—Maintenance 

Documentation MCNM–F100–148, 

dated July 14, 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 4 products of U.S. registry. 

We also estimate that it would take 

about 4 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 $210 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 

$2,200, or $550 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: 

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34874 Federal Register / Vol. 77, No. 113 / Tuesday, June 12, 2012 / Proposed Rules 

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: 

Fokker Services B.V.: Docket No. FAA– 

2012–0593; Directorate Identifier 2011– 

NM–238–AD. 

(a) Comments Due Date 

We must receive comments by July 27, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Fokker Services B.V. 

Model F.28 Mark 0070 and 0100 airplanes; 

certificated in any category; serial number (s/ 

n) 11340 through 11343 inclusive, 11347, 

11348, 11350 through 11356 inclusive, 

11359, 11360, 11361, 11367 through 11371 

inclusive, 11374 through 11378 inclusive, 

11382 through 11385 inclusive, 11387 

through 11390 inclusive, 11394 through 

11397 inclusive, 11400 through 11423 

inclusive, 11425 through 11432 inclusive, 

11434 through 11439 inclusive, 11441 

through 11453 inclusive, and 11456 through 

11585 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 24, Electrical Power. 

(e) Reason 

This AD was prompted by reports of 

burned contacts in a certain production break 

plug and its corresponding receptacle. We are 

issuing this AD to prevent a high electrical 

load which may lead to overheating of the 

galley power supply wiring and/or the 

electrical connector and consequent smoke or 

fire in the galley area, which could result in 

damage to the airplane and injury to 

occupants. 

(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) Modification 

Within 24 months after the effective date 

of this AD: Modify the galley power supply 

wiring, in accordance with the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–24–044, dated July 

14, 2011, which includes Fokker Manual 

Change Notification—Maintenance 

Documentation MCNM–F100–148, dated July 

14, 2011. 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA 1601 Lind Avenue 

SW., Renton, Washington 98057–3356; 

telephone (425) 227–1137; fax (425) 227– 

1149. Information may be emailed to: 9– 

ANM–116–AMOC–REQUESTS@faa.gov. 

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. 

(i) Related Information 

Refer to MCAI EASA Airworthiness 

Directive 2011–0183, dated September 23, 

2011; and Fokker Service Bulletin SBF 100– 

24–044, dated July 14, 2011, which includes 

Fokker Manual Change Notification— 

Maintenance Documentation MCNM–F100– 

148, dated July 14, 2011; for related 

information. 

Issued in Renton, Washington, on May 31, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–14211 Filed 6–11–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0594; Directorate 

Identifier 2012–NM–019–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 

movement of the rudder pedals being 

impeded due to corrosion of the 

trunnion shaft of the rudder feel trim 

unit (RFTU). This proposed AD would 

require inspecting to determine if 

certain RFTUs are installed, an 

operational check for signs of seizure of 

affected parts, repetitive lubrication for 

certain RFTUs, and replacing the RFTU 

with a new RFTU if necessary. 

Installation of replaced RFTUs with 

conformal bushings terminates the 

repetitive lubrication requirements. We 

are proposing this AD to detect and 

correct any sign of seizure of the 

trunnion shaft and its bushing, which 

could cause a rudder control jam or a 

large and rapid alternating rudder input 

leading to a structural failure of the 

vertical fin. 

DATES: We must receive comments on 

this proposed AD by July 27, 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 

mstockstill on DSK4VPTVN1PROD with PROPOSALS