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 

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Federal Register / Vol. 77, No. 113 / Tuesday, June 12, 2012 / Proposed Rules 34875 

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–2012–0594; Directorate Identifier 

2011–NM–019–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 aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2012–02, 

dated January 9, 2012 (referred to after 

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

condition for the specified products. 

The MCAI states: 

There have been several reported incidents 

on DHC–8 Series 400 aeroplanes where the 

movement of the rudder pedals has been 

impeded. An investigation showed that the 

Rudder Feel Trim Unit (RFTU) trunnion shaft 

was corroded. The root cause of the corrosion 

was a quality escape where cadmium plating 

on the trunnion bushing within the RFTU 

assembly was not removed. Corrosion on the 

shaft and in the trunnion bushing seized the 

trunnion and caused difficulties in 

controlling the rudder movement. 

This condition, if not corrected, could cause 

a rudder control jam or a large and rapid 

alternating rudder input leading to a 

structural failure of the vertical fin. 

This [TCCA] Airworthiness Directive (AD) is 

issued [inspect to determine serial number, 

an operational check for seizure, repetitive 

lubrication and] to replace the affected 

RFTUs to limit the possibility of binding and 

replace the affected RFTUs with units that 

have been reworked with conformal bushings 

to terminate the lubrication requirements. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Bombardier, Inc. has issued Service 

Bulletin 84–27–57, dated July 22, 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 83 products of U.S. registry. 

We also estimate that it would take 

about 5 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 $35,275, or $425 per 

product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 10 work-hours and require parts 

costing $0, for a cost of $850 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 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– 

0594; Directorate Identifier 2012–NM– 

019–AD. 

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34876 Federal Register / Vol. 77, No. 113 / Tuesday, June 12, 2012 / Proposed Rules 

(a) Comments Due Date 

We must receive comments by July 27, 

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, 4003 and subsequent, equipped with 

rudder feel trim unit part number 399500– 

1007. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27: Flight Controls. 

(e) Reason 

This 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). 

We are issuing 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. 

(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 

Within 600 flight hours or six months after 

the effective date of this AD whichever 

occurs first, inspect the RTFU to determine 

whether the serial number (S/N) is in the 

range from 0009 through 0388 without a 

suffix ‘‘A,’’ in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–27–57, dated July 22, 

2011. A review of airplane maintenance 

records is acceptable in lieu of this 

inspection if the serial number of the RFTU 

can be conclusively determined from that 

review. 

(1) If the RFTU’s serial number is not in 

the range from 0009 through 0388 or if the 

serial number has a suffix ‘‘A,’’ no further 

action is required for this paragraph. 

(2) If the RFTU’s serial number is in the 

range from 0009 through 0388 without a 

suffix ‘‘A,’’ before further flight, perform an 

operational check of the RFTU for any sign 

of seizure of the trunnion and its bushing, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–27–57, dated July 22, 2011. 

(i) If a seizure of the RFTU trunnion and 

its bushings is found: Before further flight, 

replace the RFTU with a new RFTU, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–27–57, dated July 22, 2011. 

(ii) If no seizure of the RFTU trunnion and 

its bushings is found: Before further flight, 

lubricate the RFTU, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–27–57, dated July 22, 

2011. Repeat the lubrication of the RFTU at 

intervals not to exceed 600 flight hours until 

the replacement required by paragraph (h) is 

done. 

(h) Replacement 

For airplanes identified in paragraph (g)(2) 

of this AD: Within 6,000 flight hours after the 

effective date of this AD, replace all affected 

RFTUs with units that have a serial number 

outside the range from 0009 through 0388 or 

that have a serial number with a suffix ‘‘A,’’ 

in accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–27–57, dated July 22, 2011. 

(i) Parts Installation 

As of the effective date of this AD, no 

person may install a RFTU P/N 399500–1007 

with a serial number from 0009 through 0388 

without a suffix ‘‘A’’ on any airplane. 

(j) 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. 

(k) Related Information 

(1) Refer to MCAI Canadian Airworthiness 

Directive CF–2012–02, dated January 9, 2012; 

and Bombardier Service Bulletin 84–27–57, 

dated July 22, 2011; for related information. 

(2) For 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. 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 May 31, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–14212 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–2012–0595; Directorate 

Identifier 2012–NM–055–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 777 

airplanes. This proposed AD was 

prompted by reports of failure of wire 

support clamps in the forward section of 

the aft pressure bulkhead. This 

proposed AD would require a detailed 

inspection of the clamps on the power 

feeder cable auxiliary power unit (APU) 

to determine if certain clamps are 

installed, and related investigative and 

corrective actions if necessary. We are 

proposing this AD to prevent failure of 

the clamp, which could result in wire 

chafing and potential arcing and 

consequent fire in section 48 (a 

flammable fluid leakage zone) or heat 

damage to the APU power feeder cable, 

insulation blankets, or pressure 

bulkhead. 

DATES: We must receive comments on 

this proposed AD by July 27, 2012. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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. 

For service information identified in 

this proposed AD, contact Boeing 

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