This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

75906 

Vol. 77, No. 247 

Wednesday, December 26, 2012 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1311; Directorate 

Identifier 2011–NM–204–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–8–102, 

–103, and –106 airplanes, and Model 

DHC–8–200, –300, and –400 series 

airplanes. This proposed AD was 

prompted by reports of excessive wear 

found in the clevis (bolt) hole where the 

rod assembly attaches to the rudder/ 

brake pedal bellcrank, due to prolonged 

fretting. This proposed AD would 

require measuring the bellcrank clevis 

holes, inspecting for cracking of the 

bellcrank, and re-working the clevis 

holes with steel bushings, or replacing 

the bellcrank. We are proposing this AD 

to detect and correct a worn or cracked 

clevis hole, which could cause failure of 

the bellcrank on one side, with 

subsequent asymmetric braking and 

consequent runway excursion. 

DATES: We must receive comments on 

this proposed AD by February 11, 2013. 

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: 

Luke Walker, 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– 

7363; 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–2012–1311; Directorate Identifier 

2011–NM–204–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 AD 

CF–2011–32, dated August 15, 2011 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. The MCAI states: 

There have been several in-service reports 

of excessive wear found in the bolt [clevis] 

hole where the rod assembly, Part Numbers 

(P/N) 82710795–001 or 82710024–003, is 

attached to the rudder/brake pedal bellcrank. 

An investigation revealed that the wear was 

attributed to prolonged fretting. 

Failure of the bellcrank on one side could 

lead to asymmetric braking and may lead to 

runway excursion. 

This directive mandates [measuring clevis 

holes for length, and for certain bellcranks 

doing a liquid penetrant inspection for 

cracking, and] the re-work [by installing steel 

bushings] or replacement of each bellcrank, 

P/N 82710022–001/–002, 82710029–001/– 

002, 82710813–001/–002 and 82710814–001/ 

–002, found with a worn [or cracked] bolt 

hole. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Bombardier, Inc. has issued Service 

Bulletins 8–27–111 and 84–27–55, both 

dated June 15, 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 


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affect about 178 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. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$75,650, or $425 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 16 work-hours and require parts 

costing up to $2,532, for a cost of $3,892 

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. 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– 

1311; Directorate Identifier 2011–NM– 

204–AD. 

(a) Comments Due Date 

We must receive comments by February 

11, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. 

airplanes, certificated in any category, as 

specified in paragraphs (c)(1) and (c)(2) of 

this AD. 

(1) Model DHC–8–102, –103, –106, –201, 

–202, –301, –311, and –315 airplanes: Serial 

numbers 003 through 672 inclusive. 

(2) Model DHC–8–400, –401 and –402 

airplanes: Serial numbers 4003 through 4372 

inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27: Flight controls. 

(e) Reason 

This AD was prompted by reports of 

excessive wear found in the clevis (bolt) hole 

where the rod assembly attaches to the 

rudder/brake pedal bellcrank, due to 

prolonged fretting. We are issuing this AD to 

detect and correct a worn or cracked clevis 

hole, which could cause failure of the 

bellcrank on one side, with subsequent 

asymmetric braking and consequent runway 

excursion. 

(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) Actions for Model DHC–8–100, –200, and 

–300 Series Airplanes 

For Model DHC–8–102, –103, –106, –201, 

–202, –301, –311, and –315 airplanes: Within 

6,000 flight hours or 24 months after the 

effective date of this AD, whichever occurs 

first, measure the edge-to-edge length of the 

clevis holes of each bellcrank; and, if the 

length is less than or equal to 0.218 inch, 

inspect for cracking of each bellcrank using 

liquid penetrant; in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–27–111, dated June 15, 

2011. 

(1) If no cracking is found: Before further 

flight, rework the bellcrank, in accordance 

with the Accomplishment Instructions of 

Bombardier Service Bulletin 8–27–111, dated 

June 15, 2011. 

(2) If any clevis hole is greater than 0.218 

inch, or if any cracking is found: Before 

further flight, replace the bellcrank with a 

new bellcrank, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–27–111, dated June 15, 

2011. 

(h) Actions for Certain Model DHC–8–400 

Series Airplanes 

For Model DHC–8–400, –401, and –402 

airplanes that have accumulated less than or 

equal to 15,000 total flight hours as of the 

effective date of this AD: Within 6,000 flight 

hours after the effective date of this AD, but 

not to exceed 15,600 total flight hours, 

measure the edge-to-edge length of the clevis 

holes of each bellcrank, and inspect for 

cracking of each bellcrank using liquid 

penetrant; in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–27–55, dated June 15, 

2011. 

(1) If no cracking is found, and the edgeto-edge length of all clevis holes is less than 

or equal to 0.218 inch: Within 6,000 flight 

hours after the effective date of this AD, but 

not to exceed 15,600 total flight hours, 

rework or replace the bellcrank, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–27–55, dated June 15, 2011. 

(2) If no cracking is found, and any clevis 

hole edge-to-edge length is greater than 0.218 

inch but less than or equal to 0.248 inch: 

Within 6,000 flight hours after the effective 

date of this AD, replace the bellcrank with a 

new bellcrank, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–27–55, dated June 15, 

2011. 

(3) If no cracking is found, and any clevis 

hole edge-to-edge length is greater than 0.248 

inch but less than or equal to 0.278 inch: 

Within 1,200 flight hours after doing the 

measurement/inspection required by 

paragraph (h) of this AD, replace the 

bellcrank with a new bellcrank, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–27–55, dated June 15, 2011. 

(4) If any cracking is found, or if any clevis 

hole edge-to-edge length exceeds 0.278 inch: 

Before further flight, replace the bellcrank 


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75908 Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Proposed Rules 

with a new bellcrank, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–27–55, dated June 15, 

2011. 

(i) Actions for Certain Other Model DHC–8– 

400 Series Airplanes 

For Model DHC–8–400, –401, and –402 

airplanes that have accumulated more than 

15,000 total flight hours as of the effective 

date of this AD: Within 600 flight hours after 

the effective date of this AD, measure the 

edge-to-edge length of the clevis holes of 

each bellcrank, and inspect for cracking of 

each bellcrank using liquid penetrant; in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–27–55, dated June 15, 2011. 

(1) If no cracking is found, and the edgeto-edge length of all clevis holes is less than 

or equal to 0.218 inch: At the later of the 

compliance times specified in paragraphs 

(i)(1)(i) and (i)(1)(ii) of this AD, rework or 

replace the bellcrank, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–27–55, dated June 15, 

2011. 

(i) Within 6,000 flight hours after the 

effective date of this AD, but not to exceed 

15,600 total flight hours. 

(ii) Within 1,200 flight hours after the 

effective date of this AD. 

(2) If no cracking is found, and any clevis 

hole edge-to-edge length is greater than 0.218 

inch but less than or equal to 0.248 inch: 

Within 6,000 flight hours after the effective 

date of this AD, replace the bellcrank with a 

new bellcrank, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–27–55, dated June 15, 

2011. 

(3) If no cracking is found, and any clevis 

hole edge-to-edge length is greater than 0.248 

inch but less than or equal to 0.278 inch: 

Within 1,200 flight hours after the effective 

date of this AD, replace the bellcrank with a 

new bellcrank, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–27–55, dated June 15, 

2011. 

(4) If any cracking is found, or any clevis 

hole edge-to-edge length exceeds 0.278 inch: 

Before further flight, replace the bellcrank 

with a new bellcrank, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–27–55, dated June 15, 

2011. 

(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–2011–32, dated August 15, 

2011, and the service bulletins specified in 

paragraphs (k)(1) (i) and (k)(1)(ii) of this AD, 

for related information. 

(i) Bombardier Service Bulletin 8–27–111, 

dated June 15, 2011. 

(ii) Bombardier Service Bulletin 84–27–55, 

dated June 15, 2011. 

(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, 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on 

December 17, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–30925 Filed 12–21–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1313; Directorate 

Identifier 2012–NM–080–AD] 

RIN 2120–AA64 

Airworthiness Directives; Gulfstream 

Aerospace Corporation 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Gulfstream Aerospace Corporation 

Model GV and GV–SP airplanes. This 

proposed AD was prompted by reports 

of two failures of the fuel boost pump 

and over-heat damage found on the 

internal components and external 

housing. This proposed AD would 

require doing an inspection to 

determine if fuel boost pumps having a 

certain part number are installed, 

replacing the fuel boost pumps having 

a certain part number, and revising the 

airplane maintenance program to 

include revised instructions for 

continued airworthiness. We are 

proposing this AD to prevent fuel 

leakage into the dry cavity of the boost 

pump and outside of the fuel pump, and 

to prevent capacitor clearance issues in 

the dry cavity, which together could 

result in an uncontrolled fire in the 

wheel well. 

DATES: We must receive comments on 

this proposed AD by February 11, 2013. 

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 Gulfstream, Triumph 

Aerostructures, and GE Aviation service 

information identified in this proposed 

AD, contact Gulfstream Aerospace 

Corporation, Technical Publications 

Dept., P.O. Box 2206, Savannah, GA 

31402–2206; telephone 800–810–4853; 

fax 912–965–3520; email 

pubs@gulfstream.com; Internet http:// 

www.gulfstream.com/product_support/

technical_pubs/pubs/index.htm. 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 Management Facility 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 Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 


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