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

3854 

Vol. 76, No. 14 

Friday, January 21, 2011 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0058; Directorate 

Identifier 2010–CE–071–AD] 

RIN 2120–AA64 

Airworthiness Directives; REIMS 

AVIATION S.A. Model F406 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above that would 

supersede an existing AD. This 

proposed AD results from mandatory 

continuing airworthiness information 

(MCAI) originated by an aviation 

authority of another country to identify 

and correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as: 

In early 2005, several reports had been 

received regarding discovery of cracks in 

rudder pulley brackets installed on Reims 

F406 aeroplanes. This pulley bracket, Part 

Number (P/N) 6015511–1, is installed on 

aeroplanes with the optional ‘‘Camera Hole’’ 

modification. 

This condition, if not detected and 

corrected, could result in the loss of rudder 

control on the airplane. 

The proposed AD would require actions 

that are intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by March 7, 2011. 

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 20590, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Reims 

Aviation Industries, Ae ́rodrome de 

Reims Prunay, 51360 Prunay, France; 

telephone + 33 3 26 48 46 65; fax + 33 

3 26 49 18 57; e-mail Jn.sirot@reimsaviation.fr. You may review copies of 

the referenced service information at the 

FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. 

For information on the availability of 

this material at the FAA, call 816–329– 

4148. 

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 

(telephone (800) 647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Albert Mercado, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4119; fax: (816) 329–4090. 

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–2011–0058; Directorate Identifier 

2010–CE–071–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 because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

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 

On January 12, 2007, we issued AD 

2007–02–12, Amendment 39–14899 (72 

FR 3047; January 24, 2007). That AD 

required actions intended to address an 

unsafe condition on the products listed 

above. 

Since we issued AD 2007–02–12, 

REIMS AVIATION S.A. discovered that 

airplane serial number (SN) F406–0091 

had inadvertently not been included in 

the service information and has revised 

the service information to correct the 

omission. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued AD No.: 2010– 

0230, dated November 5, 2010 (referred 

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

an unsafe condition for the specified 

products. The MCAI states: 

In early 2005, several reports had been 

received regarding discovery of cracks in 

rudder pulley brackets installed on Reims 

F406 aeroplanes. This pulley bracket, Part 

Number (P/N) 6015511–1, is installed on 

aeroplanes with the optional ‘‘Camera Hole’’ 

modification. 

This condition, if not detected and 

corrected, could result in the loss of rudder 

control on the airplane. 

To address this unsafe condition, DGAC 

France issued Emergency (Urgent) AD UF– 

2005–080, followed by the final AD F–2005– 

080, requiring repetitive inspections of the 

P/N 6015511–1 rudder pulley bracket and 

replacement of the bracket with a modified 

bracket, P/N 4061–2701–1, as terminating 

action. 

Recently, Reims discovered that aeroplane 

s/n F406–0091 had inadvertently not been 

included in the SB and this has been revised 

to correct the omission. 

For the reasons described above, this AD 

retains the requirements of DGAC France AD 

F–2005–080, which is superseded, and adds 

aeroplane s/n F406–0091 to the Applicability 

of the AD, by referencing Revision 2 of the 

Reims Aviation Industries SB F406–58. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Reims Aviation S.A. has issued Reims 

Aviation Industries Service Bulletin No. 

F406–58, REV 1, dated October 27, 

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Federal Register / Vol. 76, No. 14 / Friday, January 21, 2011 / Proposed Rules 3855 

2006; and Reims Aviation Industries 

Service Bulletin No. F406–58, REV 2, 

dated July 27, 2010. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of the 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 this State of 

Design Authority, they have notified us 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This Proposed AD 

and the MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a Note within the 

proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

will affect 7 products of U.S. registry. 

We also estimate that it would take 

about 11 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 $750 per 

product. 

Based on these figures, we estimate 

the cost of the proposed AD on U.S. 

operators to be $11,795, or $1,685 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); and 

3. 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 

removing Amendment 39–14899 (72 FR 

3047; January 24, 2007), and adding the 

following new AD: 

Reims Aviation S.A.: Docket No. FAA–2011– 

0058; Directorate Identifier 2010–CE– 

071–AD. 

Comments Due Date 

(a) We must receive comments by March 7, 

2011. 

Affected ADs 

(b) This AD supersedes AD 2007–02–12, 

Amendment 39–14899. 

Applicability 

(c) This AD applies to Reims Aviation S.A. 

Model F406 airplanes, serial numbers (SNs) 

0002, 0003, 0004, 0006, 0008, 0009, 0010, 

0012, 0013, 0017, 0024, 0025, 0039, 0042, 

0044, 0045, 0066, 0070, 0073, 0074, 0075, 

0077, 0080 through 0092, certificated in any 

category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 27: Flight Controls. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

In early 2005, several reports had been 

received regarding discovery of cracks in 

rudder pulley brackets installed on Reims 

F406 aeroplanes. This pulley bracket, Part 

Number (P/N) 6015511–1, is installed on 

aeroplanes with the optional ‘‘Camera Hole’’ 

modification. 

This condition, if not detected and 

corrected, could result in the loss of rudder 

control on the airplane. 

To address this unsafe condition, DGAC 

France issued Emergency (Urgent) AD UF– 

2005–080, followed by the final AD F–2005– 

080, requiring repetitive inspections of the 

P/N 6015511–1 rudder pulley bracket and 

replacement of the bracket with a modified 

bracket, P/N 4061–2701–1, as terminating 

action. 

Recently, Reims discovered that aeroplane 

s/n F406–0091 had inadvertently not been 

included in the SB and this has been revised 

to correct the omission. 

For the reasons described above, this AD 

retains the requirements of DGAC France AD 

F–2005–080, which is superseded, and adds 

aeroplane s/n F406–0091 to the Applicability 

of the AD, by referencing Revision 2 of the 

Reims Aviation Industries SB F406–58. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) For all affected SNs except F406–0091: 

(i) Within the next 10 hours time-in-service 

(TIS) after February 13, 2007 (the effective 

date retained from AD 2007–02–12), perform 

the initial inspection as specified in Reims 

Aviation Industries Service Bulletin No. 

F406–58, REV 1, dated October 27, 2006; or 

Reims Aviation Industries Service Bulletin 

No. F406–58, REV 2, dated July 27, 2010. 

(ii) If no cracking is found following the 

initial inspection required in paragraph 

(f)(1)(i) of this AD, repetitively thereafter 

inspect every 50 hours TIS or 1 month, 

whichever occurs first, until the installation 

of the modified pulley bracket specified in 

paragraphs (f)(1)(iii) or (f)(1)(iv) of this AD is 

done. 

(iii) If any cracking is found during the 

inspection required in paragraph (f)(1)(i) of 

this AD, before further flight, install the 

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modified pulley bracket as specified in Reims 

Aviation Industries Service Bulletin No. 

F406–58, REV 1, dated October 27, 2006; or 

Reims Aviation Industries Service Bulletin 

No. F406–58, REV 2, dated July 27, 2010. 

This installation terminates the repetitive 

inspections required in paragraph (f)(1)(ii) of 

this AD. 

(iv) Within the next 100 hours TIS or 2 

months after February 13, 2007 (the effective 

date retained from AD 2007–02–12), 

whichever occurs first, install the modified 

pulley bracket as specified in Reims Aviation 

Industries Service Bulletin No. F406–58, REV 

1, dated October 27, 2006; or Reims Aviation 

Industries Service Bulletin No. F406–58, REV 

2, dated July 27, 2010. This installation 

terminates the repetitive inspections required 

in paragraph (f)(1)(ii) of this AD. 

(v) The modified pulley bracket specified 

in Reims Aviation Industries Service Bulletin 

No. F406–58, REV 1, dated October 27, 2006; 

or Reims Aviation Industries Service Bulletin 

No. F406–58, REV 2, dated July 27, 2010, 

may be installed at any time after the 

inspection required in paragraph (f)(1)(i) of 

this AD, as long as no cracking is found, but 

no later than the compliance time specified 

in paragraph (f)(1)(iv) of this AD. If cracking 

is found, it must be replaced before further 

flight as required in paragraph (f)(1)(iii) of 

this AD. 

(2) For serial number F406–0091: 

(i) Within the next 10 hours TIS after the 

effective of this AD, perform the initial 

inspection as specified in Reims Aviation 

Industries Service Bulletin No. F406–58, REV 

2, dated July 27, 2010. 

(ii) If no cracking is found following the 

initial inspection required in paragraph 

(f)(2)(i) of this AD, repetitively thereafter 

inspect every 50 hours TIS or 1 month, 

whichever occurs first, until the installation 

of the modified pulley bracket specified in 

paragraphs (f)(2)(iii) and (f)(2)(iv) of this AD 

is done. 

(iii) If any cracking is found during the 

inspection required in paragraph (f)(2)(i) of 

this AD, before further flight, install the 

modified pulley bracket as specified in Reims 

Aviation Industries Service Bulletin No. 

F406–58, REV 2, dated July 27, 2010. This 

installation terminates the repetitive 

inspections required in paragraph (f)(2)(ii) of 

this AD. 

(iv) Within the next 100 hours TIS or 2 

months after the effective of this AD, 

whichever occurs first, install the modified 

pulley bracket as specified in Reims Aviation 

Industries Service Bulletin No. F406–58, REV 

2, dated July 27, 2010. This installation 

terminates the repetitive inspections required 

in paragraph (f)(2)(ii) of this AD. 

(v) The modified pulley bracket specified 

in Reims Aviation Industries Service Bulletin 

No. F406–58, REV 2, dated July 27, 2010, 

may be installed at any time after the 

inspection required in paragraph (f)(2)(i) of 

this AD as long as no cracking is found, but 

no later than the compliance time specified 

in paragraph (f)(2)(iv) of this AD. If cracking 

is found, it must be replaced before further 

flight as required in paragraph (f)(2)(iii) of 

this AD. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Albert Mercado, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4119; fax: (816) 329– 

4090. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, a federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave., SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency (EASA) AD 2010–0230, dated 

November 5, 2010; Reims Aviation Industries 

Service Bulletin No. F406–58, REV 1, dated 

October 27, 2006; and Reims Aviation 

Industries Service Bulletin No. F406–58, REV 

2, dated July 27, 2010, for related 

information. For service information related 

to this AD, contact Reims Aviation 

Industries, Ae ́rodrome de Reims Prunay, 

51360 Prunay, France; telephone + 33 3 26 

48 46 65; fax + 33 3 26 49 18 57; e-mail 

Jn.sirot@reims-aviation.fr. You may review 

copies of the referenced service information 

at the FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call 816–329–4148. 

Issued in Kansas City, Missouri, on January 

14, 2011. 

John Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–1221 Filed 1–20–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0028; Directorate 

Identifier 2009–NM–228–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 Series 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 

Model 737–100, –200, –200C, –300, 

–400, and –500 series airplanes. This 

proposed AD would result in all 

airplanes having new relays with a 

ground fault interrupter (GFI) feature. 

This proposed AD would require, 

depending on airplane configuration, 

doing certain wiring changes, replacing 

the fuel pump power control relays for 

the main, center and auxiliary tanks, as 

applicable, with new relays having a 

GFI feature, performing certain bonding 

resistance measurements, and 

modifying relay module assemblies. The 

proposed AD also would require 

revising the maintenance program to 

incorporate Airworthiness Limitations 

(AWLs) 28–AWL–23 (for Model 737– 

100, 737–200, and 737–200C series 

airplanes), and 28–AWL–22 (for Model 

737–300, 737–400, and 737–500 series 

airplanes). This proposed AD results 

from fuel system reviews conducted by 

the manufacturer. We are proposing this 

AD to prevent damage to the fuel pumps 

caused by electrical arcing that could 

introduce an ignition source in the fuel 

tank, which, in combination with 

flammable fuel vapors, could result in a 

fuel tank explosion and consequent loss 

of the airplane. 

DATES: We must receive comments on 

this proposed AD by March 7, 2011. 

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. 

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