3856 Federal Register / Vol. 76, No. 14 / Friday, January 21, 2011 / Proposed Rules 

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. 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS

Federal Register / Vol. 76, No. 14 / Friday, January 21, 2011 / Proposed Rules 3857 

• 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: Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.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 or 425–227–1152. 

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: 

Georgios Roussos, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, FAA, Seattle Aircraft Certification 

Office (ACO), 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; 

telephone (425) 917–6482; fax (425) 

917–6590. 

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–2011–0028; Directorate Identifier 

2009–NM–228–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:// 

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 FAA has examined the 

underlying safety issues involved in fuel 

tank explosions on several large 

transport airplanes, including the 

adequacy of existing regulations, the 

service history of airplanes subject to 

those regulations, and existing 

maintenance practices for fuel tank 

systems. As a result of those findings, 

we issued a regulation titled ‘‘Transport 

Airplane Fuel Tank System Design 

Review, Flammability Reduction and 

Maintenance and Inspection 

Requirements’’ (66 FR 23086, May 7, 

2001). In addition to new airworthiness 

standards for transport airplanes and 

new maintenance requirements, this 

rule included Special Federal Aviation 

Regulation No. 88 (‘‘SFAR 88,’’ 

Amendment 21–78, and subsequent 

Amendments 21–82 and 21–83). 

Among other actions, SFAR 88 

requires certain type design (i.e., type 

certificate (TC) and supplemental type 

certificate (STC)) holders to substantiate 

that their fuel tank systems can prevent 

ignition sources in the fuel tanks. This 

requirement applies to type design 

holders for large turbine-powered 

transport airplanes and for subsequent 

modifications to those airplanes. It 

requires them to perform design reviews 

and to develop design changes and 

maintenance procedures if their designs 

do not meet the new fuel tank safety 

standards. As explained in the preamble 

to the rule, we intended to adopt 

airworthiness directives to mandate any 

changes found necessary to address 

unsafe conditions identified as a result 

of these reviews. 

In evaluating these design reviews, we 

have established four criteria intended 

to define the unsafe conditions 

associated with fuel tank systems that 

require corrective actions. The 

percentage of operating time during 

which fuel tanks are exposed to 

flammable conditions is one of these 

criteria. The other three criteria address 

the failure types under evaluation: 

Single failures, single failures in 

combination with a latent condition(s), 

and in-service failure experience. For all 

four criteria, the evaluations included 

consideration of previous actions taken 

that may mitigate the need for further 

action. 

We have determined that the actions 

identified in this AD are necessary to 

reduce the potential of ignition sources 

inside fuel tanks, which, in combination 

with flammable fuel vapors, could result 

in a fuel tank explosion and consequent 

loss of the airplane. 

As part of an SFAR88 analysis, Boeing 

determined that the power control 

relays for the main tank fuel boost 

pumps, the center tank fuel boost 

pumps, and for certain airplanes, the 

auxiliary tank fuel boost pumps should 

be replaced with new relays having a 

ground fault interrupter (GFI) feature. 

The relays are located in the P6 circuit 

breaker panel in the flight compartment. 

The GFI relay feature is intended to 

protect the fuel boost pumps from 

damage caused from electrical arcing by 

removing electrical power from the 

pump if a ground fault is detected. 

Electrical arcing, if not prevented 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. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin 737–28A1212, Revision 

1, dated August 27, 2010. Depending on 

airplane configuration and on whether 

the actions in Boeing Alert Service 

Bulletin 737–28A1212, dated July 23, 

2009, were accomplished, Boeing Alert 

Service Bulletin 737–28A1212, Revision 

1, dated August 27, 2010, describes 

procedures for the following actions, 

depending on airplane configurations: 

• Doing wiring changes, 

• Replacing the fuel pump power 

control relays for the main, center and 

auxiliary tanks with new relays having 

a GFI feature, 

• Doing certain bonding resistance 

measurements to verify certain bonding 

requirements are met, and 

• Modifying the M181, M182, M183 

relay module assemblies. 

Boeing Alert Service Bulletin 737– 

28A1212, Revision 1, dated August 27, 

2010, specifies a compliance time of 60 

months for replacing the power control 

relays. 

For certain airplanes, Boeing Alert 

Service Bulletin 737–28A1212, Revision 

1, dated August 27, 2010, refers to BAE 

Systems Service Bulletin 65–49808–24– 

01, Revision 1, dated July 19, 2010, as 

an additional source of guidance for 

doing the modification of the relay 

module assemblies and bond resistance 

measurements. 

In addition, we have reviewed Section 

9 of Boeing 737–100/200/200C/300/400/ 

500 Airworthiness Limitations (AWLs) 

and Certification Maintenance 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS

3858 Federal Register / Vol. 76, No. 14 / Friday, January 21, 2011 / Proposed Rules 

Requirements, D6–38278–CMR, 

Revision May 2009 (hereafter referred to 

as ‘‘Document D6–38278–CMR’’). 

Document D6–38278–CMR describes, 

among other actions, new AWLs for the 

applicable fuel boost pumps that 

incorporate ground fault interrupter 

relays for certain Model 737–100, –200, 

and –200C airplanes (i.e., AWL 28– 

AWL–23), and for certain other Model 

737–300, –400, and –500 airplanes (i.e., 

AWL 28–AWL–22). The AWL reference 

to boost pumps applies also to all 

pumps where the GFI has been installed 

by incorporating Boeing Alert Service 

Bulletin 737–28A1212. 

FAA’s Determination and Requirements 

of This Proposed AD 

We are proposing this AD because we 

evaluated all relevant information and 

determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. This proposed AD would 

require accomplishing the actions 

specified in the service information 

described previously, except as 

described under ‘‘Difference Between 

the Proposed AD and Service 

Information.’’ 

Difference Between the Proposed AD 

and Service Information 

AWL 28–AWL–23 of Section 9 of 

Boeing 737–100/200/200C/300/400/500 

Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs), Document D6–38278–CMR, 

Revision May 2009, is applicable to 

Model 737–100, –200, and –200C 

airplanes, although it specifies only the 

Model 737–100 and –200 airplanes. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 750 airplanes of U.S. 

registry. The following table provides 

the estimated costs for U.S. operators to 

comply with this proposed AD. 

TABLE—ESTIMATED COSTS

Action Work 

hours 

Average labor 

rate per hour Parts Cost per product 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Replacement of power 

control relays.

4 to 9 1 ..... $85 $14,500 $14,840 to $15,265 1 ..... 750 $11,130,000 to 

$11,448,750.1

Modification .................... 5 ............... 85 0 $425 ............................... 750 $318,750. 

Maintenance program revision.1 ............... 85 0 $85 ................................. 750 $63,750. 

1 Depending on airplane configuration. 

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. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance 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: 

The Boeing Company: Docket No. FAA– 

2011–0028; Directorate Identifier 2009– 

NM–228–AD. 

Comments Due Date 

(a) We must receive comments by March 7, 

2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes, 

certificated in any category; as identified in 

Boeing Alert Service Bulletin 737–28A1212, 

Revision 1, dated August 27, 2010. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new inspections. Compliance with 

these inspections is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these inspections, the 

operator may not be able to accomplish the 

inspections described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance according 

to paragraph (m) of this AD. The request 

should include a description of changes to 

the required inspections that will ensure the 

continued operational safety of the airplane. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 28: Fuel. 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS

Federal Register / Vol. 76, No. 14 / Friday, January 21, 2011 / Proposed Rules 3859 

Unsafe Condition 

(e) This AD results from fuel system 

reviews conducted by the manufacturer. The 

Federal Aviation Administration is issuing 

this AD to prevent the 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. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Part 1: Wiring Changes, Relay Replacements, 

and Certain Bonding Resistance 

Measurements for Certain Airplanes 

(g) For airplanes on which Boeing Alert 

Service Bulletin 737–28A1212, dated July 23, 

2009, has not been incorporated as of the 

effective date of this AD: Within 60 months 

after the effective date of this AD, do the 

applicable action required by paragraph (g)(1) 

or (g)(2) of this AD. 

(1) Airplanes without the M181, M182, and 

M183 supplier relay modules installed: Do 

the wiring changes; replace the fuel pump 

power control relays for the main, center, and 

auxiliary tanks, as applicable, with new 

relays having a ground fault interrupter (GFI) 

feature; and do certain bonding resistance 

measurements to verify that certain bonding 

requirements are met; in accordance with 

Part 1 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–28A1212, 

Revision 1, dated August 27, 2010. 

(2) Airplanes with the M181, M182, and 

M183 supplier relay modules installed: 

Modify the M181, M182, and M183 relay 

module assemblies, and do certain bonding 

resistance measurements to verify that 

certain bonding requirements are met, in 

accordance with Part 1 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–28A1212, Revision 1, 

dated August 27, 2010. 

Note 2: Boeing Alert Service Bulletin 737– 

28A1212, Revision 1, dated August 27, 2010, 

refers to BAE Systems Service Bulletin 65– 

49808–24–01, Revision 1, dated July 19, 

2010, as an additional source of guidance for 

doing the modification and certain bonding 

resistance measurements. 

Part 2: Wiring Changes and Certain Bonding 

Measurements for Certain Airplanes 

(h) For airplanes on which Boeing Alert 

Service Bulletin 737–28A1212, dated July 23, 

2009, has been incorporated as of the 

effective date of this AD, and on which the 

M181, M182, and M183 supplier relay 

modules have not been installed: Within 60 

months after the effective date of this AD, do 

the wiring changes and certain bonding 

measurements to verify that certain bonding 

requirements are met, in accordance with 

Part 2 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–28A1212, 

Revision 1, dated August 27, 2010. 

Part 3: Certain Bonding Measurements for 

Certain Airplanes 

(i) For airplanes on which Boeing Alert 

Service Bulletin 737–28A1212, dated July 23, 

2009, has been incorporated as of the 

effective date of this AD, and that the M181, 

M182, and M183 supplier relay modules are 

installed: Within 60 months after the 

effective date of this AD, do certain bonding 

measurements to verify that certain bonding 

requirements are met, in accordance with 

Part 3 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–28A1212, 

Revision 1, dated August 27, 2010. 

Note 3: Boeing Alert Service Bulletin 737– 

28A1212, Revision 1, dated August 27, 2010, 

refers to BAE Systems Service Bulletin 65– 

49808–24–01, Revision 1, dated July 19, 

2010, as an additional source of guidance for 

doing the modification and certain bonding 

resistance measurements. 

Maintenance Program Revisions 

(j) Concurrently with accomplishing the 

actions required by paragraph (g), (h), or (i) 

of this AD, as applicable, or within 30 days 

after the effective date of this AD, whichever 

occurs later, revise the maintenance program 

by incorporating the applicable airworthiness 

limitation (AWL) specified in paragraph (j)(1) 

or (j)(2) of this AD. 

(1) For Model 737–100, –200, and –200C 

series airplanes: Airworthiness Limitation 

28–AWL–23 of Section 9 of Boeing 737–100/ 

200/200C/300/400/500 AWL and 

Certification Maintenance Requirements 

(CMRs), Document D6–38278–CMR, Revision 

May 2009. The initial compliance time for 

the actions specified in AWL 28–AWL–23 is 

within 1 year after accomplishing the 

installation required by paragraph (g), (h), or 

(i) of this AD, or within 1 year after the 

effective date of this AD, whichever occurs 

later. 

(2) For Model 737–300, –400, and –500 

series airplanes: AWL 28–AWL–22 of Section 

9 of Boeing 737–100/200/200C/300/400/500 

Airworthiness Limitation (AWL) and 

Certification Maintenance Requirements 

(CMRs), Document D6–38278–CMR, Revision 

May 2009. The initial compliance time for 

the actions specified in AWL 28–AWL–22 is 

within 1 year after accomplishing the 

installation required by paragraph (g), (h), or 

(i) of this AD, or within 1 year after the 

effective date of this AD, whichever occurs 

later. 

No Alternative Inspections or Inspection 

Interval 

(k) After accomplishment of the action 

required by paragraph (g), (h), or (i) of this 

AD, as applicable, no alternative inspections 

or inspection intervals may be used, unless 

the inspections or intervals are approved as 

an alternative means of compliance in 

accordance with the procedures specified in 

paragraph (m) of this AD. 

Credit for Actions Accomplished in 

Accordance With Earlier Revisions of AWLs 

(l) Revising the maintenance program to 

incorporate AWLs 28–AWL–22 (for Model 

737–300, –400, and –500 airplanes) and 28– 

AWL–23 (for Model 737–100, –200, and 

–200C airplanes) in accordance with 

paragraphs (g)(1) and (g)(2) of AD 2008–10– 

09 R1, amendment 39–16148, terminates the 

requirements of paragraph (j) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(m)(1) The Manager, Seattle Aircraft 

Certification 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: Georgios 

Roussos, Aerospace Engineer, Systems and 

Equipment Branch, ANM–130S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 917–6482; fax (425) 

917–6590. Or, e-mail information to 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) 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. 

Issued in Renton, Washington, on January 

12, 2011. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–1226 Filed 1–20–11; 8:45 am] 

BILLING CODE 4910–13–P 

SECURITIES AND EXCHANGE 

COMMISSION 

17 CFR Part 240 

[Release No. 34–63727; File No. S7–03–11] 

RIN 3235–AK91 

Trade Acknowledgment and 

Verification of Security-Based Swap 

Transactions 

AGENCY: Securities and Exchange 

Commission. 

ACTION: Proposed rule. 

SUMMARY: In accordance with Section 

764(a) of Title VII of the Dodd-Frank 

Wall Street Reform and Consumer 

Protection Act of 2010 (‘‘Dodd-Frank 

Act’’), the Securities and Exchange 

Commission (‘‘Commission’’) is 

proposing rule 15Fi–1 under the 

Securities Exchange Act of 1934 

(‘‘Exchange Act’’), 15 U.S.C. 78a et seq., 

which would require security-based 

swap dealers and major security-based 

swap participants to provide trade 

acknowledgments and to verify those 

trade acknowledgments in securitybased swap transactions. 

DATES: Comments should be received on 

or before February 22, 2011. 

ADDRESSES: Comments may be 

submitted by any of the following 

methods: 

Electronic Comments 

• Use the Commission’s Internet 

comment form (http://www.sec.gov/ 

rules/proposed.shtml); 

• Send an e-mail to rulecomments@sec.gov. Please include File 

WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS