Federal Register / Vol. 77, No. 60 / Wednesday, March 28, 2012 / Proposed Rules 18719 

alternative fuel consumed by exempt 

vehicles and LSEVs. Specifically, the 

SUPPLEMENTARY INFORMATION provides 

that ‘‘a correction [of the FY 2005 

alternative fuel consumption baseline] 

might be requested in the event that the 

Federal fleet’s alternative fuel use value 

for FY 2005 submitted through FAST 

did not include the electricity used in 

the Federal fleet’s LSEVs.’’ Moreover, 

the alternative fuel consumption 

baseline data set forth in Table III.1 of 

the proposed rule includes the 

alternative fuel consumed by exempt 

vehicles and LSEVs. 

DOE notes that an approach that 

required the inclusion of alternative fuel 

consumed by exempt vehicles and 

LSEVs in the FY 2005 alternative fuel 

baseline would be consistent with the 

existing method for baseline calculation 

under the alternative fuel consumption 

requirements of Executive Order 13423. 

Moreover, such an approach could 

require each Federal fleet to consume 

greater amounts of alternative fuel to 

ensure compliance with the statutorilyrequired increase in alternative fuel 

consumption as compared to an 

approach that did not account for the 

alternative fuel consumed by exempt 

vehicles and LSEVs in its baseline 

calculation. 

With this Request for Information, 

DOE requests public comment on the 

whether the FY 2005 alternative fuel 

consumption baseline should include 

the alternative fuel consumed by 

exempt vehicles and LSEVs. DOE also 

requests comment on other potential 

approaches to complying with the 

statutorily-required increase in 

alternative fuel consumption. 

Issued in Washington, DC, on March 20, 

2012. 

Timothy D. Unruh, 

Program Manager, Federal Energy 

Management Program. 

[FR Doc. 2012–7436 Filed 3–27–12; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0327; Directorate 

Identifier 2011–NM–125–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to certain The Boeing 

Company Model DC–10–10, DC–10– 

10F, DC–10–15, DC–10–30, DC–10–30F 

(KC–10A and KDC–10), DC–10–40, DC– 

10–40F, MD–10–10F, and MD–10–30F 

airplanes. The existing AD currently 

requires installing or replacing with 

improved parts, as applicable, the 

bonding straps between the metallic 

frame of the fillet and the wing leading 

edge ribs, on both the left and right 

sides of the airplane. The existing AD 

also requires, for certain airplanes, 

repositioning or replacing two bonding 

straps, doing a bonding-resistance check 

and an inspection to determine correct 

installation of certain bonding straps, 

and applicable corrective actions. Since 

we issued that AD, we have determined 

that additional actions are necessary to 

address the identified unsafe condition. 

This proposed AD would add airplanes 

to the applicability and retain the 

requirements of the existing AD. This 

proposed AD would also require, 

depending on the airplane 

configuration, installing new braided 

bonding straps, inspecting to determine 

if a certain strap is installed and 

replacing with or installing a braided 

bonding strap if necessary, measuring 

the electrical resistance of the bonding 

straps, verifying that brackets have an 

acceptable fillet seal, and corrective 

actions if necessary. We are proposing 

this AD to reduce the potential of 

ignition sources inside fuel tanks in the 

event of a severe lightning strike, which, 

in combination with flammable fuel 

vapors, could result in fuel tank 

explosions and consequent loss of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by May 14, 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 

Commercial Airplanes, Attention: Data 

& Services Management, 3855 

Lakewood Boulevard, MC D800–0019, 

Long Beach, California 90846–0001; 

telephone 206–544–5000, extension 2; 

fax 206–766–5683; email 

dse.boecom@boeing.com; Internet 

https://www.myboeingfleet. 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. 

FOR FURTHER INFORMATION CONTACT: 

Samuel Lee, Aerospace Engineer, 

Propulsion Branch, ANM–140L, FAA, 

Los Angeles Aircraft Certification 

Office, 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; 

phone: 562–627–5262; fax: 562–627– 

5210; email: Samuel.Lee@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2012–0327; Directorate Identifier 

2011–NM–125–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 

On December 17, 2009, we issued AD 

2009–26–17, Amendment 39–16156 (74 

FR 69268, December 31, 2009), for 

certain Boeing Model DC–10–10, DC– 


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18720 Federal Register / Vol. 77, No. 60 / Wednesday, March 28, 2012 / Proposed Rules 

10–10F, DC–10–15, DC–10–30, DC–10– 

30F (KC–10A and KDC–10), DC–10–40, 

DC–10–40F, MD–10–10F, and MD–10– 

30F airplanes. That AD requires 

installing or replacing with improved 

parts, as applicable, the bonding straps 

between the metallic frame of the fillet 

and the wing leading edge ribs, on both 

the left and right sides of the airplane. 

That AD also requires, for certain 

airplanes, repositioning or replacing two 

bonding straps, and doing a bondingresistance check and an inspection to 

determine correct installation of certain 

bonding straps, and applicable 

corrective actions. That AD resulted 

from fuel system reviews conducted by 

the manufacturer. We issued that AD to 

reduce the potential of ignition sources 

inside fuel tanks in the event of a severe 

lightning strike, which, in combination 

with flammable fuel vapors, could result 

in fuel tank explosions and consequent 

loss of the airplane. 

Actions Since Existing AD 2009–26–17, 

Amendment 39–16156 (74 FR 69268, 

December 31, 2009) Was Issued 

Since we issued AD 2009–26–17, 

Amendment 39–16156 (74 FR 69268, 

December 31, 2009), Boeing has issued 

new service information that specifies 

additional actions that are necessary to 

address the identified unsafe condition. 

Relevant Service Information 

We reviewed Boeing Service Bulletin 

DC10–53–111, Revision 7, dated March 

16, 2011, which makes minor 

corrections and adds part number 

substitutions. 

We also reviewed Boeing Service 

Bulletin DC10–53–109, Revision 8, 

dated March 10, 2011. This service 

information reinstates airplanes 

inadvertently omitted from the prior 

revision of this service information, and 

describes new additional actions. This 

service information describes: 

• New procedures for installing new 

braided bonding straps, depending on 

the airplane configuration. 

• Inspecting to determine if a certain 

strap is installed, and replacing with or 

installing a braided bonding strap if 

necessary. 

• Measuring the electrical resistance 

of the bonding straps. 

• Verifying that brackets have an 

acceptable fillet seal. 

• Corrective actions if necessary. 

Corrective actions include cleaning 

braided bonding straps, and repairing 

damaged or missing fillet seals. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would retain all 

requirements of AD 2009–26–17, 

Amendment 39–16156 (74 FR 69268, 

December 31, 2009). This proposed AD 

would also require accomplishing the 

additional actions specified in the 

service information described 

previously. 

Changes to Existing AD 2009–26–17, 

Amendment 39–16156 (74 FR 69268, 

December 31, 2009) 

Since AD 2009–26–17, Amendment 

39–16156 (74 FR 69268, December 31, 

2009), was issued, the AD format has 

been revised, and certain paragraphs 

have been rearranged. As a result, the 

service bulletins listed in Table 1 of AD 

2009–26–17 are listed in paragraph 

(g)(2) of this proposed AD, and the 

service bulletins listed in Table 2 of AD 

2009–26–17 are listed in paragraph 

(g)(1) of this proposed AD. 

We also revised paragraph (h) of this 

proposed AD to describe the affected 

airplanes. Paragraph (h) of AD 2009–26– 

17, Amendment 39–16156 (74 FR 

69268, December 31, 2009), specifies 

that it is ‘‘for airplanes with fuselage 

numbers not identified in Table 2 of this 

AD * * *.’’ Since this proposed AD 

adds airplanes, we have revised that 

sentence as follows: ‘‘For airplanes with 

fuselage numbers identified in the 

applicable service bulletin listed in 

paragraph (g)(2) of this AD that are not 

also identified in the applicable service 

bulletin listed in paragraph (g)(1) of this 

AD * * *.’’ 

In addition, we have revised the 

wording of paragraph (k) of AD 2009– 

26–17, Amendment 39–16156 (74 FR 

69268, December 31, 2009); however, 

the intent of that paragraph has not 

changed. 

Costs of Compliance 

We estimate that this proposed AD 

affects 208 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Installation, inspection, and resistance measurement [retained actions from existing AD 

2009–26–17, Amendment 39–16156 (74 FR 

69268, December 31, 2009)] 

Up to 17 work-hours × $85 per 

hour = $1,445.

Up to $4,169 ........ Up to $5,614 ........ Up to $1,167,712. 

Installation, inspection, and resistance measurement [new proposed action] Up to 16 work-hours × $85 per 

hour = $1,360.

Up to $33,230 ...... Up to $34,590 ...... Up to $7,194,720. 

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 have 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. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 60 / Wednesday, March 28, 2012 / Proposed Rules 18721 

For the reasons discussed above, I 

certify that the 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. 

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 airworthiness directive (AD) 

2009–26–17, Amendment 39–16156 

(74 FR 69268, December 31, 2009), and 

adding the following new AD: 

The Boeing Company: Docket No. FAA– 

2012–0327; Directorate Identifier 2011– 

NM–125–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by May 14, 2012. 

(b) Affected ADs 

This AD supersedes AD 2009–26–17, 

Amendment 39–16156 (74 FR 69268, 

December 31, 2009). 

(c) Applicability 

This AD applies to The Boeing Company 

Model DC–10–10, DC–10–10F, DC–10–15, 

DC–10–30, DC–10–30F (KC–10A and KDC– 

10), DC–10–40, and DC–10–40F airplanes, 

and Model MD–10–10F and MD–10–30F 

airplanes that have been converted from 

Model DC–10 series airplanes; certificated in 

any category; as identified in paragraph (c)(1) 

or (c)(2) of this AD, as applicable. 

(1) Boeing Service Bulletin DC10–53–109, 

Revision 8, dated March 10, 2011 (for 

airplanes with extended wing-to-fuselage 

fillets). 

(2) Boeing Service Bulletin DC10–53–111, 

Revision 7, dated March 16, 2011 (for 

airplanes with conventional wing-to-fuselage 

fillets). 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by fuel system 

reviews conducted by the manufacturer. We 

are issuing this AD to reduce the potential of 

ignition sources inside fuel tanks in the event 

of a severe lightning strike, which, in 

combination with flammable fuel vapors, 

could result in fuel tank explosions and 

consequent loss of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Restatement of Requirements of AD 2006– 

16–03, Amendment 39–14703 (71 FR 43962, 

August 3, 2006), With New Service 

Information: Install or Replace 

For airplanes with manufacturer’s fuselage 

numbers identified in the applicable service 

bulletin listed in paragraph (g)(1) of this AD: 

Within 7,500 flight hours or 60 months after 

September 7, 2006 (the effective date of AD 

2006–16–03, Amendment 39–14703 (71 FR 

43962, August 3, 2006)), whichever occurs 

earlier: Install or replace with improved 

parts, as applicable, the bonding straps 

between the metallic frame of the fillet and 

the wing leading edge ribs, on both the left 

and right sides of the airplane, in accordance 

with the Accomplishment Instructions of the 

applicable service bulletin identified in 

paragraph (g)(1), (g)(2), or (g)(3) of this AD. 

After February 4, 2010 (the effective date of 

AD 2009–26–17, Amendment 39–16156 (74 

FR 69268, December 31, 2009)), use the 

applicable service bulletin identified in 

paragraph (g)(2) or (g)(3) of this AD. After the 

effective date of this AD, use only the 

applicable service bulletin identified in 

paragraph (g)(3) of this AD to do the actions 

required by this paragraph. 

(1) McDonnell Douglas DC–10 Service 

Bulletin 53–109, Revision 4, dated October 7, 

1992 (for airplanes with extended wing-tofuselage fillets); or McDonnell Douglas DC– 

10 Service Bulletin 53–111, Revision 3, dated 

August 24, 1992 (for airplanes with 

conventional wing-to-fuselage fillets). 

(2) Boeing Service Bulletin DC10–53–109, 

Revision 7, dated March 3, 2009 (for 

airplanes with extended wing-to-fuselage 

fillets); or Boeing Service Bulletin DC10–53– 

111, Revision 6, dated March 3, 2009 (for 

airplanes with conventional wing-to-fuselage 

fillets). 

(3) Boeing Service Bulletin DC10–53–109, 

Revision 8, dated March 10, 2011 (for 

airplanes with extended wing-to-fuselage 

fillets); or Boeing Service Bulletin DC10–53– 

111, Revision 7, dated March 16, 2011 (for 

airplanes with conventional wing-to-fuselage 

fillets). 

(h) Restatement of Requirements of AD 

2009–26–17, Amendment 39–16156 (74 FR 

69268, December 31, 2009), With New 

Service Information: Install or Replace 

For airplanes with fuselage numbers 

identified in the applicable service bulletin 

listed in paragraph (g)(2) of this AD that are 

not also identified in the applicable service 

bulletin listed in paragraph (g)(1) of this AD, 

except for airplanes identified in paragraph 

(i) or (j) of this AD: Within 7,500 flight hours 

or 60 months, whichever occurs first after 

February 4, 2010 (the effective date of AD 

2009–26–17, Amendment 39–16156 (74 FR 

69268, December 31, 2009)), install or replace 

with improved parts, as applicable, the 

bonding straps between the metallic frame of 

the fillet and the wing leading edge ribs, on 

both the left and right sides of the airplane. 

Do the actions in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin identified in 

paragraph (g)(2) or (g)(3) of this AD. After the 

effective date of this AD, use only the 

applicable service bulletin identified in 

paragraph (g)(3) of this AD to do the actions 

required by this paragraph. 

(i) Restatement of Requirements of AD 2009– 

26–17, Amendment 39–16156 (74 FR 69268, 

December 31, 2009), With New Service 

Information: Strap Repositioning for Certain 

Airplanes 

For Group 1–4, Configuration 3 airplanes, 

as identified in Boeing Service Bulletin 

DC10–53–109, Revision 7, dated March 3, 

2009: Within 7,500 flight hours or 60 months 

after February 4, 2010 (the effective date of 

AD 2009–26–17, Amendment 39–16156 (74 

FR 69268, December 31, 2009)), whichever 

occurs first, do the actions specified in 

paragraphs (i)(1) and (i)(2) of this AD. 

(1) Remove two braided bonding straps and 

install two longer braided bonding straps 

between the metallic frame of the fillet and 

the wing leading edge ribs, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin DC10–53–109, 

Revision 7, dated March 3, 2009; or Boeing 

Service Bulletin DC10–53–109, Revision 8, 

dated March 10, 2011. After the effective date 

of this AD, use only Boeing Service Bulletin 

DC10–53–109, Revision 8, dated March 10, 

2011, to do the actions required by this 

paragraph. 

(2) Measure the resistance of the previously 

installed bonding straps and, before further 

flight, do all applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 

DC10–53–109, Revision 7, dated March 3, 

2009; or Boeing Service Bulletin DC10–53– 

109, Revision 8, dated March 10, 2011. After 

the effective date of this AD, use only Boeing 

Service Bulletin DC10–53–109, Revision 8, 

dated March 10, 2011, to do the actions 

required by this paragraph. 

(j) Restatement of Requirements of AD 2009– 

26–17, Amendment 39–16156 (74 FR 69268, 

December 31, 2009), With New Service 

Information: Inspection and Corrective 

Action for Certain Airplanes 

For Group 1–2, Configuration 2 airplanes, 

as identified in Boeing Service Bulletin 

DC10–53–111, Revision 6, dated March 3, 

2009: Within 7,500 flight hours or 60 months 

after February 4, 2010 (the effective date of 

AD 2009–26–17, Amendment 39–16156 (74 

FR 69268, December 31, 2009)), whichever 

occurs first, do the actions specified in 

paragraphs (j)(1) and (j)(2) of this AD. 


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18722 Federal Register / Vol. 77, No. 60 / Wednesday, March 28, 2012 / Proposed Rules 

(1) Do a general visual inspection to verify 

correct installation of the braided bonding 

straps (one left-hand wing and one righthand wing) as shown in Sheet 7 in Figure 3 

of Boeing Service Bulletin DC10–53–111, 

Revision 6, dated March 3, 2009, or Boeing 

Service Bulletin DC10–53–111, Revision 7, 

dated March 16, 2011; and, before further 

flight, do all applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 

DC10–53–111, Revision 6, dated March 3, 

2009, or Boeing Service Bulletin DC10–53– 

111, Revision 7, dated March 16, 2011. After 

the effective date of this AD, use only Boeing 

Service Bulletin DC10–53–111, Revision 7, 

dated March 16, 2011, to do the actions 

required by this paragraph. 

(2) Measure the resistance of the previously 

installed bonding straps and, before further 

flight, do all applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 

DC10–53–111, Revision 6, dated March 3, 

2009; or Boeing Service Bulletin DC10–53– 

111, Revision 7, dated March 16, 2011. After 

the effective date of this AD, use only Boeing 

Service Bulletin DC10–53–111, Revision 7, 

dated March 16, 2011, to do the actions 

required by this paragraph. 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraphs (g), (h), (i), 

and (j) this AD, if those actions were 

accomplished before February 4, 2010 (the 

effective date of AD 2009–26–17, 

Amendment 39–16156 (74 FR 69268, 

December 31, 2009)), using Boeing Service 

Bulletin DC10–53–111, Revision 5, dated 

March 19, 2008; or Boeing Service Bulletin 

DC10–53–109, Revision 6, dated July 10, 

2008. 

(l) New Requirements of This AD: 

Installation and Corrective Actions for 

Certain Airplanes 

Within 7,500 flight hours or 60 months 

after the effective date of this AD, whichever 

comes first: Do the applicable actions 

specified in paragraphs (l)(1) through (l)(6) of 

this AD, as applicable. 

(1) For Group 1–4, Configurations 1 and 2 

airplanes, as identified in Boeing Service 

Bulletin DC10–53–109, Revision 8, dated 

March 10, 2011, except airplanes that are 

identified in paragraph (g) of this AD: 

Remove any solid metal bonding straps and 

install 7 new braided bonding straps, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 

DC10–53–109, Revision 8, dated March 10, 

2011. 

(2) For Group 1–4, Configurations 1 and 2 

airplanes, as identified in Boeing Service 

Bulletin DC10–53–109, Revision 8, dated 

March 10, 2011, that are also identified in 

paragraph (g) of this AD: Remove any solid 

metal bonding straps not removed during the 

actions required by paragraph (g) of this AD 

and install a 7th new braided bonding strap 

(paragraph (g) of this AD requires installing 

6 straps), in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin DC10–53–109, Revision 8, 

dated March 10, 2011. 

(3) For Group 1–4, Configuration 3 

airplanes, as identified in Boeing Service 

Bulletin DC10–53–109, Revision 8, dated 

March 10, 2011, except airplanes identified 

in paragraph (i) of this AD: Do the actions 

specified in paragraphs (l)(3)(i) and (l)(3)(ii) 

of this AD. 

(i) Replace one strap with new braided 

bonding strap, inspect to determine the 

existence of an installed solid metal bonding 

strap and replace any missing strap and any 

solid metal bonding strap with a new braided 

bonding strap, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin DC10–53–109, Revision 8, 

dated March 10, 2011. 

(ii) Measure the electrical resistance across 

each bonding joint of the 6 previouslyinstalled braided strap assemblies and verify 

that brackets have an acceptable fillet seal, 

and do all applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 

DC10–53–109, Revision 8, dated March 10, 

2011. Do all applicable corrective actions 

before further flight. 

(4) For Group 1–4, Configuration 3 

airplanes, as identified in Boeing Service 

Bulletin DC10–53–109, Revision 8, dated 

March 10, 2011, that are also identified in 

paragraph (i) of this AD: Do the actions 

specified in paragraphs (l)(4)(i) and (l)(4)(ii) 

of this AD. 

(i) Inspect to determine the existence of an 

installed solid metal bonding strap and 

replace any missing strap and any solid metal 

bonding strap with a new braided bonding 

strap, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin DC10–53–109, Revision 8, 

dated March 10, 2011. 

(ii) Measure the electrical resistance across 

each bonding joint of the 6 previouslyinstalled braided strap assemblies and verify 

that brackets have an acceptable fillet seal, 

and do all applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 

DC10–53–109, Revision 8, dated March 10, 

2011. Do all applicable corrective actions 

before further flight. 

(5) For Group 1–4, Configuration 4 

airplanes, as identified in Boeing Service 

Bulletin DC10–53–109, Revision 8, dated 

March 10, 2011: Do the actions specified in 

paragraphs (l)(5)(i) and (l)(5)(ii) of this AD. 

(i) Inspect to determine the existence of an 

installed solid metal bonding strap, and 

replace any missing strap and any solid metal 

bonding strap with a new braided bonding 

strap, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin DC10–53–109, Revision 8, 

dated March 10, 2011. 

(ii) Measure the electrical resistance across 

each bonding joint of the 6 previouslyinstalled braided strap assemblies and verify 

that brackets have an acceptable fillet seal, 

and do all applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 

DC10–53–109, Revision 8, dated March 10, 

2011. Do all applicable corrective actions 

before further flight. 

(6) For Group 1–4, Configuration 5 

airplanes, as identified in Boeing Service 

Bulletin DC10–53–109, Revision 8, dated 

March 10, 2011: Inspect to determine the 

existence of an installed solid metal bonding 

strap, and replace any missing strap and any 

solid metal bonding strap with a new braided 

bonding strap, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin DC10–53–109, Revision 8, 

dated March 10, 2011. 

(m) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

(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. 

(3) AMOCs approved previously in 

accordance with AD 2006–16–03, 

Amendment 39–14703 (71 FR 43962, August 

3, 2006), are approved as AMOCs for the 

corresponding provisions of paragraphs (g), 

(h), (i), and (j) of this AD. 

(4) AMOCs approved previously in 

accordance with AD 2009–26–17, 

Amendment 39–16156 (74 FR 69268, 

December 31, 2009), are approved as AMOCs 

for the corresponding provisions of 

paragraphs (g), (h), (i), and (j) of this AD. 

(n) Related Information 

(1) For more information about this AD, 

contact Samuel Lee, Aerospace Engineer, 

Propulsion Branch, ANM–140L, FAA, Los 

Angeles Aircraft Certification Office, 3960 

Paramount Boulevard, Lakewood, California 

90712–4137; phone: 562–627–5262; fax: 562– 

627–5210; email: Samuel.Lee@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, 3855 Lakewood Boulevard, MC 

D800–0019, Long Beach, California 90846– 

0001; telephone 206–544–5000, extension 2; 

fax 206–766–5683; email 

dse.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. 

Issued in Renton, Washington, on March 

16, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–7386 Filed 3–27–12; 8:45 am] 

BILLING CODE 4910–13–P 


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