59728 Federal Register / Vol. 77, No. 190 / Monday, October 1, 2012 / Rules and Regulations 

identified in paragraphs (i)(1) through (i)(5) 

of this AD (* the issue date is not specified 

on the drawing.) 

(1) Fokker Manual Change Notification— 

Maintenance Documentation MCNM–F100– 

145, dated June 30, 2011. 

(2) Fokker Manual Change Notification— 

Operational Documentation MCNO–F100– 

059, dated June 30, 2011. 

(3) Fokker Drawing W41190, Sheet 013, 

Issue P*. 

(4) Fokker Drawing W41190, Sheet 014, 

Issue P*. 

(5) Fokker Drawing W41190, Sheet 016, 

Issue P*. 

(j) Prohibited Modification 

As of the effective date of this AD, no 

person may modify any airplane using 

Fokker Service Bulletin SBF100–28–021, 

dated September 6, 1991 (specified in 

European Aviation Safety Agency (EASA) AD 

2011–0158, dated August 26, 2011, and is not 

incorporated by reference in this AD). That 

service bulletin was cancelled by Fokker 

Service Bulletin SBF100–28–021, Revision 1, 

dated June 30, 2011 (not incorporated by 

reference in this AD). 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1137; fax (425) 227– 

1149. Information may be emailed to: 9– 

ANM–116–AMOC–REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(l) Related Information 

Refer to MCAI EASA Airworthiness 

Directive 2011–0158, dated August 26, 2011, 

and the service information specified in 

paragraphs (l)(1), (l)(2), and (l)(3) of this AD, 

for related information. 

(1) Fokker Service Bulletin SBF100–28– 

029, Revision 1, dated November 30, 1993. 

(2) Fokker Service Bulletin SBF100–28– 

030, Revision 1, dated December 5, 1994. 

(3) Fokker Service Bulletin SBF100–28– 

066, dated June 30, 2011, which includes the 

attachments identified in paragraphs (l)(3)(i) 

through (l)(3)(v) of this AD (* the issue date 

is not specified on the drawing). 

(i) Fokker Manual Change Notification— 

Maintenance Documentation MCNM–F100– 

145, dated June 30, 2011. 

(ii) Fokker Manual Change Notification— 

Operational Documentation MCNO–F100– 

059, dated June 30, 2011. 

(iii) Fokker Drawing W41190, Sheet 013, 

Issue P*. 

(iv) Fokker Drawing W41190, Sheet 014, 

Issue P*. 

(v) Fokker Drawing W41190, Sheet 016, 

Issue P*. 

(m) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on November 5, 2012. 

(i) Fokker Service Bulletin SBF100–28– 

066, dated June 30, 2011, which includes the 

attachments identified in paragraphs 

(m)(3)(i)(A) through (m)(3)(i)(E) of this AD (* 

the issue date is not specified on the 

drawing). 

(A) Fokker Manual Change Notification— 

Maintenance Documentation MCNM–F100– 

145, dated June 30, 2011. 

(B) Fokker Manual Change Notification— 

Operational Documentation MCNO–F100– 

059, dated June 30, 2011. 

(C) Fokker Drawing W41190, Sheet 013, 

Issue P*. 

(D) Fokker Drawing W41190, Sheet 014, 

Issue P*. 

(E) Fokker Drawing W41190, Sheet 016, 

Issue P*. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on April 29, 1996 (61 FR 

14014, March 29, 1996). 

(i) Fokker Service Bulletin SBF100–28– 

030, Revision 1, dated December 5, 1994. 

(Pages 1 through 3, 5, 8, and 10 of this 

document are identified as Revision 1, dated 

December 5, 1994. Pages 4, 6, 7, and 9 of this 

document are dated August 28, 1994 (original 

issue).) 

(ii) Reserved. 

(5) The following service information was 

approved for IBR on August 10, 1994 (59 FR 

35237, July 11, 1994). 

(i) Fokker Service Bulletin SBF100–28– 

029, Revision 1, dated November 30, 1993. 

(Pages 1 through 3 of this document are 

identified as Revision 1, dated November 30, 

1993. Pages 4 through 7 of this document are 

dated November 10, 1993 (original issue).) 

(ii) Reserved. 

(6) For service information identified in 

this AD, contact Fokker Services B.V., 

Technical Services Dept., P.O. Box 231, 2150 

AE Nieuw-Vennep, the Netherlands; 

telephone +31 (0)252–627–350; fax +31 

(0)252–627–211; email 

technicalservices.fokkerservices@stork.com; 

Internet http://www.myfokkerfleet.com. 

(7) You may review copies of the 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. 

(8) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

September 11, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–23052 Filed 9–28–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0327; Directorate 

Identifier 2011–NM–125–AD; Amendment 

39–17198; AD 2012–19–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

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. That 

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; and 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. This 

new AD adds airplanes to the 

applicability and, depending on the 

airplane configuration, requires 

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 doing 

corrective actions if necessary. This AD 

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Federal Register / Vol. 77, No. 190 / Monday, October 1, 2012 / Rules and Regulations 59729 

was prompted by fuel system reviews 

conducted by the manufacturer, and our 

determination that additional actions 

are necessary to address the identified 

unsafe condition. 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. 

DATES: This AD is effective November 5, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of November 5, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of February 4, 2010 (74 FR 

69268, December 31, 2009). 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD of September 7, 2006 (71 FR 

43962, August 3, 2006). 

ADDRESSES: 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; Internet https:// 

www.myboeingfleet. 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. 

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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

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: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2009–26–17, 

Amendment 39–16156 (74 FR 69268, 

December 31, 2009). That AD applies to 

the specified products. The NPRM 

published in the Federal Register on 

March 28, 2012 (77 FR 18719). That 

NPRM proposed to continue to require 

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 NPRM also proposed to continue 

to require, 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. That 

NPRM also proposed to add airplanes to 

the applicability, and 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 doing corrective actions if 

necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (77 FR 18719, 

March 28, 2012) and the FAA’s response 

to each comment. 

Request To Add Credit for Previous 

Actions 

FedEx requested that previous actions 

accomplished on 51 of its airplanes 

using Boeing Service Bulletin DC10–53– 

111, Revision 4, dated September 21, 

2006; or Boeing Service Bulletin DC10– 

53–111, Revision 7, dated March 16, 

2011; be acceptable as terminating 

action for the actions specified in 

paragraph (j) of the NPRM (77 FR 18719, 

March 28, 2012). 

We partially agree. We agree that the 

actions are acceptable, but do not agree 

to change the AD. We disagree that 

credit for previous actions should be 

added to the AD. Paragraphs (m)(3) and 

(m)(4) of this AD already allow previous 

accomplishment of the actions specified 

in paragraphs (g), (h), (i), and (j) of this 

AD, if those actions were done using 

alternative methods of compliance 

(AMOCs) approved in accordance with 

AD 2006–16–03, Amendment 39–14703 

(71 FR 43962, August 3, 2006); and AD 

2009–26–17, Amendment 39–16156 (74 

FR 69268, December 31, 2009). Boeing 

Service Bulletin DC10–53–111, Revision 

4, dated September 21, 2006, states that 

it is approved as an AMOC for AD 

2006–16–03. We have not changed the 

final rule in this regard. 

Request To Combine Paragraphs 

FedEx suggested that paragraphs (l)(3) 

and (l)(4) of the NPRM (77 FR 18719, 

March 28, 2012) be combined since they 

state the same thing. 

We do not agree to combine 

paragraphs (l)(3) and (l)(4) of this AD, 

because those paragraphs state different 

requirements for different airplanes. We 

have not changed the final rule in this 

regard. 

Request To Correct Effectivity 

FedEx stated that Boeing Service 

Bulletin DC10–53–111, Revision 7, 

dated March 16, 2011, incorrectly 

specifies that the reason for the revision 

was to add fuselage 317 to the effectivity 

of that service bulletin. FedEx stated 

that fuselage 317 was not and does not 

need to be added to the effectivity of 

that service bulletin, because fuselage 

317 is in the effectivity of Boeing 

Service Bulletin DC10–53–109, Revision 

8, dated March 10, 2011. 

We infer that FedEx is requesting that 

Boeing Service Bulletin DC10–53–111, 

Revision 7, dated March 16, 2011, be 

revised to correct the discrepancy in the 

stated reason for the revision of that 

service bulletin. We do not agree. 

Boeing issued Service Bulletin 

Information Notice DC10–53–111 IN 02, 

dated June 17, 2011, to clarify that 

fuselage 317 was not added to the 

effectivity of Boeing Service Bulletin 

DC10–53–111, Revision 7, dated March 

16, 2011. No change to this final rule is 

necessary in this regard. 

Explanation of Additional Changes 

Made To This AD 

We have revised certain headings 

throughout this AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

18719, March 28, 2012) for correcting 

the unsafe condition; and 

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59730 Federal Register / Vol. 77, No. 190 / Monday, October 1, 2012 / Rules and Regulations 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 18719, 

March 28, 2012). 

Costs of Compliance 

We estimate that this AD affects 208 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this 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 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 AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

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 that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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: 

2012–19–03 The Boeing Company: 

Amendment 39–17198; Docket No. 

FAA–2012–0327; Directorate Identifier 

2011–NM–125–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective November 5, 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 paragraphs 

(c)(1) and (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, and 

our determination that additional actions are 

necessary to address the identified unsafe 

condition. 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) Retained Requirements for Installation or 

Replacement for Certain Airplanes, With 

New Service Information 

This paragraph restates the installation or 

replacement requirements of paragraph (g) of 

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

FR 69268, December 31, 2009), with new 

service information. 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), 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 

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Federal Register / Vol. 77, No. 190 / Monday, October 1, 2012 / Rules and Regulations 59731 

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 wingto-fuselage fillets). 

(h) Retained Requirements for Installation or 

Replacement for Certain Other Airplanes, 

With New Service Information 

This paragraph restates the installation or 

replacement requirements of paragraph (h) of 

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

FR 69268, December 31, 2009), with new 

service information. 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), 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) Retained Requirements for Strap 

Repositioning for Certain Airplanes, With 

New Service Information 

This paragraph restates the strap 

repositioning requirements of paragraph (i) of 

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

FR 69268, December 31, 2009), with new 

service information. 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), 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) Retained Requirements for Inspection and 

Corrective Action for Certain Airplanes, 

With New Service Information 

This paragraph restates the inspection 

requirements of paragraph (j) of AD 2009–26– 

17, Amendment 39–16156 (74 FR 69268, 

December 31, 2009), with new service 

information. 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), whichever 

occurs first, do the actions specified in 

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

(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; as applicable; which are not 

incorporated by reference. 

(l) New 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 seven 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 six 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. 

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59732 Federal Register / Vol. 77, No. 190 / Monday, October 1, 2012 / Rules and Regulations 

(ii) Measure the electrical resistance across 

each bonding joint of the six 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 six 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 specified in this 

AD that is not incorporated by reference, 

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; Internet https://www.myboeingfleet. 

(o) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on November 5, 2012. 

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

Revision 8, dated March 10, 2011. 

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

Revision 7, dated March 16, 2011. 

(4) The following service information was 

approved for IBR on February 4, 2010 (74 FR 

69268, December 31, 2009). 

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

Revision 7, dated March 3, 2009. 

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

Revision 6, dated March 3, 2009. 

(5) The following service information was 

approved for IBR on September 7, 2006 (71 

FR 43962, August 3, 2006). 

(i) McDonnell Douglas DC–10 Service 

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

1992. 

(ii) McDonnell Douglas DC–10 Service 

Bulletin 53–111, Revision 3, dated August 

24, 1992. 

(6) 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; Internet https:// 

www.myboeingfleet. 

(7) 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. 

(8) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal-register/

cfr/ibr_locations.html. 

Issued in Renton, Washington, on 

September 11, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–23049 Filed 9–28–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0996; Directorate 

Identifier 2011–NM–040–AD; Amendment 

39–17202; AD 2012–19–07] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A340–500 and –600 series 

airplanes. This AD requires repetitive 

inspections for corrosion of the drag 

stay lower arm assembly of the nose 

landing gear (NLG), and replacement if 

necessary. This AD also requires 

eventual replacement of the drag stay 

lower arm assembly of the NLG with an 

improved assembly having corrosion 

protection, which terminates the 

repetitive inspections required by this 

AD. This AD was prompted by findings 

of corrosion traces in the lugs and on 

the bearing outer surface of the NLG 

during routine maintenance checks. We 

are issuing this AD to prevent failure of 

the drag stay lower arm, which could 

result in NLG collapse and consequent 

reduced controllability of the airplane 

during takeoff. 

DATES: This AD becomes effective 

October 16, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of October 16, 2012. 

We must receive comments on this 

AD by November 15, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

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