Federal Register / Vol. 75, No. 129 / Wednesday, July 7, 2010 / Proposed Rules 38943 

TABLE 1—CREDIT SERVICE INFORMATION—Continued 

Affected serial numbers— 

Bombardier 

service bulletin— Revision— Dated— 

For Model 45 airplanes having serial numbers 006 through 383, inclusive ....... 45-26-9 1 ................................ December 22, 2008. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, Wichita 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. Send information to ATTN: James 

Galstad, Aerospace Engineer, Systems and 

Propulsion Branch, ACE–116W, FAA, 

Wichita Aircraft Certification Office, 1801 

Airport Road, Room 100, Mid-Continent 

Airport, Wichita, Kansas 67209; telephone 

(316) 946–4135; fax (316) 946–4107. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

Issued in Renton, Washington, on June 29, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–16514 Filed 7–6–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0672; Directorate 

Identifier 2010–NM–047–AD] 

RIN 2120–AA64 

Airworthiness Directives; McDonnell 

Douglas Corporation Model DC–10–10, 

DC–10–10F, DC–10–30, DC–10–30F 

(KDC–10), DC–10–40, and DC–10–40F 

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 DC–10–10, DC–10–10F, DC–10– 

30, DC–10–30F (KDC–10), DC–10–40, 

and DC–10–40F airplanes. This 

proposed AD would require installing a 

support bracket and coupler on the left 

and right wing-to-fuselage transition, 

and metallic overbraid on the left and 

right leading edge wire assembly. This 

proposed AD results from fuel system 

reviews conducted by the manufacturer, 

as well as reports that the fuel quantity 

system was affected by lightninginduced transients. We are proposing 

this AD to prevent lightning-induced 

transients to the fuel quantity indication 

system, which could cause voltage 

levels to go beyond original design 

levels between fuel tank probes and 

structure, and become a potential 

ignition source at 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 August 23, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this proposed AD, contact 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; e-mail 

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. 

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: 

Samuel Lee, Aerospace Engineer, 

Propulsion Branch, ANM–140L, FAA, 

Los Angeles Aircraft Certification Office 

(ACO), 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; 

telephone (562) 627–5262; fax (562) 

627–5210. 

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–2010–0672; Directorate Identifier 

2010–NM–047–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 


cprice-sewell on DSK8KYBLC1PROD with PROPOSALS-1
38944 Federal Register / Vol. 75, No. 129 / Wednesday, July 7, 2010 / Proposed Rules 

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 fuel tank explosions and consequent 

loss of the airplane. 

Also, we received reports that the fuel 

quantity system was affected by 

lightning- induced transients. The 

fiberglass leading edge fairing at the 

wing root created an electrical 

discontinuity in the metal shielding 

provided by the wing structure. As 

rapidly changing lightning currents flow 

in the leading edge gap region during a 

nose-to-wing- tip strike, rapidly 

changing electromagnetic fields are 

created in the gap region. Boeing 

investigations have determined that 

these fields cause electrical transients to 

be inducted indirectly into the wiring of 

the fuel quantity indication system. 

Installing side entry wire braid sleeving 

on fuel probe wires in the root region of 

each wing will minimize lightninginduced transients to the fuel quantity 

indication system. Such transients 

could result in voltage levels going 

beyond original design levels between 

fuel tank probes and structure and 

becoming a potential ignition source for 

the fuel tank. 

Relevant Service Information 

We have reviewed Boeing Service 

Bulletin DC10–28–262, Revision 1, 

dated June 9, 2010. The service bulletin 

describes procedures for installing a 

support bracket and coupler on the left 

and right wing-to-fuselage transition, 

and installing metallic overbraid on the 

left and right wing leading edge wire 

assemblies. 

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 these same 

type designs. This proposed AD would 

require accomplishing the actions 

specified in the service information 

described previously. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 61 airplanes of U.S. 

registry. We also estimate that it would 

take about 28 work-hours per product to 

comply with this proposed AD. The 

average labor rate is $85 per work-hour. 

Required parts would cost about $999 

per product. Based on these figures, we 

estimate the cost of this proposed AD to 

the U.S. operators to be $206,119, or 

$3,379 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

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: 

McDonnell Douglas Corporation: Docket No. 

FAA–2010–0672; Directorate Identifier 

2010–NM–047–AD. 

Comments Due Date 

(a) We must receive comments by August 

23, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to McDonnell Douglas 

Corporation Model DC–10–10, DC–10–10F, 

DC–10–30, DC–10–30F (KDC–10), DC–10–40, 

and DC–10–40F airplanes, certificated in any 

category, as identified in Boeing Service 

Bulletin DC10–28–262, Revision 1, dated 

June 9, 2010. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 28: Fuel. 


cprice-sewell on DSK8KYBLC1PROD with PROPOSALS-1
Federal Register / Vol. 75, No. 129 / Wednesday, July 7, 2010 / Proposed Rules 38945 

Unsafe Condition 

(e) This AD results from fuel system 

reviews conducted by the manufacturer. The 

Federal Aviation Administration is issuing 

this AD to prevent lightning-induced 

transients to the fuel quantity indication 

system, which could cause voltage levels to 

go beyond original design levels between fuel 

tank probes and structure and become a 

potential ignition source at 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. 

Installation 

(g) Within 60 months after the effective 

date of this AD, install a support bracket and 

coupler on the left and right wing-to-fuselage 

transition, and metallic overbraid on the left 

and right leading edge wire assembly, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 

DC10–28–262, Revision 1, dated June 9, 

2010. 

Installation According to Previous Issue of 

Service Bulletin 

(h) Installing a support bracket and coupler 

on the left and right wing-to-fuselage 

transition, and metallic overbraid on the left 

and right leading edge wire assembly, is also 

acceptable for compliance with the 

requirements of paragraph (g) of this AD if 

done before the effective date of this AD in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 

DC10–28–262, dated January 6, 2010. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, Los Angeles 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: Samuel Lee, 

Aerospace Engineer, Propulsion Branch, 

ANM–140L, FAA, Los Angeles Aircraft 

Certification Office (ACO), 3960 Paramount 

Boulevard, Lakewood, California 90712– 

4137; telephone (562) 627–5262; fax (562) 

627–5210. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

Issued in Renton, Washington on June 29, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–16515 Filed 7–6–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0678; Directorate 

Identifier 2010–NM–020–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 777–200 and –300 

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 777–200 and –300 series 

airplanes. This proposed AD would 

require installing new operational 

software in the cabin management 

system, and loading new software into 

the mass memory card. This proposed 

AD results from an in-flight 

entertainment (IFE) systems review. We 

are proposing this AD to ensure that the 

flightcrew is able to turn off electrical 

power to the IFE system and other nonessential electrical systems through a 

switch in the flight compartment in the 

event of smoke or flames. In the event 

of smoke or flames in the airplane flight 

deck or passenger cabin, the flightcrew’s 

inability to turn off electrical power to 

the IFE system and other non-essential 

electrical systems could result in the 

inability to control smoke or flames in 

the airplane flight deck or passenger 

cabin during a non-normal or 

emergency situation. 

DATES: We must receive comments on 

this proposed AD by August 23, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this proposed AD, contact 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. 

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: Joe 

Salameh, Aerospace Engineer, Systems 

and Equipment Branch, ANM–130S, 

FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6454; 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–2010–0678; Directorate Identifier 

2010–NM–020–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 

In response to numerous reports of 

smoke or flames in the passenger cabin 

of various models of transport category 

airplanes, we conducted a 

comprehensive in-flight entertainment 

(IFE) systems review. Earlier 

investigation of the reports had revealed 

that the source of the smoke and flames 


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