20790 Federal Register / Vol. 75, No. 76 / Wednesday, April 21, 2010 / Proposed Rules 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(l) Refer to MCAI Canadian Airworthiness 

Directive CF–2006–08R1, dated August 31, 

2009; and Bombardier Service Bulletin 84– 

29–22, Revision A, dated February 24, 2009; 

for related information. 

Issued in Renton, Washington, on April 9, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–9110 Filed 4–20–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0384; Directorate 

Identifier 2010–NM–003–AD] 

RIN 2120–AA64 

Airworthiness Directives; McDonnell 

Douglas Corporation 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, MD–10– 

30F, MD–11, and MD–11F 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– 

15, DC–10–30, DC–10–30F (KC–10A 

and KDC–10), DC–10–40, DC–10–40F, 

MD–10–10F, MD–10–30F, MD–11, and 

MD–11F airplanes. This proposed AD 

would require installing an in-line fuse 

in certain float level switches and 

sleeving the wires between the fuel tank 

and the in-line fuse. For certain 

airplanes this proposed AD would also 

require installing an in-line fuse in 

certain fuel pump pressure switches. 

This proposed AD results from fuel 

system reviews conducted by the 

manufacturer. We are proposing this AD 

to prevent fuel tank explosions and 

consequent loss of the airplane. 

DATES: We must receive comments on 

this proposed AD by June 7, 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: 

Philip Kush, Aerospace Engineer, 

Propulsion Branch, ANM–140L, FAA, 

Los Angeles Aircraft Certification 

Office, 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; 

telephone (562) 627–5263; 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–2010–0384; Directorate Identifier 

2010–NM–003–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 latent condition(s), 


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Federal Register / Vol. 75, No. 76 / Wednesday, April 21, 2010 / Proposed Rules 20791 

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 proposed 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. 

An investigation conducted by the 

airplane manufacturer has revealed that 

float level switch wires located on the 

left and right wing forward spar, right 

main landing gear wheel well, 

horizontal stabilizer front spar, 

empennage, forward and aft cargo 

compartments, and fuel pump pressure 

switch wires located in the aft cargo 

compartment, are routed in the same 

bundles as power wires. If a short 

circuit between a float level switch wire 

and a power wire occurs, an overcurrent can cause excessive 

temperatures in the float level switch 

wires, which could damage the float 

level or fuel pump pressure switch wire, 

and become a potential ignition source 

for the fuel tank. Adding an in-line fuse 

as a self-contained component in each 

float level and pressure switch circuit, 

and sleeving the wires between the fuel 

tank and the in-line fuse, will minimize 

the possibility of excessive temperatures 

in the float level or pressure switch 

wires. If a short circuit between a float 

level switch wire and a power wire 

occurs, the result could be a fuel tank 

explosion and consequent loss of the 

airplane. 

Relevant Service Information 

We have reviewed Boeing Service 

Bulletin DC10–28–252, Revision 1, 

dated January 6, 2010 (for 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). This service 

bulletin describes procedures for 

installing an in-line fuse in each float 

level switch and a pressure switch 

circuit in-line fuse in the fuel tanks 

listed below, as applicable. 

• Fuel tanks 1, 2, and 3 

• Upper and lower auxiliary fuel 

tanks 

• Center wing fuel tanks 

• Forward and aft auxiliary fuel tanks 

Procedures for installing the in-line 

fuses include sleeving the wires 

between the fuel tank and the in-line 

fuse. 

We have reviewed Boeing Service 

Bulletin MD11–28–132, dated 

November 25, 2008 (for Model MD–11 

and MD–11F airplanes). This service 

bulletin describes procedures for 

installing an in-line fuse in each float 

level switch in the fuel tanks listed 

below, as applicable. 

• Fuel tanks 1, 2, and 3 

• Upper and lower auxiliary fuel 

tanks 

• Forward auxiliary fuel tanks 

• Center wing fuel tanks 

• Tail fuel tank 

Procedures for installing the in-line 

fuses include sleeving the wires 

between the fuel tank and the in-line 

fuse. 

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 281 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 

Installation/Sleeving .. Between 64 and 

136 1

$85 Between $3,139 and 

$5,598 1

Between $8,579 and 

$17,158 

281 Between 

$2,410,699 and 

$4,821,398 

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, 


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20792 Federal Register / Vol. 75, No. 76 / Wednesday, April 21, 2010 / Proposed Rules 

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–2010–0384; Directorate Identifier 

2010–NM–003–AD. 

Comments Due Date 

(a) We must receive comments by June 7, 

2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the airplanes 

identified in paragraphs (c)(1) and (c)(2) of 

this AD. 

(1) McDonnell Douglas Corporation 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; certificated in any 

category; as identified in Boeing Service 

Bulletin DC10–28–252, Revision 1, dated 

January 6, 2010. 

(2) McDonnell Douglas Corporation Model 

MD–11 and MD–11F airplanes; certificated in 

any category; as identified in Boeing Service 

Bulletin MD11–28–132, dated November 25, 

2008. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 28: Fuel. 

Unsafe Condition 

(e) This AD results from fuel system 

reviews conducted by the manufacturer. The 

Federal Aviation Administration is issuing 

this AD to prevent fuel tank explosions 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. 

Action 

(g) Within 60 months after the effective 

date of this AD do the actions specified in 

paragraph (g)(1) or (g)(2) of this AD, as 

applicable. 

(1) For 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: Install an inline fuse in each float level switch and 

pressure switch, including sleeving the wires 

between the fuel tank and the in-line fuse, in 

fuel tanks 1, 2, and 3; upper and lower 

auxiliary fuel tanks; forward and aft auxiliary 

fuel tanks; and center wing fuel tanks; as 

applicable; in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin DC10–28–252, Revision 1, 

dated January 6, 2010. 

(2) For Model MD–11 and MD–11F 

airplanes: Install an in-line fuse in each float 

level switch, including sleeving the wires 

between the fuel tank and the in-line fuse, in 

fuel tanks 1, 2, and 3; upper and lower 

auxiliary fuel tanks; forward auxiliary fuel 

tank; center wing fuel tanks; and tail fuel 

tank; as applicable; in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin MD11–28–132, dated 

November 25, 2008. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(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. Send information to ATTN: 

Philip Kush, Aerospace Engineer, Propulsion 

Branch, ANM–140L, FAA, Los Angeles 

Aircraft Certification Office, 3960 Paramount 

Boulevard, Lakewood, California 90712– 

4137; telephone (562) 627–5263; 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 April 9, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–9111 Filed 4–20–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0383; Directorate 

Identifier 2009–NM–214–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747–100, 747–100B, 

747–100B SUD, 747–200B, 747–200C, 

747–200F, 747–300, 747–400, 747SR, 

and 747SP 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 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–200C, 747–200F, 

747–300, 747–400, 747SR, and 747SP 

series airplanes. This proposed AD 

would require repetitive detailed 

inspections of certain overwing 

intercostal webs, and related 

investigative and corrective actions if 

necessary. This proposed AD results 

from reports of cracks in overwing 

intercostal webs. We are proposing this 

AD to detect and correct such cracking, 

which could grow and result in a 

severed intercostal. If an intercostal is 

severed, cracks could develop in the 

adjacent frame structure and skin, 

resulting in a rapid loss of cabin 

pressure. 

DATES: We must receive comments on 

this proposed AD by June 7, 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. 


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