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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Federal Register / Vol. 75, No. 76 / Wednesday, April 21, 2010 / Proposed Rules 20793 

FOR FURTHER INFORMATION CONTACT: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6437; 

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–2010–0383; Directorate Identifier 

2009–NM–214–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 

We have received several reports of 

cracks in overwing intercostal webs 

between station (STA) 1160 and STA 

1220. Most of the cracks were found 

near the intercostal lower chord and a 

few cracks were found near the 

intercostal upper chord. The cracks 

ranged from 0.2 inch to 3.5 inches long. 

The cracks are caused by cyclic 

buckling of the web from normal flight 

loads. The earliest report of a web crack 

occurred on an airplane with 3,697 

flight cycles; however, no cracks have 

been reported in the upper or lower 

chord of the overwing intercostals. This 

condition, if not corrected, could result 

in crack growth and a severed 

intercostal. If an intercostal is severed, 

cracks could develop in the adjacent 

frame structure and skin, resulting in 

rapid loss of cabin pressure. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin 747–53A2750, dated 

August 27, 2009. Boeing Alert Service 

Bulletin 747–53A2750, dated August 27, 

2009, describes procedures for doing a 

repetitive detailed inspection for 

cracking of the left-side and right-side 

overwing intercostal webs at STAs 1160, 

1180, 1200, and 1220, and related 

investigative and corrective actions if 

necessary. The related investigative 

action is doing a detailed inspection for 

cracking of the upper chord, lower 

chord, and stiffener of the intercostal 

and adjacent frame assembly structure if 

a crack is found in the web of an 

overwing intercostal. Depending on 

findings, the corrective actions are 

replacing any cracked overwing 

intercostal web (the replacement of the 

overwing intercostal web includes doing 

an open-hole HFEC inspection for 

cracking of the fastener holes common 

to the replacement); and contacting 

Boeing for repair instructions of any 

cracked intercostal upper chord, lower 

chord, stiffener, or adjacent frame 

assembly structure, and of any crack 

found during any open-hole HFEC 

inspections, and doing the repair. 

For any airplane having a STA 1160, 

1180, 1200, or 1220 overwing intercostal 

web that has been replaced in 

accordance with this service bulletin, 

Boeing Alert Service Bulletin 747– 

53A2750, dated August 27, 2009, 

specifies procedures for doing repetitive 

detailed inspections for cracking of the 

replaced web, and related investigative 

and corrective actions if necessary. 

Related investigative actions include 

doing a detailed inspection for cracking 

of the upper chord, lower chord, and 

stiffener of the intercostal, and adjacent 

frame assembly structure. Corrective 

actions include replacing any cracked 

overwing intercostal web; and 

contacting Boeing for repair instructions 

of any cracked intercostal upper chord, 

lower chord, stiffener, or adjacent frame 

assembly structure, and of any crack 

found during any open-hole HFEC 

inspections, and doing the repair. 

FAA’s Determination and Requirements 

of This Proposed AD 

We are proposing this AD because we 

evaluated all relevant information and 

determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. This proposed AD would 

require accomplishing the actions 

specified in the service information 

described previously, except as 

discussed under ‘‘Differences Between 

the Proposed Rule and Service 

Bulletin.’’ 

Differences Between the Proposed Rule 

and Service Bulletin 

Boeing Alert Service Bulletin 747– 

53A2750, dated August 27, 2009, 

specifies to contact the manufacturer for 

instructions on how to repair certain 

conditions, but this proposed AD would 

require repairing those conditions in 

one of the following ways: 

• Using a method that we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 86 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 

Inspection ..................... 4 $85 None ............ $340 per inspection 

cycle 

86 $29,240 per inspection 

cycle 

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 


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20794 Federal Register / Vol. 75, No. 76 / Wednesday, April 21, 2010 / Proposed Rules 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

DOT Regulatory Policies and Procedures 

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

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new AD: 

The Boeing Company: Docket No. FAA– 

2010–0383; Directorate Identifier 2009– 

NM–214–AD. 

Comments Due Date 

(a) We must receive comments by June 7, 

2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to 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, certificated in any category; as 

identified in Boeing Alert Service Bulletin 

747–53A2750, dated August 27, 2009. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Unsafe Condition 

(e) This AD results from reports of cracks 

in overwing intercostal webs between station 

(STA) 1160 and STA 1220. The Federal 

Aviation Administration is issuing 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. 

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. 

Repetitive Inspections of the Overwing 

Intercostal Web 

(g) Before the accumulation of 8,000 total 

flight cycles, or within 1,500 flight cycles 

after the effective date of this AD, whichever 

occurs later: Do a detailed inspection of the 

left-side and right-side STAs 1160, 1180, 

1200, and 1220 overwing intercostal webs, 

and all applicable related investigative and 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2750, dated August 

27, 2009, except as required by paragraph (i) 

of this AD. Do all applicable related 

investigative and corrective actions before 

further flight. If no cracking is found during 

any detailed inspection, repeat the inspection 

thereafter at intervals not to exceed 3,000 

flight cycles. 

(h) For any airplane with an overwing 

intercostal web replaced in accordance with 

Boeing Alert Service Bulletin 747–53A2750, 

dated August 27, 2009: Within 6,000 flight 

cycles after the web was replaced, do a 

detailed inspection of the replacement 

overwing intercostal web, and do all 

applicable related investigative and 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2750, dated August 

27, 2009, except as required by paragraph (i) 

of this AD. Do all applicable related 

investigative and corrective actions before 

further flight. If no cracking is found during 

any detailed inspection, repeat the inspection 

thereafter at intervals not to exceed 3,000 

flight cycles. 

Exception to Service Bulletin 

(i) If any cracking is found during any 

inspection required by this AD, and Boeing 

Alert Service Bulletin 747–53A2750, dated 

August 27, 2009, specifies contacting Boeing 

for appropriate action: Before further flight, 

repair the cracking using a method approved 

in accordance with the procedures provided 

in paragraph (j) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, Seattle 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: Ivan 

Li, Aerospace Engineer, Airframe Branch, 

ANM–120S, FAA, Seattle Aircraft 

Certification Office (ACO), 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 917–6437; fax (425) 

917–6590. Information may be e-mailed to: 9- 

ANM-Seattle-ACO-AMOC-Requests@faa.gov. 

(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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization that has been 

authorized by the Manager, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

Issued in Renton, Washington, on April 9, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–9112 Filed 4–20–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2009–0190; Airspace 

Docket No. 09–ASW–5] 

Proposed Amendment of Class E 

Airspace; Hamilton, TX 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This action proposes to 

amend Class E airspace at Hamilton, TX, 

adding additional controlled airspace to 

accommodate new Standard Instrument 

Approach Procedures (SIAP) at 

Hamilton Municipal Airport, Hamilton, 

TX. The FAA is taking this action to 

enhance the safety and management of 

Instrument Flight Rules (IFR) operations 

for SIAPs at the airport. 

DATES: Comments must be received on 

or before June 7, 2010. 

ADDRESSES: Send comments on this 

proposal to the U.S. Department of 

Transportation, Docket Operations, 1200 

New Jersey Avenue, SE., West Building 

Ground Floor, Room W12–140, 


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