Federal Register / Vol. 77, No. 113 / Tuesday, June 12, 2012 / Proposed Rules 34881 

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. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(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 2008–08–24, 

Amendment 39–15478 (73 FR 21242, April 

21, 2008), are not approved as AMOCs with 

this AD. 

(i) Related Information 

(1) For more information about this AD, 

contact Ansel James, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–917–6497; fax: 425–917– 

6590; email: ansel.james@faa.gov. 

(2) For service information identified in 

this 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; email 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. 

Issued in Renton, Washington, on May 31, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–14245 Filed 6–11–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0498; Directorate 

Identifier 2011–NM–212–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 747–400, 

–400D, and –400F series airplanes. This 

proposed AD was prompted by reports 

of crown frame web cracking at left 

buttock line (LBL) 15.0, station (STA) 

320. This proposed AD would require a 

measurement of the web at STA 320 

and, depending on findings, various 

inspections for cracks and missing 

fasteners, web and fastener replacement, 

and related investigative and corrective 

actions. We are proposing this AD to 

prevent complete fracture of the crown 

frame assembly, and consequent damage 

to the skin and in-flight decompression 

of the airplane. 

DATES: We must receive comments on 

this proposed AD by July 27, 2012. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; email 

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 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Bill 

Ashforth, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 

Lind Avenue SW., Renton, Washington 

98057–3356; phone: 425–917–6432; fax: 

425–917–6590; email: 

Bill.Ashforth@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2012–0498; Directorate Identifier 2011– 

NM–212–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 five reports of 

crown frame web cracking at left 

buttock line (LBL) 15.0, station (STA) 

320. One airplane crack length was not 

specified and reported at 9,456 flight 

cycles. Three cracks of 0.65 inch in 

length were reported after 9,354 flight 

cycles on one airplane, 12,851 flight 

cycles on the second airplane, and 

29,866 flight cycles on the third 

airplane. A crack of 0.85 inch was 

reported at 29,956 flight cycles on 

another airplane. 

Investigation revealed that in these 

airplanes, the web was made from 0.08- 

inch thick material and did not conform 

to production drawings. Also, an 

operator reported missing fasteners from 

locations common to the frame web and 

lower chord on the first delivered Model 

747–400 after 10,317 flight cycles. This 

airplane also had a web made from 0.08- 

inch thick material and did not conform 

to production drawings. 

This condition, if not corrected, could 

result in complete fracture of the crown 

frame assembly, and consequent damage 

to the skin and in-flight decompression 

of the airplane. 

Relevant Service Information 

We reviewed Boeing Service Bulletin 

747–53A2784, Revision 1, dated 

September 14, 2011. For information on 

the procedures and compliance times, 

see this service information at http:// 

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34882 Federal Register / Vol. 77, No. 113 / Tuesday, June 12, 2012 / Proposed Rules 

www.regulations.gov by searching for 

Docket No. FAA No. FAA–2012–0498. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information identified 

previously, except as discussed under 

‘‘Differences Between the Proposed AD 

and the Service Information.’’ This 

proposed AD also provides options for 

accomplishing the actions that are 

required for airplanes on which no 

cracking is found in the crown frame 

web. 

The phrase ‘‘related investigative 

actions’’ is used in this proposed AD. 

‘‘Related investigative actions’’ are those 

actions that are identified as follow-on 

actions that are: (1) Related to the 

preceding required action, and (2) are 

on-condition actions that further 

investigate the nature of any condition 

found. Related investigative actions 

could include, for example, inspections 

and operational tests. 

In addition, the phrase ‘‘corrective 

actions’’ is used in this proposed AD. 

‘‘Corrective actions’’ are those actions 

that are on-condition actions that 

correct or address any condition found. 

Corrective actions could include, for 

example, repairs, removal and 

replacement, and modifications. 

Accomplishment of the inspection 

required by AD 2009–19–05, 

Amendment 39–16022 (74 FR 48138, 

September 22, 2009), would terminate 

the requirements of the postreplacement inspections required by 

paragraph (j) of this proposed AD. 

Differences Between the Proposed AD 

and the Service Information 

Boeing Service Bulletin 747– 

53A2784, Revision 1, dated September 

14, 2011, 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: 

• In accordance with 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 

affects 29 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

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

Measurement ............................ 1 work-hour × $85 per hour = 

$85.

$0 .................. $85 .......................................... $2,465. 

Inspection and web replacement.208 work-hours × $85 per 

hour = $17,680.

Up to $21,887 Up to $39,567 ......................... Up to $1,147,443. 

Post-replacement inspection .... 135 work-hours × $85 per 

hour = $11,475 per inspection cycle.

$0 .................. $11,475 per inspection cycle .. $332,775 per inspection 

cycle. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition crack 

repairs specified in this proposed AD. 

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), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

The Boeing Company: Docket No. FAA– 

2012–0498; Directorate Identifier 2011– 

NM–212–AD. 

(a) Comments Due Date 

We must receive comments by July 27, 

2012. 

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Federal Register / Vol. 77, No. 113 / Tuesday, June 12, 2012 / Proposed Rules 34883 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–400, –400D, and –400F series 

airplanes, certificated in any category, as 

specified in Boeing Service Bulletin 747– 

53A2784, Revision 1, dated September 14, 

2011. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of crown 

frame web cracking at left buttock line (LBL) 

15.0, station (STA) 320. We are proposing 

this AD to prevent complete fracture of the 

crown frame assembly, and consequent 

damage to the skin and in-flight 

decompression of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Crown Frame Web Measurement 

At the applicable compliance time 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Service Bulletin 747–53A2784, 

Revision 1, dated September 14, 2011, except 

as specified in paragraph (k)(1) of this AD, 

measure the thickness of the crown frame 

web at station (STA) 320, in accordance with 

the Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2784, Revision 1, 

dated September 14, 2011. For airplanes with 

a 0.136 to 0.145-inch-thick web, no further 

action is required by this AD. 

(h) Detailed Inspection and Web 

Replacement With No Web Repair Doubler 

For airplanes on which the web measures 

0.078- to 0.083-inch thick during the 

measurement required by paragraph (g) of 

this AD, and on which repair doubler is not 

installed: At the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Service Bulletin 747–53A2784, Revision 1, 

dated September 14, 2011, except as 

specified in paragraph (k)(1) of this AD, do 

a detailed inspection for cracks and a general 

visual inspection for missing fasteners of the 

crown frame web at STA 320; and do all 

applicable related investigative and 

corrective actions; in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2784, Revision 1, 

dated September 14, 2011, except as 

specified in paragraph (k)(2) of this AD. Do 

the applicable related investigative and 

corrective actions at the applicable times in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Service Bulletin 747–53A2784, Revision 1, 

dated September 14, 2011, except as 

specified in paragraph (k)(1) of this AD. 

Boeing Service Bulletin 747–53A2784, 

Revision 1, dated September 14, 2011, 

provides options for accomplishing the 

actions that are required for airplanes on 

which no cracking is found in the crown 

frame web. 

(i) Detailed Inspection and Web 

Replacement With Web Repair Doubler 

For airplanes on which the web measures 

0.078- to 0.083-inch thick during the 

measurement required by paragraph (g) of 

this AD, and on which a repair doubler is 

installed: At the applicable compliance time 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Service Bulletin 747–53A2784, 

Revision 1, dated September 14, 2011, except 

as specified in paragraph (k)(1) of this AD, do 

the actions specified in paragraphs (i)(1) and 

(i)(2) of this AD, and do all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2784, Revision 1, 

dated September 14, 2011, except as 

provided by paragraph (k)(2) of this AD. Do 

all applicable corrective actions before 

further flight. 

(1) Replace the web with a new web and 

do all applicable related investigative 

actions. 

(2) Do a detailed inspection for cracks in 

the upper or lower chord of the crown frame 

web at STA 320. 

(j) Post-Replacement Repetitive Inspections 

of Replaced Web 

Following any web replacement required 

by this AD, at the times specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Service Bulletin 747–53A2784, Revision 1, 

dated September 14, 2011: Do a detailed 

inspection for cracks of the web, upper 

chord, lower chord, and lower chord splice, 

and do all applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

53A2784, Revision 1, dated September 14, 

2011, except as provided by paragraph (k)(2) 

of this AD. Do all applicable corrective 

actions before further flight. If no crack is 

found, repeat the inspection thereafter at the 

intervals specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

747–53A2784, Revision 1, dated September 

14, 2011. Accomplishment of the inspections 

required by AD 2009–19–05, Amendment 

39–16022 (74 FR 48138, September 22, 2009), 

terminates the requirements of this 

paragraph. 

(k) Exceptions to the Service Information 

(1) Where Boeing Service Bulletin 747– 

53A2784, Revision 1, dated September 14, 

2011, specifies a compliance time ‘‘after the 

original issue date of the service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(2) Where Boeing Service Bulletin 747– 

53A2784, Revision 1, dated September 14, 

2011, specifies to contact Boeing for 

appropriate action, accomplish applicable 

actions before further flight using a method 

approved in accordance with the procedures 

specified in paragraph (l) of this AD. 

(l) Alternative Methods of Compliance 

(AMOCs) 

(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. 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. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(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) 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 (ODA) 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. 

(m) Related Information 

(1) For more information about this AD, 

contact Bill Ashforth, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425–917– 

6432; fax: 425–917–6590; email: 

Bill.Ashforth@faa.gov. 

(2) For service information identified in 

this 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; email me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You may 

also review the referenced service 

information in the docket at 

www.regulations.gov (refer to Docket No. 

FAA–2012–0498). You may review copies of 

the referenced service information at the 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on May 31, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–14253 Filed 6–11–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF COMMERCE 

Minority Business Development 

Agency 

15 CFR Part 1400 

[Docket No. 120517080–2132–02] 

Petition for Inclusion of the ArabAmerican Community in the Groups 

Eligible for MBDA Services 

AGENCY: Minority Business 

Development Agency, Commerce. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS