This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

58416 

Vol. 76, No. 183 

Wednesday, September 21, 2011 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0919; Directorate 

Identifier 2010–NM–088–AD] 

RIN 2120–AA64 

Airworthiness Directives; Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company Model L–1011 

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 L–1011 series airplanes. This 

proposed AD would require repetitive 

inspections for cracking of the wing rear 

spar and upper surface zones, and repair 

if necessary. This proposed AD results 

from a damage tolerance analysis 

conducted by the manufacturer 

indicating that fatigue cracking could 

occur in those areas. We are proposing 

this AD to detect and correct such 

fatigue cracking, which could result in 

cracking that grows large enough to 

reduce the wing strength below 

certificated requirements and possibly 

cause fracture of the rear spar, resulting 

in extensive damage to the wing and 

possible fuel leaks. 

DATES: We must receive comments on 

this proposed AD by November 7, 2011. 

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 Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company, Airworthiness 

Office, Dept. 6A0M, Zone 0252, Column 

P–58, 86 S. Cobb Drive, Marietta, 

Georgia 30063; telephone 770–494– 

5444; fax 770–494–5445; e-mail 

ams.portal@lmco.com; Internet http:// 

www.lockheedmartin.com/ams/tools/ 

TechPubs.html. 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: Carl 

Gray, Aerospace Engineer, Airframe 

Branch, ACE–117A, FAA, Atlanta 

Aircraft Certification Office (ACO), 1701 

Columbia Avenue, College Park, Georgia 

30337; phone: 404–474–5554; fax: 404– 

474–5606; e-mail: Carl.W.Gray@faa.gov. 

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–2011–0919; Directorate Identifier 

2010–NM–088–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 previously issued AD 94–05–01, 

Amendment 39–8839 (59 FR 10275, 

March 4, 1994), and AD 2000–21–01, 

Amendment 39–11933 (65 FR 62994, 

October 20, 2000), which require 

modifications to extend the life of the 

wing rear spar inboard area. The 

modifications required by those two 

ADs removed cracks in the wing upper 

skin and installed repair bushings as 

necessary. The lower spar cap was 

modified by adding nested angles and 

cold working the attachment holes. 

Based upon a damage tolerance 

analysis, additional inspections are 

required to ensure the structural 

integrity of the structure modified in 

accordance with those two ADs as well 

as the adjoining baseline structure. If 

cracking is undetected and unrepaired, 

it could result in cracking that grows 

large enough to reduce the wing 

strength below certificated requirements 

and possibly cause fracture of the rear 

spar, resulting in extensive damage to 

the wing and possible fuel leaks. 

Relevant Service Information 

We have reviewed Lockheed Service 

Bulletin 093–57–226, dated August 31, 

2009. This service bulletin describes 

procedures for repetitive eddy current 

non-destructive inspections (NDI) and 

detailed inspections for cracking of the 

wing rear spar and upper surface zones. 

The service bulletin identifies 

inspections for the airplane models in 

the zones identified in the following 

table, titled ‘‘Inspections.’’ 

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Federal Register / Vol. 76, No. 183 / Wednesday, September 21, 2011 / Proposed Rules 58417 

TABLE—INSPECTIONS

Airplane models Inspection type Zone(s) 

L–1011–385–1, L–1011–385–1–14, and L–1011–385– 

1–15.

Non-destructive ............................................................ 1A through 1E. 

Detailed Visual ............................................................. 1F. 

L–1011–385–3 ............................................................... Non-destructive ............................................................ 3A through 3E. 

Detailed Visual ............................................................. 3F. 

For airplanes on which cracking is 

found during any inspection, this 

service information specifies a bolt hole 

eddy current inspection to verify the 

cracking. The corrective actions for 

cracking include repairing cracking if 

the cracking is within specified limits, 

or contacting the manufacturer for 

repair instructions if the cracking is not 

within specified limits. 

Related Rulemaking 

AD 94–05–01, Amendment 39–8839 

(59 FR 10275, March 4, 1994), and AD 

2000–21–01, Amendment 39–11933 (65 

FR 62994, October 20, 2000), specify 

structural modification installations on 

Model L–1011 series airplanes. This 

proposed AD would not change the 

requirements of AD 94–05–01 and AD 

2000–21–01. However, this proposed 

AD would require new inspections for 

structures affected by the modifications 

required by those two ADs. 

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 Lockheed Service Bulletin 

093–57–226, dated August 31, 2009, 

described previously. 

Differences Between the Proposed AD 

and the Service Information 

This proposed AD specifies initial 

compliance times and repetitive 

inspection intervals that differ from 

those contained in Lockheed Service 

Bulletin 093–57–226, dated August 31, 

2009. The changes have been 

coordinated with Lockheed Martin and 

they concur with the FAA’s position. 

The compliance times were changes to 

simplify the inspection requirements. 

We also propose that all crack findings 

be repaired before further flight. We 

have determined that the compliance 

times, as proposed, represent the 

maximum interval of time allowable for 

the affected airplanes to continue to 

safely operate before the inspections 

and repairs, if necessary, are done. 

Although that service bulletin 

specifies that operators may contact the 

manufacturer for disposition of certain 

repairs, this proposed AD would require 

operators to repair those conditions in 

accordance with a method approved by 

the FAA. 

Interim Action 

We consider this proposed AD 

interim action. If final action is later 

identified, we might consider further 

rulemaking then. 

Costs of Compliance 

We estimate that this proposed AD 

affects 4 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 

Models: L–1011–385–1, L–1011–385–1– 

14, L–1011–385–1–15, Zones 1A 

through 1E (Non-destructive Inspection).

21 work-hours × $85 per 

hour = $1,785 per inspection cycle.

$0 $1,785 per inspection cycle.$3,570 per inspection cycle 

(2 airplanes). 

Models: L–1011–385–1, L–1011–385–1– 

14, L–1011–385–1–15, Zone 1F (Detailed Inspection).

5 work-hours × $85 per hour 

= $425 per inspection 

cycle.

0 $425 per inspection 

cycle.

$850 per inspection cycle 

(2 airplanes). 

Model: L–1011–385–3, Zones 1A through 

1E (Non-destructive Inspection).

24 work-hours × $85 per 

hour = $2,040 per inspection cycle.

0 $2,040 per inspection cycle.$4,080 per inspection cycle 

(2 airplanes). 

Model: L–1011–385–3, Zone 1F (Detailed 

Inspection).

5 work-hours × $85 per hour 

= $425 per inspection 

cycle.

0 $425 per inspection 

cycle.

$850 per inspection cycle 

(2 airplanes). 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

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 

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58418 Federal Register / Vol. 76, No. 183 / Wednesday, September 21, 2011 / Proposed Rules 

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 AD: 

Lockheed Martin Corporation/Lockheed 

Martin Aeronautics Company: Docket 

No. FAA–2011–0919; Directorate 

Identifier 2010–NM–088–AD. 

Comments Due Date 

(a) We must receive comments by 

November 7, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Lockheed Martin 

Corporation/Lockheed Martin Aeronautics 

Company Model L–1011–385–1, L–1011– 

385–1–14, L–1011–385–1–15, and L–1011– 

385–3 airplanes, certificated in any category, 

serial numbers 1002 through 1250 inclusive. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 57, Wings. 

Unsafe Condition 

(e) This AD results from a damage 

tolerance analysis conducted by the 

manufacturer that indicates fatigue cracking 

could occur in the wing rear spar and upper 

surface zones. The Federal Aviation 

Administration is issuing this AD to detect 

and correct such fatigue cracking, which 

could result in cracking that grows large 

enough to reduce the wing strength below 

certificated requirements and possibly cause 

fracture of the rear spar, resulting in 

extensive damage to the wing and possible 

fuel leaks. 

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. 

Inspections of Wing Rear Spar and Upper 

Surface Zones, and Corrective Actions 

(g) At the applicable time specified in 

paragraph (k) of this AD, do eddy current 

non-destructive inspections (NDI) and 

detailed inspections for cracking at the 

applicable zones specified in paragraph (g)(1) 

or (g)(2) of this AD, in accordance with the 

Accomplishment Instructions of Lockheed 

Service Bulletin 093–57–226, dated August 

31, 2009. Repeat the inspections thereafter at 

the applicable interval specified in Table 1 of 

this AD. 

(1) For Model L–1011–385–1, L–1011–385– 

1–14, and L–1011–385–1–15 airplanes: Zones 

1A through 1E, and Zone 1F. 

(2) For Model L–1011–385–3 airplanes: 

Zones 3A through 3E, and Zone 3F. 

Additional Inspection if Cracking is Found 

(h) Except as specified in paragraph (j) of 

this AD, if any cracking is detected during 

any inspection required by paragraph (g) of 

this AD: Before further flight, remove the 

fastener(s) at the suspect area, as defined in 

Lockheed Service Bulletin 093–57–226, 

dated August 31, 2009; and do a secondary 

eddy current inspection to detect cracking of 

fastener holes with suspected crack 

indications; in accordance with the 

Accomplishment Instructions of Lockheed 

Service Bulletin 093–57–226, dated August 

31, 2009. 

Repair 

(i) Except as specified in paragraph (j) of 

this AD, if a crack finding is confirmed by 

the inspection required by paragraph (h) of 

this AD and the cracking is within the 

allowable repair limits specified in Lockheed 

Martin Repair Drawing LCC7622–369, 

Revision March 30, 1995: Before further 

flight, repair the cracking, in accordance with 

Lockheed Martin Repair Drawing LCC7622– 

369, Revision March 30, 1995. If a crack 

finding confirmed by the inspection required 

by paragraph (h) of this AD is not within the 

allowable repair limits specified in Lockheed 

Martin Repair Drawing LCC7622–369, 

Revision March 30, 1995: Before further 

flight, repair the cracking, in accordance with 

a method approved by the Manager, Atlanta 

Aircraft Certification Office (ACO), FAA. For 

a repair method to be approved by the 

Manager, Atlanta ACO, as required by this 

paragraph, the Manager’s approval letter 

must specifically refer to this AD. 

Exception to Service Bulletin 

(j) If any cracking is found during any 

inspection required by this AD, and 

Lockheed Service Bulletin 093–57–226, 

dated August 31, 2009; or Lockheed Martin 

Repair Drawing LCC7622–369, Revision 

March 30, 1995; specifies contacting 

Lockheed for appropriate action: Before 

further flight, repair the cracking in 

accordance with a method approved by the 

Manager, Atlanta ACO, FAA. For a repair 

method to be approved by the Manager, 

Atlanta ACO, as required by this paragraph, 

the Manager’s approval letter must 

specifically refer to this AD. 

Compliance Times for Inspections 

(k) Do the inspections required by 

paragraph (g) of this AD at the applicable 

time specified in table 1 of this AD. 

TABLE 1—COMPLIANCE TIMES FOR INSPECTIONS

Airplane models and zones Compliance time Repetitive interval 

(whichever occurs later) (not to exceed) 

L–1011–385–1 having accumulated 

fewer than 7,000 flight cycles 

after the accomplishment of Lockheed Martin Service Bulletin 093– 

57–184, 093–57–196, or 093–57– 

215; as of the effective date of 

this AD; Zones 1A through 1E 

(Non-destructive Inspection (NDI)).

Within 7,000 flight cycles or 10 

years after the accomplishment of 

Lockheed Martin Service Bulletin 

093–57–184, 093–57–196, or 

093–57–215, whichever occurs 

first.

Within 1,000 flight cycles after the 

effective date of this AD.

1,100 flight cycles. 

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Federal Register / Vol. 76, No. 183 / Wednesday, September 21, 2011 / Proposed Rules 58419 

TABLE 1—COMPLIANCE TIMES FOR INSPECTIONS—Continued 

L–1011–385–1 having accumulated 

fewer than 7,000 flight cycles 

after the accomplishment of Lockheed Martin Service Bulletin 093– 

57–184, 093–57–196, or 093–57– 

215; as of the effective date of 

this AD; Zone 1F (Detailed Inspection).

Within 7,000 flight cycles or 10 

years after the accomplishment of 

Lockheed Martin Service Bulletin 

093–57–184, 093–57–196, or 

093–57–215, whichever occurs 

first.

Within 90 flight cycles or 30 days 

after the effective date of this AD, 

whichever occurs later.

90 flight cycles. 

L–1011–385–1 having accumulated 

7,000 flight cycles or more flight 

cycles after the accomplishment 

of Lockheed Martin Service Bulletin 093–57–184, 093–57–196, or 

093–57–215; as of the effective 

date of this AD; Zones 1A through 

1E (NDI).

Within 1,000 flight cycles or 12 

months after the effective date of 

this AD, whichever occurs first.

N/A ................................................... 1,100 flight cycles. 

L–1011–385–1 having accumulated 

7,000 flight cycles or more after 

the accomplishment of Lockheed 

Martin Service Bulletin 093–57– 

184, 093–57–196, or 093–57– 

215; as of the effective date of 

this AD; Zone 1F (Detailed Inspection).

Within 90 flight cycles after the effective date of this AD.Within 30 days after the effective 

date of this AD.

90 flight cycles. 

L–1011–385–1–14 having accumulated fewer than 6,900 flight cycles after the accomplishment of 

Lockheed Martin Service Bulletin 

093–57–184, 093–57–196, or 

093–57–215; as of the effective 

date of this AD; Zones 1A through 

1E (NDI).

Within 6,900 flight cycles or 10 

years after the accomplishment of 

Lockheed Martin Service Bulletin 

093–57–184, 093–57–196, or 

093–57–215, whichever occurs 

first.

Within 1,000 flight cycles after the 

effective date of this AD.

900 flight cycles. 

L–1011–385–1–14 having accumulated fewer than 6,900 flight cycles after the accomplishment of 

Lockheed Martin Service Bulletin 

093–57–184, 093–57–196, or 

093–57–215; as of the effective 

date of this AD; Zone 1F (Detailed Inspection).

Within 6,900 flight cycles or 10 

years after the accomplishment of 

Lockheed Martin Service Bulletin 

093–57–184, 093–57–196, or 

093–57–215, whichever occurs 

first.

Within 90 flight cycles or 30 days 

after the effective date of this AD, 

whichever occurs later.

90 flight cycles. 

L–1011–385–1–14 having accumulated 6,900 or more flight cycles 

after the accomplishment of Lockheed Martin Service Bulletin 093– 

57–184, 093–57–196, or 093–57– 

215; as of the effective date of 

this AD; Zones 1A through 1E 

(NDI).

Within 1,000 flight cycles or 12 

months after the effective date of 

this AD, whichever occurs first.

N/A ................................................... 900 flight cycles. 

L–1011–385–1–14 having accumulated 6,900 or more flight cycles 

after the accomplishment of Lockheed Martin Service Bulletin 093– 

57–184, 093–57–196, or 093–57– 

215; as of the effective date of 

this AD; Zone 1F (Detailed Inspection).

Within 90 flight cycles after the effective date of this AD.Within 30 days after the effective 

date of this AD.

90 flight cycles. 

L–1011–385–1–15 having accumulated fewer than 5,600 flight cycles after the accomplishment of 

Lockheed Martin Service Bulletin 

093–57–184, 093–57–196, or 

093–57–215; as of the effective 

date of this AD; Zones 1A through 

1E (NDI).

Within 5,600 flight cycles or 10 

years after the accomplishment of 

Lockheed Martin Service Bulletin 

093–57–184, 093–57–196, or 

093–57–215, whichever occurs 

first.

Within 1,000 flight cycles after the 

effective date of this AD.

500 flight cycles. 

L–1011–385–1–15 having accumulated fewer than 5,600 flight cycles after the accomplishment of 

Lockheed Martin Service Bulletin 

093–57–184, 093–57–196, or 

093–57–215; as of the effective 

date of this AD; Zone 1F (Detailed Inspection).

Within 5,600 flight cycles or 10 

years after the accomplishment of 

Lockheed Martin Service Bulletin 

093–57–184, 093–57–196, or 

093–57–215, whichever occurs 

first.

Within 60 flight cycles or 30 days 

after the effective date of this AD, 

whichever occurs later.

60 flight cycles. 

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58420 Federal Register / Vol. 76, No. 183 / Wednesday, September 21, 2011 / Proposed Rules 

TABLE 1—COMPLIANCE TIMES FOR INSPECTIONS—Continued 

L–1011–385–1–15 having accumulated 5,600 or more flight cycles 

after the accomplishment of Lockheed Martin Service Bulletin 093– 

57–184, 093–57–196, or 093–57– 

215; as of the effective date of 

this AD; Zones 1A through 1E 

(NDI).

Within 1,000 flight cycles or 12 

months after the effective date of 

this AD, whichever occurs first.

N/A ................................................... 500 flight cycles. 

L–1011–385–1–15 having accumulated 5,600 or more flight cycles 

after the accomplishment of Lockheed Martin Service Bulletin 093– 

57–184, 093–57–196, or 093–57– 

215; as of the effective date of 

this AD; Zone 1F (Detailed Inspection).

Within 60 flight cycles after the effective date of this AD.Within 30 days after the effective 

date of this AD.

60 flight cycles. 

L–1011–385–3 having accumulated 

fewer than 8,400 flight cycles 

after the accomplishment of Lockheed Martin Service Bulletin 093– 

57–184, 093–57–196, or 093–57– 

215; as of the effective date of 

this AD; Zones 1A through 1E 

(NDI).

Within 8,400 flight cycles or 10 

years after the accomplishment of 

Lockheed Martin Service Bulletin 

093–57–184, 093–57–196, or 

093–57–215, whichever occurs 

first.

Within 1,000 flight cycles after the 

effective date of this AD.

1,200 flight cycles. 

L–1011–385–3 having accumulated 

fewer than 8,400 flight cycles 

after the accomplishment of Lockheed Martin Service Bulletin 093– 

57–184, 093–57–196, or 093–57– 

215; as of the effective date of 

this AD; Zone 1F (Detailed Inspection).

Within 90 flight cycles or 30 days 

after the effective date of this AD, 

whichever occurs later.

Within 85 flight cycles or 30 days 

after the effective date of this AD, 

whichever occurs later.

85 flight cycles. 

L–1011–385–3 having accumulated 

8,400 or more flight cycles after 

the accomplishment of Lockheed 

Martin Service Bulletin 093–57– 

184, 093–57–196, or 093–57– 

215; as of the effective date of 

this AD; Zones 1A through 1E 

(NDI).

Within 1,000 flight cycles or 12 

months after the effective date of 

this AD, whichever occurs first.

N/A ................................................... 1,200 flight cycles. 

L–1011–385–3 having accumulated 

8,400 or more flight cycles after 

the accomplishment of Lockheed 

Martin Service Bulletin 093–57– 

184, 093–57–196, or 093–57– 

215; as of the effective date of 

this AD; Zone 1F (Detailed Inspection).

Within 85 flight cycles after the effective date of this AD.Within 30 days after the effective 

date of this AD.

85 flight cycles. 

Alternative Methods of Compliance 

(AMOCs) 

(l)(1) The Manager, Atlanta 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. 

Related Information 

(m) For more information about this AD, 

contact Carl Gray, Aerospace Engineer, 

Airframe Branch, ACE–117A, FAA, Atlanta 

ACO, 1701 Columbia Avenue, College Park, 

Georgia 30337; phone: 404–474–5554; fax: 

404–474–5606; e-mail: Carl.W.Gray@faa.gov. 

Issued in Renton, Washington, on 

September 14, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–24270 Filed 9–20–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF COMMERCE 

Bureau of Economic Analysis 

15 CFR Part 806 

[Docket No. 110822526–1525–01] 

RIN 0691–AA80 

Direct Investment Surveys: BE–12, 

Benchmark Survey of Foreign Direct 

Investment in the United States 

AGENCY: Bureau of Economic Analysis, 

Commerce. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: This proposed rule would 

amend regulations of the Department of 

Commerce’s Bureau of Economic 

Analysis (BEA) to set forth the reporting 

requirements for the 2012 BE–12, 

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