Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations 41647 

a request for consent has been 

submitted, consent shall be deemed to 

be granted. 

(e) Expiration by operation of law. 

Notwithstanding any determination by 

the Corporation as receiver to withhold 

consent under this section, the 

prohibitions described in 12 U.S.C. 

5390(c)(13)(C)(i) are no longer 

applicable 90 days after the 

appointment of the receiver. 

(f) Limitations. Any consent granted 

by the Corporation as receiver under 

this section shall not act to waive or 

relinquish any rights granted to the 

Corporation in any capacity, pursuant to 

any other applicable law or any 

agreement or contract, and shall not be 

construed as waiving, limiting or 

otherwise affecting the rights or powers 

of the Corporation as receiver to take 

any action or to exercise any power not 

specifically mentioned, including but 

not limited to any rights, powers or 

remedies of the receiver regarding 

transfers taken in contemplation of the 

covered financial company’s insolvency 

or with the intent to hinder, delay or 

defraud the covered financial company 

or the creditors of such company, or that 

is a fraudulent transfer under applicable 

law. 

(g) Exceptions. (1) This section shall 

not apply in the case of a contract that 

is repudiated or disaffirmed by the 

Corporation as receiver. 

(2) This section shall not apply to a 

director or officer liability insurance 

contract, a financial institution bond, 

the rights of parties to certain qualified 

financial contracts pursuant to 12 U.S.C. 

5390(c)(8), the rights of parties to 

netting contracts pursuant to 12 U.S.C. 

4401 et seq., or any extension of credit 

from any Federal reserve bank or the 

Corporation to any covered financial 

company or any security interest in the 

assets of a covered financial company 

securing any such extension of credit. 

§ 380.52 Adequate protection. 

(a) If the Corporation as receiver 

determines that it will use, sell, or lease 

or grant a security interest or other lien 

against property of the covered financial 

company that is subject to a security 

interest of a claimant, the receiver shall 

provide adequate protection by any of 

the following means: 

(1) Making a cash payment or periodic 

cash payments to the claimant to the 

extent that the sale, use, or lease of the 

property or the grant of a security 

interest or other lien against the 

property by the Corporation as receiver 

results in a decrease in the value of such 

claimant’s security interest in the 

property; 

(2) Providing to the claimant an 

additional or replacement lien to the 

extent that the sale, use, or lease of the 

property or the grant of a security 

interest against the property by the 

Corporation as receiver results in a 

decrease in the value of the claimant’s 

security interest in the property; or 

(3) Providing any other relief that will 

result in the realization by the claimant 

of the indubitable equivalent of the 

claimant’s security interest in the 

property. 

(b) Adequate protection of the 

claimant’s security interest will be 

presumed if the value of the property is 

not depreciating or is sufficiently greater 

than the amount of the claim so that the 

claimant’s security interest is not 

impaired. 

§ 380.53 Repudiation of secured contract. 

To the extent that a contract to which 

a covered financial company is a party 

is secured by property of the covered 

financial company, the repudiation of 

the contract by the Corporation as 

receiver shall not be construed as 

permitting the avoidance of any legally 

enforceable and perfected security 

interest in the property, and the security 

interest shall secure any claim for 

repudiation damages. 

By order of the Board of Directors. 

Dated at Washington, DC, this 6th day of 

July 2011. 

Federal Deposit Insurance Corporation. 

Robert E. Feldman, 

Executive Secretary. 

[FR Doc. 2011–17397 Filed 7–14–11; 8:45 am] 

BILLING CODE 6714–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1305; Directorate 

Identifier 2010–NM–074–AD; Amendment 

39–16749; AD 2011–15–02] 

RIN 2120–AA64 

Airworthiness Directives; Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company Model 382, 

382B, 382E, 382F, and 382G Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

all Model 382, 382B, 382E, 382F, and 

382G airplanes. That AD currently 

requires revising the FAA-approved 

maintenance program by incorporating 

new airworthiness limitations for fuel 

tank systems to satisfy Special Federal 

Aviation Regulation No. 88 

requirements. That AD also requires the 

accomplishment of certain fuel system 

modifications, the initial inspections of 

certain repetitive fuel system limitations 

to phase in those inspections, and repair 

if necessary. This new AD corrects 

certain part number references, adds an 

additional inspection area, and for 

certain airplanes, requires certain 

actions to be re-accomplished according 

to revised service information. This AD 

was prompted by a report of incorrect 

accomplishment information in the 

service information cited by the existing 

AD. We are issuing this AD to prevent 

the potential for ignition sources inside 

fuel tanks caused by latent failures, 

alterations, repairs, or maintenance 

actions, which, in combination with 

flammable fuel vapors, could result in a 

fuel tank explosion and consequent loss 

of the airplane. 

DATES: This AD is effective August 19, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of August 19, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of November 3, 2008 (73 FR 

56464, dated September 29, 2008). 

ADDRESSES: For service information 

identified in this 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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

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41648 Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: Neil 

Duggan, Aerospace Engineer, 

Propulsion and Services Branch, ACE– 

118A, FAA, Atlanta Aircraft 

Certification Office, 1701 Columbia 

Avenue, College Park, GA 30337; phone: 

(404) 474–5576; fax: (404) 474–5606; 

e-mail: neil.duggan@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede airworthiness 

directive (AD) 2008–20–01, amendment 

39–15680 (73 FR 56464, September 29, 

2008). That AD applies to the specified 

products. The NPRM published in the 

Federal Register on January 5, 2011 (76 

FR 485). That NPRM proposed to 

continue to require revising the 

maintenance program by incorporating 

new airworthiness limitations for fuel 

tank systems to satisfy Special Federal 

Aviation Regulation No. 88 

requirements. That NPRM also proposed 

to continue to require the 

accomplishment of certain fuel system 

modifications, the initial inspections of 

certain repetitive fuel system limitations 

to phase in those inspections, and repair 

if necessary. That NPRM also proposed 

to correct certain part number 

references, add an additional inspection 

area, and for certain airplanes, require 

certain actions to be re-accomplished 

according to revised service 

information. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the proposal and the FAA’s 

response to the comment. 

Request To Revise Cost Estimate 

Lynden Air Cargo requested that the 

cost for revising the Instructions for 

Continued Airworthiness be included in 

the Costs of Compliance estimate. 

Lynden Air Cargo stated that there is a 

significant amount of work-hours 

associated with revising ‘‘company 

manuals, job cards, maintenance 

programs, computerized tracking 

programs and record keeping 

documents’’ so that the operator can 

comply with the requirements of a new 

AD. Lynden Air Cargo estimated that 

these actions will take at least 80 workhours for its office staff, and estimated 

that this cost would affect other 

operators. Lynden Air Cargo also 

pointed out that this work load for the 

office staff will have a greater impact on 

smaller fleet operators with smaller 

staff. 

We agree that a requirement of the 

new AD will require an update of the 

maintenance program to incorporate 

references to revised service 

information. This action is estimated to 

take approximately 1 work-hour per 

airplane. However, we disagree with 

increasing the estimated work-hours for 

the time that it takes for writing job 

cards, tracking programs, or recordkeeping, since those actions are not 

directly required by this AD. The costs 

specified by Lynden Air Cargo will not 

be the same for all operators. The Costs 

of Compliance estimate has been revised 

accordingly. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

There are about 62 airplanes of the 

affected design in the worldwide fleet. 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD. The average labor 

rate per hour is $85. The costs of the 

new requirements of this AD are as 

follows: 

ESTIMATED COSTS FOR NEW ACTIONS

Action Work hours Parts Cost per airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Inspection of fuel probes ........ 24 None ........... $2,040, per inspection cycle 24 $48,960, per inspection cycle. 

Maintenance program revision 1 None ........... $85 ......................................... 24 $2,040. 

Actions necessary for airplanes on which Lockheed 

Service Bulletin 382–28–19, 

Revision 3, dated November 30, 2006, has been 

done.

24 None ........... $2,040 .................................... 24 $48,960. 

The current costs for AD 2008–20–01 

are repeated for the convenience of 

affected operators, as follows: 

ESTIMATED COSTS FOR ACTIONS REQUIRED BY AD 2008–20–01 

Action Work hours Parts Cost per 

product 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Maintenance program revision ............................................... 1 None ........... $85 24 $2,040 

Installation of new, improved fuel dump masts ..................... 12 $10,288 ....... $11,308 24 $271,392 

Dry bay zonal inspection, inspection and repair of static 

ground terminals, marking the wiring for the fuel quantity 

indicating system, initial inspection of lightning and static 

bonding jumpers.

952 None ........... $80,920 24 $1,942,080 

Installation of GFIs and flame arrestors ................................. 120 $115,000 ..... $125,200 24 $3,004,800 

Initial inspection of GFIs and flame arrestors ........................ 8 None ........... $680 24 $16,320 

Installation of lightning bonding jumpers ................................ 910 $10,000 ....... $87,350 24 $2,096,400 

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Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations 41649 

ESTIMATED COSTS FOR ACTIONS REQUIRED BY AD 2008–20–01—Continued 

Action Work hours Parts Cost per 

product 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Sealant application ................................................................. 320 None ........... $27,200 24 $652,800 

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 have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

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 that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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 

removing airworthiness directive (AD) 

2008–20–01, Amendment 39–15680 (73 

FR 56464, September 29, 2008), and 

adding the following new AD: 

2011–15–02 Lockheed Martin Corporation/ 

Lockheed Martin Aeronautics Company: 

Amendment 39–16749; Docket No. 

FAA–2010–1305; Directorate Identifier 

2010–NM–074–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective August 19, 2011. 

Affected ADs 

(b) This AD supersedes AD 2008–20–01, 

Amendment 39–15680. 

Applicability 

(c) This AD applies to all Lockheed Martin 

Corporation/Lockheed Martin Aeronautics 

Company Model 382, 382B, 382E, 382F, and 

382G airplanes, certificated in any category. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new inspections. Compliance with 

these inspections is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these inspections, the 

operator may not be able to accomplish the 

inspections described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance according 

to paragraph (o) of this AD. The request 

should include a description of changes to 

the required inspections that will ensure the 

continued operational safety of the airplane. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 28: Fuel. 

Unsafe Condition 

(e) This AD results from a design review 

of the fuel tank systems. The Federal 

Aviation Administration is issuing this AD to 

prevent the potential for ignition sources 

inside fuel tanks caused by latent failures, 

alterations, repairs, or maintenance actions, 

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. 

RESTATEMENT OF REQUIREMENTS OF AD 2008–20– 

01, WITH NEW SERVICE INFORMATION: 

Maintenance Program Revision 

(g) Before December 16, 2008, revise the 

maintenance program to incorporate the fuel 

system limitations (FSLs) and the critical 

design configuration control limitations 

(CDCCLs) specified in the Accomplishment 

Instructions of the Lockheed Service Bulletin 

382–28–22, Revision 3, dated March 28, 

2008; except as provided by paragraphs 

(g)(1), (g)(2), and (g)(3) of this AD, and except 

that the modifications and initial inspections 

specified in table 1 of this AD must be done 

at the compliance time specified in 

paragraph (h) of this AD. 

(1) For the CDCCLs specified in paragraphs 

2.C.(3)(e), 2.C.(3)(h), 2.C.(4)(a), 2.C.(5)(c), 

2.C.(7)(h), and 2.C.(8) of the Accomplishment 

Instructions of Lockheed Service Bulletin 

382–28–22, Revision 3, dated March 28, 

2008, do the applicable actions in accordance 

with the Accomplishment Instructions of 

Lockheed Service Bulletin 382–28–19, 

Revision 3, dated November 30, 2006; or 

Revision 4, dated September 18, 2008. After 

the effective date of this AD, use only 

Revision 4. 

(2) Where paragraph 2.C.(1)(c) of the 

Accomplishment Instructions of Lockheed 

Service Bulletin 382–28–22, Revision 3, 

dated March 28, 2008, specifies to change the 

maintenance program to indicate that 

repetitive inspections of the lightning and 

static bonding jumpers must be done in 

accordance with Lockheed Service Bulletin 

382–28–21, instead do the repetitive 

inspections in accordance with Lockheed 

Service Bulletin 382–28–19, Revision 3, 

dated November 30, 2006; or Revision 4, 

dated September 18, 2008. After the effective 

date of this AD, use only Revision 4. 

(3) Where Lockheed Service Bulletin 382– 

28–22, Revision 3, dated March 28, 2008, 

specifies to inspect, this AD requires doing 

a general visual inspection. 

Note 2: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

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41650 Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’ 

Fuel System Modifications, Initial 

Inspections, and Repair if Necessary 

(h) Within 36 months after November 3, 

2008 (the effective date of AD 2008–20–01), 

do the applicable actions specified in table 1 

of this AD, and repair any discrepancy before 

further flight, in accordance with the 

Accomplishment Instructions of Lockheed 

Service Bulletin 382–28–22, Revision 3, 

dated March 28, 2008. 

TABLE 1—MODIFICATIONS AND INITIAL INSPECTIONS

Action Additional source of guidance for accomplishing the action 

For airplanes having any serial number prior to 4962: Install new, improved fuel dump masts in accordance with paragraph 2.C.(1)(d) of 

the Accomplishment Instructions of Lockheed Service Bulletin 382– 

28–22, Revision 3, dated March 28, 2008.

Lockheed Service Bulletin 382–28–9, dated May 13, 1983. 

Mark the fuel quantity indicating system (FQIS) wires in accordance 

with paragraphs 2.C.(1)(a)2, 2.C.(4)(b), and 2.C.(4)(c) of the Accomplishment Instructions of Lockheed Service Bulletin 382–28–22, Revision 3, dated March 28, 2008.

Lockheed Service Bulletin 382–28–19, Revision 4, dated September 

18, 2008. 

Do the dry bay zonal inspection and inspect the static ground terminals 

of the fuel system plumbing in accordance with paragraph 2.C.(1)(a) 

of the Accomplishment Instructions of Lockheed Service Bulletin 

382–28–22, Revision 3, dated March 28, 2008.

Lockheed Service Bulletin 382–28–19, Revision 4, dated September 

18, 2008. 

Install ground fault interrupters (GFIs) and flame arrestors for protection 

of the fuel system in accordance with paragraphs 2.C.(1)(b) and 

2.C.(7)(c) of the Accomplishment Instructions of Lockheed Service 

Bulletin 382–28–22, Revision 3, dated March 28, 2008.

Lockheed Service Bulletin 382–28–20, Revision 11, dated April 20, 

2010. 

Inspect the GFIs for protection of the fuel system in accordance with 

paragraph 2.C.(1)(b)1 of the Accomplishment Instructions of Lockheed Service Bulletin 382–28–22, Revision 3, dated March 28, 2008.

Paragraph 2.C.(2) of the Accomplishment Instructions of Lockheed 

Service Bulletin 382–28–22, Revision 3, dated March 28, 2008. 

Install the lightning bonding jumpers (straps) in accordance with paragraphs 2.C.(1)(c) and 2.C.(6)(a) of the Accomplishment Instructions 

of Lockheed Service Bulletin 382–28–22, Revision 3, dated March 

28, 2008.

Lockheed Service Bulletin 382–28–21, Revision 4, dated January 6, 

2010. 

Inspect the lightning and static bonding jumpers (straps) in accordance 

with paragraphs 2.C.(1)(c) of the Accomplishment Instructions of 

Lockheed Service Bulletin 382–28–22, Revision 3, dated March 28, 

2008.

Lockheed Service Bulletin 382–28–19, Revision 4, dated September 

18, 2008. 

Apply a certain sealant to the interior of the main wing fuel tanks; and 

apply a certain sealant to the all external fuel tank nose caps, mid 

sections, and tail sections; as applicable; in accordance with paragraphs 2.C.(1)(e)1, 2.C.(1)(e)3, and 2.C.(7)(i)1 of the Accomplishment Instructions of Lockheed Service Bulletin 382–28–22, Revision 

3, dated March 28, 2008.

Lockheed Service Bulletin 382–28–24, Revision 1, dated November 5, 

2007, including the Errata Notice, dated January 7, 2008. 

No Alternative Inspections, Inspection 

Intervals, or CDCCLs 

(i) After accomplishing the actions 

specified in paragraphs (g) and (h) of this AD, 

no alternative inspections, inspection 

intervals, or CDCCLs may be used unless the 

inspections, intervals, or CDCCLs are 

approved as an alternative method of 

compliance in accordance with the 

procedures specified in paragraph (o) of this 

AD. 

No Reporting Requirement 

(j) Although Lockheed Service Bulletin 

382–28–19, Revision 3, dated November 30, 

2006, specifies to notify Lockheed of any 

discrepancies found during inspection, this 

AD does not require that action. 

NEW REQUIREMENTS OF THIS AD: 

Incorrect Steps in a Service Bulletin 

(k) Where the last two bulleted steps of 

paragraphs 2.C.(2)(b)5 and 2.C.(2)(c)3 of 

Lockheed Service Bulletin 382–28–22, 

Revision 3, dated March 28, 2008, specify 

that the GFI FAILURE and GROUND FAULT 

DETECTED lights illuminate for 2 seconds, 

this AD does not require those steps. 

Additional Inspection Area 

(l) For airplanes on which Lockheed 

Service Bulletin 382–28–19, Revision 3, 

dated November 30, 2006, has not been done: 

Where table 1 of this AD specifies to do the 

dry bay zonal inspection, do an inspection of 

the fuel probes as part of the dry bay zonal 

inspections, in accordance with the service 

information specified in paragraph (h) of this 

AD for the dry bay zonal inspections. Do the 

inspections at the time specified in paragraph 

(h) of this AD, or within 9 months after the 

effective date of this AD, whichever occurs 

later. 

Actions for Airplanes on Which a Previous 

Issue of Lockheed Service Bulletin 382–28– 

19 Was Done 

(m) For airplanes on which any action was 

done in accordance with Lockheed Service 

Bulletin 382–28–19, Revision 3, dated 

November 30, 2006: Within the compliance 

time specified in paragraph (h) of this AD, or 

within 9 months after the effective date of 

this AD, whichever occurs later, do the 

actions required by paragraphs (m)(1) 

through (m)(4) of this AD and repair any 

discrepancy before further flight, in 

accordance with Accomplishment 

Instructions of Lockheed Service Bulletin 

382–28–19, Revision 4, dated September 18, 

2008. Although Lockheed Service Bulletin 

382–28–19, Revision 4, dated September 18, 

2008, specifies to notify Lockheed of any 

discrepancies found during inspection, this 

AD does not require that action. 

(1) Inspect the fuel probes as part of the 

zonal inspections of the dry bay areas and 

other areas. 

(2) Inspect generator feeder and control 

wire bundles for correct separation from 

other wires in the wing leading edge and 

fuselage areas, and for correct separation 

from fuel tank boundaries in the wing 

leading edge area. 

(3) Inspect for correct spot-tying of certain 

wire bundles that are within 2 to 12 inches 

of hot equipment or wires with flameresistant lacing braid, or, for wiring in 

powerplant areas, with fiberglass braid. 

(4) Inspect for use of the correct shielding 

specification and separation of the FQIS 

wiring in certain locations from alternating 

current (AC) power wires. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(n) Actions done before the effective date 

of this AD in accordance with Lockheed 

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Federal Register / Vol. 76, No. 136 / Friday, July 15, 2011 / Rules and Regulations 41651 

Service Bulletin 382–28–20, Revision 8, 

dated October 13, 2009; Revision 9, dated 

December 14, 2009; or Revision 10, dated 

March 18, 2010; are acceptable for 

compliance with the requirements of 

paragraph (h) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(o)(1) The Manager, Atlanta 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. 

(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 for AD 2008–20–01 

are approved as AMOCs for this AD. 

Related Information 

(p) For more information about this AD, 

contact Neil Duggan, Aerospace Engineer, 

Propulsion and Services Branch, ACE–118A, 

FAA, Atlanta Aircraft Certification Office, 

1701 Columbia Avenue, College Park, GA 

30337; phone: (404) 474–5576; fax: (404) 

474–5606; e-mail: neil.duggan@faa.gov. 

Material Incorporated by Reference 

(q) You must use Lockheed Service 

Bulletin 382–28–19, Revision 4, dated 

September 18, 2008; or Lockheed Service 

Bulletin 382–28–22, Revision 3, dated March 

28, 2008; as applicable; to do the actions 

required by this AD, unless the AD specifies 

otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Lockheed Service Bulletin 382–28–19, 

Revision 4, dated September 18, 2008, under 

5 U.S.C. 552(a) and 1 CFR part 51. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of Lockheed Service Bulletin 382– 

28–22, Revision 3, dated March 28, 2008, on 

November 3, 2008 (73 FR 56464, September 

29, 2008). 

(3) For service information identified in 

this 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. 

(4) You may review copies of the service 

information at the FAA, 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. 

(5) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call 202–741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on July 1, 

2011. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–17399 Filed 7–14–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0217; Directorate 

Identifier 2010–NM–165–AD; Amendment 

39–16748; AD 2011–15–01] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model DC–9–81 (MD–81), 

DC–9–82 (MD–82), DC–9–83 (MD–83), 

DC–9–87 (MD–87), and MD–88 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD requires 

a detailed inspection to detect distress 

and existing repairs to the leading edge 

structure of the vertical stabilizer at the 

splice at Station Zfs = 52.267; repetitive 

inspections for cracking in the front spar 

cap forward flanges of the vertical 

stabilizer, and either the aft flanges or 

side skins; repetitive inspections for 

loose and missing fasteners; and related 

investigative and corrective actions if 

necessary. This AD was prompted by 

reports of cracked vertical stabilizer 

skin, a severed front spar cap, elongated 

fastener holes at the leading edge of the 

vertical stabilizer, and a cracked front 

spar web and front spar cap bolt holes 

in the vertical stabilizer. We are issuing 

this AD to detect and correct such 

cracking damage, which could result in 

the structure being unable to support 

limit load, and could lead to the loss of 

the vertical stabilizer. 

DATES: This AD is effective August 19, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of August 19, 2011. 

ADDRESSES: For service information 

identified in this 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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Roger Durbin, Aerospace Engineer, 

Airframe Branch, ANM–120L, Los 

Angeles Aircraft Certification Office, 

3960 Paramount Boulevard, Lakewood, 

California 90712–4137; phone: 562– 

627–5233; fax: 562–627–5210; e-mail: 

Roger.Durbin@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to the 

specified products. That NPRM 

published in the Federal Register on 

March 14, 2011 (76 FR 13543). That 

NPRM proposed to require a detailed 

inspection to detect distress and 

existing repairs to the leading edge 

structure of the vertical stabilizer at the 

splice at Station Zfs = 52.267; repetitive 

inspections for cracking in the front spar 

cap forward flanges of the vertical 

stabilizer, and either the aft flanges or 

side skins; repetitive inspections for 

loose and missing fasteners; and related 

investigative and corrective actions if 

necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

mstockstill on DSK4VPTVN1PROD with RULES