Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Proposed Rules 485 

Accomplishment Instructions of Fokker 

Service Bulletin SBF28–57–097, Revision 1, 

dated June 10, 2010. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(i) Inspections accomplished before the 

effective date of this AD according to Fokker 

Service Bulletin SBF28–57–097, dated May 

6, 2010, are considered acceptable for 

compliance with the requirements of 

paragraph (g) of this AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(j) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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: Tom Rodriguez, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1137; fax (425) 227–1149. Information 

may be e-mailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. 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. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: A Federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave., SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

Related Information 

(k) Refer to MCAI European Aviation 

Safety Agency (EASA) Airworthiness 

Directive 2010–0156, dated August 3, 2010; 

and Fokker Service Bulletin SBF28–57–097, 

Revision 1, dated June 10, 2010; for related 

information. 

Issued in Renton, Washington, on 

December 28, 2010. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–33337 Filed 1–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1305; Directorate 

Identifier 2010–NM–074–AD] 

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), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to all Model 

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

airplanes. The existing 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 proposed AD would 

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. This 

proposed AD results from a report of 

incorrect accomplishment information 

in the service information cited by the 

existing AD. We are proposing 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: We must receive comments on 

this proposed AD by February 22, 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 

(telephone 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

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; 

telephone (404) 474–5576; fax (404) 

474–5606. 

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 


srobinson on DSKHWCL6B1PROD with PROPOSALS
486 Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Proposed Rules 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2010–1305; Directorate Identifier 

2010–NM–074–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

The FAA has examined the 

underlying safety issues involved in fuel 

tank explosions on several large 

transport airplanes, including the 

adequacy of existing regulations, the 

service history of airplanes subject to 

those regulations, and existing 

maintenance practices for fuel tank 

systems. As a result of those findings, 

we issued a regulation titled ‘‘Transport 

Airplane Fuel Tank System Design 

Review, Flammability Reduction and 

Maintenance and Inspection 

Requirements’’ (66 FR 23086, May 7, 

2001). In addition to new airworthiness 

standards for transport airplanes and 

new maintenance requirements, this 

rule included Special Federal Aviation 

Regulation No. 88 (‘‘SFAR 88,’’ 

Amendment 21–78, and subsequent 

Amendments 21–82 and 21–83). 

Among other actions, SFAR 88 

requires certain type design (i.e., type 

certificate (TC) and supplemental type 

certificate (STC)) holders to substantiate 

that their fuel tank systems can prevent 

ignition sources in the fuel tanks. This 

requirement applies to type design 

holders for large turbine-powered 

transport airplanes and for subsequent 

modifications to those airplanes. It 

requires them to perform design reviews 

and to develop design changes and 

maintenance procedures if their designs 

do not meet the new fuel tank safety 

standards. As explained in the preamble 

to the rule, we intended to adopt 

airworthiness directives to mandate any 

changes found necessary to address 

unsafe conditions identified as a result 

of these reviews. 

In evaluating these design reviews, we 

have established four criteria intended 

to define the unsafe conditions 

associated with fuel tank systems that 

require corrective actions. The 

percentage of operating time during 

which fuel tanks are exposed to 

flammable conditions is one of these 

criteria. The other three criteria address 

the failure types under evaluation: 

single failures, single failures in 

combination with a latent condition(s), 

and in-service failure experience. For all 

four criteria, the evaluations included 

consideration of previous actions taken 

that may mitigate the need for further 

action. 

We have determined that the actions 

identified in this AD are necessary to 

reduce the potential of ignition sources 

inside fuel tanks, which, in combination 

with flammable fuel vapors, could result 

in fuel tank explosions and consequent 

loss of the airplane. 

On September 11, 2008, we issued AD 

2008–20–01, amendment 39–15680 (73 

FR 56464, September 29, 2008), for all 

Model 382, 382B, 382E, 382F, and 382G 

airplanes. That AD requires revising the 

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. That AD resulted from a 

design review of the fuel tank systems. 

We issued that 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. 

Actions Since Existing AD Was Issued 

Since we issued AD 2008–20–01, we 

received information from the 

manufacturer that Lockheed Service 

Bulletin 382–28–21, Revision 2, dated 

November 20, 2006 (referenced in AD 

2008–20–01 as a source of additional 

guidance), contained an error in 

referencing certain part numbers for 

tube, fuel tank, and bulkhead joint 

jumpers. The part numbers as 

referenced in Revision 2 of that service 

bulletin do not exist. The manufacturer 

has published Lockheed Service 

Bulletin 382–28–21, Revision 4, dated 

January 6, 2010, to provide the correct 

part number references. We have 

revised Table 1 of this AD accordingly. 

We have also received information 

from the manufacturer that 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, contain an error. Those 

steps specify that the GFI FAILURE and 

GROUND FAULT DETECTED lights 

illuminate for 2 seconds. An alternate 

means of compliance (AMOC) for AD 

2008–20–01 was issued to disregard 

those steps. The manufacturer has 

advised that it is planning to publish a 

revision to Lockheed Service Bulletin 

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

2008. However, we have determined 

that delaying this action until after the 

release of this planned revision is not 

warranted, since sufficient notice of the 

error in Lockheed Service Bulletin 382– 

28–22, Revision 3, dated March 28, 

2008, exists. 

Relevant Service Information 

We have also reviewed Lockheed 

Service Bulletin 382–28–19, Revision 4, 

dated September 18, 2008. That service 

bulletin describes procedures that are 

similar to those in Lockheed Service 

Bulletin 382–28–19, Revision 3, dated 

November 30, 2006 (which was 

referenced in AD 2008–20–01 as a 

source of additional guidance). 

However, Revision 4 of Lockheed 

Service Bulletin 382–28–19 specifies an 

additional inspection area (fuel probes) 

for the dry bay and other areas and 

revises actions. Revision 4 of that 

service bulletin also specifies that for 

airplanes on which the actions 

described in Revision 3 of Lockheed 

Service Bulletin 382–28–19 are done, it 

is necessary to do the additional action 

of inspecting the fuel probes when 

doing the zonal inspection of the dry 

bay areas and other areas and reaccomplish certain inspections of 

certain fuel system electrical wires 

(such as ensuring that generator wire 

bundles are separated from fuel tank 

boundaries, certain wire bundles are 

spot tied with certain lacing braid, and 

that the fuel quantity indication system 

(FQIS) wiring in certain locations is 

routed separately from AC power wires 

and is shielded using the correct 

standard). 

We have also reviewed Lockheed 

Service Bulletin 382–28–20, Revision 

11, dated April 20, 2010. That service 

bulletin describes procedures that are 

similar to Lockheed Service Bulletin 

382–28–20, Revision 5, dated June 19, 

2008 (which was referenced as a source 

of guidance in AD 2008–20–01), for 

installing ground fault interrupters 

(GFIs) and flame arrestors for protection 

of the fuel system. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to develop on 

other airplanes of the same type design. 

For this reason, we are proposing this 

AD, which would supersede AD 2008– 

20–01 and would retain the 

requirements of the existing AD. This 


srobinson on DSKHWCL6B1PROD with PROPOSALS
Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Proposed Rules 487 

proposed AD would also require certain 

actions to be re-accomplished according 

to revised service information described 

previously, except as discussed under 

‘‘Difference Between the Proposed AD 

and the Service Information.’’ 

Difference Between the Proposed AD 

and the Service Information 

Although Lockheed Service Bulletin 

382–28–19, Revision 4, dated September 

18, 2008, describes procedures for 

notifying Lockheed of any discrepancies 

found during inspection, this proposed 

AD would not require that action. 

Explanation of Change to This AD 

We have removed the ‘‘Service 

Bulletin Reference’’ paragraph from this 

NPRM. That paragraph was identified as 

paragraph (f) in AD 2008–20–01. 

Instead, we have provided the full 

service bulletin citations throughout 

this NPRM. 

Explanation of Change to Applicability 

We have revised the NPRM to identify 

the legal name of the manufacturer as 

published in the most recent type 

certificate data sheet for the affected 

airplane models. 

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 proposed AD. The 

average labor rate per hour is $85. The 

costs of the new requirements of this 

proposed 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. 

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 this proposed 

AD 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 

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 

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 that the 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. See the ADDRESSES section 

for a location to examine the regulatory 

evaluation. 


srobinson on DSKHWCL6B1PROD with PROPOSALS
488 Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Proposed Rules 

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 

removing amendment 39–15680 (73 FR 

56464, September 29, 2008) and adding 

the following new AD: 

Lockheed Martin Corporation/Lockheed 

Martin Aeronautics Company: Docket 

No. FAA–2010–1305; Directorate 

Identifier 2010–NM–074–AD. 

Comments Due Date 

(a) The FAA must receive comments on 

this AD action by February 22, 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, 

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. 


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Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Proposed Rules 489 

TABLE 1—MODIFICATIONS AND INITIAL INSPECTIONS—Continued 

Action Additional source of guidance for accomplishing the action 

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 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 (k) 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 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 

Service Bulletin 382–28–20, Revision 8, 

dated October 13, 2009; Revision 9, dated 

December 14, 2009; or Revision 10, dated 

March 18, 2010; is 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. Send information to ATTN: Neil 

Duggan, Aerospace Engineer, Propulsion and 

Services Branch, ACE–118A, FAA, Atlanta 

ACO, 1701 Columbia Avenue, College Park, 

GA 30337; telephone (404) 474–5576; fax 

(404) 474–5606. 

(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) AMOCs approved for AD 2008–20–01 

are approved as AMOCs for this AD. 

Issued in Renton, Washington, on 

December 27, 2010. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–33335 Filed 1–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

Proposed Modification of the 

Minneapolis, MN, Class B Airspace 

Area; Public Meetings 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of meetings. 

SUMMARY: This notice announces four 

fact-finding informal airspace meetings 

to solicit information from airspace 

users and others concerning a proposal 

to revise the Class B airspace area at 

Minneapolis, MN. The purpose of these 

meetings is to provide interested parties 

an opportunity to present views, 


srobinson on DSKHWCL6B1PROD with PROPOSALS