56098 Federal Register / Vol. 74, No. 209 / Friday, October 30, 2009 / Rules and Regulations 

participation in the Program and may 

restrict further sales under the Program 

until SBA determines that the Seller has 

provided sufficient documentation. 

§ 120.1721 SBA’s right to investigate. 

SBA may undertake such 

investigation as it deems necessary to 

determine whether it is entitled to seek 

recovery from the Seller and Seller 

agrees to take whatever actions are 

necessary to facilitate such 

investigation. 

§ 120.1722 SBA’s offset rights. 

SBA shall have the right to offset any 

amount owed by Lender to SBA, 

including, without limitation, an offset 

against CSA’s obligation to pay Lender 

pursuant to any Section 504 First 

Mortgage Loan Pool Guarantee 

Agreement. 

§ 120.1723 Pool Loan receivables received 

by Seller. 

Any Pool Loan Receivables received 

by Seller in connection with obligations 

under Seller’s Pool Loan must be 

forwarded by Seller to CSA within two 

business days of receipt of collected 

funds. 

§ 120.1724 Servicing and liquidation 

expenses. 

All ordinary and reasonable expenses 

of servicing and liquidating Seller’s Pool 

Loan shall be paid by, or be recoverable 

from, Obligor, and all such ordinary and 

reasonable expenses incurred by Seller 

or SBA which are not recoverable from 

Obligor shall be shared ratably by Seller, 

SBA, and the Pool Originator pursuant 

to the applicable percentages set forth in 

the First Lien Position 504 Loan Pool 

Guarantee Agreement. 

§ 120.1725 No Program Preference by 

Seller or Pool Originator. 

The Seller and the Pool Originator 

must not establish a Program Preference, 

which is defined in 13 CFR 120.10. 

§ 120.1726 Pool Certificates a Seller 

cannot purchase. 

Neither a Seller, nor any of its 

Program Associates or Affiliates, may 

purchase a Pool Certificate that is 

backed by a Loan Interest in a Pool Loan 

that the Seller, or any of its Program 

Associates or Affiliates, originated or 

owned, and, in the event such purchase 

occurs, SBA’s guarantee shall not be in 

effect with respect to any such Pool 

Certificate. 

Dated: October 26, 2009. 

Karen G. Mills, 

Administrator. 

[FR Doc. E9–26211 Filed 10–28–09; 11:15 

am] 

BILLING CODE 8025–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1000; Directorate 

Identifier 2009–NM–164–AD; Amendment 

39–16070; AD 2008–10–07 R1] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–200C, 747–200F, 

747–300, 747SR, and 747SP Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is revising an 

existing airworthiness directive (AD), 

which applies to all Boeing Model 747– 

100, 747–100B, 747–100B SUD, 747– 

200B, 747–200C, 747–200F, 747–300, 

747SR, and 747SP series airplanes. That 

AD currently requires revising the FAAapproved maintenance program by 

incorporating new airworthiness 

limitations (AWLs) for fuel tank systems 

to satisfy Special Federal Aviation 

Regulation No. 88 requirements. That 

AD also requires the initial inspection of 

certain repetitive AWL inspections to 

phase in those inspections, and repair if 

necessary. This AD clarifies the 

intended effect of the AD on spare and 

on-airplane fuel tank system 

components. This AD results from a 

design review of the fuel tank systems. 

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 November 

16, 2009. 

On June 12, 2008 (73 FR 25977, May 

8, 2008), the Director of the Federal 

Register approved the incorporation by 

reference of a certain publication listed 

in the AD. 

We must receive any comments on 

this AD by December 14, 2009. 

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 AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. 

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 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: 

Douglas Bryant, Aerospace Engineer, 

Propulsion Branch, ANM–140S, Seattle 

Aircraft Certification Office, FAA, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6505; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On April 28, 2008, we issued AD 

2008–10–07, amendment 39–15513 (73 

FR 25977, May 8, 2008). That AD 

applies to all Boeing Model 747–100, 

747–100B, 747–100B SUD, 747–200B, 

747–200C, 747–200F, 747–300, 747SR, 

and 747SP series airplanes. That AD 

requires revising the FAA-approved 

maintenance program by incorporating 

new airworthiness limitations (AWLs) 

for fuel tank systems to satisfy Special 

Federal Aviation Regulation No. 88 

requirements. That AD also requires the 

initial inspection of certain repetitive 

AWL inspections to phase in those 

inspections, and repair if necessary. 

That AD resulted from a design review 

of the fuel tank systems. The actions 

specified in that AD are intended 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 


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Federal Register / Vol. 74, No. 209 / Friday, October 30, 2009 / Rules and Regulations 56099 

explosion and consequent loss of the 

airplane. 

Critical design configuration control 

limitations (CDCCLs) are limitation 

requirements to preserve a critical 

ignition source prevention feature of the 

fuel tank system design that is necessary 

to prevent the occurrence of an unsafe 

condition. The purpose of a CDCCL is 

to provide instruction to retain the 

critical ignition source prevention 

feature during configuration change that 

may be caused by alterations, repairs, or 

maintenance actions. A CDCCL is not a 

periodic inspection. 

Actions Since AD Was Issued 

Since we issued that AD, we have 

determined that it is necessary to clarify 

the AD’s intended effect on spare and 

on-airplane fuel tank system 

components, regarding the use of 

maintenance manuals and instructions 

for continued airworthiness. 

Section 91.403(c) of the Federal 

Aviation Regulations (14 CFR 91.403(c) 

specifies the following: 

No person may operate an aircraft for 

which a manufacturer’s maintenance manual 

or instructions for continued airworthiness 

has been issued that contains an 

airworthiness limitation section unless the 

mandatory * * * procedures * * * have 

been complied with. 

Some operators have questioned 

whether existing components affected 

by the new CDCCLs must be reworked. 

We did not intend for the AD to 

retroactively require rework of 

components that had been maintained 

using acceptable methods before the 

effective date of the AD. Owners and 

operators of the affected airplanes 

therefore are not required to rework 

affected components identified as 

airworthy or installed on the affected 

airplanes before the required revisions 

of the FAA-approved maintenance 

program. But once the CDCCLs are 

incorporated into the FAA-approved 

maintenance program, future 

maintenance actions on components 

must be done in accordance with those 

CDCCLs. 

FAA’s Determination and Requirements 

of This AD 

The unsafe condition described 

previously is likely to exist or develop 

on other airplanes of the same type 

design. For this reason, we are issuing 

this AD to revise AD 2008–10–07. This 

new AD retains the requirements of the 

existing AD, and adds a new note to 

clarify the intended effect of the AD on 

spare and on-airplane fuel tank system 

components. 

Explanation of Additional Change to 

AD 

AD 2008–10–07 allowed the use of 

alternative inspections, inspection 

intervals, and CDCCLs if they are part of 

a later revision of the Boeing 747–100/ 

200/300/SP Airworthiness Limitations 

(AWLs) and Certification Maintenance 

Requirements (CMRs), D6–13747–CMR, 

Revision March 2008. AD 2008–10–07 

also allowed use of later revisions of 

Boeing 747–100/200/300/SP 

Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs), D6–13747–CMR, Revision 

March 2008. Those provisions have 

been removed from this AD. Allowing 

the use of ‘‘a later revision’’ of a specific 

service document violates Office of the 

Federal Register policies for approving 

materials that are incorporated by 

reference. Affected operators, however, 

may request approval to use an 

alternative inspection, inspection 

interval, or CDCCL that is part of a later 

revision of the referenced service 

document as an alternative method of 

compliance, under the provisions of 

paragraph (k) of this AD. 

Costs of Compliance 

This revision imposes no additional 

economic burden. The current costs for 

this AD are repeated for the 

convenience of affected operators, as 

follows: 

There are about 308 airplanes of the 

affected design in the worldwide fleet. 

The following table provides the 

estimated costs, at an average labor rate 

of $80 per work hour, for U.S. operators 

to comply with this AD. 

ESTIMATED COSTS

Action Work hours Parts Cost per 

airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Maintenance program revision .............................................. 8 None ............ $640 93 $59,520 

Inspections ............................................................................ 8 None ............ 640 93 59,520 

FAA’s Justification and Determination 

of the Effective Date 

This revision merely clarifies the 

intended effect on spare and on-airplane 

fuel tank system components, and 

makes no substantive change to the 

AD’s requirements. For this reason, it is 

found that notice and opportunity for 

prior public comment for this action are 

unnecessary, and good cause exists for 

making this amendment effective in less 

than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments before it becomes effective. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2009–1000; Directorate Identifier 2009– 

NM–164–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this AD. We will consider all 

comments received by the closing date 

and may amend this 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 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 


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56100 Federal Register / Vol. 74, No. 209 / Friday, October 30, 2009 / Rules and Regulations 

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 the 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 AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

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 part 39 of the Federal 

Aviation Regulations (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 39–15513 (73 FR 

25977, May 8, 2008) and adding the 

following new AD: 

2008–10–07 R1 Boeing: Amendment 39– 

16070. Docket No. FAA–2009–1000; 

Directorate Identifier 2009–NM–164–AD. 

Effective Date 

(a) This airworthiness directive (AD) is 

effective November 16, 2009. 

Affected ADs 

(b) This AD revises AD 2008–10–07. 

Applicability 

(c) This AD applies to all Boeing Model 

747–100, 747–100B, 747–100B SUD, 747– 

200B, 747–200C, 747–200F, 747–300, 747SR, 

and 747SP series 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 (AMOC) 

according to paragraph (k) 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. 

Unsafe Condition 

(d) This AD results from a design review 

of the fuel tank systems. 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. 

Compliance 

(e) 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 AD 2008–10–07 With 

Changes to Compliance Method: Service 

Information Reference 

(f) The term ‘‘Revision March 2008 of 

Document D6–13747–CMR,’’ as used in this 

AD, means Boeing 747–100/200/300/SP 

Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs), D6–13747–CMR, Revision March 

2008. (For the purposes of Revision March 

2008 of Document D6–13747–CMR, the 

Model 747SR series airplane is basically a 

Model 747–100 series airplane with certain 

modifications to improve fatigue life.) 

Maintenance Program Revision 

(g) Before December 16, 2008, revise the 

FAA-approved maintenance program to 

incorporate the information in Section D, 

‘‘AIRWORTHINESS LIMITATIONS— 

SYSTEMS,’’ AWLs No. 28–AWL–01 through 

No. 28–AWL–19 inclusive, of Revision 

March 2008 of Document D6–13747–CMR; 

except that the initial inspections required by 

paragraph (h) of this AD must be done at the 

applicable compliance time specified in that 

paragraph. As an optional action, AWLs No. 

28–AWL–20 through No. 28–AWL–23 

inclusive, as identified in Section D of 

Revision March 2008 of Document D6– 

13747–CMR, also may be incorporated into 

the FAA-approved maintenance program. 

Initial Inspections and Repair if Necessary 

(h) Do the inspections specified in Table 1 

of this AD at the compliance time specified 

in Table 1 of this AD, and repair any 

discrepancy, in accordance with Section D of 

Revision March 2008 of Document D6– 

13747–CMR. The repair must be done before 

further flight. Accomplishing the inspections 

identified in Table 1 of this AD as part of an 

FAA-approved maintenance program before 

the applicable compliance time specified in 

Table 1 of this AD constitutes compliance 

with the requirements of this paragraph. 

Note 2: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’ 

Note 3: For the purposes of this AD, a 

special detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. The examination is likely to 

make extensive use of specialized inspection 

techniques and/or equipment. Intricate 

cleaning and substantial access or 

disassembly procedure may be required.’’ 

TABLE 1—INITIAL INSPECTIONS

AWL No. Description 

Compliance time 

(whichever occurs later) 

Threshold Grace period 

28–AWL–01 ....... A detailed inspection of external wires 

over the center fuel tank for damaged 

clamps, wire chafing, and wire bundles in contact with the surface of the 

center fuel tank.

Within 144 months since the date of 

issuance of the original standard airworthiness certificate or the date of 

issuance of the original export certificate of airworthiness.

Within 72 months after June 12, 2008 

(the effective date of AD 2008–10– 

07). 


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Federal Register / Vol. 74, No. 209 / Friday, October 30, 2009 / Rules and Regulations 56101 

TABLE 1—INITIAL INSPECTIONS—Continued 

AWL No. Description 

Compliance time 

(whichever occurs later) 

Threshold Grace period 

28–AWL–03 ....... A special detailed inspection of the 

lightning shield to ground termination 

on the out-of-tank fuel quantity indicating system to verify functional integrity.

Within 144 months since the date of 

issuance of the original standard airworthiness certificate or the date of 

issuance of the original export certificate of airworthiness.

Within 24 months after June 12, 2008. 

28–AWL–13 ....... A special detailed inspection of the fault 

current bond of the fueling shutoff 

valve actuator of the center wing tank 

to verify electrical bond.

Within 144 months since the date of 

issuance of the original standard airworthiness certificate or the date of 

issuance of the original export certificate of airworthiness.

Within 60 months after June 12, 2008. 

No Alternative Inspections, Inspection 

Intervals, or Critical Design Configuration 

Control Limitations (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 AMOC in accordance with 

the procedures specified in paragraph (k) of 

this AD. 

Credit for Actions Done According to 

Previous Revisions of the Service 

Information 

(j) Actions done before the June 12, 2008, 

in accordance with Boeing 747–100/200/300/ 

SP Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs), D6–13747–CMR, Revision March 

2006; Revision May 2006; Revision December 

2006; Revision January 2007; Revision 

September 2007; or Revision January 2008; 

are acceptable for compliance with the 

corresponding requirements of paragraphs (g) 

and (h) of this AD. 

New Information 

Explanation of CDCCL Requirements 

Note 4: Notwithstanding any other 

maintenance or operational requirements, 

components that have been identified as 

airworthy or installed on the affected 

airplanes before the revision of the FAAapproved maintenance program, as required 

by paragraph (g) of this AD, do not need to 

be reworked in accordance with the CDCCLs. 

However, once the FAA-approved 

maintenance program has been revised, 

future maintenance actions on these 

components must be done, in accordance 

with the CDCCLs. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. Send information to ATTN: 

Douglas Bryant, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

ACO, FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

917–6505; fax (425) 917–6590. Or, e-mail 

information to 9-ANM-Seattle-ACO-AMOCRequests-faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

Material Incorporated by Reference 

(l) You must use Boeing 747–100/200/300/ 

SP Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs), D6–13747–CMR, Revision March 

2008, to do the actions required by this AD, 

unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

previously approved the incorporation by 

reference of Boeing 747–100/200/300/SP 

Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs), D6–13747–CMR, Revision March 

2008, on June 12, 2008 (73 FR 25977, May 

8, 2008). 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; e-mail me.boecom@boeing.com; 

Internet https://www.myboeingfleet.com. 

(3) You may review copies of the 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 or 425–227–1152. 

(4) 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 NARA, 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 October 

22, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–26123 Filed 10–29–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1001; Directorate 

Identifier 2009–NM–166–AD; Amendment 

39–16071; AD 2008–04–18 R1] 

RIN 2120–AA64 

Airworthiness Directives; EMBRAER 

Model EMB–120, –120ER, –120FC, 

–120QC, and –120RT Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above that would revise 

an existing AD. This AD results from 

mandatory continuing airworthiness 

information (MCAI) originated by an 

aviation authority of another country to 

identify and correct an unsafe condition 

on an aviation product. The MCAI 

describes the unsafe condition as: 

It has been found that former revisions of 

the Maintenance Review Board Report 

(MRBR) of the EMB–120( ) aircraft do not 

fully comply with some Critical Design 

Configuration Control Limitations (CDCCL) 

and Fuel System Limitations (FSL). These 

limitations are necessary to preclude ignition 

sources in the fuel system, as required by 

RBHA–E88/SFAR–88 (Special Federal 

Aviation Regulation No. 88). 

* * * * * 


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