57888 Federal Register / Vol. 69, No. 187 / Tuesday, September 28, 2004 / Proposed Rules 

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

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD):

Dassault Aviation [Formerly Avions Marcel 

Dassault-Breguet Aviation (AMD/BA)]:

Docket No. FAA–2004–19177; 

Directorate Identifier 2002–NM–202–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

must receive comments on this AD action by 

October 28, 2004. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Model Falcon 10 

series airplanes, certificated in any category. 

Unsafe Condition 

(d) This AD was prompted by reports of 

failure of the piston rod of the drag strut 

actuator of the NLG. We are issuing this AD 

to prevent cracking and/or fracture of the 

piston rod of the drag strut actuator of the 

NLG, which could result in a gear-up 

landing, structural damage, and possible 

injury to passengers and crew. 

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. 

Airplane Flight Manual (AFM) Revision 

(f) Within 5 days after the effective date of 

this AD: Revise the Limitations Section of the 

Falcon 10 AFM by incorporating Dassault 

Temporary Change (TC) No. 24 into the AFM. 

That TC provides procedures to the flight 

crew for touchdown using the main landing 

gear to avoid a three-point landing. 

Thereafter, operate the airplane in 

accordance with the limitations specified in 

the AFM revision. 

(g) When the information in TC No. 24 has 

been included in general revisions of the 

AFM, the TC may be removed from the AFM, 

provided the relevant information in the 

general revision is identical to that in TC No. 

24. 

Repetitive Inspections 

(h) Within 7 months after the effective date 

of this AD: Do an ultrasonic inspection of the 

piston rod of the drag strut actuator of the 

NLG for cracks in accordance with Dassault 

Service Bulletin F10–294, dated March 20, 

2002. After the initial inspection has been 

done, the TC required by paragraph (f) of this 

AD may be removed from the AFM. 

(1) If any crack is found, before further 

flight, do the terminating modification 

specified in paragraph (i) of this AD. 

(2) If no crack is found, repeat the 

inspection thereafter at intervals not to 

exceed 700 landings on the drag strut 

actuator.

Terminating Modification 

(i) Accomplishment of the modification of 

the drag strut actuator in accordance with 

Dassault Service Bulletin F10–297, dated 

October 1, 2003, and prior or concurrent 

accomplishment of the related modification 

in accordance with Messier-Hispano-Bugatti 

Service Bulletin 511–32–26, dated November 

9, 1979, ends the repetitive inspections 

required by paragraph (h)(2) of this AD. 

Additional Source of Service Information 

(j) Messier-Dowty Service Bulletin 747721–

32–057, dated February 5, 2003, is referenced 

in Dassault Service Bulletin F10–294 as an 

additional source of service information for 

replacing the drag strut actuator rod. 

Actions Not Required 

(k) Dassault Service Bulletin F10–294 

recommends returning the drag strut actuator 

to the component repair agent for 

replacement if a crack is found, but this AD 

requires doing the terminating modification 

specified in paragraph (i) of this AD. 

(l) Dassault Service Bulletins F10–294 and 

F10–297 recommend submitting certain 

inspection results to the manufacturer. This 

AD does not require those actions. 

Part Installation 

(m) As of the effective date of this AD, no 

person may install on any airplane a drag 

strut actuator having part number 747721. 

Alternative Methods of Compliance 

(AMOCs) 

(n) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

Related Information 

(o) French airworthiness directive 2002–

137(B) dated March 20, 2002, also addresses 

the subject of this AD.

Issued in Renton, Washington, on 

September 17, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–21643 Filed 9–27–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–19176; Directorate 

Identifier 2003–NM–36–AD] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) Model EMB–135 and –145 

Series Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) for all EMBRAER Model 

EMB–135 and –145 series airplanes. 

That AD currently requires repetitive 

inspections of the electrical connectors 

of the electric fuel pumps to detect 

discrepancies, and follow-on corrective 

actions. This proposed AD would 

extend the repetitive intervals for the 

inspections; add new criteria for 

replacing discrepant fuel pumps; add a 

new requirement for applying anticorrosion spray; add a requirement to 

replace all fuel pumps with improved 

fuel pumps; and add repetitive 

inspections after all six fuel pumps are 

replaced. This proposed AD is 

prompted by the manufacturer’s 

development of a new modification that 

addresses the unsafe condition in the 

existing AD. We are proposing this AD 

to prevent an ignition source in the fuel 

tank or adjacent dry bay, which could 

result in fire or explosion.

DATES: We must receive comments on 

this proposed AD by October 28, 2004.

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed AD. 

• DOT Docket Web site: Go to

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street SW, Nassif Building, 

room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street SW, Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

You can get the service information 

identified in this proposed AD from 

Empresa Brasileira de Aeronautica S.A. 

(EMBRAER), P.O. Box 343—CEP 12.225, 

Sao Jose dos Campos—SP, Brazil. 

You may examine the contents of this 

AD docket on the Internet at http://

dms.dot.gov, or at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street 

SW, room PL–401, on the plaza level of 

the Nassif Building, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–1175; 

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: 

Federal Register / Vol. 69, No. 187 / Tuesday, September 28, 2004 / Proposed Rules 57889

Docket Management System (DMS) 

The FAA has implemented new 

procedures for maintaining AD dockets 

electronically. As of May 17, 2004, new 

AD actions are posted on DMS and 

assigned a docket number. We track 

each action and assign a corresponding 

directorate identifier. The DMS AD 

docket number is in the form ‘‘Docket 

No. FAA–2004–99999.’’ The Transport 

Airplane Directorate identifier is in the 

form ‘‘Directorate Identifier 2004–NM–

999–AD.’’ Each DMS AD docket also 

lists the directorate identifier (‘‘Old 

Docket Number’’) as a cross-reference 

for searching purposes. 

Comments Invited 

We invite you to submit any written 

relevant data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–

2004–19176; Directorate Identifier 

2003–NM–36–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the proposed AD. We will 

consider all comments received by the 

closing date and may amend the 

proposed AD in light of those 

comments. 

We will post all comments we 

receive, without change, to http://

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this proposed AD. 

Using the search function of our docket 

web site, anyone can find and read the 

comments in any of our dockets, 

including the name of the individual 

who sent the comment (or signed the 

comment on behalf of an association, 

business, labor union, etc.). You may 

review the DOT’s complete Privacy Act 

Statement in the Federal Register

published on April 11, 2000 (65 FR 

19477–78), or you may visit http://

dms.dot.gov.

We are reviewing the writing style we 

currently use in regulatory documents. 

We are interested in your comments on 

whether the style of this document is 

clear, and your suggestions to improve 

the clarity of our communications that 

affect you. You can get more 

information about plain language at 

http://www.faa.gov/language and http://

www.plainlanguage.gov.

Examining the Docket 

You may examine the AD docket in 

person at the Docket Management 

Facility office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket 

Management Facility office (telephone 

(800) 647–5227) is located on the plaza 

level of the Nassif Building at the DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the DMS 

receives them. 

Discussion 

The FAA has examined the 

underlying safety issues involved in 

recent 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’’ (67 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 another 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. 

Based on this process, 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 8, 2000, we issued AD 

2000–19–02, amendment 39–11903 (65 

FR 56233, September 18, 2000), for all 

EMBRAER Model EMB–135 and –145 

series airplanes. That AD requires 

repetitive inspections of the electrical 

connectors of the electric fuel pumps to 

detect discrepancies, and follow-on 

corrective actions. That AD was 

prompted by a report of damage to the 

pins and elastomeric inserts in the 

hermetically sealed wire connectors of 

the electric fuel pumps located in the 

main wing fuel tanks. We issued that 

AD to prevent failure of the electrical 

connectors or electrical arcing across the 

connector pins of the pump, and 

consequent fuel fire or explosion. 

Actions Since Existing AD Was Issued 

The preamble to AD 2000–19–02 

stated that we considered the 

requirements ‘‘interim action’’ and that 

the manufacturer was developing a 

modification to address the unsafe 

condition. That AD explained that we 

may consider further rulemaking if a 

modification is developed, approved, 

and available. The manufacturer now 

has developed a modification, and we 

have determined that further 

rulemaking is indeed necessary; this 

proposed AD follows from that 

determination.

Relevant Service Information 

EMBRAER has issued Service Bulletin 

145–28–0013, dated April 25, 2001. 

This service bulletin supersedes 

EMBRAER Service Bulletin 145–28–

A013, dated August 16, 2000, which 

was cited in AD 2000–19–02 as the 

appropriate source of service 

information for accomplishing the 

actions required by that AD. 

EMBRAER Service Bulletin 145–28–

0013 describes procedures for: 

• Repetitive inspections of the 

electrical connectors of the fuel pumps 

to detect discrepancies such as 

corrosion, surface irregularities, 

damaged plating, blackened pins, 

damaged elastomeric inserts, cracks, 

erosion, or charring of the connector. 

• Applying anti-corrosion spray on 

the male contacts of the fuel pump 

electrical connectors if no discrepancy 

is found. 

• Replacing the fuel pumps with new, 

improved fuel pumps (with gold-plated 

connectors), and a follow-on inspection 

57890 Federal Register / Vol. 69, No. 187 / Tuesday, September 28, 2004 / Proposed Rules 

of the mating aircraft connectors, if any 

discrepancy is found. 

• Replacing only the socket contacts 

with new contacts having the same part 

number if no damage is found to the 

mating aircraft connectors; or replacing 

the affected connector with a new 

connector having the same part number 

if any damage is found to the mating 

aircraft connectors; and applying anticorrosion spray on the male contacts of 

the electrical connectors for the new, 

improved fuel pumps. 

The Departmento de Aviacao Civil 

(DAC) mandated the service bulletin 

and issued Brazilian airworthiness 

directive 2000–08–01R2, dated February 

13, 2002, to ensure the continued 

airworthiness of these airplanes in 

Brazil. 

FAA’s Determination and Requirements 

of the Proposed AD 

These airplane models are 

manufactured in Brazil and are type 

certificated for operation in the United 

States under the provisions of section 

21.29 of the Federal Aviation 

Regulations (14 CFR 21.29) and the 

applicable bilateral airworthiness 

agreement. Pursuant to this bilateral 

airworthiness agreement, the DAC has 

kept the FAA informed of the situation 

described above. We have examined the 

DAC’s findings, evaluated all pertinent 

information, and determined that AD 

action is necessary for airplanes of this 

type design that are certificated for 

operation in the United States. 

Therefore, we are proposing this AD, 

which would supersede AD 2000–19–02 

to continue to require repetitive 

inspections of the electrical connectors 

of the electric fuel pumps to detect 

discrepancies, and follow-on corrective 

actions. This proposed AD would also 

extend the repetitive intervals for the 

inspections; add new criteria for 

replacing discrepant fuel pumps, add a 

new requirement for applying anticorrosion spray; add a requirement to 

replace all fuel pumps with improved 

fuel pumps; and add repetitive 

inspections after all six pumps are 

replaced. The proposed AD would 

require you to use the service 

information described previously to 

perform these actions, except as 

discussed under ‘‘Differences Among 

the Proposed AD, the Service Bulletin, 

and the Brazilian Airworthiness 

Directive.’’

Differences Among the Proposed AD, 

the Service Bulletin, and the Brazilian 

Airworthiness Directive 

The service bulletin states that you 

may replace the fuel pumps with 

electric fuel pumps that have part 

number (P/N) 2C7–1, but this proposed 

AD would require you to replace them 

with fuel pumps that have P/N 2C7–4. 

The Brazilian airworthiness directive 

does not give a time for replacing all six 

fuel pumps, but this proposed AD 

would require you to replace all six fuel 

pumps with new, improved pumps 

within 8,000 flight hours after the 

effective date of the proposed AD. 

We have coordinated these 

differences with the DAC. 

Changes to Existing AD 

This proposed AD would retain all 

requirements of AD 2000–19–02. Since 

AD 2000–19–02 was issued, the AD 

format has been revised, and certain 

paragraphs have been rearranged. As a 

result, the corresponding paragraph 

identifiers have changed in this 

proposed AD, as listed in the following 

table:

REVISED PARAGRAPH IDENTIFIERS

Requirement in AD 

2000–19–02 

Corresponding

requirement in this

proposed AD 

Paragraph (a) ............ Paragraph (f). 

Paragraph (b) ............ Paragraph (n). 

Paragraph (c) ............ Paragraph (g). 

Paragraph (d) ............ Paragraph (h). 

We have also included a definition of 

‘‘general visual inspection,’’ which was 

not included in the existing AD. This 

definition is in Note 1 of the proposed 

AD. 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this proposed AD.

ESTIMATED COSTS

Action Work hours 

Average 

labor rate 

per hour 

Parts Cost per airplane 

Number of 

U.S.- registered airplanes 

Fleet cost 

Inspections (required by AD 

2000–19–02).

1 per inspection cycle.$65 None ...... $65 per inspection ....... 290 $18,850 per inspection 

cycle. 

Repetitive inspections (new 

proposed action).

1 per inspection cycle.65 None ...... $65 per inspection 

cycle.

290 $18,850 per inspection 

cycle. 

Replacing the fuel pump 

(new proposed action).

1 per pump 

(6 per airplane).

65 Free ....... $390 ............................. 290 $113,100. 

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. 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, 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:

Federal Register / Vol. 69, No. 187 / Tuesday, September 28, 2004 / Proposed Rules 57891

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

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by 

removing amendment 39–11903 (65 FR 

56233, September 18, 2000) and adding 

the following new airworthiness 

directive (AD):

Empresa Brasileira de Aeronautica S.A. 

(EMBRAER): Docket No. FAA–2004–

19176; Directorate Identifier 2003–NM–

36–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

must receive comments on this AD action by 

October 28, 2004. 

Affected ADs 

(b) This AD supersedes AD 2000–19–02, 

amendment 39–11903. 

Applicability 

(c) This AD applies to all EMBRAER Model 

EMB–135 and –145 series airplanes, 

certificated in any category. 

Unsafe Condition 

(d) This AD was prompted by the 

manufacturer’s development of a new 

modification that addresses the unsafe 

condition in the AD 2000–19–02. We are 

issuing this AD to prevent an ignition source 

in the fuel tank or adjacent dry bay, which 

could result in fire or explosion. 

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 the Requirements of AD 

2000–19–02

Repetitive Inspections 

(f) Perform a general visual inspection of 

the electrical connectors of the fuel pumps in 

the right- and left-hand wings to detect 

discrepancies (including blackened 

connector pins, damage to electrometric 

insert, cracks, erosion, or charring), in 

accordance with EMBRAER Alert Service 

Bulletin S.B. 145–28–A013, dated August 16, 

2000, at the times specified in paragraphs 

(f)(1), (f)(2), and (f)(3) of this AD, as 

applicable. Repeat the inspection thereafter 

at intervals not to exceed 400 flight hours 

until the inspection required by paragraph (i) 

of this AD is done. 

(1) For airplanes having 1,200 total flight 

hours or less as of October 3, 2000 (the 

effective date of AD 2000–19–02, amendment 

39–11903): Prior to the accumulation of 1,600 

total flight hours. 

(2) For airplanes having more than 1,200 

total flight hours, but less than 4,000 total 

flight hours, as of October 3, 2000: Within 

400 flight hours after October 3, 2000. 

(3) For airplanes having 4,000 total flight 

hours or more as of October 3, 2000: Prior to 

the accumulation of 4,400 total flight hours, 

or within 50 flight hours after October 3, 

2000, whichever occurs later.

Note 1: For the purposes of this AD, a 

general visual inspection is ‘‘a visual 

examination of a 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 normal available 

lighting conditions such as daylight, hangar 

lighting, flashlight or drop-light 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.’’

Follow-On Corrective Actions 

(g) If any discrepancy (including blackened 

connector pins, damage to electrometric 

insert, cracks, erosion, or charring) is 

detected after accomplishment of any 

inspection required by paragraph (f) of this 

AD: Before further flight, replace the fuel 

pump and its mating airplane connector in 

accordance with EMBRAER Alert Service 

Bulletin S.B. 145–28–A013, dated August 16, 

2000. 

(h) After accomplishment of the 

replacement required by paragraph (g) of this 

AD, before further flight: Perform a general 

visual inspection of the electrical connectors 

adjacent to the fuel pump to detect damage 

(visible cracks, erosion, or charring), in 

accordance with EMBRAER Alert Service 

Bulletin S.B. 145–28–A013, dated August 16, 

2000, and accomplish the requirements in 

paragraph (h)(1) or (h)(2) of this AD, as 

applicable. 

(1) If any damage is detected, before further 

flight, replace the connectors with new ones 

in accordance with the alert service bulletin. 

(2) If no damage is detected, before further 

flight, replace only the socket contacts with 

new contacts in accordance with the alert 

service bulletin. 

New Requirements of This AD 

Inspections 

(i) Do a general visual inspection of the 

electrical connectors of the fuel pumps in the 

right- and left-hand wings to detect 

discrepancies (including any corrosion, 

surface irregularities, damaged plating, 

blackened pins, damaged elastomeric inserts, 

cracks, erosion, or charring of the connector). 

Do the first inspection at the applicable time 

in paragraph (i)(1) or (i)(2) of this AD, in 

accordance with Part I of the 

Accomplishment Instructions of EMBRAER 

Service Bulletin 145–28–0013, dated April 

25, 2001. Repeat the inspection thereafter at 

intervals not to exceed 1,200 flight hours 

until all six fuel pumps are replaced in 

accordance with paragraph (k) or (l) of this 

AD. When all six fuel pumps have been 

replaced in accordance with paragraph (k) or 

(l) of this AD, repeat the inspection thereafter 

at intervals not to exceed 8,000 flight hours. 

Doing the inspection required by this 

paragraph terminates the repetitive 

inspections required by paragraph (f) of this 

AD. 

(1) For airplanes that have been inspected 

in accordance with paragraph (f) of this AD 

as of the effective date of this AD: Within 

1,200 flight hours since the most recent 

inspection done in accordance with 

paragraph (f) of this AD.

(2) For airplanes that have not been 

inspected in accordance with paragraph (f) of 

this AD as of the effective date of this AD: 

Within 1,200 flight hours after the effective 

date of this AD. 

Corrective Action if No Discrepancy Is Found 

(j) If there is no evidence of a discrepancy 

found during any inspection required by 

paragraph (i) of this AD: Before further flight, 

apply anti-corrosion spray on the male 

contacts of the fuel pump electrical 

connectors in accordance with the 

Accomplishment Instructions of EMBRAER 

Service Bulletin 145–28–0013, dated April 

25, 2001. 

Replacement if Any Discrepancy Is Found 

(k) If any evidence of a discrepancy is 

found during any inspection required by 

paragraph (i) of this AD: Before further flight, 

replace the electric fuel pump with a new 

electric fuel pump that has part number (P/

N) 2C7–4, in accordance with the 

Accomplishment Instructions of EMBRAER 

Service Bulletin 145–28–0013, dated April 

25, 2001. After the replacement, repeat the 

inspection required by paragraph (i) of this 

AD at the applicable interval in that 

paragraph. 

Replacement 

(l) Within 8,000 flight hours after the 

effective date of this AD, replace any electric 

fuel pump that has not been replaced in 

accordance with paragraph (k) of this AD 

with a new electric fuel pump that has part 

number (P/N) 2C7–4, in accordance with the 

Accomplishment Instructions of EMBRAER 

Service Bulletin 145–28–0013, dated April 

25, 2001. After the replacement, repeat the 

inspection required by paragraph (i) of this 

AD at intervals not to exceed 8,000 flight 

hours. 

Inspection and Corrective Actions 

(m) Before further flight after replacing a 

fuel pump, as required by paragraph (k) and 

(l) of this AD: Do a general visual inspection 

for damage of the mating aircraft connectors; 

and do the applicable corrective action in 

paragraph (m)(1) or (m)(2) of this AD; in 

accordance with the Accomplishment 

Instructions of EMBRAER Service Bulletin 

145–28–0013, dated April 25, 2001. 

(1) If there is any sign of damage to the 

mating aircraft connectors: Replace the 

affected connector with a new connector, and 

apply anti-corrosion spray on the male 

contacts of the fuel pump electric connectors. 

(2) If there is no sign of damage to the 

mating aircraft connectors: Replace only the 

socket contacts with new socket contacts, 

and apply anti-corrosion spray on the male 

contacts of the fuel pump electric connectors. 

Master Minimum Equipment List (MMEL) 

(n) The inspections required by paragraphs 

(f) and (i) of this AD apply to the six electric 

fuel pumps in the right- and left-hand wings 

(three pumps in each wing). For pump 

replacement planning purposes, the airplane 

may be operated in accordance with the 

provisions and limitations specified in an 

operator’s FAA-approved MMEL, provided 

57892 Federal Register / Vol. 69, No. 187 / Tuesday, September 28, 2004 / Proposed Rules 

that no more than one fuel pump on each 

wing on the airplane is inoperative.

Note 2: When operating under the MMEL, 

operators must comply with the unusable 

fuel quantity as referenced in the Limitations 

Section of the appropriate FAA-approved 

Airplane Flight Manual (AFM).

Parts Installation 

(o) As of the effective date of this AD, no 

person may install a fuel pump, P/N 2C7–1, 

on any airplane. 

Alternative Methods of Compliance (AMOCs) 

(p)(1) 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. 

(2) Alternative methods of compliance, 

approved previously per AD 2000–19–02, 

amendment 39–11903, are not approved as 

alternative methods of compliance with this 

AD. 

Related Information 

(q) Brazilian airworthiness directive 2000–

08–01R2, dated February 13, 2002, also 

addresses the subject of this AD.

Issued in Renton, Washington, on 

September 20, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–21644 Filed 9–27–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NM–182–AD] 

RIN 2120–AA64 

Airworthiness Directives; Saab Model 

SAAB SF340A and SAAB 340B Series 

Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Supplemental notice of 

proposed rulemaking; reopening of 

comment period. 

SUMMARY: This document revises an 

earlier proposed airworthiness directive 

(AD), applicable to certain Saab Model 

SAAB SF340A and SAAB 340B series 

airplanes, that would have required 

replacement of the retract actuator 

bracket attachment bolt (RABAB) of the 

main landing gear (MLG) with a new 

RABAB, and reidentification of the MLG 

shock strut. This new action revises the 

proposed rule by referencing new 

service information; and by adding an 

inspection for corrosion, fretting, or 

other damage of any RABAB installed in 

accordance with the old service 

information; and applicable corrective 

actions. The actions specified by this 

new proposed AD are intended to 

prevent failure of the RABAB, which 

could result in loosening of the actuator 

bracket and consequent failure of the 

MLG to retract, with considerable 

damage to other landing gear parts, 

including the MLG trunnion fitting. 

This action is intended to address the 

identified unsafe condition.

DATES: Comments must be received by 

October 25, 2004.

ADDRESSES: Submit comments in 

triplicate to the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, ANM–114, 

Attention: Rules Docket No. 2002–NM–

182–AD, 1601 Lind Avenue, SW., 

Renton, Washington 98055–4056. 

Comments may be inspected at this 

location between 9 a.m. and 3 p.m., 

Monday through Friday, except Federal 

holidays. Comments may be submitted 

via fax to (425) 227–1232. Comments 

may also be sent via the Internet using 

the following address: 9-anmnprmcomment@faa.gov. Comments sent 

via fax or the Internet must contain 

‘‘Docket No. 2002–NM–182–AD’’ in the 

subject line and need not be submitted 

in triplicate. Comments sent via the 

Internet as attached electronic files must 

be formatted in Microsoft Word 97 or 

2000 or ASCII text. 

The service information referenced in 

the proposed rule may be obtained from 

Saab Aircraft AB, SAAB Aircraft 

Product Support, S–581.88, Link’’ping, 

Sweden. This information may be 

examined at the FAA, Transport 

Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer; 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2125; 

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: 

Comments Invited 

Interested persons are invited to 

participate in the making of the 

proposed rule by submitting such 

written data, views, or arguments as 

they may desire. Communications shall 

identify the Rules Docket number and 

be submitted in triplicate to the address 

specified above. All communications 

received on or before the closing date 

for comments, specified above, will be 

considered before taking action on the 

proposed rule. The proposals contained 

in this action may be changed in light 

of the comments received. 

Submit comments using the following 

format: 

• Organize comments issue-by-issue. 

For example, discuss a request to 

change the compliance time and a 

request to change the service bulletin 

reference as two separate issues. 

• For each issue, state what specific 

change to the proposed AD is being 

requested. 

• Include justification (e.g., reasons or 

data) for each request. 

Comments are specifically invited on 

the overall regulatory, economic, 

environmental, and energy aspects of 

the proposed rule. All comments 

submitted will be available, both before 

and after the closing date for comments, 

in the Rules Docket for examination by 

interested persons. A report 

summarizing each FAA-public contact 

concerned with the substance of this 

proposal will be filed in the Rules 

Docket. 

Commenters wishing the FAA to 

acknowledge receipt of their comments 

submitted in response to this action 

must submit a self-addressed, stamped 

postcard on which the following 

statement is made: ‘‘Comments to 

Docket Number 2002–NM–182–AD.’’

The postcard will be date stamped and 

returned to the commenter. 

Availability of NPRMs 

Any person may obtain a copy of this 

NPRM by submitting a request to the 

FAA, Transport Airplane Directorate, 

ANM–114, Attention: Rules Docket No. 

2002–NM–182–AD, 1601 Lind Avenue, 

SW., Renton, Washington 98055–4056. 

Discussion 

A proposal to amend part 39 of the 

Federal Aviation Regulations (14 CFR 

part 39) to add an airworthiness 

directive (AD), applicable to certain 

Saab Model SAAB SF340A and SAAB 

340B series airplanes, was published as 

a notice of proposed rulemaking 

(NPRM) in the Federal Register on April 

15, 2004 (69 FR 19952). That NPRM 

would have required replacement of the 

retract actuator bracket attachment bolt 

(RABAB) of the main landing gear 

(MLG) with a new RABAB, and 

reidentification of the MLG shock strut. 

That NPRM was prompted by reports of 

failures of the RABAB of the MLG due 

to hydrogen embrittlement. This can be 

caused by failure to fully de-embrittle 

after electroplating the RABAB during 

manufacture. That condition, if not 

corrected, could result in loosening of 

the retract actuator bracket and 

consequent failure of the MLG to retract, 

with considerable damage to other 

landing gear parts, including the MLG 

trunnion fitting.