Federal Register / Vol. 73, No. 168 / Thursday, August 28, 2008 / Rules and Regulations 50711 

A320–25–1248, Revision 01, dated April 16, 

2003; as applicable. 

(1) For all airplanes: Modify the shelf (floor 

panel) above ADIRU 3 by installing shims 

between the shelf and the webs of the shelf 

support structure. 

(2) For airplanes with Airbus Modification 

25900P3941 or Airbus Service Bulletin 

A320–25–1200 accomplished as of January 

27, 2004: Modify the polycarbonate guard 

(umbrella) protecting the ADIRUs by 

installing shims between the guard and the 

shelf support structure. 

(3) For airplanes with Airbus Modification 

23027P2852 or Airbus Service Bulletin 

A320–52–1038 accomplished as of January 

27, 2004: Modify the ladder located in the 

avionics compartment by machining the slot 

at the foot of the ladder to increase the depth 

by 0.236 inch. 

New Requirements of This AD 

Modification for Certain Airplanes 

(g) For all airplanes equipped with any 

ADIRU installed in accordance with Airbus 

Modification 31070, 31742, or 35517, except 

airplanes on which Airbus Modification 

30650 or 30872 has been accomplished in 

production: Within 46 months after the 

effective date of this AD, modify the ADIRU 

shelf supports by accomplishing all of the 

applicable actions specified in the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–25–1248, Revision 01, 

dated April 16, 2003. 

Replacement of ADIRUs 

(h) For all airplanes except those on which 

Airbus Modification 35517 has been 

incorporated in production: Within 46 

months after the effective date of this AD, 

replace all three ADIRUs with improved 

ADIRUs having P/N 465020–0303–0316 in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320–

34–1350, dated March 20, 2006; or Airbus 

Service Bulletin A320–34–1350, Revision 01, 

dated December 12, 2007. 

Alternative Methods of Compliance 

(AMOCs) 

(i) 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 Tim Dulin, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057–

3356; telephone (425) 227–2141; fax (425) 

227–1149. Before using any approved AMOC 

on any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

Related Information 

(j) European Aviation Safety Agency 

airworthiness directive 2007–0217, dated 

August 9, 2007, also addresses the subject of 

this AD. 

Material Incorporated by Reference 

(k) You must use service information 

identified in Table 1 of this AD, as 

applicable, to perform the actions that are 

required by this AD, unless the AD specifies 

otherwise. 

TABLE 1—ALL MATERIAL INCORPORATED BY REFERENCE

Service bulletin Revision level Date 

Airbus Service Bulletin A320–25–1248 ........................................................................................... Original ...................... February 16, 2001. 

Airbus Service Bulletin A320–25–1248 ........................................................................................... 01 .............................. April 16, 2003. 

Airbus Service Bulletin A320–34–1350 ........................................................................................... Original ...................... March 20, 2006. 

Airbus Service Bulletin A320–34–1350 ........................................................................................... 01 .............................. December 12, 2007. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the documents identified in Table 2 of this 

AD in accordance with 5 U.S.C. 552(a) and 

1 CFR part 51. 

TABLE 2—NEW MATERIAL INCORPORATED BY REFERENCE

Service bulletin Revision level Date 

Airbus Service Bulletin A320–25–1248 ........................................................................................... 01 .............................. April 16, 2003. 

Airbus Service Bulletin A320–34–1350 ........................................................................................... Original ...................... March 20, 2006. 

Airbus Service Bulletin A320–34–1350 ........................................................................................... 01 .............................. December 12, 2007. 

(2) On January 27, 2004 (68 FR 74172, 

December 23, 2003), the Director of the 

Federal Register approved the incorporation 

by reference of Airbus Service Bulletin 

A320–25–1248, dated February 16, 2001. 

(3) Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, for a 

copy of this service information. You may 

review copies at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington; or 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/ 

cfr/ibr-locations.html. 

Issued in Renton, Washington, on August 

6, 2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–19138 Filed 8–27–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27785; Directorate 

Identifier 2006–NM–267–AD; Amendment 

39–15649; AD 2008–17–11] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) Model ERJ 170 Airplanes 

and Model ERJ 190 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

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50712 Federal Register / Vol. 73, No. 168 / Thursday, August 28, 2008 / Rules and Regulations 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. 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 some ‘‘caution’’

messages issued by the Flight Guidance 

Control System (FGCS) are not displayed on 

aircraft equipped with [certain] EPIC 

software load[s] * * *. Therefore, following 

a possible failure on one FGCS channel 

during a given flight, such a failure condition 

will remain undetected * * *. If another 

failure occurs on the second FGCS channel, 

the result may be a hardover command by the 

autopilot. 

An unexpected hardover command 

may cause a sudden roll, pitch, or yaw 

movement, which could result in 

reduced controllability of the airplane. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

October 2, 2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 2, 2008. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–1175; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (NPRM) to amend 

14 CFR part 39 to include an AD that 

would apply to the specified products. 

That supplemental NPRM was 

published in the Federal Register on 

April 11, 2008 (73 FR 19770). That 

supplemental NPRM proposed to 

correct an unsafe condition for the 

specified products. The mandatory 

continuing airworthiness information 

(MCAI) for Model ERJ 170 airplanes 

states: 

It has been found that some ‘‘caution’’

messages issued by the Flight Guidance 

Control System (FGCS) are not displayed on 

aircraft equipped with EPIC software load 

versions 17.3, 17.4, 17.5, 17.6, or 17.7. 

Therefore, following a possible failure on one 

FGCS channel during a given flight, such a 

failure condition will remain undetected or 

latent in subsequent flights. If another failure 

occurs on the second FGCS channel, the 

result may be a hardover command by the 

autopilot. 

The MCAI for Model ERJ 190 

airplanes states: 

It has been found that some ‘‘caution’’

messages issued by the Flight Guidance 

Control System (FGCS) are not displayed on 

aircraft equipped with EPIC software load 

versions 4.3, 4.4, 4.5, 4.6, or 4.7. Therefore, 

following a possible failure on one FGCS 

channel during a given flight, such a failure 

condition will remain undetected or latent in 

subsequent flights. If another failure occurs 

on the second FGCS channel, the result may 

be a hardover command by the autopilot. 

An unexpected hardover command 

may cause a sudden roll, pitch, or yaw 

movement, which could result in 

reduced controllability of the airplane. 

Corrective actions include a functional 

check of the FGCS channels 

engagement, installation of an upgrade 

to the Primus EPIC Field-Loadable 

Software, and replacement of the 

actuator input-output processor if 

necessary. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request To Extend Compliance Time 

EMBRAER and Air Transport 

Association (ATA), on behalf of one of 

its members, US Airways, request that 

we extend the compliance time for 

installing Primus EPIC Field-Loadable 

Software Version 19.3 or higher 

specified in paragraph (f)(2) of the 

supplemental NPRM from ‘‘within 8 

months after the effective date’’ to a 

specific later date. ATA requests the 

compliance time be extended until 

April 2009; EMBRAER suggests ‘‘no 

later than April 30, 2009.’’ US Airways 

states that a future upgrade, EPIC 21.4, 

is expected in August 2008. US Airways 

also states that airlines would prefer to 

wait to install EPIC 21.4 due to 

problems with EPIC Loads 19.3 and 

19.4. EMBRAER states that the Ageˆncia 

Nacional de Aviac ̧a ̃o Civil (ANAC) will 

issue new revisions to Brazilian 

Airworthiness Directives 2006–11–02 

and 2006–11–03 to extend the 

compliance time to April 30, 2009, for 

installation of EPIC Load 19.3 or 19.4. 

We agree to revise the compliance 

time. ANAC has issued Brazilian 

Airworthiness Directives 2006–11–02R3 

and 2006–11–03R3, both effective June 

13, 2008, which revise the compliance 

time of the previous airworthiness 

directives. The latest Brazilian 

airworthiness directives specify a 

compliance time of no later than April 

30, 2009, to install the software. Based 

on the nature of the software issues and 

potential for certain caution messages to 

not be displayed in the event of certain 

other failures, we have determined that 

a two-month extension of the 

compliance time will not have a 

significant effect on the overall safety 

risk. We have revised the compliance 

time for installing the software specified 

in paragraph (f)(2) of this AD to ‘‘within 

10 months after the effective date of the 

AD.’’ The 10-month compliance time is 

based on the calendar date specified in 

the Brazilian airworthiness directives 

and approximates the elapsed time 

between the issuance of this AD and 

April 30, 2009. 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

98 products of U.S. registry. We also 

estimate that it will take about 2 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $80 per work-hour. 

Based on these figures, we estimate the 

cost of this AD to the U.S. operators to 

be $15,680, or $160 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

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Federal Register / Vol. 73, No. 168 / Thursday, August 28, 2008 / Rules and Regulations 50713 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this 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 this AD: 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains the NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2008–17–11 Empresa Brasileira de 

Aeronautica S.A. (EMBRAER): 

Amendment 39–15649. Docket No. 

FAA–2007–27785; Directorate Identifier 

2006–NM–267–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective October 2, 2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to EMBRAER Model 

ERJ 170–100 LR, –100 STD, –100 SE, –100 

SU, –200 LR, –200 STD, and –200 SU 

airplanes, certificated in any category, 

equipped with Primus EPIC software load 

version 17.3, 17.4, 17.5, 17.6, or 17.7; and 

Model ERJ 190–100 STD, –100 LR, –100 IGW, 

–200 STD, –200 LR, and –200 IGW airplanes, 

certificated in any category, equipped with 

Primus EPIC software load version 4.3, 4.4, 

4.5, 4.6, or 4.7. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 22: Auto Flight. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) for Model 

ERJ 170 airplanes states: 

It has been found that some ‘‘caution’’

messages issued by the Flight Guidance 

Control System (FGCS) are not displayed on 

aircraft equipped with EPIC software load 

versions 17.3, 17.4, 17.5, 17.6, or 17.7. 

Therefore, following a possible failure on one 

FGCS channel during a given flight, such a 

failure condition will remain undetected or 

latent in subsequent flights. If another failure 

occurs on the second FGCS channel, the 

result may be a hardover command by the 

autopilot. 

The MCAI for Model ERJ 190 airplanes 

states: 

It has been found that some ‘‘caution’’

messages issued by the Flight Guidance 

Control System (FGCS) are not displayed on 

aircraft equipped with EPIC software load 

versions 4.3, 4.4, 4.5, 4.6, or 4.7. Therefore, 

following a possible failure on one FGCS 

channel during a given flight, such a failure 

condition will remain undetected or latent in 

subsequent flights. If another failure occurs 

on the second FGCS channel, the result may 

be a hardover command by the autopilot. 

An unexpected hardover command may 

cause a sudden roll, pitch, or yaw movement, 

which could result in reduced controllability 

of the airplane. Corrective actions include a 

functional check of the FGCS channels 

engagement, installation of an upgrade to the 

Primus EPIC Field-Loadable Software, and 

replacement of the actuator input-output 

processor if necessary. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Within 300 flight hours after the 

effective date of this AD, do a functional 

check of the FGCS channels engagement, in 

accordance with EMBRAER Service Bulletin 

170–22–0003 or Service Bulletin 190–22–

0002, both Revision 01, both dated November 

5, 2007, as applicable. Repeat the functional 

check thereafter at intervals not to exceed 

600 flight hours, until the terminating action 

described by paragraph (f)(2) of this AD has 

been done. If any malfunction of the FGCS 

is discovered during any functional check 

required by this paragraph, before further 

flight, do all applicable replacements of the 

actuator input-output processor in 

accordance with the applicable service 

bulletin. 

Note 1: For the purpose of this AD, a 

functional check is: ‘‘A quantitative check to 

determine if one or more functions of an item 

perform within specified limits.’’

(2) Within 10 months after the effective 

date of this AD, install Primus EPIC FieldLoadable Software Version 19.3 or higher, in 

accordance with EMBRAER Service Bulletin 

170–31–0019, Revision 01, dated June 25, 

2007; or Service Bulletin 190–31–0009, 

Revision 02, dated June 29, 2007; as 

applicable. Doing this installation ends the 

repetitive functional checks required by 

paragraph (f)(1) of this AD. 

(3) Any functional check done before the 

effective date of this AD in accordance with 

EMBRAER Service Bulletin 170–22–0003 or 

190–22–0002, both dated November 9, 2006, 

as applicable, is considered acceptable for 

compliance with the requirements of 

paragraph (f)(1) of this AD. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) 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: Todd Thompson, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1175; fax (425) 227–1149. Before using 

any approved AMOC on any airplane to 

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50714 Federal Register / Vol. 73, No. 168 / Thursday, August 28, 2008 / Rules and Regulations 

which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(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 FAAapproved 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: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI Brazilian Airworthiness 

Directives 2006–11–02R3 and 2006–11–03R3, 

both effective June 13, 2008; EMBRAER 

Service Bulletins 170–22–0003 and 190–22–

0002, both Revision 01, both dated November 

5, 2007; EMBRAER Service Bulletin 170–31–

0019, Revision 01, dated June 25, 2007; and 

EMBRAER Service Bulletin 190–31–0009, 

Revision 02, dated June 29, 2007; for related 

information. 

Material Incorporated by Reference 

(i) You must use the applicable service 

information specified in Table 1 of this AD 

to do the actions required by this AD, unless 

the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Empresa Brasileira de 

Aeronautica S.A. (EMBRAER), P.O. Box 

343—CEP 12.225, Sao Jose dos Campos—SP, 

Brazil. 

(3) You may review copies at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue, SW., Renton, Washington; or 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/cfr/ibrlocations.html. 

TABLE 1—MATERIAL INCORPORATED

BY REFERENCE

EMBRAER 

Service 

Bulletin—

Revision— Dated—

170–22–

0003.

01 November 5, 2007. 

170–31–

0019.

01 June 25, 2007. 

190–22–

0002.

01 November 5, 2007. 

190–31–

0009.

02 June 29, 2007. 

Issued in Renton, Washington, on August 

6, 2008. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E8–19143 Filed 8–27–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0621; Directorate 

Identifier 2008–NM–015–AD; Amendment 

39–15653; AD 2008–17–15] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–600, –700, –800, and –900 

Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Boeing Model 737–600, –700, –800, and 

–900 series airplanes. This AD requires 

installing hot short protector (HSP) 

support brackets and equipment for the 

fuel quantity indicating system (FQIS) 

fuel densitometer and other specified 

actions as applicable. This AD also 

requires revising the Airworthiness 

Limitations (AWLs) section of the 

Instructions for Continued 

Airworthiness to incorporate AWL No. 

28–AWL–07. This AD results from fuel 

system reviews conducted by the 

manufacturer. We are issuing this AD to 

prevent the center tank fuel 

densitometer from overheating and 

becoming a potential ignition source 

inside the center fuel tank, which, in 

combination with flammable fuel 

vapors, could result in a center fuel tank 

explosion and consequent loss of the 

airplane. 

DATES: This AD is effective October 2, 

2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 2, 2008. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, P.O. Box 3707, 

Seattle, Washington 98124–2207. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (telephone 800–647–5527) 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Georgios Roussos, Aerospace Engineer, 

Systems and Equipment Branch, ANM–

130S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6482; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to 

certain Boeing Model 737–600, –700, 

–800, and –900 series airplanes. That 

NPRM was published in the Federal 

Register on June 9, 2008 (73 FR 32491). 

That NPRM proposed to require 

installing hot short protector (HSP) 

support brackets and equipment for the 

fuel quantity indicating system (FQIS) 

fuel densitometer and other specified 

actions as applicable. That NPRM 

proposed to also require revising the 

Airworthiness Limitations (AWLs) 

section of the Instructions for Continued 

Airworthiness to incorporate AWL No. 

28–AWL–07. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the single comment 

received. Boeing concurs with the 

NPRM. 

Change to Final Rule Regarding Later 

Revisions of Service Information 

We removed all references to the use 

of ‘‘later revisions’’ of the applicable 

service information from this AD to be 

consistent with FAA and Office of the 

Federal Register policies. We may 

consider approving the use of later 

revisions of the service information as 

an alternative method of compliance 

with this AD, as provided by paragraph 

(k) of this AD. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously. 

We also determined that this change 

will not increase the economic burden 

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