Federal Register / Vol. 73, No. 16 / Thursday, January 24, 2008 / Rules and Regulations 4061 

AD to prevent chafing of the forward boost 

pump wiring that could lead to arcing to the 

inside of the 45-degree angle fitting, 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. 

Modification 

(f) Within 78 months after the effective 

date of this AD, modify the conduit for the 

forward fuel boost pump of the center fuel 

tank, by accomplishing all of the actions 

specified in Boeing Service Bulletin 717–28–

0007, Revision 1, dated September 23, 2003. 

Credit for Actions Done According to 

Previous Issue of Service Bulletin 

(g) Actions done before the effective date 

of this AD in accordance with Boeing Service 

Bulletin 717–28–0007, dated August 22, 

2002, are acceptable for compliance with the 

requirements of paragraph (f) of this AD 

provided that a leak check of the conduit is 

accomplished in accordance with Boeing 717 

Airplane Maintenance Manual (AMM) Task 

28–22–28–700–801, ‘‘Leak Test of the Fuel 

Pump Electrical Conduit.’’

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, Los Angeles Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 

(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 appropriate principal inspector 

(PI) in the FAA Flight Standards District 

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

FSDO. 

Material Incorporated by Reference 

(i) You must use Boeing Service Bulletin 

717–28–0007, Revision 1, dated September 

23, 2003, 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 Boeing Commercial 

Airplanes, Long Beach Division, 3855 

Lakewood Boulevard, Long Beach, California 

90846, Attention: Data and Service 

Management, Dept. C1–L5A (D800–0024). 

(3) You may review copies of the service 

information incorporated by reference 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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on January 

14, 2008. 

Stephen P. Boyd, 

Assistant Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E8–971 Filed 1–23–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–28375; Directorate 

Identifier 2007–NM–015–AD; Amendment 

39–15346; AD 2008–02–16] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 767–200 and 767–300 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Boeing Model 767–200 and 767–300 

series airplanes. This AD requires 

reworking certain duct assemblies in the 

environmental control system (ECS). 

This AD results from reports of duct 

assemblies in the ECS with burned 

Boeing Material Specification (BMS) 8–

39 polyurethane foam insulation. This 

AD also results from a report from the 

airplane manufacturer that airplanes 

were assembled with duct assemblies in 

the ECS wrapped with BMS 8–39 

polyurethane foam insulation, a 

material of which the fire retardant 

properties deteriorate with age. We are 

issuing this AD to prevent a potential 

electrical arc from igniting the BMS 8–

39 polyurethane foam insulation on the 

duct assemblies of the ECS, which could 

propagate a small fire and lead to a 

larger fire that might spread throughout 

the airplane through the ECS. 

DATES: This AD becomes effective 

February 28, 2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of February 28, 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: Sue 

McCormick, Aerospace Engineer, Cabin 

Safety and Environmental Systems 

Branch, ANM–150S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (303) 342–1082; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to certain Boeing Model 767–200 

and 767–300 series airplanes. That 

NPRM was published in the Federal 

Register on June 19, 2007 (72 FR 33701). 

That NPRM proposed to require 

reworking certain duct assemblies in the 

environmental control system (ECS). 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Support for the Proposed AD 

Boeing concurs with the requirements 

of this AD. 

Request To Remove Airplane From the 

Proposed Applicability 

Hawaiian Airlines requests that we 

revise the proposed AD to remove one 

of its airplanes from the proposed 

applicability. Hawaiian states that the 

airplane came to them with two ducts 

installed in the affected area that do not 

have insulation installed on them. Each 

of these ducts has a part number not 

listed in Boeing Service Bulletin 767–

21A0167, Revision 1, dated December 

19, 2006. We referred to Boeing Service 

Bulletin 767–21A0167, Revision 1, as 

the appropriate source of service 

information for doing the actions 

specified in the proposed AD. Hawaiian 

quotes text from a Boeing message, in 

which Boeing confirms that the two 

subject duct assemblies do not need 

rework in accordance with the service 

bulletin because neither of the ducts 

assemblies are wrapped with Boeing 

Material Specification (BMS) 8–39 

polyurethane foam insulation. 


jlentini on PROD1PC65 with RULES
4062 Federal Register / Vol. 73, No. 16 / Thursday, January 24, 2008 / Rules and Regulations 

We agree. We have verified that the 

subject airplane should not be subject to 

this AD for the reasons stated above. 

Therefore, we have revised the 

applicability of this final rule to remove 

the subject airplane from the 

applicability of this AD. We have also 

revised the Costs of Compliance section 

of this final rule to remove the cost for 

this airplane. 

Request To Clarify Acceptable 

Compliance 

Hawaiian Airlines also requests that 

we revise the proposed AD to add 

language to clarify whether or not BMS 

8–300 insulation must be installed on 

an affected duct. Hawaiian reiterates 

that it has one airplane with two ducts 

installed, which do not have any 

insulation installed. 

We do not agree that it is necessary 

to make the requested clarification. As 

stated previously, we have determined 

that the subject airplane is not subject 

to this AD. Therefore, we have made no 

change to the final rule in this regard. 

Conclusion 

We reviewed the relevant data, 

considered the comments 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 

on any operator or increase the scope of 

the AD. 

Costs of Compliance 

There are about 129 airplanes of the 

affected design in the worldwide fleet. 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD. 

ESTIMATED COSTS

Action Work hours Average labor 

rate per hour 

Parts cost per 

airplane 

Average cost 

per airplane 

Number of 

U.S.-registered 

airplanes 

Average fleet 

cost 

Duct assembly rework ........ 7, per duct (average 50 

ducts per airplane).

$80 $4,955 $32,955 95 $3,130,725 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 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 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 Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

2008–02–16 Boeing: Amendment 39–15346. 

Docket No. FAA–2007–28375; 

Directorate Identifier 2007–NM–015–AD. 

Effective Date 

(a) This AD becomes effective February 28, 

2008. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model 767–200 and 

767–300 series airplanes, certificated in any 

category; as identified in Boeing Service 

Bulletin 767–21A0167, Revision 1, dated 

December 19, 2006; excluding variable 

number VK031. 

Unsafe Condition 

(d) This AD results from reports of duct 

assemblies in the environmental control 

system (ECS) with burned Boeing Material 

Specification (BMS) 8–39 polyurethane foam 

insulation. This AD also results from a report 

from the airplane manufacturer that airplanes 

were assembled with duct assemblies in the 

ECS wrapped with BMS 8–39 polyurethane 

foam insulation, a material of which the fire 

retardant properties deteriorate with age. We 

are issuing this AD to prevent a potential 

electrical arc from igniting the BMS 8–39 

polyurethane foam insulation on the duct 

assemblies or the ECS, which could 

propagate a small fire and lead to a larger fire 

that might spread throughout the airplane 

through the ECS. 

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. 

ECS Duct Assembly Rework 

(f) Except as provided by paragraph (g) of 

this AD, within 72 months after the effective 

date of this AD, rework the duct assemblies 

in the ECS for the air distribution system at 

sections 41, 45, and 46; the Gasper air system 

at sections 41, 43, 45, and 46; the forward 

electronic and electrical (E/E) compartment 

air supply; and the instrument panel cooling 

supply; in accordance with the 

Accomplishment Instructions and 

Appendices A and B of Boeing Service 

Bulletin 767–21A0167, Revision 1, dated 

December 19, 2006. 


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Federal Register / Vol. 73, No. 16 / Thursday, January 24, 2008 / Rules and Regulations 4063 

Optional Part Installed 

(g) If an affected duct assembly having a 

part number other than part number 

217T2109–12, or a part number other than 

any part number specified in the applicable 

figure of Boeing Service Bulletin 767–

21A0167, Revision 1, dated December 19, 

2006, is found installed, and that part 

number is listed as an optional part number 

in the table in paragraph 3.B.2., ‘‘Optional 

Part Table,’’ of the Accomplishment 

Instructions of the service bulletin: No 

rework is required for that duct assembly 

only. 

Parts Installation 

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

person may install on any airplane an air 

distribution system, Gasper air system, 

forward E/E compartment air supply, or 

instrument panel cooling supply duct 

assembly with BMS 8–39 polyurethane foam 

insulation. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, Seattle Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested in 

accordance with the procedures found in 14 

CFR 39.19. 

(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 appropriate principal inspector 

(PI) in the FAA Flight Standards District 

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

FSDO. 

Material Incorporated by Reference 

(j) You must use Boeing Service Bulletin 

767–21A0167, Revision 1, dated December 

19, 2006, 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 Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207. 

(3) You may review copies of the service 

information incorporated by reference 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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on January 

14, 2008. 

Stephen P. Boyd, 

Assistant Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E8–972 Filed 1–23–08; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–29170; Directorate 

Identifier 2007–NM–075–AD; Amendment 

39–15345; AD 2008–02–15] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A319 and A320 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

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: 

Some taperlocks used in the wing-tofuselage junction at rib 1 were found to be 

non-compliant with the applicable 

specification, resulting in a loss of pretension in the fasteners. In such conditions, 

the structural integrity of the aircraft could be 

affected. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

February 28, 2008. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 28, 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: Tim 

Dulin, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–2141; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on September 13, 2007 (72 FR 

52309). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Some taperlocks used in the wing-tofuselage junction at rib 1 were found to be 

non-compliant with the applicable 

specification, resulting in a loss of pretension in the fasteners. In such conditions, 

the structural integrity of the aircraft could be 

affected. 

This Airworthiness Directive mandates a 

repetitive internal inspection of the lower 

stiffeners, and a repetitive external 

inspection of the lower panels in center and 

outer wing box at level of rib 1 junction. 

The corrective action includes 

contacting Airbus for repair instructions 

and repair if any crack is found. 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 Refer to Revised Service 

Information 

The Air Transport Association (ATA), 

on behalf of one of its members, United 

Airlines, and Airbus ask that we refer to 

Airbus Service Bulletins A320–57–1129 

and A320–57–1130, both Revision 02, 

both dated July 17, 2007, for 

accomplishing the specified actions. 

We agree with the requests to refer to 

Revision 02 of Airbus Service Bulletins 

A320–57–1129 and A320–57–1130. In 

the NPRM, we referred to Airbus 

Service Bulletins A320–57–1129, and 

A320–57–1130, both Revision 01, both 

dated July 28, 2006, as the appropriate 

sources of service information for 

accomplishing the required actions. 

Revision 02 of the service bulletins 

updates the operator and aircraft 

effectivity to show the latest 

information. No additional work is 

required by these revisions of the 

service bulletins. We have changed 

paragraphs (f)(1) and (f)(2) of this AD to 

refer to Revision 02 of the service 

bulletins. We have also changed 

paragraphs (f)(1) and (f)(2) to give credit 

to operators that have done the actions 

previously in accordance with Revision 

01 of the service bulletins. We have also 

revised the sentence giving credit for an 

earlier service bulletin in paragraph 

(f)(2) of this AD for clarity. 

Request To Allow Installation of a Pin 

and Sleeve Fastener 

ATA, on behalf of one of its members, 

Northwest Airlines (NWA), states that 

installation of a pin-and-sleeve fastener, 

instead of the taperlok fastener, should 

be allowed due to the practical 

difficulties in accomplishing the NPRM 


jlentini on PROD1PC65 with RULES