Federal Register / Vol. 70, No. 225 / Wednesday, November 23, 2005 / Rules and Regulations 70713 

frequency converters fail to shut off. We are 

issuing this AD to prevent overheating of the 

output wiring of the frequency converters, 

which could result in the failure of a wire 

bundle and consequent adverse effects on 

other systems sharing the affected wire 

bundle. 

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. 

Replace Frequency Converters 

(f) Within 18 months after the effective 

date of this AD, do the actions specified in 

either paragraph (f)(1) or (f)(2) of this AD. 

(1) Replace the frequency converters used 

to supply power for medical and galley 

utility outlets with modified frequency 

converters, and do any related actions, by 

doing all of the actions specified in the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–25–0334, Revision 1, 

dated June 19, 2003. 

(2) Remove and deactivate the frequency 

converters used to supply power for medical 

and galley utility outlets, and cap and stow 

the frequency converter wire bundles, in 

accordance with B.1. through B.6. of the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–25–0334, Revision 1, 

dated June 19, 2003. As of the effective date 

of this AD, no person may install a frequency 

converter that has been removed and 

deactivated in accordance with this 

paragraph, unless it is modified in 

accordance with the Accomplishment 

Instructions of the service bulletin. 

Credit for Previous Service Bulletin 

(g) Actions done before the effective date 

of this AD in accordance with Boeing Service 

Bulletin 767–25–0334, dated November 7, 

2002, are acceptable for compliance with the 

requirements of paragraph (f) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(h) The Manager, Seattle 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. 

Material Incorporated by Reference 

(i) You must use Boeing Service Bulletin 

767–25–0334, Revision 1, dated June 19, 

2003, to perform the actions that are required 

by this AD, unless the AD specifies 

otherwise. The Director of the Federal 

Register approved the incorporation by 

reference of this document in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Contact Boeing Commercial Airplanes, P.O. 

Box 3707, Seattle, Washington 98124–2207, 

for a copy of this service information. You 

may review copies at the Docket Management 

Facility, U.S. Department of Transportation, 

400 Seventh Street, SW., Room PL–401, 

Nassif Building, Washington, DC; on the 

Internet at http://dms.dot.gov; or at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at the NARA, 

call (202) 741–6030, or go to http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

November 10, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–23054 Filed 11–22–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–19682; Directorate 

Identifier 2004–NM–88–AD; Amendment 39–

14383; AD 2005–24–03] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 737–600, –700, –700C, and –800 

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 737–600, –700, –700C, 

and –800 series airplanes. This AD 

requires inspecting/measuring the 

length of the attachment fasteners 

between the nacelle support fittings and 

the lower wing skin panels, and related 

investigative/corrective actions if 

necessary. This AD results from a report 

from the manufacturer that in 

production, during the installation of 

certain attachment fasteners for the 

nacelle support fittings, only one 

washer was installed instead of two. We 

are issuing this AD to prevent 

inadequate fastener clamp-up, which 

could result in cracking of the fastener 

holes, cracking along the lower wing 

skin panels, fuel leaking from the wing 

fuel tanks onto the engines, and possible 

fire. 

DATES: This AD becomes effective 

December 28, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 28, 2005. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., Nassif Building, room PL–401, 

Washington, DC. 

Contact Boeing Commercial 

Airplanes, PO Box 3707, Seattle, 

Washington 98124–2207, for service 

information identified in this AD. 

FOR FURTHER INFORMATION CONTACT: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6440; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the airworthiness 

directive (AD) docket on the Internet at 

http://dms.dot.gov or 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 street address stated in the 

ADDRESSES section. 

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 737–600, 

–700, –700C, and –800 series airplanes. 

That NPRM was published in the 

Federal Register on November 24, 2004 

(69 FR 68268). That NPRM proposed to 

require inspecting/measuring the length 

of the attachment fasteners between the 

nacelle support fittings and the lower 

wing skin panels, and related 

investigative/corrective actions if 

necessary. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Support for the NPRM 

One commenter supports the actions 

described in the NPRM. 

Notice of Service Bulletin Revision 

One commenter, the manufacturer, 

notes that there is an error in the 

variable numbers listed in the effectivity 

of Boeing Service Bulletin 737–57–1275, 

dated September 4, 2003 (which was 

referenced as the appropriate source of 

service information for accomplishing 

the proposed actions). The commenter 

states that this error is corrected in the 

next revision of the service bulletin and 

that correcting this error in the service 

bulletin will not alter the NPRM’s 

applicability. 

We agree with the commenter that the 

applicability of this AD is not affected 

by the change in variable numbers. The 

applicability of this AD refers to the 

airplane line numbers and not to the 

variable numbers. 

70714 Federal Register / Vol. 70, No. 225 / Wednesday, November 23, 2005 / Rules and Regulations 

Since the issuance of the NPRM, 

Boeing has issued Service Bulletin 737–

57–1275, Revision 1, dated August 18, 

2005, which contains the same 

procedures as the original issue along 

with the corrected variable numbers. 

Revision 1 of the service bulletin also 

divides the effectivity into four groups 

in order to provide clarification on the 

different fastener installation 

configurations. We have revised this AD 

to reference Revision 1 as the 

appropriate source of service 

information for accomplishing the 

required actions. We have also added 

paragraph (h) to this AD to give credit 

for actions done before the effective date 

of this AD in accordance with the 

original issue of the service bulletin. 

Clarification of Sealant Specification 

One commenter notes that Figures 1 

and 2 of Boeing Service Bulletin 737–

57–1275, dated September 4, 2003, 

specify an obsolete sealant. The 

commenter states that the ‘‘Parts and 

Materials Supplied by the Operator’’

section of the service bulletin specifies 

to refer to the Qualified Parts List (QPL) 

at the end of the Boeing Material 

Specification (BMS) for supplier data; 

however, there is no QPL for BMS 5–26 

because it is obsolete. The commenter 

points out that BMS 5–45 has 

superseded BMS 5–26. 

We agree with the commenter that 

BMS 5–45 is the correct specification for 

the sealant. Boeing Service Bulletin 

737–57–1275, Revision 1, dated August 

18, 2005, does contain the correct 

references to BMS 5–45. As stated 

previously, we have revised this AD to 

reference Revision 1 as the appropriate 

source of service information for 

accomplishing the required actions. No 

further work is necessary for airplanes 

on which Boeing Service Bulletin 737–

57–1275, dated September 4, 2003, was 

accomplished. 

Request To Revise Compliance Time 

One commenter requests that we 

revise the compliance time specified in 

paragraph (f)(2) of the NPRM from prior 

to the accumulation of ‘‘30,000 flight 

cycles or 30,000 flight hours, whichever 

is first’’ to prior to the accumulation of 

‘‘30,000 flight cycles or 37,000 flight 

hours, whichever is first.’’ The 

commenter states that 15 of its airplanes 

are not scheduled for a heavy ‘‘C’’ check 

maintenance within the 30,000-flighthour window and the proposed 

compliance time would result in 

unnecessary financial hardship. No 

technical justification was provided. 

We do not agree with the commenter 

to revise the compliance time. In 

developing an appropriate compliance 

time, we considered the safety 

implications, the manufacturer’s 

recommendation, and normal 

maintenance schedules for timely 

accomplishment of the inspection. We 

have determined that the compliance 

time, as proposed, represents the 

maximum interval of time allowable for 

the affected airplanes to continue to 

safely operate before the inspection is 

done. However, paragraph (i) of this AD 

provides affected operators the 

opportunity to apply for an adjustment 

of the compliance time if the operator 

also presents data that justify the 

adjustment. We have not revised this 

AD in this regard. 

Explanation of Change Made to This 

AD 

Boeing Commercial Airplanes has 

received a Delegation Option 

Authorization (DOA). We have revised 

this AD to delegate the authority to 

approve an alternative method of 

compliance for any repair required by 

this AD to an Authorized Representative 

for the Boeing Commercial Airplanes 

DOA rather than a Designated 

Engineering Representative (DER). 

Clarification of Alternative Method of 

Compliance (AMOC) Paragraph 

We have revised this AD to clarify the 

appropriate procedure for notifying the 

principal inspector before using any 

approved AMOC on any airplane to 

which the AMOC applies. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

received, and determined that air safety 

and the public interest require adopting 

the AD with the changes described 

previously. We have determined that 

these changes will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Costs of Compliance 

There are about 751 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 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Inspection/Measurement .................................................... 12 $65 Nominal ... $780 302 $235,560 

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 

Federal Register / Vol. 70, No. 225 / Wednesday, November 23, 2005 / Rules and Regulations 70715 

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): 

2005–24–03 Boeing: Amendment 39–14383. 

Docket No. FAA–2005–19682; 

Directorate Identifier 2004–NM–88–AD. 

Effective Date 

(a) This AD becomes effective December 

28, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Boeing Model 737–

600, –700, –700C, and –800 series airplanes; 

line numbers 1 through 761 inclusive, except 

for line numbers 596, 683, 742, 749, 750, 751, 

754, 755, 759, and 760; certificated in any 

category. 

Unsafe Condition 

(d) This AD was prompted by a report from 

the manufacturer that in production, during 

installation of certain attachment fasteners 

for the nacelle support fittings, only one 

washer was installed instead of two. We are 

issuing this AD to prevent inadequate 

fastener clamp-up, which could result in 

cracking of the fastener holes, cracking along 

the lower wing skin panels, fuel leaking from 

the wing fuel tanks onto the engines, and 

possible fire. 

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. 

Inspection/Measurement and Related 

Investigative and Corrective Actions 

(f) At the applicable time specified in 

paragraph (f)(1) or (f)(2) of this AD: Inspect/ 

measure the length of certain attachment 

fasteners between the lower wing skin panels 

and the nacelle support fittings. Do the 

inspection/measurement, and all applicable 

related investigative and corrective actions, 

in accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 737–

57–1275, Revision 1, dated August 18, 2005, 

except as provided by paragraph (g) of this 

AD. 

(1) For airplanes modified by 

Supplemental Type Certificate (STC) 

ST00830SE as of the effective date of this AD: 

Prior to the accumulation of 25,000 total 

flight hours or 25,000 total flight cycles, 

whichever is first. 

(2) For airplanes not modified by STC 

ST00830SE as of the effective date of this AD: 

Prior to the accumulation of 30,000 total 

flight hours or 30,000 total flight cycles, 

whichever is first. 

(g) If accomplishing a corrective action as 

required by paragraph (f) of this AD, and the 

service bulletin specifies to contact Boeing 

for repair information: Before further flight, 

do the repair using a method approved in 

accordance with paragraph (i) of this AD. 

Actions Accomplished According to 

Previous Issue of Service Bulletin 

(h) Actions accomplished before the 

effective date of this AD in accordance with 

Boeing Service Bulletin 737–57–1275, dated 

September 4, 2003, are considered acceptable 

for compliance with the corresponding action 

specified in this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(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. 

(2) Before using any AMOC approved in 

accordance with 14 CFR 39.19 on any 

airplane to which the AMOC applies, notify 

the appropriate principal inspector in the 

FAA Flight Standards Certificate Holding 

District Office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who has been 

authorized by the Manager, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

Material Incorporated by Reference 

(j) You must use Boeing Service Bulletin 

737–57–1275, Revision 1, dated August 18, 

2005, to perform the actions that are required 

by this AD, unless the AD specifies 

otherwise. The Director of the Federal 

Register approved the incorporation by 

reference of this document in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Contact Boeing Commercial Airplanes, P.O. 

Box 3707, Seattle, Washington 98124–2207, 

for a copy of this service information. You 

may review copies at the Docket Management 

Facility, U.S. Department of Transportation, 

400 Seventh Street SW., room PL–401, Nassif 

Building, Washington, DC; on the Internet at 

http://dms.dot.gov; or at the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at the 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 

November 10, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–23056 Filed 11–22–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–23087; Directorate 

Identifier 2005–NM–225–AD; Amendment 

39–14386; AD 2005–24–06] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A318–100, A319–100, A320–200, A321–

100, and A321–200 Series Airplanes, 

and Model A320–111 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Airbus Model A318–100, A319–100, 

A320–200, A321–100, and A321–200 

series airplanes, and Model A320–111 

airplanes. This AD requires an 

inspection to determine whether certain 

braking and steering control units 

(BSCUs) are installed or have ever been 

installed. For airplanes on which certain 

BSCUs are installed or have ever been 

installed, this AD requires an inspection 

of the nose landing gear (NLG) upper 

support and corrective action if 

necessary, and a check of the NLG strut 

inflation pressure and an adjustment if 

necessary. For some of these airplanes, 

this AD also requires a revision to the 

aircraft flight manual to incorporate an 

operating procedure to recover normal 

steering in the event of a steering 

failure. This AD results from a report of 

an incident where an airplane landed 

with the NLG turned 90 degrees from 

centerline. We are issuing this AD to 

prevent landings with the NLG turned 

90 degrees from centerline, which could 

result in reduced controllability of the 

airplane. 

DATES: This AD becomes effective 

November 30, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of November 30, 2005.