10344 Federal Register / Vol. 72, No. 45 / Thursday, March 8, 2007 / Rules and Regulations 

Pembroke Pines, FL 33023; telephone: (954) 

893–1400; fax: (954) 964–4141. 

(3) You may review copies at the FAA, 

Central Region, Office of the Regional 

Counsel, 901 Locust, Room 506, Kansas City, 

Missouri 64106; 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 Kansas City, Missouri, on March 

1, 2007. 

Kim Smith, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. E7–3990 Filed 3–7–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–25000; Directorate 

Identifier 2006–NM–096–AD; Amendment 

39–14955; AD 2005–24–03 R1] 

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 revising an 

existing airworthiness directive (AD) 

that applies to certain Boeing Model 

737–600, –700, –700C, and –800 series 

airplanes. That AD currently 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. That AD resulted 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. 

This new AD corrects errors found in 

the existing AD. We are issuing this AD 

to prevent inadequate fastener clampup, 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: The effective date of this AD is 

April 12, 2007. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of April 12, 2007. 

On December 28, 2005 (70 FR 70713, 

November 23, 2005), the Director of the 

Federal Register approved the 

incorporation by reference of Boeing 

Service Bulletin 737–57–1275, Revision 

1, dated August 18, 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, P.O. 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 98057–3356; telephone 

(425) 917–6440; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the 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 proposed to amend part 39 

of the Federal Aviation Regulations (14 

CFR part 39) with an airworthiness 

directive (AD) to revise AD 2005–24–03, 

amendment 39–14383 (70 FR 70713, 

November 23, 2005). The existing AD 

applies to certain Boeing Model 737–

600, –700, –700C, and –800 series 

airplanes. The proposed AD was 

published in the Federal Register on 

June 13, 2006 (71 FR 34026). That action 

proposed to continue 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. That action also proposed to 

correct errors found in the existing AD. 

Comment 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comment received. 

Request To Cite Revised Service 

Information 

Boeing states that, subsequent to the 

drafting of the subject AD, Boeing 

Service Bulletin 737–57–1275, Revision 

2, dated July 12, 2006, was issued. 

Boeing notes that Revision 2 will aid 

operators in completing the required 

tasks by more effectively and efficiently 

performing the inspections, while 

reducing the likelihood of introducing 

damage reported during completion of 

the previous revisions. Boeing 

recommends that Boeing Service 

Bulletin 737–57–1275, Revision 3, dated 

October 17, 2006, be incorporated into 

the NPRM, which further improves ease 

in completing the required tasks. 

(Revision 3 was not yet issued when the 

comment was submitted, but has since 

been issued.) 

We agree with this request. We have 

reviewed Revision 3 of the referenced 

service bulletin which specifies that no 

more work is necessary on airplanes 

changed as shown in the original issue, 

dated September 4, 2003; Revision 1, 

dated August 18, 2005; and Revision 2, 

dated July 12, 2006. (We referred to 

Revision 1 in the NPRM as the 

appropriate source of service 

information for accomplishing the 

required actions.) We have determined 

that Revision 3 shows changes of 

operators in the effectivity and clarifies 

the oversize limits for replacement 

fasteners, but does not add any further 

actions or increase the economic burden 

on operators. Therefore, we have 

changed the AD to add Boeing Service 

Bulletin 737–57–1275, Revision 3, dated 

October 17, 2006, as the appropriate 

source of service information for 

accomplishing the requirements in 

paragraph (f) of this AD after the 

effective date of this AD. 

Conclusion 

We have carefully reviewed the 

available data, including the comment 

received, and determined that air safety 

and the public interest require adopting 

the AD with the change described 

previously. We have determined that 

this change 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. The requirements 

that were previously required by AD 

2005–24–03 are retained in this AD; this 

AD adds no additional economic burden 

on U.S. operators. The current costs are 

repeated for the convenience of affected 

operators, as follows: 

Estimated Costs 


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Federal Register / Vol. 72, No. 45 / Thursday, March 8, 2007 / Rules and Regulations 10345 

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 

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 removing amendment 39–14383 (70 

FR 70713, November 23, 2005) and 

adding the following new airworthiness 

directive (AD): 

2005–24–03 R1 Boeing: Amendment 39–

14955. Docket No. FAA–2006–25000; 

Directorate Identifier 2006–NM–096–AD. 

Effective Date 

(a) The effective date of this AD is April 

12, 2007. 

Affected ADs 

(b) This AD revises AD 2005–24–03. 

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 results from a determination 

that errors were inadvertently included in the 

existing AD. 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. 

After the effective date of this AD only 

Boeing Service Bulletin 737–57–1275, 

Revision 3, dated October 17, 2006; shall be 

used. 

(1) For Model 737–700 series airplanes 

modified by Supplemental Type Certificate 

(STC) ST00830SE as of December 28, 2005 

(the effective date of AD 2005–24–03): 

Accomplish the actions at the later of the 

times specified in paragraphs (f)(1)(i) and 

(f)(1)(ii) of this AD. 

(i) Prior to the accumulation of 25,000 total 

flight hours or 25,000 total flight cycles, 

whichever is first. 

(ii) Within 12 months after December 28, 

2005. 

(2) For all other airplanes: Accomplish the 

actions at the later of the times specified in 

paragraphs (f)(2)(i) and (f)(2)(ii) of this AD. 

(i) Prior to the accumulation of 30,000 total 

flight hours or 30,000 total flight cycles, 

whichever is first. 

(ii) Within 12 months after December 28, 

2005. 

(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 December 

28, 2005, in accordance with Boeing Service 

Bulletin 737–57–1275, dated September 4, 

2003; are considered acceptable for 

compliance with the corresponding actions 

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) AMOCs approved previously in 

accordance with AD 2005–24–03, are 

approved as AMOCs for the corresponding 

provisions of this AD. 

(3) 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. 

(4) 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. 


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10346 Federal Register / Vol. 72, No. 45 / Thursday, March 8, 2007 / Rules and Regulations 

Material Incorporated by Reference 

(j) You must use the service information 

identified in Table 1 of this AD to perform 

the actions that are required by this AD, 

unless the AD specifies otherwise. 

TABLE 1.—ALL MATERIAL

INCORPORATED BY REFERENCE

Boeing Service 

Bulletin 

Revision 

level Date 

737–57–1275 .. 1 August 18, 

2005. 

737–57–1275 .. 3 October 17, 

2006. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Boeing Service Bulletin 737–57–1275, 

Revision 3, dated October 17, 2006; in 

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

part 51. 

(2) On December 28, 2005 (70 FR 70713, 

November 23, 2005), the Director of the 

Federal Register approved the incorporation 

by reference of Boeing Service Bulletin 737–

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

(3) 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 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. 

Issued in Renton, Washington, on February 

12, 2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–3006 Filed 3–7–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–24709; Directorate 

Identifier 2006–CE–28–AD; Amendment 39–

14980; AD 2007–05–19] 

RIN 2120–AA64 

Airworthiness Directives; Glasflugel 

Models H 301 ‘‘Libelle,’’ H 301B 

‘‘Libelle,’’ Standard ‘‘Libelle,’’ and 

Standard Libelle-201B Sailplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA adopts a new 

airworthiness directive (AD) for all 

Glasflugel Models H 301 ‘‘Libelle,’’ H 

301B ‘‘Libelle,’’ Standard ‘‘Libelle,’’ and 

Standard Libelle-201B sailplanes. This 

AD requires you to replace the rudder 

actuator arm (manufactured according 

to drawing No. 301–45–10) with an 

improved design rudder actuator arm 

(manufactured following drawing No. 

301–45–13). This AD results from 

mandatory continuing airworthiness 

information (MCAI) issued by the 

airworthiness authority for Germany. 

We are issuing this AD to detect and 

correct damage to the rudder actuator 

arm, which could result in failure of the 

rudder actuator arm. This failure could 

result in reduced or loss of rudder 

control. 

DATES: This AD becomes effective on 

April 12, 2007. 

As of April 12, 2007, the Director of 

the Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulation. 

ADDRESSES: To get the service 

information identified in this AD, 

contact Glasflugel, Glasfaser-FlugzeugService GmbH, Hansjory Steifeneder, 

Hofener Weg, 72582 Grabenstetten, 

Federal Republic of Germany; 

telephone: 011 49 7382 1032. 

To view the AD docket, go to the 

Docket Management Facility; U.S. 

Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

001 or on the Internet at http:// 

dms.dot.gov. The docket number is 

FAA–2006–24709; Directorate Identifier 

2006–CE–28–AD. 

FOR FURTHER INFORMATION CONTACT: 

Gregory Davison, Glider Project Officer, 

ACE–112, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329–

4130; facsimile: (816) 329–4090. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On August 4, 2006, we issued a 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) to 

include an AD that would apply to all 

Glasflugel Models H 301 ‘‘Libelle,’’ H 

301B ‘‘Libelle,’’ Standard ‘‘Libelle,’’ and 

Standard Libelle-201B sailplanes. This 

proposal was published in the Federal 

Register as a notice of proposed 

rulemaking (NPRM) on August 11, 2006 

(71 FR 46128). The NPRM proposed to 

require you to replace the rudder 

actuator arm (manufactured according 

to drawing No. 301–45–10) with an 

improved design rudder actuator arm 

(manufactured following drawing No. 

301–45–13). 

Comments 

We provided the public the 

opportunity to participate in developing 

this AD. The following presents the 

comment received on the proposal and 

FAA’s response to the comment: 

Comment Issue: Service Documents and 

Parts Manufacturer Approval 

Jack Buster of the Modification and 

Replacement Parts Association 

(MARPA) requests the following be 

incorporated into the regulatory action: 

1. Service documents deemed essential to 

the accomplishment of this proposed action 

be incorporated by reference and published 

in the Docket Management System (DMS); 

and 

2. The issue of parts manufacturer approval 

(PMA) be addressed in the proposed action 

and that all Directorates within the FAA treat 

the issue the same per Section 1, paragraph 

(b)(10) of Executive Order 12866. 

We agree that the service documents 

are essential and should be incorporated 

by reference. However, we do not 

incorporate by reference any document 

in a proposed AD action; instead we 

incorporate by reference the document 

in the final rule. Since we are issuing 

the proposal as a final rule AD action, 

the service information referenced in 

this action will be incorporated by 

reference. 

We are currently reviewing issues 

surrounding the posting of service 

bulletins in the Department of 

Transportation’s DMS as part of the AD 

docket. Once we have thoroughly 

examined all aspects of this issue and 

have made a final determination, we 

will consider whether our current 

practice needs to be revised. 

On the PMA issue, Mr. Buster’s 

comments are timely in that the FAA is 

currently reviewing this issue as it 

applies to all products: Transport 

airplanes, commuter airplanes, general 

aviation airplanes, engines and 

propellers, rotorcraft, and appliances. 

The FAA acknowledges that there are 

different ways of addressing this issue 

to ensure that unsafe PMA parts are 

identified and addressed. Once we have 

thoroughly examined all aspects of this 

issue including input from industry and 

have made a final determination, we 

will consider developing a standardized 

approach and standardized language on 

how to address PMA parts in 

airworthiness directives. 

We have determined that to delay this 

AD action would be inappropriate since 

an unsafe condition exists and that 

replacement of certain parts must be 

done to ensure continued safety. 

Therefore, we have made no change to 

the AD in this regard. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 


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