12068 Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Rules and Regulations 

Effective Date 

(a) This AD becomes effective on April 19, 

2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Models 58 and G58 

airplanes, serial numbers TH–2097 through 

TH–2150, with optional propeller 

unfeathering accumulators installed, that are 

certificated in any category. 

Unsafe Condition 

(d) This AD results from several reports on 

the affected airplanes of chafing damage on 

the left propeller accumulator oil tube 

assembly. This includes an in-flight oil leak 

from the left engine on a Raytheon Aircraft 

Company Model G58 airplane. We are 

issuing this AD to detect, correct, and 

prevent any chafing damage of the left 

propeller accumulator oil tube assembly, 

which could result in loss of engine oil. Loss 

of engine oil may lead to fire or smoke in the 

engine compartment, inability to unfeather 

the propeller, engine damage, or loss of 

engine power. 

Compliance 

(e) To address this problem, you must do 

the following, unless already done: 

Actions Compliance Procedures 

(1) Inspect the left propeller accumulator oil 

tube assembly for chafing.

For airplanes that have not had a 100-hour 

time-in-service (TIS) inspection or the inspection following Raytheon Safety 

Communique ́ No. 271, dated May 2006: 

Within the next 25 hours TIS after April 19, 

2007 (the effective date of this AD). For airplanes that have had a 100-hour TIS inspection or the inspection following 

Raytheon Safety Communique ́ No. 271, 

dated May 2006: Within the next 50 hours 

TIS after April 19, 2007 (the effective date 

of this AD).

Follow Raytheon Aircraft Company Mandatory 

Service Bulletin No. SB 61–3806, issued: 

August 2006. 

(2) If any chafing is found in the inspection required by paragraph (e)(1) of this AD, replace 

the propeller accumulator oil tube assembly.

Before further flight after the inspection required by paragraph (e)(1) of this AD.Follow Raytheon Aircraft Company Mandatory 

Service Bulletin No. SB 61–3806, issued: 

August 2006. 

(3) Reposition and secure with clamps the left 

manifold pressure hose and its metal identification tags to ensure clearance between it 

and all tubes, hoses, electrical wires, parts, 

components, and structure.

Before further flight after the inspection or replacement required in paragraphs (e)(1) 

and (e)(2) of this AD.

Follow Raytheon Aircraft Company Mandatory 

Service Bulletin No. SB 61–3806, issued: 

August 2006. 

Material Incorporated by Reference 

(f) You must use Raytheon Aircraft 

Company Mandatory Service Bulletin No. SB 

61–3806, issued: August 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 Raytheon Aircraft Company, 

9709 E. Central, Wichita, Kansas 67201–

0085; telephone: (800) 429–5372 or (316) 

676–3140. 

(3) You may review copies at the FAA, 

Central Region, Office of the Regional 

Counsel, 901 Locust, 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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Kansas City, Missouri, on March 

7, 2007. 

David R. Showers, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–4523 Filed 3–14–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–24369; Directorate 

Identifier 2006–NM–001–AD; Amendment 

39–14990; AD 2007–06–09] 

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 superseding an 

existing airworthiness directive (AD), 

which applies to certain Boeing Model 

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

airplanes. That AD currently requires 

replacing the point ‘‘D’’ splice fitting 

between windows number 1 and 2 with 

a new splice fitting; performing an eddy 

current inspection for cracking of the 

holes in the structure common to the 

new splice fitting, including doing any 

related investigative actions; and 

performing corrective actions if 

necessary. This new AD adds repetitive 

inspections for cracking of the skin just 

below each splice fitting, and related 

corrective actions if necessary. This AD 

results from full-scale fuselage fatigue 

testing on the splice fitting that failed 

prior to the design objective on Boeing 

Model 737–800 series airplanes, and a 

report of a cracked splice fitting on an 

operational airplane. We are issuing this 

AD to prevent cracking of the existing 

fitting, which may result in cracking 

through the skin and consequent 

decompression of the flight deck. 

DATES: This AD becomes effective April 

19, 2007. 

The incorporation by reference of 

Boeing Alert Service Bulletin 737–

53A1222, Revision 3, dated January 3, 

2007, as listed in the regulations, is 

approved by the Director of the Federal 

Register as of April 19, 2007. 

On December 21, 2005 (70 FR 72595, 

December 6, 2005), the Director of the 

Federal Register approved the 

incorporation by reference of Boeing 

Alert Service Bulletin 737–53A1222, 

Revision 2, dated October 20, 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, 


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Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Rules and Regulations 12069 

Washington 98124–2207, for service 

information identified in this AD. 

FOR FURTHER INFORMATION CONTACT: 

Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6447; 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 

supersedes AD 2005–25–03, amendment 

39–14396 (70 FR 72595, December 6, 

2005). The existing AD applies to 

certain Boeing Model 737–600, –700, 

–700C, and –800 series airplanes. That 

NPRM was published in the Federal 

Register on April 11, 2006 (71 FR 

18251). That NPRM proposed to 

continue to require replacing the point 

‘‘D’’ splice fitting between windows 

number 1 and 2 with a new splice 

fitting; performing an eddy current 

inspection for cracking of the holes in 

the structure common to the new splice 

fitting, including doing any related 

investigative actions; and performing 

corrective actions if necessary. That 

NPRM also proposed to add repetitive 

inspections for cracking of the skin just 

below each splice fitting, and related 

corrective actions if necessary. 

Explanation of Revision Service 

Information 

The NPRM referred to Boeing Alert 

Service Bulletin 737–53A1222, Revision 

2, as the appropriate source of service 

information for the inspection of 

paragraph (g). Boeing has since revised 

the service bulletin. Revision 3, dated 

January 3, 2007, corrects and clarifies 

certain information and adds fastener 

options, but adds no additional work for 

airplanes with splice fittings replaced as 

specified in a previous version of the 

service bulletin. We have revised this 

final rule to refer to Revision 3 of the 

service bulletin for the inspection in 

paragraph (g), and to provide credit for 

work done in accordance with Revision 

2. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments that have 

been received on the NPRM. 

Support for the NPRM 

One commenter, Continental Airlines, 

agrees with the NPRM. 

Request To Provide an Alternate 

Method of Compliance (AMOC) 

KLM Engineering and Maintenance 

requests that the FAA review the 

inspection methods for the proposed 

one-time inspection of certain fastener 

locations during the point ‘‘D’’ splice 

fitting replacement. The commenter 

advises that, for certain fastener 

locations, an eddy current open fastener 

hole is impractical and may not even be 

possible due to structure build-up. The 

commenter requests that an AMOC be 

given specifying fluorescent penetrant 

inspections instead of the eddy current 

open fastener hole inspections. The 

commenter notes that use of the 

fluorescent penetrant inspections has 

been coordinated with the 

manufacturer. 

Since we issued the NPRM, the 

manufacturer issued Revision 3 of 

Boeing Alert Service Bulletin (ASB) 

737–53A1222. Revision 3, dated January 

3, 2007, contains procedures for 

performing fluorescent penetrant 

inspections. This final rule incorporates 

the revised service bulletin; therefore, 

no AMOC will be necessary to do this 

type of inspection. We have not changed 

this AD regarding this issue. 

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 563 airplanes of the 

affected design in the worldwide fleet. 

We estimate that about 243 airplanes are 

on the U.S. Register, and that the 

average labor rate is $80 per hour. The 

following table provides the estimated 

costs for U.S. operators to comply with 

this AD. 

ESTIMATED COSTS

Action Work hours Parts Cost per 

airplane Fleet cost 

Replacing splice fittings with new fittings (required by AD 2005–25–03) ....... 36 $15,445 $18,325 $4,452,975 

External detailed inspection (new action) ........................................................ 1 0 80 1 19,440 

1Per inspection cycle. 

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: 


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12070 Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Rules and Regulations 

(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 39–14396 (70 

FR 72595, December 6, 2005) and by 

adding the following new airworthiness 

directive (AD): 

2007–06–09 Boeing: Amendment 39–14990. 

Docket No. FAA–2006–24369; 

Directorate Identifier 2006–NM–001–AD. 

Effective Date 

(a) This AD becomes effective April 19, 

2007. 

Affected ADs 

(b) This AD supersedes AD 2005–25–03. 

Applicability 

(c) This AD applies to Boeing Model 737–

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

certificated in any category; as identified in 

Boeing Alert Service Bulletin (ASB) 737–

53A1222, Revision 3, dated January 3, 2007. 

Unsafe Condition 

(d) This AD results from full-scale fuselage 

fatigue testing on a splice fitting that failed 

prior to the design objective on Boeing Model 

737–800 series airplanes, and a report of a 

cracked splice fitting on an operational 

airplane. We are issuing this AD to prevent 

cracking of the existing fitting, which may 

result in cracking through the skin and 

consequent decompression of the flight deck. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Restatement of Certain Requirements of AD 

2005–25–03 

Replacing the Splice Fittings 

(f) Replace the splice fittings with new 

splice fittings in accordance with the 

Accomplishment Instructions of Boeing ASB 

737–53A1222, Revision 2, dated October 20, 

2005, or Revision 3, dated January 3, 2007, 

at the times specified in paragraph (f)(1) or 

(f)(2) of this AD, as applicable. Before further 

flight, do any related investigative actions by 

accomplishing all the applicable actions 

specified in the Accomplishment 

Instructions. 

(1) For airplanes that have accumulated 

fewer than 13,500 total flight cycles as 

December 21, 2005 (the effective date of AD 

2005–25–03): Replace prior to the 

accumulation of 13,500 total flight cycles, or 

within 1,000 flight cycles after December 21, 

2005, whichever occurs later. 

(2) For airplanes that have accumulated 

13,500 or more total flight cycles as of 

December 21, 2005: Replace 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 18,000 total 

flight cycles, or within 1,000 flight cycles 

after December 21, 2005, whichever occurs 

first. 

(ii) Within 90 days after December 21, 

2005. 

New Requirements of This AD 

Repetitive Inspections 

(g) Within 24,000 flight cycles after 

accomplishing the actions specified in 

paragraph (f) of this AD, perform an external 

detailed inspection of the skin just below 

each splice fitting, in accordance with the 

Accomplishment Instructions of Boeing ASB 

737–53A1222, Revision 3, dated January 3, 

2007. Thereafter, repeat the external detailed 

inspections at intervals not to exceed 24,000 

flight cycles. 

Corrective Actions 

(h) If any cracking is found during any 

inspection required by this AD, prior to 

further flight, repair in accordance with a 

method approved by the Manager, Seattle 

Aircraft Certification Office (ACO), FAA, or 

with a method approved in accordance with 

the procedures specified in paragraph (j) of 

this AD. 

Acceptable Method of Compliance 

(i) Replacing the splice fitting and any 

related investigative actions before December 

21, 2005 (the effective date of AD 2005–25–

03), in accordance with Boeing Service 

Bulletin 737–53–1222, dated June 6, 2002; or 

Boeing ASB 737–53A1222, Revision 1, dated 

January 30, 2003, is acceptable for 

compliance with the requirements of 

paragraph (f) of this AD. An inspection done 

before the effective date of this AD in 

accordance with Boeing ASB 737–53A1222, 

Revision 2, dated October 20, 2005, is 

acceptable for compliance with the 

requirements of paragraph (g) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, Seattle 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) Before using any AMOC approved in 

accordance with § 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. 

(4) AMOCs approved previously in 

accordance with AD 2005–25–03, 

amendment 39–14396, are approved as 

AMOCs for the corresponding provisions of 

paragraphs (f) and (h) of this AD. 

Material Incorporated by Reference 

(k) You must use Boeing Alert Service 

Bulletin 737–53A1222, Revision 2, dated 

October 20, 2005; or Boeing Alert Service 

Bulletin 737–53A1222, Revision 3, dated 

January 3, 2007; to perform the actions that 

are required by this AD, unless the AD 

specifies otherwise. 

(1) The incorporation by reference of 

Boeing Alert Service Bulletin 737–53A1222, 

Revision 3, dated January 3, 2007, is 

approved by the Director of the Federal 

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

and 1 CFR part 51. 

(2) On December 21, 2005 (70 FR 72595, 

December 6, 2005), the Director of the 

Federal Register approved the incorporation 

by reference of Boeing Alert Service Bulletin 

737–53A1222, Revision 2, dated October 20, 

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, S.W., 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 March 7, 

2007. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–4540 Filed 3–14–07; 8:45 am] 

BILLING CODE 4910–13–P 


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