64852 Federal Register / Vol. 69, No. 216 / Tuesday, November 9, 2004 / Rules and Regulations 

Part 2: Shipside Cable Assemblies 

(c) For Groups 1 through 69 identified in 

the service bulletin: Within 18 months after 

the effective date of this AD, do the actions 

specified in paragraphs (c)(1) through (c)(3) 

of this AD, and any applicable corrective 

action by doing all actions in paragraphs 1., 

and 3. through 10., as applicable, of Part 2 

of the Work Instructions of the service 

bulletin. Do the actions per the service 

bulletin. Do any applicable corrective actions 

before further flight. 

(1) Do a general visual inspection of the P1 

connector end of the jumper cables of the 

centerline AWP9606 shipside cable 

assemblies to determine if SK2464–9 

connectors are present. 

(2) Replace the P1 connector ends on the 

applicable shipside cable assemblies with 

new connector ends. 

(3) Replace the connectors of the 

applicable shipside cable assemblies with 

new connectors. 

Differences Between AD and Referenced 

Service Bulletin 

(d) Although the service bulletin 

referenced in this AD specifies to submit 

certain information to the manufacturer, this 

AD does not include that requirement. 

(e) Although the service bulletin describes 

the procedure for a general visual inspection 

of the connector cables of the shipside cable 

assemblies for signs of arcing or signs of 

moisture penetration for certain airplanes, 

this AD does not require that inspection.

Note 2: Where there are differences 

between the AD and the service bulletin, the 

AD prevails.

Parts Installation 

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

person shall install a cable assembly having 

a part number in the ‘‘Existing Part Number’’

column of the applicable table specified in 

paragraph 2.C.3, ‘‘Parts Necessary for Each 

Airplanes’’ of the service bulletin, on any 

airplane. 

Alternative Methods of Compliance (AMOC) 

(g) In accordance with 14 CFR 39.19, the 

Manager, Los Angeles Aircraft Certification 

Office, FAA, is authorized to approve 

AMOCs for this AD. 

Incorporation by Reference 

(h) The action shall be done in accordance 

with Boeing Alert Service Bulletin MD11–

33A065, excluding Appendix, Revision 02, 

dated April 1, 2003. This incorporation by 

reference was approved by the Director of the 

Federal Register in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. Copies may be 

obtained from Boeing Commercial Airplanes, 

Long Beach Division, 3855 Lakewood 

Boulevard, Long Beach, California 90846, 

Attention: Data and Service Management, 

Dept. C1–L5A (D800–0024). Copies may be 

inspected 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.

Effective Date 

(i) This amendment becomes effective on 

December 14, 2004.

Issued in Renton, Washington, on October 

25, 2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–24620 Filed 11–8–04; 8:45 am] 

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. 2003–NM–106–AD; Amendment 

39–13855; AD 2004–22–27] 

RIN 2120–AA64

Airworthiness Directives; Boeing 

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

–900 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to certain Boeing Model 737–

600, –700, –700C, –800, and –900 series 

airplanes, that requires a general visual 

inspection for sealant at the interface 

between the diagonal brace fitting and 

the aft bulkhead and at the four bolts 

common to the interface. It also requires 

applying sealant if none is present or if 

it is not continuous. This action is 

necessary to prevent flammable fluid in 

the upper or rear pylon areas from 

leaking past unsealed areas and onto a 

hot engine nozzle, which could result in 

ignition of the fluid, causing an 

undetected and uncontrollable fire to 

spread into the engine struts. This 

action is intended to address the 

identified unsafe condition.

DATES: Effective December 14, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of December 

14, 2004.

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Boeing Commercial Airplanes, 

P.O. Box 3707, Seattle, Washington 

98124–2207. This information may be 

examined at the Federal Aviation 

Administration (FAA), Transport 

Airplane Directorate, Rules Docket, 

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.

FOR FURTHER INFORMATION CONTACT:

Doug Pegors, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6504; fax (425) 917–6590.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) to 

include an airworthiness directive (AD) 

that is applicable to certain Boeing 

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

–900 series airplanes was published in 

the Federal Register on May 3, 2004 (69 

FR 24101). That action proposed to 

require a general visual inspection for 

sealant at the interface between the 

diagonal brace fitting and the aft 

bulkhead and at the four bolts common 

to the interface. It also proposed to 

require applying sealant if none is 

present or if it is not continuous. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. Due 

consideration has been given to the 

comments received. 

Request To Extend Compliance Time 

One commenter requests that the FAA 

extend the compliance time for the 

general visual inspection from 18 

months or 3,500 flight cycles, whichever 

occurs first, to 24 months or 4,500 flight 

cycles, whichever occurs first. The 

commenter states that access is common 

for the proposed inspection and Boeing 

Maintenance Planning Document (MPD) 

tasks 54–040–1 through 54–050–02, 

dated February 10, 2004, and that it 

would be more cost efficient if the 

commenter could perform the 

inspection and MPD tasks during the 

same maintenance visit, every 24 

months. 

We do not agree with the request to 

extend the compliance time. The 

commenter provided no justification for 

the change other than for the 

convenience of its maintenance 

program. In developing an appropriate 

compliance time for this action, we 

considered the recommendation of the 

manufacturer, urgency associated with 

the subject unsafe condition, and the 

practical aspect of accomplishing the 

required inspection within a period of 

time that corresponds to the normal 

scheduled maintenance for most 

affected operators. However, under the 

provisions of paragraph (c) of the final 

Federal Register / Vol. 69, No. 216 / Tuesday, November 9, 2004 / Rules and Regulations 64853

rule, we may approve requests for 

adjustments to the compliance time if 

data are submitted to substantiate that 

such an adjustment would provide an 

acceptable level of safety. 

Conclusion 

After careful review of the available 

data, including the comment noted 

above, the FAA has determined that air 

safety and the public interest require the 

adoption of the rule as proposed. 

Clarification of Changes to the Final 

Rule 

We have revised paragraph (a)(2) of 

the final rule and added new paragraph 

(a)(3) to eliminate any possible 

ambiguity created by use of the term 

‘‘and/or’’ in the proposed AD. 

Cost Impact 

There are approximately 946 

airplanes of the affected design in the 

worldwide fleet. The FAA estimates that 

436 airplanes of U.S. registry will be 

affected by this AD, that it will take 

approximately 2 work hours per 

airplane to accomplish the required 

actions, and that the average labor rate 

is $65 per work hour. Based on these 

figures, the cost impact of the AD on 

U.S. operators is estimated to be 

$56,680, or $130 per airplane. 

The cost impact figure discussed 

above is based on assumptions that no 

operator has yet accomplished any of 

the requirements of this AD action, and 

that no operator would accomplish 

those actions in the future if this AD 

were not adopted. The cost impact 

figures discussed in AD rulemaking 

actions represent only the time 

necessary to perform the specific actions 

actually required by the AD. These 

figures typically do not include 

incidental costs, such as the time 

required to gain access and close up, 

planning time, or time necessitated by 

other administrative actions. 

Manufacturer warranty remedies may be 

available for labor costs associated with 

this AD. As a result, the costs 

attributable to this AD may be less than 

stated above. 

Regulatory Impact 

The regulations adopted herein 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. Therefore, it is 

determined that this final rule does not 

have federalism implications under 

Executive Order 13132. 

For the reasons discussed above, I 

certify that this action (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. A final evaluation has 

been prepared for this action and it is 

contained in the Rules Docket. A copy 

of it may be obtained from the Rules 

Docket at the location provided under 

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety.

Adoption of the Amendment

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (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. Section 39.13 is amended by adding 

the following new airworthiness 

directive:

2004–22–27 Boeing: Amendment 39–13855. 

Docket 2003–NM–106–AD.

Applicability: Model 737–600, –700, 

–700C, –800, and –900 series airplanes, line 

numbers 1 through 946 inclusive; certificated 

in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent flammable fluid in the upper or 

rear pylon areas from leaking past unsealed 

areas and onto a hot engine nozzle, which 

could result in ignition of the fluid, causing 

an undetected and uncontrollable fire to 

spread into the engine struts; accomplish the 

following: 

Inspection of Sealant 

(a) Within 18 months or 3,500 flight cycles 

after the effective date of this AD, whichever 

occurs first: Perform a general visual 

inspection for sealant at the interface of the 

diagonal brace fitting and the aft bulkhead 

and at the four bolts common to the interface, 

in accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–54–1039, Revision 1, 

dated October 10, 2002. 

(1) If the findings of the general visual 

inspection are as described in paragraphs 

(a)(1)(i) and (a)(1)(ii) of this AD, then no 

further action is required by this AD. 

(i) The seal is continuous or there is 

evidence of fay seal sqeeze out present. 

(ii) The bolts have evidence of sealant 

squeeze out or a cap seal exists. 

Application of Fillet Seal 

(2) The seal is not continuous and there is 

no evidence of fay seal squeeze out present, 

before further flight, fillet seal around the 

interface of the diagonal brace fitting and the 

aft bulkhead, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–54–

1039, Revision 1, dated October 10, 2002. 

Application of Cap Seal 

(3) If the bolts do not have evidence of 

sealant squeeze out and no cap seal exists, 

before further flight, cap seal the four bolts 

common to the interface, in accordance with 

the Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–54–

1039, Revision 1, dated October 10, 2002. 

Credit for Actions Accomplished per 

Previous Service Bulletin 

(b) Actions accomplished before the 

effective date of this AD per Boeing Special 

Attention Service Bulletin 737–54–1039, 

dated June 13, 2002, are acceptable for 

compliance with the corresponding actions 

of paragraph (a) of this AD. 

Alternative Methods of Compliance (AMOC) 

(c) In accordance with 14 CFR 39.19, the 

Manager, Seattle Aircraft Certification Office, 

FAA, is authorized to approve AMOCs for 

this AD. 

Incorporation by Reference 

(d) Unless otherwise specified in this AD, 

the actions shall be done in accordance with 

Boeing Special Attention Service Bulletin 

737–54–1039, Revision 1, dated October 10, 

2002. This incorporation by reference was 

approved by the Director of the Federal 

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

and 1 CFR part 51. Copies may be obtained 

from Boeing Commercial Airplanes, P.O. Box 

3707, Seattle, Washington 98124–2207. 

Copies may be inspected 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. 

Effective Date 

(e) This amendment becomes effective on 

December 14, 2004.

Issued in Renton, Washington, on October 

26, 2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–24626 Filed 11–8–04; 8:45 am] 

BILLING CODE 4910–13–P