64850 Federal Register / Vol. 69, No. 216 / Tuesday, November 9, 2004 / Rules and Regulations 

2004–22–18 McDonnell Douglas:

Amendment 39–13846. Docket 2000–

NM–32–AD.

Applicability: Model MD–11 and –11F 

airplanes, as listed in Boeing Service Bulletin 

MD11–22–026, dated December 19, 2003; 

certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent electrical shorting of the brake 

coils of the auto throttle servo (ATS), which 

could result in smoke in the cockpit and/or 

passenger cabin, accomplish the following: 

Inspect ATS 

(a) Within 36 months after the effective 

date of this AD, do an inspection to 

determine the part number (P/N) of the ATS 

assembly of the servo assembly of the TCM, 

in accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 

MD11–22–026, dated December 19, 2003. 

Corrective Actions 

(b) Before further flight after doing the 

inspection required by paragraph (a) of this 

AD, do the applicable corrective action(s) 

specified in ‘‘Table-Corrective Actions,’’ in 

accordance with Boeing Service Bulletin 

MD11–22–026, dated December 19, 2003.

TABLE.—CORRECTIVE ACTIONS

If— Then—

(1) P/N 4059004–903 is installed ....................... Reidentify the TCM assembly. 

(2) P/N 4059004–903 is not installed ................. Replace the existing ATS assembly of the TCM assembly with a new ATS assembly, and reidentify the TCM assembly; or return TCM assembly to Boeing for modification and reidentification. 

Parts Installation 

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

person shall install a thrust control module 

assembly having part number ABH7760–1, 

ABH7760–501, ABH7760–503, SR11761001–

3, SR11761001–5, SR11761001–7, 

SR11270022–3, SR11761001–9, 

SR11270022–5, or SR11761001–11, on any 

airplane. 

Alternative Methods of Compliance 

(d) In accordance with 14 CFR 39.19, the 

Manager, Los Angeles Aircraft Certification 

Office, FAA, is authorized to approve 

alternative methods of compliance for this 

AD. 

Incorporation by Reference 

(e) The actions shall be done in accordance 

with Boeing Service Bulletin MD11–22–026, 

dated December 19, 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; at the 

FAA, Los Angeles Aircraft Certification 

Office, 3960 Paramount Boulevard, 

Lakewood, California; 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 

(f) 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. 04–24621 Filed 11–8–04; 8:45 am] 

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. 2001–NM–54–AD; Amendment 

39–13845; AD 2004–22–17] 

RIN 2120–AA64

Airworthiness Directives; McDonnell 

Douglas Model MD–11 and –11F 

Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to certain McDonnell 

Douglas Model MD–11 and MD–11F 

airplanes, that requires an inspection of 

the connector cables for signs of arcing 

and/or signs of moisture penetration 

into the overhead decoder units (ODU), 

and replacement of the affected ODU(s) 

with a new ODU, if necessary. This 

action also requires modification and 

reidentification of the cable assemblies 

and the connect cable assemblies at 

shipside power to the ODU, ODU to 

ODU, and adjacent bag racks; and 

replacing certain connectors of the ODU 

and shipside power cable assemblies. 

The actions specified by this AD are 

intended to prevent moisture from 

entering through the rear of the 

connector of the ODUs located in the 

overhead baggage stowage racks, which 

could result in a short, damage to the 

connector pins, and consequent smoke 

and/or fire in the cabin. 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, 

Long Beach Division, 3855 Lakewood 

Boulevard, Long Beach, California 

90846, Attention: Data and Service 

Management, Dept. C1–L5A (D800–

0024). 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:

Brett Portwood, Aerospace Engineer, 

Systems and Equipment Branch, ANM–

130L, FAA, Los Angeles Aircraft 

Certification Office, 3960 Paramount 

Boulevard, Lakewood, California 

90712–4137; telephone (562) 627–5350; 

fax (562) 627–5210.

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 McDonnell 

Douglas Model MD–11 and MD–11F 

airplanes was published as a 

supplemental notice of proposed 

rulemaking (NPRM) in the Federal 

Register on July 13, 2004 (69 FR 41987). 

That action proposed to require an 

inspection of the connector cables for 

signs of arcing and/or signs of moisture 

penetration into the overhead decoder 

units (ODU), and replacement of the 

affected ODU(s) with a new ODU, if 

necessary. That action also proposed to 

require modification and 

Federal Register / Vol. 69, No. 216 / Tuesday, November 9, 2004 / Rules and Regulations 64851

reidentification of the cable assemblies 

and the connect cable assemblies at 

shipside power to the ODU, ODU to 

ODU, and adjacent bag racks; and 

replacing certain connectors of the ODU 

and shipside power cable assemblies. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. No 

comments were submitted in response 

to the proposal or the FAA’s 

determination of the cost to the public. 

Conclusion 

The FAA has determined that air 

safety and the public interest require the 

adoption of the rule as proposed. 

Cost Impact 

There are approximately 114 

airplanes of the affected design in the 

worldwide fleet. The FAA estimates that 

28 airplanes of U.S. registry will be 

affected by this AD, that it will take 

approximately between 295 and 2,056 

work hours per airplane (i.e., 2 work 

hours per ODU and shipside connector; 

the number of ODUs and shipside 

connectors per airplane will vary 

between 59 and 1,028 depending on the 

airplane’s configuration) to accomplish 

the required actions, and that the 

average labor rate is $65 per work hour. 

Required parts will cost approximately 

between $2,264 and $130,864 per 

airplane (depending on the airplane 

configuration). Based on these figures, 

the cost impact of the AD on U.S. 

operators is estimated to be between 

$21,439 and $264,504 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. The 

manufacturer may cover the cost of 

replacement parts associated with this 

proposed AD, subject to warranty 

conditions. As a result, the costs 

attributable to the proposed 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:

2004–22–17 McDonnell Douglas:

Amendment 39–13845. Docket 2001–

NM–54–AD.

Applicability: Model MD–11 and –11F 

airplanes, as listed in Boeing Alert Service 

Bulletin MD11–33A065, Revision 02, dated 

April 1, 2003; certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent moisture from entering through 

the rear of the connector of the overhead 

decoder units (ODU) located in the overhead 

baggage stowage racks, which could result in 

a short, damage to the connector pins, and 

consequent smoke and/or fire in the cabin, 

accomplish the following: 

Service Bulletin References 

(a) The term ‘‘service bulletin,’’ as used in 

this AD, means Boeing Alert Service Bulletin 

MD11–33A065, Revision 02, dated April 1, 

2003. 

Part 1: Cable Assemblies of the ODU 

(b) Within 18 months after the effective 

date of this AD, do the actions specified in 

paragraphs (b)(1) through (b)(4) of Table 1 of 

this AD, as applicable, and any applicable 

corrective actions by doing all actions in Part 

1 of the Work Instructions of the service 

bulletin. Do the actions per the service 

bulletin. Do any applicable corrective actions 

before further flight.

TABLE 1.—CABLE ASSEMBLIES OF THE ODUS

For Airplanes Identified in the Service Bulletin 

as— Actions—

(1) Groups 1 through 69 ..................................... Do a general visual inspection of the P1 connector end of all AWP9604 cable assemblies of 

the ODUs to determine if SK2464–15 connectors are present. 

(2) Groups 1 through 69 ..................................... Replace the connector ends on the applicable cable assemblies of the ODUs with new connector ends. 

(3) Groups 1 through 72 ..................................... Do general visual inspection of the cable connectors for signs of arcing or signs of moisture 

penetration into the ODUs. 

(4) Groups 70 through 72 ................................... Replace the connectors of the applicable cable assemblies of the ODUs with new connectors. 

Note 1: For the purposes of this AD, a 

general visual inspection is defined as: ‘‘A 

visual examination of an interior or exterior 

area, installation, or assembly to detect 

obvious damage, failure, or irregularity. This 

level of inspection is made from within 

touching distance unless otherwise specified. 

A mirror may be necessary to enhance visual 

access to all exposed surfaces in the 

inspection area. This level of inspection is 

made under normally available lighting 

conditions such as daylight, hangar lighting, 

flashlight, or droplight and may require 

removal or opening of access panels or doors. 

Stands, ladders, or platforms may be required 

to gain proximity to the area being checked.’’

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