Federal Register / Vol. 69, No. 213 / Thursday, November 4, 2004 / Rules and Regulations 64253

2004–22–21 Grob-Werke: Amendment 39–

13849; Docket No. FAA–2004–18030; 

Directorate Identifier 2004–CE–13–AD. 

When Does This AD Become Effective? 

(a) This AD becomes effective on December 

27, 2004.

What Other ADs Are Affected by This 

Action? 

(b) None. 

What Airplanes Are Affected by This AD? 

(c) This AD affects Model G120A airplanes, 

all serial numbers, that are certificated in any 

category. 

What Is the Unsafe Condition Presented in 

This AD? 

(d) This AD is the result of mandatory 

continuing airworthiness information (MCAI) 

issued by the airworthiness authority for 

Germany. The actions specified in this AD 

are intended to detect and correct any 

disbonding/crack in the area between the 

vertical stabilizer main spar and nearby 

stabilizer skin, which could result in possible 

structural failure. This failure could lead to 

difficulty in airplane flight control. 

What Must I Do To Address This Problem? 

(e) To address this problem, you must do 

the following:

Actions Compliance Procedures 

(1) Inspect the area between the vertical stabilizer main spar and the nearby vertical stabilizer skin for any disbonding/crack along 

the spar/skin contact (both sides of the 

vertical stabilizer).

Within the next 50 hours time-in-service (TIS) 

after December 27, 2004 (the effective date 

of this AD), unless already done. Repetitively inspect thereafter at every 50 hours 

TIS.

Follow GROB Luft-und Raumfahrt Service 

Bulletin No. MSB 1121–049, dated April 20, 

2004. The applicable airplane maintenance 

manual also addresses this issue. 

(2) If any disbonding/crack is found during any 

inspection required by paragraph (e)(1) of 

this AD: 

(i) Get a repair instruction from the manufacturer; and 

(ii) Follow this repair instruction. 

(iii) The repetitive inspections of paragraph 

(e)(1) of this AD are still required after any 

repair. 

Before further flight after any inspection required by paragraph (e)(1) of this AD where 

any disbonding/crack is found.

Follow GROB Luft-und Raumfahrt Service 

Bulletin No. MSB1121–049, dated April 20, 

2004; and any repair instruction obtained 

from GROB Luft-und Raumfahrt, 

Lettenbachstrasse 9, D–86874 

Tussenhausen-Mattsies, Federal Republic 

of Germany; telephone: 011 49 8268 

998139; facsimile: 011 49 8268 998200. 

Obtain approval of this repair instruction 

through the FAA at the address specified in 

paragraph (f) of this AD. The applicable airplane maintenance manual also addresses 

this issue. 

(3) Calculate weight and balance after any repair required by paragraph (e)(2) of this AD.Before further flight after any repair required 

by paragraph (e0(2) of this AD.

Follow GROB Luft-und Raumfahrt Service 

Bulletin No. MSB1121–049, dated April 20, 

2004. The applicable airplane maintenance 

manual also addresses this issue. 

May I Request an Alternative Method of 

Compliance? 

(f) You may request a different method of 

compliance or a different compliance time 

for this AD by following the procedures in 14 

CFR 39.19. Unless FAA authorizes otherwise, 

send your request to your principal 

inspector. The principal inspector may add 

comments and will send your request to the 

Manager, Standards Office, Small Airplane 

Directorate, FAA. For information on any 

already approved alternative methods of 

compliance, contact Karl Schletzbaum, 

Aerospace Engineer, FAA, Small Airplane 

Directorate, 901 Locust, Room 301, Kansas 

City, Missouri 64106; telephone: (816) 329–

4146; facsimile: (816) 329–4090. 

Is There Other Information That Relates to 

This Subject? 

(g) German AD Number D–2004–204, dated 

April 23, 2004, also addresses the subject of 

this AD. 

Does This AD Incorporate Any Material by 

Reference? 

(h) You must do the actions required by 

this AD following the instructions in GROB 

Luft-und Raumfahrt Service Bulletin No. 

MSB1121–049, dated April 20, 2004. The 

Director of the Federal Register approved the 

incorporation by reference of this service 

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

and 1 CFR part 51. To get a copy of this 

service information, contact GROB Luft-und 

Raumfahrt, Lettenbachstrasse 9, D–86874 

Tussenhausen-Mattsies, Federal Republic of 

Germany; telephone: 011 49 8268 998139; 

facsimile: 011 49 8268 998200. To review 

copies of this service information, go to the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, go 

to: http://www.archives.gov/federal_register/

code_of_federal_regulations/

ibr_locations.html or call (202) 741–6030. 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–

2004–18030.

Issued in Kansas City, Missouri, on 

October 27, 2004. 

David R. Showers, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–24522 Filed 11–3–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–NM–217–AD; Amendment 

39–13843; AD 2004–22–15] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 747–400 and –400D Series 

Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD), 

applicable to certain Boeing Model 747–

400 series airplanes, that currently 

requires installation of strap assemblies 

on the ceiling panels and rails that 

support the video monitors. For certain 

airplanes, this amendment requires 

replacement of certain plate assemblies 

within the ceiling panel strap 

assemblies with new, improved plate 

assemblies. This amendment also 

revises the applicability by adding 

airplanes. The actions specified by this 

AD are intended to prevent ceiling 

panels from falling into the passenger 

cabin area in the event of failure of 

64254 Federal Register / Vol. 69, No. 213 / Thursday, November 4, 2004 / Rules and Regulations 

certain latch assemblies on the ceiling 

panels, which could result in 

consequent injury to the flightcrew and 

passengers. This action is intended to 

address the identified unsafe condition.

DATES: Effective December 9, 2004. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of December 

9, 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:

Patrick Gillespie, Aerospace Engineer, 

Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, 

Seattle Aircraft Certification Office; 

telephone (425) 917–6429; fax (425) 

917–6590.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) 

by superseding AD 99–18–07, 

amendment 39–11273 (64 FR 47372, 

August 31, 1999), which is applicable to 

certain Boeing Model 747–400 series 

airplanes, was published in the Federal 

Register on June 23, 2004 (69 FR 34969). 

That action proposed to continue to 

require installation of strap assemblies 

on the ceiling panels and rails that 

support the video monitors. For certain 

airplanes, that action also proposed to 

require replacement of certain plate 

assemblies within the ceiling panel 

strap assemblies with new, improved 

plate assemblies. That action also 

proposed to revise the applicability by 

adding airplanes. 

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. 

Change to This Final Rule 

The Summary section of the proposed 

AD inadvertantly stated that the existing 

AD that is being superseded, AD 99–18–

07, amendment 39–11273 (64 FR 47372, 

August 31, 1999), is applicable to 

certain Boeing Model 747–400 and 747–

400D series airplanes. The existing AD 

is applicable only to certain Boeing 

Model 747–400 series airplanes. The 

Summary section of this final rule has 

been changed to correctly state that the 

existing AD is applicabe to certain 

Boeing Model 747–400 series airplanes. 

Conclusion 

We have carefully reviewed the 

available data 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. 

Cost Impact 

There are approximately 346 

airplanes of the affected design in the 

worldwide fleet. The FAA estimates that 

43 airplanes of U.S. registry will be 

affected by this AD. 

The actions that are currently 

required by AD 99–18–07, and retained 

in this AD, take approximately 9 work 

hours per ceiling panel, and between 18 

and 126 work hours per airplane to 

accomplish, at an average labor rate of 

$65 per work hour. Required parts cost 

between $1,366 and $9,575 per airplane. 

Based on these figures, the cost impact 

of the previously required actions on 

U.S. operators is estimated to be 

between $2,536 and $17,765 per 

airplane. 

The installation of new plates that is 

required by this new AD will take 

approximately 7 work hours per ceiling 

panel, and between 18 and 126 work 

hours per airplane, at an average labor 

rate of $65 per work hour. Required 

parts will cost between $1,700 and 

$12,200 per airplane. Based on these 

figures, the cost impact of the new 

requirements of this AD on U.S. 

operators is estimated to be between 

$2,870 and $20,390 per airplane. 

The cost impact figures discussed 

above are 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.

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 

removing amendment 39–11273 (64 FR 

47372, August 31, 1999), and by adding 

a new airworthiness directive (AD), 

amendment 39–13843, to read as 

follows:

2004–22–15 Boeing: Amendment 39–13843. 

Docket 2003–NM–217–AD. Supersedes 

AD 99–18–07, Amendment 39–11273.

Applicability: Model 747–400 and –400D 

series airplanes, as listed in Boeing Alert 

Service Bulletin 747–25A3142, Revision 3, 

dated August 14, 2003; certificated in any 

category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent ceiling panels from falling into 

the passenger cabin area in the event of 

failure of certain latch assemblies on the 

ceiling panels, which could result in 

Federal Register / Vol. 69, No. 213 / Thursday, November 4, 2004 / Rules and Regulations 64255

consequent injury to the flightcrew and 

passengers, accomplish the following: 

Replacement of Plate Assemblies in the 

Ceiling Panel Strap Assemblies 

(a) For airplanes on which ceiling panel 

strap assemblies were installed in accordance 

with Boeing Alert Service Bulletin 747–

25A3142, dated October 16, 1997; or 

Revision 1, dated August 6, 1998; or had 

plate assembly 411U5513–123 installed in 

production as of the effective date of this AD: 

Within 24 months after the effective date of 

this AD, replace any plate assembly having 

part number (P/N) 411U5513–123, with a 

new, improved plate assembly having P/N 

411U5513–131, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–25A3142, Revision 3, 

dated August 14, 2003. 

Installation of Ceiling Panel Strap 

Assemblies 

(b) For airplanes on which ceiling panel 

strap assemblies were not installed in 

accordance with Boeing Alert Service 

Bulletin 747–25A3142, dated October 16, 

1997; or Revision 1, dated August 6, 1998: 

Within 24 months after the effective date of 

this AD, install strap assemblies on the 

ceiling panels and rails that support the 

video monitors in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–25A3142, Revision 3, 

dated August 14, 2003. 

Actions Done per Previous Issue of Service 

Bulletin 

(c) Accomplishment of the specified 

actions before the effective date of this AD 

per Boeing Alert Service Bulletin 747–

25A3142, Revision 2, dated March 20, 2003, 

is considered acceptable for compliance with 

the applicable requirements of paragraphs (a) 

and (b) of this AD. 

Alternative Methods of Compliance 

(d)(1) In accordance with 14 CFR 39.19, the 

Manager, Seattle Aircraft Certification Office, 

FAA, is authorized to approve alternative 

methods of compliance (AMOCs) for this AD. 

(2) Alternative methods of compliance, 

approved previously in accordance with AD 

99–18–07, amendment 39–11273, are 

approved as alternative methods of 

compliance with the applicable actions of 

this AD. 

Incorporation by Reference 

(e) Unless otherwise specified in this AD, 

the actions shall be done in accordance with 

Boeing Alert Service Bulletin 747–25A3142, 

Revision 3, dated August 14, 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, 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 

(f) This amendment becomes effective on 

December 9, 2004.

Issued in Renton, Washington, on October 

21, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–24521 Filed 11–3–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–19492; Directorate 

Identifier 2004–NM–200–AD; Amendment 

39–13844; AD 2004–22–16] 

RIN 2120–AA64 

Airworthiness Directives; Gulfstream 

Model GV and GV–SP Series Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Gulfstream Model GV and GV–SP series 

airplanes. This AD requires a one-time 

general visual inspection for contact or 

insufficient clearance between the crew 

oxygen bottle/supports and any wiring 

harness, and related investigative and 

corrective actions if necessary. This AD 

also requires, for certain airplanes, 

adjusting the wiring harness to obtain a 

minimum clearance between the crew 

oxygen bottle and wiring, and applying 

Teflon sheeting, as applicable; and for 

certain other airplanes, reworking 

certain wiring bundles. This AD is 

prompted by reports of insufficient 

clearance between certain wiring 

harnesses and the crew oxygen bottle on 

several in-production and in-service 

airplanes. We are issuing this AD to 

prevent chafing of the electrical wires of 

the wiring harness against the crew 

oxygen bottle, which could result in 

electrical shorting and possible fire in 

the underfloor structure of the airplane.

DATES: Effective November 19, 2004. 

The incorporation by reference of 

certain publications listed in the AD is 

approved by the Director of the Federal 

Register as of November 19, 2004. 

We must receive comments on this 

AD by January 3, 2005.

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD. 

• DOT Docket Web site: Go to

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street SW., Nassif Building, 

room PL–401, Washington, DC 20590. 

Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

For service information identified in 

this AD, contact Gulfstream Aerospace 

Corporation, P.O. Box 2206, Mail 

Station D–10, Savannah, Georgia 31402–

9980. You can examine this information 

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.

You can examine the contents of this 

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., room PL–401, on the plaza level of 

the Nassif Building, Washington, DC. 

This docket number is FAA–2004–

19492; the directorate identifier for this 

docket is 2004–NM–200–AD.

Docket Management System (DMS) 

The FAA has implemented new 

procedures for maintaining AD dockets 

electronically. As of May 17, 2004, new 

AD actions are posted on DMS and 

assigned a docket number. We track 

each action and assign a corresponding 

directorate identifier. The DMS AD 

docket number is in the form ‘‘Docket 

No. FAA–2004–99999.’’ The Transport 

Airplane Directorate identifier is in the 

form ‘‘Directorate Identifier 2004–NM–

999–AD.’’ Each DMS AD docket also 

lists the directorate identifier (‘‘Old 

Docket Number’’) as a cross-reference 

for searching purposes. 

Examining the Dockets 

You can 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 DOT