58256 Federal Register / Vol. 69, No. 189 / Thursday, September 30, 2004 / Rules and Regulations 

Alternative Methods of Compliance 

(AMOCs) 

(g) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

Related Information 

(h) French airworthiness directive F–2004–

117, dated July 21, 2004, also addresses the 

subject of this AD. 

Material Incorporated by Reference 

(i) Unless the AD specifies otherwise, you 

must use the temporary revisions to the 

applicable Airbus A330 or A340 Airplane 

Flight Manual, listed in Table 3 of this AD, 

to perform the actions that are required by 

this AD:

TABLE 3.—INCORPORATION BY REFERENCE

Temporary revision— Date—

4.02.00/23 ................................................................................. June 28, 2004. 

4.02.00/24 ................................................................................. June 28, 2004. 

4.02.00/38 ................................................................................. June 28, 2004. 

4.02.00/39 ................................................................................. June 28, 2004. 

The Director of the Federal Register 

approves the incorporation by reference of 

this document in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. For copies of the 

service information, contact Airbus, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France. You can review copies at the 

Docket Management Facility, U.S. 

Department of Transportation, 400 Seventh 

Street SW., room PL–401, Nassif Building, 

Washington, DC; 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 Renton, Washington, on 

September 20, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–21650 Filed 9–29–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–NM–44–AD; Amendment 

39–13807; AD 2004–20–02] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 707 and 720 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to all Boeing Model 707 and 

720 series airplanes, that requires an 

inspection of the main landing gear 

(MLG) lock support fitting and the wing 

fillet flap support link for damage, and 

corrective action, if necessary; and 

replacement of the bolts and bushings at 

the joint between the MLG lock support 

fitting and the wing fillet flap support 

link. This action is necessary to prevent 

stress corrosion cracking of the bolts 

and wearing of the joint between the 

lock support fitting and the support 

link, which could lead to failure of the 

joint and could cause the collapse of the 

MLG. This action is intended to address 

the identified unsafe condition.

DATES: Effective November 4, 2004. 

The incorporation by reference of a 

certain publication listed in the 

regulations is approved by the Director 

of the Federal Register as of November 

4, 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:

Candice Gerretsen, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6428; 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 all Boeing Model 

707 and 720 series airplanes was 

published in the Federal Register on 

February 13, 2004 (69 FR 7174). That 

action proposed to require an inspection 

of the main landing gear (MLG) lock 

support fitting and the wing fillet flap 

support link for damage, and corrective 

action, if necessary; and replacement of 

the bolts and bushings at the joint 

between the MLG lock support fitting 

and the wing fillet flap support link. 

Comment 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. Due 

consideration has been given to the one 

comment received. 

Request To Revise ‘‘Parts Installation’’

Paragraph 

One commenter requests to revise 

‘‘Parts Installation’’ paragraph (e) of the 

proposed AD. The commenter suggests 

including ‘‘and no person shall install a 

bushing other than an aluminum nickel 

bronze * * *.’’ The commenter notes 

that the root cause of the unsafe 

condition of the proposed AD is 

corrosion and galling between the bolt 

and steel bushings. 

We agree with the commenter. We 

inadvertently omitted the bushings from 

paragraph (e) of the proposed AD. As 

specified in paragraph (d) of the 

proposed AD, bolts and bushings are to 

be replaced with new CRES bolts and 

Cadmium-plated Al-Ni-Br bushings. The 

intent of paragraph (e) of the proposed 

AD was to prevent bolts and bushings 

other than CRES bolts and Cadmiumplated Al-Ni-Br bushings from being 

installed. We have revised paragraph (e) 

of the final rule accordingly. 

Conclusion 

After careful review of the available 

data, including the comment noted 

above, we have determined that air 

safety and the public interest require the 

adoption of the rule with the changes 

previously described. We have 

determined that these changes will 

neither increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Cost Impact 

There are approximately 230 

airplanes of the affected design in the 

Federal Register / Vol. 69, No. 189 / Thursday, September 30, 2004 / Rules and Regulations 58257

worldwide fleet. We estimate that 42 

airplanes of U.S. registry will be affected 

by this AD, that it will take 

approximately 14 work hours per 

airplane to accomplish the required 

replacement and inspections, 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 $38,220, or $910 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. 

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:

2004–20–02 Boeing: Amendment 39–13807. 

Docket 2003–NM–44–AD.

Applicability: All Model 707 and 720 series 

airplanes, certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously.

To prevent stress corrosion cracking of the 

bolts and wearing of the joint between the 

lock support fitting and the support link, 

which could lead to failure of the joint and 

could cause the collapse of the main landing 

gear (MLG), accomplish the following: 

Service Bulletin References 

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

this AD, means the Accomplishment 

Instructions of Boeing 707 Alert Service 

Bulletin A3511, dated January 23, 2003. 

Initial Inspection 

(b) Within 12 months or 1,000 flight cycles 

after the effective date of this AD, whichever 

comes first, perform a high frequency eddy 

current (HFEC) inspection of the MLG lock 

support fitting and the support link for cracks 

and corrosion in accordance with the service 

bulletin. 

Corrective Actions 

(c) If any crack or corrosion is found, 

during the HFEC inspection required by 

paragraph (b) of this AD, before further flight, 

rework the lock support fitting or support 

link, in accordance with the service bulletin, 

except as specified in paragraphs (c)(1) and 

(c)(2) of this AD. 

(1) If the service bulletin specifies to 

contact Boeing for rework limits: Before 

further flight, repair or replace the lock 

support fitting or support link per a method 

approved by the Manager, Seattle Aircraft 

Certification Office (ACO), FAA; or per data 

meeting the type certification basis of the 

airplane approved by a Boeing Company 

Designated Engineering Representative who 

has been authorized by the Manager, Seattle 

ACO, to make such findings. For a repair/

replacement method to be approved, the 

approval must specifically reference this AD. 

(2) Where the service bulletin specifies to 

rework the forward and aft lug bore and faces 

common to the lock support fitting of the 

MLG as given in Boeing Service Bulletin 

707–2837, this AD requires rework to be 

accomplished only in accordance with 

Revision 5 of Boeing 707 Service Bulletin 

2837, dated March 31, 1978. 

Replacement of Bolts and Bushings 

(d) Within 12 months or 1,000 flight cycles 

after the effective date of this AD, whichever 

comes first, replace the bolts and bushings at 

the joint between the lock support fitting for 

the MLG and the wing fillet flap with new 

CRES bolts and Cadmium-plated Al-Ni-Br 

bushings in accordance with the service 

bulletin. 

Parts Installation 

(e) As of the effective date of this AD, only 

bolts specified in paragraph (e)(1) of this AD 

and bushings specified in paragraph (e)(2) of 

this AD, may be installed at the joint between 

the MLG lock support fitting and the support 

link, on any airplane. 

(1) CRES bolts, part number (P/N) 

BACB30LR10DK56 or P/N 

BACB30LR10DK62. 

(2) Cadmium-plated aluminum nickel 

bronze bushings as specified in the service 

bulletin. 

Alternative Methods of Compliance 

(f) In accordance with 14 CFR 39.19, the 

Manager, Seattle ACO, FAA, is authorized to 

approve alternative methods of compliance 

for this AD. 

Incorporation by Reference 

(g) Unless otherwise specified in this AD, 

the actions shall be done in accordance with 

Boeing 707 Alert Service Bulletin A3511, 

dated January 23, 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 

(h) This amendment becomes effective on 

November 4, 2004.

Issued in Renton, Washington, on 

September 16, 2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–21649 Filed 9–29–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2003–NE–57–AD; Amendment 

39–13798; AD 2004–19–04] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc RB211–22B, RB211–524, and 

RB211–535 Series Turbofan Engines

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule; correction.