Federal Register / Vol. 69, No. 216 / Tuesday, November 9, 2004 / Rules and Regulations 64835

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. 2003–NM–06–AD; Amendment 

39–13852; AD 2004–22–24] 

RIN 2120–AA64

Airworthiness Directives; Boeing 

Model 707 and 720 Series Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD), 

applicable to all Boeing Model 707 and 

720 series airplanes, that currently 

requires inspections of the upper and 

lower chords of the wing front and rear 

spars, repair if necessary, and 

application of corrosion inhibitor to the 

inspected areas. This amendment 

removes the requirements of the existing 

AD, requires new detailed inspections 

and new high frequency eddy current 

(HFEC) inspections for corrosion and 

cracking, and requires certain related 

follow-on and investigative actions, if 

necessary. This amendment also 

expands the area of inspection to 

include the dry bay areas. The actions 

specified by this AD are intended to 

find and fix corrosion and stress 

corrosion cracking of the upper and 

lower chords on the wing front and rear 

spars, which could result in reduced 

structural integrity of the wing. 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, PO 

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) 

by superseding AD 2001–08–02, 

amendment 39–12179 (66 FR 20383, 

April 23, 2001), which is applicable to 

all Boeing Model 707 and 720 series 

airplanes, was published in the Federal 

Register on June 3, 2004 (69 FR 31325). 

The action proposed to remove the 

requirements of the existing AD, require 

new detailed inspections and new high 

frequency eddy current (HFEC) 

inspections for corrosion and cracking, 

and require certain related follow-on 

and investigative actions, if necessary. 

The action also proposed to expand the 

area of inspection to include the dry bay 

areas. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. Due 

consideration has been given to the 

single comment received. 

Request To Waive the HFEC Inspections 

The commenter requests that the 

proposed AD be revised to permit a 

waiver for the HFEC inspections. The 

commenter states that it has been doing 

the close visual inspections specified in 

Boeing Alert Service Bulletin 3240, 

Revision 4, dated September 6, 2001 

(referenced as the appropriate source of 

service information in the proposed 

AD), and has not found any evidence of 

cracks. The commenter also states that 

doing HFEC inspections, in addition to 

the close visual inspections, would 

cause an adverse economic impact on 

its operations due to additional downtime of the airplane to accommodate 

HFEC inspections. 

The FAA does not agree to ‘‘waive’’

the requirement to perform the HFEC 

inspections. As explained in the 

preamble of the proposed AD, we have 

received a report indicating that, six 

months after an operator performed the 

visual inspections specified in Revision 

3 of Boeing Service Bulletin 3240 

(specified in AD 2001–08–02 as an 

appropriate source of service 

information) a 31-inch crack was 

detected during a routine inspection. 

We have determined that the detailed 

‘‘visual’’ inspections required by the 

previous AD are not sufficient to ensure 

that evidence of cracking is detected in 

a timely manner. Therefore, we find that 

HFEC inspections are necessary to 

ensure timely detection of any evidence 

of cracking. No change has been made 

to this final rule. 

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. 

Cost Impact 

There are approximately 230 

airplanes of the affected design in the 

worldwide fleet. The FAA estimates that 

42 airplanes of U.S. registry will be 

affected by this AD. 

The new actions in this AD do not 

include those actions required by AD 

2001–08–02. Therefore, cost impact 

figures for those actions are not 

necessary nor provided for in this AD. 

The new actions required by this AD 

will take approximately 212 work hours 

per airplane to accomplish, at an 

average labor rate of $65 per work hour. 

Based on these figures, the cost impact 

of the requirements of this AD on U.S. 

operators is estimated to be $578,760, or 

$13,780 per airplane.

The cost impact figure discussed 

above is based on assumptions that no 

operator has yet accomplished any of 

the current or proposed requirements of 

this AD, 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 

64836 Federal Register / Vol. 69, No. 216 / Tuesday, November 9, 2004 / Rules and Regulations 

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 39–12179 (66 FR 

20383, April 23, 2001), and by adding a 

new airworthiness directive (AD), 

amendment 39–13852, to read as 

follows:

2004–22–24 Boeing: Amendment 39–13852, 

Docket 2003–NM–06–AD. Supersedes 

AD 2001–08–02, Amendment 39–12179.

Applicability: All Model 707 and 720 series 

airplanes, certificated in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To find and fix corrosion and stress 

corrosion cracking of the upper and lower 

spar chords on the front and rear spars of the 

wing, which could result in reduced 

structural integrity of the wing, accomplish 

the following: 

Superseding the Requirements of AD 2001–

08–02

Note 1: As of the effective date of this AD, 

the requirements of AD 2001–08–02, 

amendment 39–12179, are no longer effective 

or required. 

Definition of Service Bulletin 

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

this AD, means the Accomplishment 

Instructions of Boeing 707 Alert Service 

Bulletin A3240, Revision 4, dated September 

6, 2001. 

Detailed Inspection 

(b) Within 30 days after the effective date 

of this AD, do a detailed inspection of the 

entire length of the external surfaces of the 

front and rear wing spar chords and the 

internal surfaces of the front spar chords in 

the dry bays of the wings for corrosion, any 

signs of corrosion (e.g., blistering or signs of 

fuel leaks), or cracking; per the service 

bulletin. If no corrosion or cracking is found, 

before further flight: Except as specified in 

paragraph (e) of this AD, accomplish any 

applicable follow-on actions or investigative 

actions, per the service bulletin. 

Other Repetitive Inspections 

(c) Within 6 months after the effective date 

of this AD, perform a detailed inspection and 

a high frequency eddy current (HFEC) 

inspection of the entire length of the external 

surfaces of the front and rear wing spar 

chords and the internal surfaces of the front 

spar chords in the dry bays of the wings for 

any corrosion, signs of corrosion (e.g., 

blistering or signs of fuel leaks), or cracking; 

per the service bulletin. If no corrosion or 

cracking is found, before further flight, 

accomplish any applicable follow-on or 

investigative actions specified in the service 

bulletin and the actions specified in 

paragraph (e) of this AD. Thereafter, repeat 

the detailed and HFEC inspections at 

intervals not to exceed 12 months. 

Repair of Corrosion 

(d) If any corrosion or signs of corrosion 

(e.g., blistering or signs of fuel leaks) are 

found during any inspection required by this 

AD: Before further flight, repair per 

paragraph (d)(1) or (d)(2) of this AD, as 

applicable. 

(1) If the corrosion is within the areas and 

limits specified in the service bulletin: 

Except as required by paragraph (e) of this 

AD, repair and accomplish all applicable 

follow-on and investigative actions, per the 

service bulletin.

(2) If the corrosion is outside the areas or 

limits specified in the service bulletin, repair 

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 (DER) who has 

been authorized by the Manager, Seattle 

ACO, to make such findings. For a repair 

method to be approved by the Manager, 

Seattle ACO, as required by this paragraph, 

the approval letter must specifically 

reference this AD. 

Application of Corrosion Inhibitor 

(e) Where the service bulletin specifies to 

apply BMS 3–23 (a corrosion inhibitor) or a 

Boeing approved equivalent, this AD requires 

that BMS 3–23 must be used or that any 

application of an equivalent corrosion 

inhibitor be approved by the Manager, Seattle 

ACO, or per data meeting the type 

certification basis of the airplane approved 

by a Boeing Company DER who has been 

authorized by the Manager, Seattle ACO, to 

make such findings. For a repair method to 

be approved by the Manager, Seattle ACO, as 

required by this paragraph, the approval 

letter must specifically reference this AD. 

Repair of Cracking 

(f) If any cracking is found during any 

inspection required by this AD, including 

cracks that have been previously stop-drilled 

but not permanently repaired: Before further 

flight, repair per a method approved by the 

Manager, Seattle ACO; or per data meeting 

the type certification basis of the airplane 

approved by a Boeing Company DER who has 

been authorized by the Manager, Seattle 

ACO, to make such findings. For a repair 

method to be approved by the Manager, 

Seattle ACO, as required by this paragraph, 

the approval letter must specifically 

reference this AD. Operators should note that 

‘‘stop drilling’’ of cracks as a means to defer 

repair is not permitted by this AD. 

Alternative Methods of Compliance 

(g) In accordance with 14 CFR 39.19, the 

Manager, Seattle ACO, is authorized to 

approve alternative methods of compliance 

for this AD. 

Incorporation by Reference 

(h) Unless otherwise specified in this AD, 

the actions shall be done in accordance with 

Boeing 707 Alert Service Bulletin A3240, 

Revision 4, dated September 6, 2001. 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, PO Box 3707, Seattle, 

Washington 98124–2207. Copies may be 

inspected at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington; or for information on the 

availability of this material at the National 

Archives and Records Administration 

(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 

26, 2004. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 04–24627 Filed 11–8–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. 2002–NM–246–AD; Amendment 

39–13854; AD 2004–22–26] 

RIN 2120–AA64

Airworthiness Directives; Airbus Model 

A330, A340–200, and A340–300 Series 

Airplanes

AGENCY: Federal Aviation 

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a 

new airworthiness directive (AD), 

applicable to certain Airbus Model 

A330, A340–200, and A340–300 series 

airplanes. This AD requires repetitive 

inspections for evidence of corrosion 

and sheared attachment bolts of the 

sensor struts at flap track 4 on the left 

and right sides of the airplane; related