AD 2004-20-02

[Federal Register Volume 69, Number 189 (Thursday, September 30, 2004)]
[Rules and Regulations]
[Pages 58256-58257]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 04-21649]


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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.

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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: 
<a href="http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html">http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html</a>.

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 Cadmium-plated 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

[[Page 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

0
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

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
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: <a href="http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html">http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html</a>.

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]
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