[Federal Register Volume 69, Number 216 (Tuesday, November 9, 2004)]
[Rules and Regulations]
[Pages 64835-64836]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-24627]



[[Page 64835]]

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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.

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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 
down-time 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

[[Page 64836]]

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

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 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