[Federal Register: November 9, 2004 (Volume 69, Number 216)]
[Rules and Regulations]
[Page 64835-64836]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr09no04-3]
[[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]
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