[Federal Register Volume 69, Number 28 (Wednesday, February 11, 2004)]
[Rules and Regulations]
[Pages 6532-6533]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-2581]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-213-AD; Amendment 39-13465; AD 2004-03-21]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model 717-200
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain McDonnell Douglas Model 717-200 airplanes, that
requires inspection of the inboard ends of the outer skin panels of the
horizontal stabilizer at Station Xh=7.234 for
material defects, and corrective action, if necessary. This action is
necessary to detect material defects in the inboard ends of the outer
skin panels of the horizontal stabilizer, which could lead to cracks
and an associated loss of strength in the attachments, and consequent
reduced structural integrity of the horizontal stabilizer. This action
is intended to address the identified unsafe condition.
DATES: Effective March 17, 2004.
The incorporation by reference of a certain publication listed in
the regulations is approved by the Director of the Federal Register as
of March 17, 2004.
ADDRESSES: The service information referenced in this AD may be
obtained from Boeing Commercial Airplanes, Long Beach Division, 3855
Lakewood Boulevard, Long Beach, California 90846, Attention: Data and
Service Management, Dept. C1-L5A (D800-0024). 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 FAA, Los Angeles Aircraft Certification Office,
3960 Paramount Boulevard, Lakewood, California; or at the Office of the
Federal Register, 800 North Capitol Street, NW., suite 700, Washington,
DC.
FOR FURTHER INFORMATION CONTACT: Maureen Moreland, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137;
telephone (562) 627-5238; fax (562) 627-5210.
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 certain McDonnell Douglas Model
717-200 airplanes was published in the Federal Register on September
18, 2003 (68 FR 54690). That action proposed to require inspection of
the inboard ends of the outer skin panels of the horizontal stabilizer
at Station Xh=7.234 for material defects, and
corrective action, if necessary.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were submitted in response
to the proposal or the FAA's determination of the cost to the public.
Conclusion
The FAA has determined that air safety and the public interest
require the adoption of the rule as proposed.
Cost Impact
There are approximately 56 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 41 airplanes of U.S. registry
will be affected by this AD, that it will take approximately 4 work
hours per airplane to accomplish the required inspection, 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 $10,660, or
$260 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
[[Page 6533]]
incidental costs, such as the time required to gain access and close
up, planning time, or time necessitated by other administrative
actions. Manufacturer warranty remedies may be available for labor
costs associated with this proposed AD. As a result, the costs
attributable to the proposed AD may be less than stated above.
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:
2004-03-21 McDonnell Douglas: Amendment 39-13465. Docket 2002-NM-
213-AD.
Applicability: Model 717-200 airplanes, as listed in Boeing
Service Bulletin 717-55-0005, dated June 27, 2002; certificated in
any category.
Compliance: Required as indicated, unless accomplished
previously.
To detect material defects in the inboard ends of the outer skin
panels of the horizontal stabilizer at Station Xh=7.234, which could lead to cracks and an associated
loss of strength in the attachments, and consequent reduced
structural integrity of the horizontal stabilizer, accomplish the
following:
Inspection
(a) Prior to the accumulation of 10,000 total flight cycles, or
within 15 months after the effective date of this AD, whichever
occurs later, do an ultrasonic inspection of the inboard ends of the
outer skin panels of the horizontal stabilizer at Station Xh=7.234 for material defects, per the Accomplishment
Instructions of Boeing Service Bulletin 717-55-0005, dated June 27,
2002.
Corrective Action
(b) If any defects are found during the inspection required by
paragraph (a) of this AD, and the service bulletin specifies
contacting Boeing for appropriate action: Before further flight,
repair per a method approved by the Manager, Los Angeles 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, Los Angeles ACO, to make such findings. For a repair method
to be approved, as required by this paragraph, the approval letter
must specifically refer to this AD.
Alternative Methods of Compliance
(c) In accordance with 14 CFR 39.19, the Manager, Los Angeles
ACO, FAA, is authorized to approve alternative methods of compliance
for this AD.
Incorporation by Reference
(d) Unless otherwise specified in this AD, the actions shall be
done in accordance with Boeing Service Bulletin 717-55-0005, dated
June 27, 2002. 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, Long Beach Division, 3855 Lakewood Boulevard, Long Beach,
California 90846, Attention: Data and Service Management, Dept. C1-
L5A (D800-0024). Copies may be inspected at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or
at the FAA, Los Angeles Aircraft Certification Office, 3960
Paramount Boulevard, Lakewood, California; or at the Office of the
Federal Register, 800 North Capitol Street, NW., suite 700,
Washington, DC.
Effective Date
(e) This amendment becomes effective on March 17, 2004.
Issued in Renton, Washington, on January 30, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-2581 Filed 2-10-04; 8:45 am]
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