[Federal Register: April 14, 2004 (Volume 69, Number 72)]
[Rules and Regulations]
[Page 19758-19759]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr14ap04-3]
[[Page 19758]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-212-AD; Amendment 39-13571; AD 2004-08-02]
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 a general visual inspection to detect corrosion of the left-
and right-hand horizontal stabilizer hinge fitting bolts, barrel nuts,
and the associated holes in the horizontal stabilizer structure, and to
detect corrosion of the left- and right-hand elevator sector pinch
bolts and associated holes, as applicable; and corrective actions, if
necessary. This action is necessary to detect and correct corrosion of
the left- and right-hand horizontal stabilizer hinge fitting bolts,
barrel nuts, and associated holes in the horizontal stabilizer
structure, and the left- and right-hand elevator sector pinch bolts and
associated holes, which could lead to loss of a hinge fitting and
reduced structural integrity of the horizontal stabilizer. This action
is intended to address the identified unsafe condition.
DATES: Effective May 19, 2004.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of May 19, 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 November 26,
2003 (68 FR 66382). That action proposed to require a general visual
inspection to detect corrosion of the left- and right-hand horizontal
stabilizer hinge fitting bolts, barrel nuts, and the associated holes
in the horizontal stabilizer structure, and to detect corrosion of the
left- and right-hand elevator sector pinch bolts and associated holes,
as applicable; and corrective actions, 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 84 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 67 airplanes of U.S. registry
will be affected by this AD. The work hours vary according to the
configuration group to which the affected airplane belongs.
The following table shows the estimated cost impact for airplanes
affected by this AD:
Table--Cost Impact
----------------------------------------------------------------------------------------------------------------
Work hours per
Airplane configuration group airplane Labor rate per Cost per airplane
(estimated) work hour (estimated)
----------------------------------------------------------------------------------------------------------------
1...................................................... 61 $65 $3,965
2...................................................... 57 65 3,705
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The cost impact figures discussed above are 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. Manufacturer warranty remedies may be available
for labor costs associated with this AD. As a result, the costs
attributable to the 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.
[[Page 19759]]
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:
2004-08-02 McDonnell Douglas: Amendment 39-13571. Docket 2002-NM-
212-AD.
Applicability: Model 717-200 airplanes, as listed in Boeing
Service Bulletin 717-55-0003, dated June 18, 2002; certificated in
any category.
Compliance: Required as indicated, unless accomplished
previously.
To detect and correct corrosion of the left- and right-hand
horizontal stabilizer hinge fitting bolts, barrel nuts, and
associated holes in the horizontal stabilizer structure, and the
left- and right-hand elevator sector pinch bolts and associated
holes, which could lead to loss of a hinge fitting and reduced
structural integrity of the horizontal stabilizer; accomplish the
following:
Service Bulletin References
(a) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of Boeing Service Bulletin 717-55-0003,
dated June 18, 2002.
Initial Inspection
(b) Prior to the accumulation of 18,000 total flight cycles, or
within 15 months after the effective date of this AD, whichever is
later: Perform the general visual inspections specified in
paragraphs (c) and (d) of this AD, as applicable, in accordance with
the service bulletin.
Note 1: For the purposes of this AD, a general visual inspection
is defined as: ``A visual examination of an interior or exterior
area, installation, or assembly to detect obvious damage, failure,
or irregularity. This level of inspection is made from within
touching distance unless otherwise specified. A mirror may be
necessary to enhance visual access to all exposed surfaces in the
inspection area. This level of inspection is made under normally
available lighting conditions such as daylight, hangar lighting,
flashlight, or droplight and may require removal or opening of
access panels or doors. Stands, ladders, or platforms may be
required to gain proximity to the area being checked.''
Horizontal Stabilizer Hinge Fitting Bolt Inspection
(c) For Group 1 and Group 2 airplanes identified in paragraph
1.A.1. of the service bulletin: Perform a general visual inspection
of the left- and right-hand horizontal stabilizer hinge fitting
bolts, barrel nuts, and the associated holes in the horizontal
stabilizer for corrosion in accordance with the service bulletin.
(1) If no corrosion is found, before further flight, install
bolts and barrel nuts with applicable corrosion protection, in
accordance with the service bulletin.
(2) If any corrosion is found, before further flight, remove the
corrosion and do the actions specified in paragraph (c)(2)(i) or
(c)(2)(ii) of this AD, as applicable, in accordance with the service
bulletin.
(i) If corrosion rework is within tolerance limits, before
further flight, perform the corrective actions in accordance with
the service bulletin, as applicable.
(ii) If corrosion rework exceeds the tolerance limits and the
service bulletin specifies to contact Boeing for repair: Before
further flight, repair in accordance with a method approved by the
Manager, Los Angeles Aircraft Certification Office (ACO), FAA; or in
accordance with 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, Los
Angeles ACO, to make such findings. For a repair method to be
approved, the approval must specifically reference this AD.
Elevator Sector Pinch Bolt Inspection
(d) For Group 1 airplanes identified in paragraph 1.A.1. of the
service bulletin: Perform a general visual inspection of the left-
and right-hand elevator sector pinch bolts and associated holes for
corrosion in accordance with the service bulletin.
(1) If no corrosion is found, before further flight, install
bolts and barrel nuts with applicable corrosion protection in
accordance with the service bulletin.
(2) If any corrosion is found, before further flight, remove the
corrosion and do the actions specified in paragraph (d)(2)(i) or
(d)(2)(ii) of this AD, as applicable, in accordance with the service
bulletin.
(i) If corrosion rework is within tolerance limits, before
further flight, perform the corrective actions in accordance with
the service bulletin, as applicable.
(ii) If corrosion rework exceeds the tolerance limits and the
service bulletin specifies to contact Boeing for repair: Before
further flight, repair in accordance with a method approved by the
Manager, Los Angeles ACO, FAA; or in accordance with data meeting
the type certification basis of the airplane approved by a Boeing
Company DER who has been authorized by the Manager, Los Angeles ACO,
to make such findings. For a repair method to be approved, the
approval must specifically reference this AD.
Alternative Methods of Compliance
(e) In accordance with 14 CFR 39.19, the Manager, Los Angeles
Aircraft Certification Office (ACO), FAA, is authorized to approve
alternative methods of compliance (AMOCs) for this AD.
Incorporation by Reference
(f) Unless otherwise specified in this AD, the actions shall be
done in accordance with Boeing Service Bulletin 717-55-0003, dated
June 18, 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
(g) This amendment becomes effective on May 19, 2004.
Issued in Renton, Washington, on April 6, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-8299 Filed 4-13-04; 8:45 am]
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