[Federal Register: January 30, 2004 (Volume 69, Number 20)]
[Rules and Regulations]
[Page 4450-4452]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr30ja04-3]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-43-AD; Amendment 39-13441; AD 2004-02-06]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model DC-10-10, DC-
10-10F, DC-10-15, DC-10-30, DC-10-30F, DC-10-30F (KC-10A- and KDC-10),
DC-10-40, DC-10-40F, MD-10-10F, and MD-10-30F Airplanes; and Model MD-
11 and MD-11F 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 transport category airplanes.
For certain airplanes, this amendment requires a general visual
inspection to detect cracking in the nuts on the lower attach bolt
assemblies of the forward attach bracket of the inboard flap outboard
hinge, replacement of both upper and lower attach bolt assemblies with
new bolts and nuts made from Inconel material, and replacement of
certain preload-indicating (PLI) washers with new washers. For certain
other airplanes, this amendment requires replacement of the lower
attach bolt assemblies of the inboard forward attach bracket of the
inboard flap outboard hinge with new bolts and nuts made from Inconel
material, and replacement of PLI washers with new washers. This action
is necessary to prevent separation of the inboard flap outboard hinge
from the wing structure and consequent reduced controllability of the
airplane. This action is intended to address the identified unsafe
condition.
DATES: Effective March 5, 2004.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of March 5, 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: Ronald Atmur, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137;
telephone (562) 627-5224; 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
transport category airplanes was published in the Federal Register on
September 30, 2003 (68 FR 56216). That action proposed to require, for
certain airplanes, a general visual inspection to detect cracking in
the nuts on the lower attach bolt assemblies of the forward attach
bracket of the inboard flap outboard hinge, replacement of both upper
and lower attach bolt assemblies with new bolts and nuts made from
Inconel material, and replacement of certain preload-indicating (PLI)
washers with new washers. For certain other airplanes, that action
proposed to require replacement of the lower attach bolt assemblies of
the inboard forward attach bracket of the inboard flap outboard hinge
with new bolts and nuts made from Inconel material, and replacement of
PLI washers with new washers.
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.
[[Page 4451]]
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 394 Model DC-10 and Model MD-10 airplanes,
and approximately 192 Model MD-11 and -11F airplanes of the affected
design in the worldwide fleet. The FAA estimates that 252 DC-10 and
Model MD-10 airplanes, and 76 Model MD-11 and -11F airplanes of U.S.
registry will be affected by this AD, and that the average labor rate
is $65 per hour.
The following table shows the estimated cost impact for airplanes
affected by this AD:
Table--Cost Impact Estimate
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Labor cost per Parts cost per
Model Work hours airplane airplane Fleet cost
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DC-10 and MD-10 airplanes....................... 25 $1,625 $4,139 $1,452,528
MD-11 and -11F airplanes........................ 13 845 2,041 219,336
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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.
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:
2004-02-06 McDonnell Douglas: Amendment 39-13441. Docket 2003-NM-43-
AD.
Applicability: Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30,
DC-10-30F, DC-10-30F (KC-10A- and KDC-10), DC-10-40, DC-10-40F, MD-
10-10F, and MD-10-30F airplanes, as listed in Boeing Alert Service
Bulletin DC10-57A149, dated January 7, 2003; and Model MD-11 and MD-
11F airplanes, as listed in Boeing Alert Service Bulletin MD11-
57A068, dated January 7, 2003; certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent separation of the inboard flap outboard hinge from
the wing structure and consequent reduced controllability of the
airplane, accomplish the following:
Replacements Accomplished per Previous Service Bulletins
(a) Replacements of steel bolts and nuts with Inconel bolts and
nuts accomplished before the effective date of this AD per Boeing
Service Bulletin DC10-57-116, Revision 01, dated November 25, 1996;
Boeing Service Bulletin DC10-57-116, Revision 02, dated December 22,
1998; Boeing Service Bulletin DC10-57-116, Revision 03, dated May
12, 1999; and per Condition 1, Group 1 or 2, Option 1, of Boeing
Alert Service Bulletin MD11-57A067, including Appendices A and B,
dated July 10, 2002; are considered acceptable for compliance with
the corresponding action specified in this AD.
General Visual Inspection, Model DC-10 and MD-10 Airplanes
(b) Within six months after the effective date of this AD, for
all affected Model DC-10 and MD-10 airplanes, remove the
encapsulating sealant from the nut side only of both assemblies and
do a general visual inspection of the inboard flap, outboard hinge,
forward attach bracket, lower attach bolt assembly nuts to detect
cracking in the nuts, in accordance with the Accomplishment
Instructions in Boeing Alert Service Bulletin DC10-57A149, dated
January 7, 2003.
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.''
Replacement, Model DC-10 and MD-10 Airplanes
(c) Following the general visual inspection described in
paragraph (b) of this AD, for all affected Model DC-10 and MD-10
airplanes, accomplish the applicable action(s) described in Table 1
of this AD at the specified times, per the Accomplishment
Instructions in Boeing Alert Service Bulletin DC10-57A149, dated
January 7, 2003. Although the Accomplishment Instructions specify to
submit certain information and discrepant parts to the manufacturer,
this AD does not include such a requirement.
[[Page 4452]]
Table 1.--Inspection and Replacement, Model DC-10 and MD-10 Airplanes
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Condition Actions to accomplish
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(1) Cracks in either nut............................ (i) Option 1 (Preferred): Prior to further flight, replace
both upper and lower attach bolt assemblies with new
bolts and nuts made from Inconel material.
(ii) Option 2: Prior to further flight, replace both lower
attach bolt assemblies with new bolts and nuts made from
Inconel material, and replace the preload-indicating
(PLI) washers with new washers. Within 24 months after
the effective date of this AD, replace both upper attach
bolt assemblies with new bolts and nuts made from Inconel
material, and replace the preload-indicating (PLI)
washers with new washers.
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(2) No cracks in nuts............................... Within 24 months after the effective date of this AD,
replace both upper and lower attach bolt assemblies with
bolts and nuts made from Inconel material, and replace
the PLI washers with new washers, as applicable.
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Replacement, Model MD-11 and -11F Airplanes
(d) Replace the inboard flap, outboard hinge, forward attach
bracket, lower attach bolt assemblies of the affect Model MD-11 and
MD-11F airplanes with new bolts and nuts made from Inconel material
and replace the PLI washers with new PLI washers within the
compliance time for the applicable condition described in Table 2 of
this AD. Accomplish all replacements per the Accomplishment
Instructions in Boeing Alert Service Bulletin MD11-57A068, dated
January 7, 2003.
Table 2.--Condition and Compliance Time, Model MD-11 and -11F Airplanes
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Condition Compliance time
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MD-11 and MD-11F airplanes that have not replaced steel Within 18 months after the effective date of this AD.
bolts and nuts with new like parts or Inconel bolts
per group 1 or 2, option 1 or 2 of Boeing Alert
Service Bulletin MD11-57A067, including Appendices A
and B, dated July 10, 2002.
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MD-11 and MD-11F airplanes that have replaced steel Within 36 months after the effective date of this AD.
bolts and nuts with new steel bolts and steel nuts per
group 1 or 2, option 2, table 2, note 7 of Boeing
Alert Service Bulletin MD11-57A067, including
Appendices A and B, dated July 10, 2002.
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MD-11 and MD-11F airplanes that have replaced steel Within 60 months after the effective date of this AD.
bolts and nuts with new steel bolts and new Inconel
nuts per Group 1 or 2, Option 2 of Boeing Alert
Service Bulletin MD11-57A067, including Appendices A
and B, dated July 10, 2002.
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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) The actions shall be done in accordance with Boeing Alert
Service Bulletin DC10-57A149, dated January 7, 2003; or Boeing Alert
Service Bulletin MD11-57A068, dated January 7, 2003; as applicable.
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 March 5, 2004.
Issued in Renton, Washington, on January 20, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-1909 Filed 1-29-04; 8:45 am]
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