[Federal Register Volume 69, Number 20 (Friday, January 30, 2004)]
[Rules and Regulations]
[Pages 4450-4452]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-1909]


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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
----------------------------------------------------------------------------------------------------------------
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
----------------------------------------------------------------------------------------------------------------

    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.
-----------------------------------------------------
(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.
----------------------------------------------------------------------------------------------------------------

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
----------------------------------------------------------------------------------------------------------------
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.
--------------------------------------------------------
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.
--------------------------------------------------------
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.
----------------------------------------------------------------------------------------------------------------

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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