Airworthiness Directives; McDonnell Douglas Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, MD-10-30F, MD-11, and MD-11F Airplanes

[Federal Register Volume 69, Number 48 (Thursday, March 11, 2004)]
[Rules and Regulations]
[Pages 11504-11506]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-4937]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-362-AD; Amendment 39-13515; AD 2004-05-20]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-10-10, DC-
10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, 
DC-10-40F, MD-10-10F, MD-10-30F, 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, 
that requires modification of the installation wiring for the electric 
motor operated auxiliary hydraulic pumps in the right wheel well area 
of the main landing gear, and repetitive inspections of the numbers 1 
and 2 electric motors of the auxiliary hydraulic pumps for electrical 
resistance, continuity, mechanical rotation, and associated airplane 
wiring resistance/voltage; and corrective actions if necessary. This 
action is necessary to prevent failure of the electric motors of the 
hydraulic pump and associated wiring, which could result in fire at the 
auxiliary hydraulic pump and consequent damage to the adjacent 
electrical equipment and/or structure. This action is intended to 
address the identified unsafe condition.

DATES: Effective April 15, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 15, 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 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: Ken Sujishi, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130L, FAA, Los Angeles Aircraft 
Certification Office, 3960 Paramount Boulevard, Lakewood, California 
90712; telephone (562) 627-5353; 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 
DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), 
DC-10-40, DC-10-40F, MD-10-10F, MD-10-30F, MD-11, and MD-11F airplanes, 
was published in the Federal Register on October 15, 2003 (68 FR 
59349). That action proposed to require modification of the 
installation wiring for the electric motor operated auxiliary hydraulic 
pumps in the right wheel well area of the main landing gear, and 
repetitive inspections of the numbers 1 and 2 electric motors of the 
auxiliary hydraulic pumps for electrical resistance, continuity, 
mechanical rotation, and associated airplane wiring resistance/voltage; 
and corrective actions if necessary.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

[[Page 11505]]

Requests To Extend Repetitive Inspection Interval

    Two commenters state that they support the intent of the proposed 
rule, but they request that the proposed repetitive inspection interval 
of 2,500 flight hours be extended to every 18 months or 6,000 flight 
hours. One commenter states that it has been inspecting the affected 
pump installations every 18 months or 6,000 flight hours and that none 
of the affected airplanes or pumps removed from the affected airplanes 
exhibit signs of arcing, burnt wiring, or other conditions indicative 
of a fire.
    The FAA does not agree that the repetitive interval should be 
extended. In the ``Discussion'' section of the preamble of the proposed 
AD we advised that investigation revealed that the unsafe condition had 
occurred on airplanes that had been in service several years and/or had 
the auxiliary hydraulic pump previously overhauled. In addition, two 
reports of short circuit failure of the motor electrical connector of 
the auxiliary hydraulic pump occurred even though the affected 
airplanes were being inspected at intervals of 18 months or 6,000 
flight hours. Therefore, we have determined that an inspection interval 
of 2,500 flight hours will provide an adequate interval to detect and 
correct the identified unsafe condition.

Conclusion

    After careful review of the available data, including the comments 
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 409 Model DC-10 airplanes of the affected 
design in the worldwide fleet. The FAA estimates that 322 airplanes of 
U.S. registry will be affected by this AD.
    It will take approximately 9 work hours per airplane to do the 
modification specified in Boeing Alert Service Bulletin DC10-29A144, at 
an average labor rate of $65 per work hour. Required parts will cost 
would be between $4,886 and $7,920 per airplane. Based on these 
figures, the cost impact of the modification is estimated to be between 
$5,471 and $8,505 per airplane.
    It will take approximately 1 work hour per airplane to do the 
inspection specified in Boeing Alert Service Bulletin DC10-29A142, at 
an average labor rate of $65 per work hour. Based on these figures, the 
cost impact of the inspection is estimated to be $65 per airplane, per 
inspection cycle.
    There are approximately 195 Model MD-11 airplanes of the affected 
design in the worldwide fleet. The FAA estimates that 74 airplanes of 
U.S. registry will be affected by this AD.
    It will take approximately 13 work hours per airplane to do the 
modification specified in Boeing Alert Service Bulletin MD11-29A059, at 
an average labor rate of $65 per work hour. Required parts will cost 
between $5,183 and $9,182 per airplane. Based on these figures, the 
cost impact of the modification is estimated to be between $6,028 and 
$10,027 per airplane.
    It will take approximately 1 work hour per airplane to do the 
inspection specified in Boeing Alert Service Bulletin MD11-29A057, at 
an average labor rate of $65 per work hour. Based on these figures, the 
cost impact of the inspection is estimated to be $65 per airplane, per 
inspection cycle.
    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 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:

2004-05-20 McDonnell Douglas: Amendment 39-13515. Docket 2001-NM-
362-AD.

    Applicability: Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, 
DC-10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, MD-
10-30F, MD-11, and MD-11F airplanes; certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent failure of the electric motors of the hydraulic pump 
and associated wiring, which could result in fire at the auxiliary 
hydraulic pump and consequent damage to the adjacent electrical 
equipment and/or structure, accomplish the following:

Modification/Prior or Concurrent Actions

    (a) For airplanes listed in Boeing Alert Service Bulletin DC10-
29A144, Revision 2, dated August 1, 2003: Within 18 months after the 
effective date of this AD, do the actions specified in paragraphs 
(a)(1) and (a)(2) of this AD.
    (1) Modify the installation wiring of the electric motor 
operated auxiliary hydraulic pumps in the right wheel well area of 
the main landing gear (MLG) (including removing existing clamps, 
ground wires, if required, and sleeving from the wire assemblies; 
inspecting for cracks and chafing, installing new support bracket, 
clips, and bracket assemblies, as applicable; installing sleeving; 
re-routing and attaching wire assemblies using new clamps and 
attachments; installing an additional routing clip on lower bracket 
of fuel motor control valve, if applicable; and doing a voltage 
check and a functional test), per the Accomplishment Instructions of 
Boeing Alert Service Bulletin DC10-29A144, Revision 2, dated August 
1, 2003.
    (2) Prior to or concurrent with accomplishment of paragraph 
(a)(1) of this AD: Do the actions specified in Boeing Alert Service 
Bulletin DC10-29A142, Revision 02, dated April 17, 2003 (including 
inspecting the numbers 1 and 2 electric motors of the auxiliary 
hydraulic pumps for electrical resistance, continuity, mechanical 
rotation,

[[Page 11506]]

and associated airplane wiring resistance/voltage; and replacing the 
auxiliary hydraulic pump with a serviceable pump and repairing the 
wiring if necessary), per the Accomplishment Instructions of the 
service bulletin. Repeat the actions after that at intervals not to 
exceed 2,500 flight hours.
    (b) For airplanes listed in Boeing Alert Service Bulletin MD11-
29A059, Revision 2, dated August 1, 2003: Within 18 months after the 
effective date of this AD, do the actions specified in paragraphs 
(b)(1) and (b)(2) of this AD.
    (1) Modify the installation wiring of the electric motor 
auxiliary hydraulic pumps in the wheel well area of the right MLG 
(including removing and retaining wire assembly clamps, if 
applicable; retaining the existing ground wire assemblies; retaining 
or replacing all other wire assemblies for both connectors; 
installing spiral wrap and sleeving; wrapping upper ends of 
individual wires with tape; installing new support bracket 
assemblies, if applicable; re-routing and attaching wire assemblies 
using new clamps and attachments, if applicable; and doing a voltage 
check and a functional test), per the Accomplishment Instructions of 
Boeing Alert Service Bulletin MD11-29A059, Revision 2, dated August 
1, 2003.
    (2) Prior to or concurrent with accomplishment of paragraph 
(b)(1) of this AD: Do the actions specified in Boeing Alert Service 
Bulletin MD11-29A057, Revision 02, dated April 17, 2003 (including 
inspecting the numbers 1 and 2 electric motors of the auxiliary 
hydraulic pumps for electrical resistance, continuity, mechanical 
rotation, and associated airplane wiring resistance/voltage; and 
replacing the auxiliary hydraulic pump with a serviceable pump and 
repairing the wiring if necessary), per the Accomplishment 
Instructions of the service bulletin. Repeat the actions after that 
at intervals not to exceed 2,500 flight hours.

Alternative Methods of Compliance

    (c) In accordance with 14 CFR 39.19, the Manager, Los Angeles 
Aircraft Certification Office, FAA, is authorized to approve 
alternative methods of compliance (AMOCs) for this AD.

Incorporation by Reference

    (d) The actions shall be done in accordance with the applicable 
service bulletins listed in the following table:

                 Table 1.--Applicable Service Bulletins
------------------------------------------------------------------------
       Service bulletin         Revision level            Date
------------------------------------------------------------------------
Boeing Alert Service Bulletin  Revision 02....  April 17, 2003.
 DC10-29A142.
Boeing Alert Service Bulletin  Revision 2.....  August 1, 2003.
 DC10-29A144.
Boeing Alert Service Bulletin  Revision 02....  April 17, 2003.
 MD11-29A057.
Boeing Alert Service Bulletin  Revision 2.....  August 1, 2003.
 MD11-29A059 including
 Appendix.
------------------------------------------------------------------------

    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, 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.

Effective Date

    (e) This amendment becomes effective on April 15, 2004.

    Issued in Renton, Washington, on February 26, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-4937 Filed 3-10-04; 8:45 am]
BILLING CODE 4910-13-P

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