[Federal Register Volume 68, Number 199 (Wednesday, October 15, 2003)]
[Proposed Rules]
[Pages 59349-59352]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-25979]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-362-AD]
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: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain McDonnell Douglas 
airplanes as listed above. This proposal would 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 number 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: Comments must be received by December 1, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-362-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2001-NM-362-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    The service information referenced in the proposed rule may be 
obtained from Boeing Commercial Aircraft Group, Long Beach Division, 
3855 Lakewood Boulevard, Long Beach, California 90846, Attention: 
Technical Publications Business Administration, Dept. C1-L51 (2-60). 
This information may be examined 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.

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:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule.

[[Page 59350]]

    The proposals contained in this action may be changed in light of 
the comments received.
    Submit comments using the following format:
    [sbull] Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
    [sbull] For each issue, state what specific change to the proposed 
AD is being requested.
    [sbull] Include justification (e.g., reasons or data) for each 
request.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NM-362-AD.'' The postcard will be date stamped 
and returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket No. 2001-NM-362-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received several reports of failure of the auxiliary 
hydraulic pump systems on Model DC-10 airplanes. Some failures resulted 
in burnt electrical wiring leading to the electric motor of the 
auxiliary hydraulic pump, within the right wheel well area of the main 
landing gear (MLG). Damage also was found on the adjacent structure, 
control cables, hydraulic pipes, and hoses. These failures occurred 
during ground operations, or when powered in-flight by the air-driven 
generator. The failures were due to an electrical short within the 
electric motor which resulted in arcing damage. These failures 
consisted of a seized or difficult-to-turn rotor on the pump assembly, 
burnt and shorted motor feeder cables, and/or uncontained internal 
electric arcing failures within the electric motor. Investigation 
revealed that these conditions occurred on airplanes that had been in 
service several years and/or had the auxiliary hydraulic pump 
previously overhauled. These discrepancies can be caused by hydraulic 
fluid contamination to the electric motor portion of the pump assembly 
which causes failed rotor bearing, and/or degradation of the stator's 
encapsulate material. Such discrepancies, if not corrected, could 
result in fire at the auxiliary hydraulic pump and consequent damage to 
the adjacent electrical equipment and/or structure.

Explanation of Relevant Service Information

    We have reviewed and approved Boeing Alert Service Bulletin DC10-
29A144, Revision 2, dated August 1, 2003 (for 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, and MD-10-30F airplanes), which describes procedures 
for modification of the electrical wiring of the auxiliary hydraulic 
pump installation in the right wheel well area of the MLG. The 
modification includes, but is not limited to, removing existing clamps, 
ground wires (if required), and sleeving from the wire assemblies; 
inspecting for cracks and chafing, installing new support brackets, 
clips, and bracket assemblies, as applicable; installing sleeving; re-
routing the wire assemblies using new clamps and attachments, 
installing an additional routing clip on the lower bracket of the fuel 
motor control valve, if applicable, and doing a voltage check and a 
functional test.
    Service Bulletin DC10-29A144 recommends prior or concurrent 
accomplishment of Boeing Alert Service Bulletin DC10-29A142, Revision 
02, dated April 17, 2003, which describes procedures for repetitive 
inspections (checks) of the number 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. The corrective actions include 
replacing the auxiliary hydraulic pump with a serviceable pump, and 
repairing the wiring.
    We also have reviewed and approved Boeing Alert Service Bulletin 
MD11-29A059, Revision 2, dated August 1, 2003 (for Model MD-11 and MD-
11F airplanes), which describes procedures for modification of the 
wiring of the electric motors of the auxiliary hydraulic pump in the 
right wheel well area of the MLG. The modification includes, but is not 
limited to, 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.
    Service Bulletin MD11-29A059 recommends prior or concurrent 
accomplishment of Boeing Alert Service Bulletin MD11-29A057, Revision 
02, dated April 17, 2003, which describes procedures for repetitive 
inspections (checks) of the number 1 and 2 electric motors of the 
auxiliary hydraulic pumps for electrical resistance, continuity, 
mechanical rotation, associated airplane wiring resistance/voltage, and 
corrective actions if necessary. The corrective actions include 
replacing the auxiliary hydraulic pump with a serviceable pump and 
repairing the wiring.
    Accomplishment of the actions specified in the service bulletins is 
intended to adequately address the identified unsafe condition.

Related Rulemaking

    On July 2, 2001, we issued AD 2001-14-08, amendment 39-12319 (66 FR 
36441, July 12, 2001), for certain McDonnell Douglas Model DC-10 series 
airplanes, Model MD-10 series airplanes, and Model MD-11 series 
airplanes. That AD requires repetitive inspections of the number 1 and 
2 electric motors of the auxiliary hydraulic pump for electrical 
resistance, continuity, mechanical rotation, and associated wiring 
resistance/voltage; and corrective actions if necessary. The actions 
specified by that AD are intended to prevent various failures of 
electric motors of the auxiliary 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. That AD is being superseded by a separate action to reduce 
the repetitive inspection intervals currently required.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would require accomplishment of the actions specified in 
the service bulletins described previously, except that the proposed AD 
does not require completing the Evaluation Forms.

[[Page 59351]]

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 would be affected by this proposed AD.
    It would take approximately 9 work hours per airplane to do the 
modification specified in Service Bulletin DC10-29A144, at an average 
labor rate of $65 per work hour. Required parts would cost would be 
between $4,886 and $7,920 per airplane. Based on these figures, the 
cost impact of the proposed modification is estimated to be between 
$5,471 and $8,505 per airplane.
    It would take approximately 1 work hour per airplane to do the 
inspection specified in Service Bulletin DC10-29A142, at an average 
labor rate of $65 per work hour. Based on these figures, the cost 
impact of the proposed 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 would be affected by this proposed AD.
    It would take approximately 13 work hours per airplane to do the 
modification specified in Service Bulletin MD11-29A059, at an average 
labor rate of $65 per work hour. Required parts would cost between 
$5,183 and $9,182 per airplane. Based on these figures, the cost impact 
of the proposed modification is estimated to be between $6,028 and 
$10,027 per airplane.
    It would take approximately 1 work hour per airplane to do the 
inspection specified in Service Bulletin MD11-29A057, at an average 
labor rate of $65 per work hour. Based on these figures, the cost 
impact of the proposed inspection is estimated to be $65 per airplane, 
per inspection cycle.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the proposed requirements 
of this AD action, and that no operator would accomplish those actions 
in the future if this proposed 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 proposed herein would 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 proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this proposed 
regulation: (1) Is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
part 39 of the Federal Aviation Regulations (14 CFR part 39) as 
follows:

PART 39--AIRWORTHINESS DIRECTIVES

    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]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

McDonnell Douglas: 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 number 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.
    (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 number 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

[[Page 59352]]

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.

    Issued in Renton, Washington, on October 7, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-25979 Filed 10-14-03; 8:45 am]
BILLING CODE 4910-13-P