[Federal Register Volume 69, Number 14 (Thursday, January 22, 2004)]
[Proposed Rules]
[Pages 3036-3039]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-1308]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-119-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, 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 amendment proposes the supersedure of an existing 
airworthiness directive (AD), applicable to certain McDonnell Douglas 
Model DC-10 series airplanes, Model MD-10 series airplanes, and Model 
MD-11 series airplanes. That AD currently 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. This action would reduce the interval between 
the repetitive inspections. The actions specified by the proposed AD 
are intended to prevent various failures

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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. This action is intended to address the identified unsafe 
condition.

DATES: Comments must be received by March 8, 2004.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2003-NM-119-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. 2003-NM-119-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 or 2000 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: 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.

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 
90712-4137; 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. 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 2003-NM-119-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 Number 2003-NM-119-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On July 2, 2001, the FAA issued AD 2001-14-08, amendment 39-12319 
(66 FR 36441, July 12, 2001), applicable to certain McDonnell Douglas 
Model DC-10 series airplanes, Model MD-10 series airplanes, and Model 
MD-11 series airplanes, to require the following actions:
    1. Do an initial detailed inspection of the number 1 and 2 electric 
motors of the auxiliary hydraulic pump for electrical resistance, 
continuity, mechanical rotation, and associated wiring resistance/
voltage.
    2. Replace any failed hydraulic pump.
    3. Troubleshoot and repair any failed wiring.
    4. Do 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.
    The initial inspections were to be conducted within 6 months after 
August 16, 2001, the effective date of AD 2001-14-08, except in one 
case. For those MD-11 and MD-11F airplanes which had accumulated fewer 
than 3,000 flight hours as of the effective date of the AD, the initial 
inspection was to be done within 6 months after accumulating 3,000 
flight hours. The repetitive inspections were to be conducted every 
6,000 flight-hours or every 18 months thereafter, whichever came first.
    That AD was prompted by reports that, during ground operations or 
when powered in flight by the air driven generator, the electric motors 
of the auxiliary hydraulic pump and associated motor feeder cables 
failed on certain McDonnell Douglas Model DC-10, MD-11, and MD-90-30 
series airplanes.
    The requirements of that AD are intended to prevent such failures 
of the 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.

Actions Since Issuance of Previous Rule

    Since the issuance of that AD, Boeing has informed the FAA that the 
original compliance time was not adequate, because another incident of 
failure of an electric motor of the auxiliary hydraulic pump had 
occurred during the interval between repetitive inspections.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletin 
DC10-29A142, Revision 02, dated April 17, 2003, pertaining to certain 
Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A, KDC-
10), DC-10-40, DC-10-40F, MD-10-10F, MD-10-30F airplanes. The FAA has 
also reviewed and approved Boeing Alert Service Bulletin MD11-29A057, 
Revision 02, dated April 17, 2003, pertaining to certain Model MD-11 
and MD-11F airplanes. The actions described in those alert service 
bulletins are essentially the same as those described in Revision 01 of 
the alert service bulletins. Revision 02 of both alert service 
bulletins recommend that the repetitive inspections of the number 1 and 
2 electric motors of the auxiliary hydraulic pump for electrical 
resistance, continuity, mechanical rotation, and associated airplane 
wiring resistance/voltage be performed ``every 2,500

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flight-hours.'' Both service bulletins also recommend that results of 
the initial inspection, either positive and negative, be sent to the 
manufacturer.

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 supersede AD 2001-14-08 to require that the 
repetitive inspections of the number 1 and 2 electric motors of the 
auxiliary hydraulic pump for electrical resistance, continuity, 
mechanical rotation, and associated airplane wiring resistance/voltage; 
and corrective actions, if necessary, be performed at intervals not to 
exceed 2,500 flight hours. The actions would be required to be 
accomplished in accordance with the service bulletins, except as 
described below.

Interim Action

    This is considered to be interim action until final action is 
identified, at which time the FAA may consider further rulemaking.

Difference Between Proposed Rule and Referenced Service Bulletins

    Operators should note that, although the Accomplishment 
Instructions of the referenced alert service bulletins describe 
procedures for reporting the results, both positive and negative of the 
initial inspection to the manufacturer, this proposed AD would not 
require those actions. The FAA does not need this information from 
operators.

Explanation of Change to Applicability in Proposed AD

    The FAA has revised the applicability of the existing AD to 
identify model designations as published in the most recent type 
certificate data sheet for the affected models. The existing AD 
specifies the applicability as ``Model DC-10 and MD-10 series 
airplanes, as listed in McDonnell Douglas Alert Service Bulletin DC10-
29A142, Revision 01, dated October 21, 1999; and Model MD-11 series 
airplanes, as listed in McDonnell Douglas Alert Service Bulletin MD11-
29A057, Revision 01, dated October 21, 1999; certificated in any 
category.''
    The proposed AD specifies the applicability as ``McDonnell Douglas 
Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A, KDC-
10), DC-10-40, DC-1040F, MD-10-10F, and MD-10-30F airplanes, as listed 
in McDonnell Douglas Alert Service Bulletin DC10-29A142, Revision 01, 
dated October 21, 1999; or Revision 02, dated April 17, 2003; and Model 
MD-11 and MD-11F airplanes, as listed in McDonnell Douglas Alert 
Service Bulletin MD11-29A057, Revision 01, dated October 21, 1999; or 
Revision 02, dated April 17, 2003; certificated in any category.

Cost Impact

    There are approximately 604 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 396 airplanes of U.S. registry 
would be affected by this proposed AD.
    The repetitive inspections that are currently required by AD 2001-
14-08 take approximately 1 work hour per airplane to accomplish, at an 
average labor rate of $65 per work hour. Based on these figures, the 
cost impact on U.S. operators of the actions currently required is 
estimated to be $25,740, or $65 per airplane, per inspection cycle. The 
cost of the repetitive inspections per inspection cycle would not 
change in the proposed AD.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the current or proposed 
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 provided 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, Safety.

Adoption of the 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 removing amendment 39-12319 (66 FR 
36441, July 12, 2001), and by adding a new airworthiness directive 
(AD), to read as follows:

McDonnell Douglas: Docket 2003-NM-119-AD. Supersedes AD 2001-14-08, 
Amendment 39-12319.

    Applicability: Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, 
DC-10-30F (KC-10A, KDC-10), DC-10-40, DC-10-40F, MD-10-10F, and MD-
10-30F airplanes, as listed in McDonnell Douglas Alert Service 
Bulletin DC10-29A142, Revision 01, dated October 21, 1999; or 
Revision 02, dated April 17, 2003; and Model MD-11 and MD-11F 
airplanes, as listed in McDonnell Douglas Alert Service Bulletin 
MD11-29A057, Revision 01, dated October 21, 1999; or Revision 02, 
dated April 17, 2003; certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    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, accomplish the following:

Service Bulletin References

    (a) The term ``service bulletin,'' as used in this AD, means the 
Accomplishment Instructions of one of the following service 
bulletins, as applicable:
    (1) For Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F 
(KC-10A, KDC-10), DC-10-40, DC-10-40F, MD-10-10F, and MD-10-30F 
airplanes: McDonnell Douglas Alert Service Bulletin DC10-29A142, 
Revision 01, dated October 21, 1999; or Revision 02, dated April 17, 
2003.
    (2) For Model MD-11 and MD-11F airplanes: McDonnell Douglas 
Alert Service Bulletin MD11-29A057, Revision 01, dated October 21, 
1999; or Revision 02, dated April 17, 2003.

    Note 1: Paragraphs (b)(1), (b)(2), and (b)(3) of this AD restate 
the requirement for an

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initial detailed inspection which was contained in paragraph (a) of 
AD 2001-14-08, amendment 39-12319. Operators who have previously 
accomplished the initial detailed inspection in accordance with 
paragraph (a) of AD 2001-14-08 need not repeat that inspection.

Initial Inspection

    (b) Do a detailed inspection 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, as specified in paragraph (b)(1), (b)(2), or 
(b)(3) of this AD, as applicable.
    (1) For Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F 
(KC-10A, KDC-10), DC-10-40, DC-10-40F, MD-10-10F, and MD-10-30F 
airplanes: Do the detailed inspection within 6 months after August 
16, 2001 (the effective date of AD 2001-14-08), in accordance with 
the service bulletin.
    (2) For Model MD-11 and MD-11F airplanes that have accumulated 
3,000 flight hours or more as of August 16, 2001: Do the detailed 
inspection within 6 months after August 16, 2002, in accordance with 
the service bulletin.
    (3) For Model MD-11 and MD-11F airplanes that have accumulated 
fewer than 3,000 flight hours as of August 16, 2002: Do the 
inspection within 6 months after accumulating 3,000 flight hours, in 
accordance with the service bulletin.

    Note 2: For the purposes of this AD, a detailed inspection is 
defined as: ``An intensive visual examination of a specific 
structural area, system, installation, or assembly to detect damage, 
failure, or irregularity. Available lighting is normally 
supplemented with a direct source of good lighting at intensity 
deemed appropriate by the inspector. Inspection aids such as mirror, 
magnifying lenses, etc., may be used. Surface cleaning and elaborate 
access procedures may be required.''

Repetitive Inspections

    (c) Repeat the inspection required by paragraph (b) of this AD 
prior to accumulating an additional 2,500 flight hours after the 
effective date of this AD or prior to accumulating 6,000 flight 
hours since the previous inspection, whichever occurs first.

Condition 1, No Failures Detected

    (d) If no failures are detected during the inspection required 
by paragraph (b) or (c) of this AD, repeat the inspection at 
intervals not to exceed 2,500 flight hours.

Condition 2, Failure of Any Pump Motor

    (e) If any pump motor fails during any inspection required by 
paragraph (b) or (c) of this AD, before further flight, replace the 
auxiliary hydraulic pump with a serviceable pump in accordance with 
the applicable service bulletin. Repeat the inspection required by 
paragraph (c) of this AD thereafter at intervals not to exceed 2,500 
flight hours.

Condition 3, Failure of Any Wiring

    (f) If any airplane wiring fails during any inspection required 
by paragraph (b) or (c) of this AD, before further flight, 
troubleshoot and repair the wiring in accordance with the applicable 
service bulletin. Repeat the inspection required by paragraph (c) of 
this AD thereafter at intervals not to exceed 2,500 flight hours.

Alternative Methods of Compliance

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

    Issued in Renton, Washington, on January 9, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-1308 Filed 1-21-04; 8:45 am]
BILLING CODE 4910-13-P