Document ID: FAA-2008-0735-0001
Agency: faa
Document Type: Rule
Title: 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
Posted Date: 2008-07-28T04:00Z

[Federal Register: July 28, 2008 (Volume 73, Number 145)]
[Proposed Rules]               
[Page 43643-43646]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr28jy08-11]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0735; Directorate Identifier 2008-NM-085-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 (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to certain McDonnell Douglas transport 
category airplanes. The existing AD currently 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; 
repetitive inspections of the numbers 1 and 2 electric motors of the 
auxiliary hydraulic pumps for electrical

[[Page 43644]]

resistance, continuity, mechanical rotation, and associated airplane 
wiring resistance/voltage; and corrective actions if necessary. This 
proposed AD would, for certain airplanes, also require modifying and 
rerouting, as applicable, certain components of the wiring of the 
electric motor for the auxiliary hydraulic pump located in the right 
wheel well. This proposed AD results from reports of failure of the 
electric motor for the auxiliary hydraulic pump. We are proposing this 
AD 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.

DATES: We must receive comments on this proposed AD by September 11, 
2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Boeing 
Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, 
Long Beach, California 90846, Attention: Data and Service Management, 
Dept. C1-L5A (D800-0024).

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (telephone 800-647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

FOR FURTHER INFORMATION CONTACT: Ken Sujishi, Aerospace Engineer, Cabin 
Safety/Mechanical and Environmental Systems Branch, ANM-150L, 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

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0735; 
Directorate Identifier 2008-NM-085-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On February 26, 2004, we issued AD 2004-05-20, amendment 39-13515 
(69 FR 11504, March 11, 2004), for 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. 
That AD 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. That AD resulted from several reports of failure of the 
auxiliary hydraulic pump systems on Model DC-10 airplanes. We issued 
that AD 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.

Actions Since Existing AD Was Issued

    Since we issued AD 2004-05-20, we have determined that the actions 
specified in Boeing Alert Service Bulletin DC10-29A144, Revision 2, 
dated August 1, 2003, do not completely resolve the unsafe condition 
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, and DC-10-40F airplanes. (We referred to that 
service bulletin in AD 2004-05-20 as the appropriate source of service 
information for modifying the installation wiring of the electric 
motor-operated auxiliary hydraulic pumps in the right wheel well area 
of the main landing gear for the airplanes listed above and for Model 
MD-10-10F and MD-10-30F airplanes.) Boeing has now issued new service 
information, described below, that includes revised procedures to 
resolve the unsafe condition 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, and DC-10-40F 
airplanes.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin DC10-29A148, dated 
March 20, 2008, for 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, and 
DC-10-40F airplanes. The service bulletin describes procedures for 
modifying and rerouting, as applicable, certain components of the 
wiring of the electric motor for the auxiliary hydraulic pump located 
in the right main landing gear wheel well.
    The rerouting involves relocating bracket assemblies to meet 
certain specified dimensions, or rerouting the brake pressure sensor 
wire assembly, as applicable.
    The modification includes various installations, and investigative 
(inspections, checks) and corrective actions, as applicable. The 
installations and the investigative and corrective actions are 
described below:
     Installing a new support assembly, new nut clips, and new 
bracket assemblies.
     Inspecting the wire insulation for cracks, splits or 
tears, and for evidence of wire chafing.
     Replacing wires if necessary.
     Installing protective sleeving.
     Checking the resistance of the electric motor ground 
wires, and corrective action if the resistance is not within the 
specified measurement. The corrective action for incorrect resistance 
involves checking the electrical bond surface; inspecting wires for 
cracks, damage, corrosion, or cross connection; checking sockets and 
lugs for proper crimp and ground studs for proper torque; and replacing 
the wire, socket, lug, and ground stud if necessary.
    We have also reviewed Boeing Alert Service Bulletin DC10-29A142, 
Revision 3, dated October 15, 2005, for McDonnell Douglas Model DC-10-
10, DC-10-10F, DC-10-15, DC-10-30, DC-

[[Page 43645]]

10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, and MD-10-
30F airplanes. We referred to Boeing Alert Service Bulletin DC10-
29A142, Revision 02, dated April 17, 2003, in AD 2004-05-20 as the 
appropriate source of service information for doing prior/concurrent 
actions. The procedures in Revision 3 are essentially the same as those 
in Revision 02, with editorial changes that do not affect how the 
actions are done.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to develop on other airplanes of the 
same type design. For this reason, we are proposing this AD, which 
would supersede AD 2004-05-20, and would retain the requirements of the 
existing AD. This proposed AD would also require accomplishing the 
actions specified in Boeing Alert Service Bulletin DC10-29A148 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, and DC-10-40F airplanes.

Change to Existing AD

    This proposed AD would retain all requirements of AD 2004-05-20. 
Since AD 2004-05-20 was issued, the AD format has been revised, and 
certain paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers have changed in this proposed AD, as listed in 
the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                             Corresponding  requirement
       Requirement in AD 2004-05-20             in this  proposed AD
------------------------------------------------------------------------
Paragraph (a).............................  Paragraph (f).
Paragraph (b).............................  Paragraph (g).
------------------------------------------------------------------------

Costs of Compliance

    There are about 409 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this proposed AD.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                            Average                                                    Number of
                                                             labor                                                       U.S.-
               Action                     Work hours        rate per           Parts             Cost per airplane     registered        Fleet cost
                                                              hour                                                     airplanes
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Modification (required by AD 2004-   9...................        $80  $4,886 to $7,920......  $5,606 to $8,640......          322  $1,805,132 to
 05-20).                                                                                                                            $2,782,080.
Inspection (required by AD 2004-05-  1...................         80  $0....................  $80, per inspection             322  $25,760, per
 20).                                                                                          cycle.                               inspection cycle.
Modification/rerouting (new          2 to 18.............         80  $5,380 to $5,872......  $5,540 to $7,312......          128  $709,120 to $935,936.
 proposed action).
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Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD 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.
    For the reasons discussed above, I certify that the 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. 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket. See the 
ADDRESSES section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-13515 (69 FR 11504, March 11, 2004) and adding 
the following new airworthiness directive (AD):

McDonnell Douglas: Docket No. FAA-2008-0735; Directorate Identifier 
2008-NM-085-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by September 
11, 2008.

Affected ADs

    (b) This AD supersedes AD 2004-05-20.

Applicability

    (c) This AD applies to 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; 
certificated in any category; as identified in the applicable 
service bulletin listed in Table 1 of this AD.

[[Page 43646]]

                                     Table 1.--Airplanes Affected by This AD
----------------------------------------------------------------------------------------------------------------
       McDonnell Douglas model--                Identified in--                     Referenced in--
----------------------------------------------------------------------------------------------------------------
DC-10-10, DC-10-10F, DC-10-15, DC-10-    Boeing Alert Service          Paragraph (f) of this AD.
 30, DC-10-30F (KC-10A and KDC-10), DC-   Bulletin DC10-29A144,
 10-40, DC-10-40F, MD-10-10F, and MD-10-  Revision 2, dated August 1,
 30F airplanes.                           2003.
MD-11 and MD-11F airplanes.............  Boeing Alert Service          Paragraph (g) of this AD.
                                          Bulletin MD11-29A059,
                                          Revision 2, dated August 1,
                                          2003.
DC-10-10, DC-10-10F, DC-10-15, DC-10-    Boeing Alert Service          Paragraph (h) of this AD.
 30, DC-10-30F (KC-10A and KDC-10), DC-   Bulletin DC10-29A148, dated
 10-40, and DC-10-40F airplanes.          March 20, 2008.
----------------------------------------------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from reports of failure of the electric 
motor for the auxiliary hydraulic pump. We are issuing this AD 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.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Restatement of the Requirements of AD 2004-05-20

Modification/Prior or Concurrent Actions

    (f) 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 listed in Boeing Alert Service Bulletin DC10-29A144, 
Revision 2, dated August 1, 2003: Within 18 months after April 15, 
2004 (the effective date of AD 2004-05-20), do the actions specified 
in paragraphs (f)(1) and (f)(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 the lower 
bracket of the 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 concurrently with accomplishment of paragraph 
(f)(1) or (h) of this AD: Do the actions specified in Boeing Alert 
Service Bulletin DC10-29A142, Revision 02, dated April 17, 2003; or 
Revision 3, dated October 15, 2005; (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. After the effective date of this AD, 
Revision 3 must be used.
    (g) For Model MD-11 and MD-11F airplanes listed in Boeing Alert 
Service Bulletin MD11-29A059, Revision 2, dated August 1, 2003: 
Within 18 months after April 15, 2004, do the actions specified in 
paragraphs (g)(1) and (g)(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 concurrently with accomplishment of paragraph 
(g)(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.

New Requirements of This AD

Modification and Rerouting

    (h) 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, and DC-10-40F airplanes identified in 
Boeing Alert Service Bulletin DC10-29A148, dated March 20, 2008: 
Within 24 months after the effective date of this AD, modify and 
reroute, as applicable, components of the wiring of the electric 
motor for the auxiliary hydraulic pump located in the right wheel 
well, and do all applicable investigative and corrective actions 
before further flight. Do all actions in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin DC10-
29A148, dated March 20, 2008. The concurrent requirements, including 
the repetitive inspections, of paragraph (f)(2) of this AD continue 
to apply to these airplanes.

Alternative Methods of Compliance (AMOCs)

    (i)(1) The Manager, Los Angeles Aircraft Certification Office 
(ACO), FAA, has the authority to approve AMOCs for this AD, if 
requested in accordance with the procedures found in 14 CFR 39.19.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.

    Issued in Renton, Washington, on July 21, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-17198 Filed 7-25-08; 8:45 am]

BILLING CODE 4910-13-P