[Federal Register Volume 68, Number 105 (Monday, June 2, 2003)]
[Proposed Rules]
[Pages 32693-32695]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-13659]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-387-AD]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model DC-9-81 (MD-
81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 
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 airplane 
models. This proposal would require a one-time inspection for chafing 
or signs of arcing of the wire bundle for the auxiliary hydraulic pump, 
follow-on actions, and corrective actions if necessary. This action is 
necessary to prevent shorted wires or arcing at the auxiliary hydraulic 
pump, which could result in loss of auxiliary hydraulic power, or a 
fire in the wheel well of the airplane. This action is intended to 
address the identified unsafe condition.

DATES: Comments must be received by July 17, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-387-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056.

[[Page 32694]]

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-387-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 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: Elvin Wheeler, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130L, FAA, Los Angeles Aircraft 
Certification Office, 3960 Paramount Boulevard, Lakewood, California 
90712-4137; telephone (562) 627-5344; 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 2001-NM-387-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-387-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received reports of shorted wires and evidence of 
arcing on the power cables of the auxiliary hydraulic pump on several 
McDonnell Douglas Model DC-9-83 airplanes. One incident of arcing 
resulted in a fire in the airplane wheel well. Investigation revealed 
that the backshell connector assembly was damaged from sharp bending of 
the wires and chafed wires in the wheel well. This condition, if not 
corrected, could lead to shorted wires or arcing at the auxiliary 
hydraulic pump, which could result in loss of auxiliary hydraulic 
power, or a fire in the wheel well of the airplane.
    The wire bundle for the auxiliary hydraulic pump on certain Model 
DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-87 (MD-87), and MD-88 airplanes 
is identical to that installed on the affected Model DC-9-83 (MD-83) 
airplanes. Therefore, all of these models may be subject to the same 
unsafe condition.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletin 
MD80-29A068, Revision 02, dated November 19, 2002. (That service 
bulletin ``supersedes and cancels'' McDonnell Douglas Service Bulletins 
MD80-29-042 and MD80-29-048.) Boeing Alert Service Bulletin MD80-
29A068, Revision 02, describes procedures for a one-time inspection for 
chafing or signs of arcing of the wire bundle for the auxiliary 
hydraulic pump, follow-on actions, and corrective action if necessary. 
Follow-on actions include rerouting the wire bundle, replacing the 
existing straight connector backshell assembly with a new 90-degree 
backshell connector assembly, replacing an existing bracket with a new 
improved bracket, replacing existing connector contacts with new 
contacts, and installing protective sleeving. Corrective actions, 
depending on conditions found during the inspection, include repairing 
chafing damage or replacing any damaged wire with a new wire. 
Accomplishment of the actions specified in the service bulletin is 
intended to adequately address the identified unsafe condition.

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 bulletin described previously.

Changes to 14 CFR Part 39/Effect on the Proposed AD

    On July 10, 2002, the FAA issued a new version of 14 CFR part 39 
(67 FR 47997, July 22, 2002), which governs the FAA's airworthiness 
directives system. The regulation now includes material that relates to 
altered products, special flight permits, and alternative methods of 
compliance. Because we have now included this material in part 39, we 
no longer need to include it in each individual AD.

Cost Impact

    There are approximately 1,063 Model DC-9-81 (MD-81), DC-9-82 (MD-
82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 732 
airplanes of U.S. registry would be affected by this proposed AD.
    It would take approximately 1 work hour per airplane to accomplish 
the proposed inspection, at an average labor rate of $60 per work hour. 
Based on these figures, the cost impact of the proposed inspection on 
U.S. operators is estimated to be $43,920, or $60 per airplane.
    It would take approximately 3 work hours per airplane to accomplish 
the proposed follow-on actions, at an average labor rate of $60 per 
work hour. Required parts would cost approximately $48 per airplane. 
Based on these figures, the cost impact of the proposed AD on U.S. 
operators is estimated to be $166,896, or $228 per airplane.

[[Page 32695]]

    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. The manufacturer may 
cover the cost of replacement parts associated with this proposed AD, 
subject to warranty conditions. Manufacturer warranty remedies may also 
be available for labor costs associated with this proposed AD. As a 
result, the costs attributable to the proposed AD may be less than 
stated above.

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-387-AD.

    Applicability: Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 
(MD-83), DC-9-87 (MD-87), and MD-88 airplanes; as listed in Boeing 
Alert Service Bulletin MD80-29A068, Revision 02, dated November 19, 
2002; certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent shorted wires or arcing at the auxiliary hydraulic 
pump, which could result in loss of auxiliary hydraulic power, or a 
fire in the wheel well of the airplane, accomplish the following:

One-Time Inspection

    (a) Within 18 months after the effective date of this AD, do a 
one-time general visual inspection for chafing or signs of arcing of 
the wire bundle for the auxiliary hydraulic pump, per the 
Accomplishment Instructions of Boeing Alert Service Bulletin MD80-
29A068, Revision 02, dated November 19, 2002. Start inspecting at 
the P1-32 plug and end at the fuel tank bulkhead. Before further 
flight after the inspection, do paragraphs (a)(1) and (a)(2) of this 
AD, as applicable, per the Accomplishment Instructions of the 
service bulletin.

    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.''


    Note 2: Boeing Alert Service Bulletin MD80-29A068, Revision 02, 
dated November 19, 2002, ``supersedes and cancels'' McDonnell 
Douglas Service Bulletins MD80-29-042 and MD80-29-048.

Corrective Actions

    (1) If any chafing or sign of arcing is found, repair chafing 
damage or replace any damaged wire with a new wire, as applicable.

Follow-On Actions

    (2) Perform all applicable follow-on actions specified in the 
service bulletin, including, but not limited to, rerouting the wire 
bundle, replacing the existing straight connector backshell assembly 
with a new 90-degree connector backshell assembly, replacing an 
existing bracket with a new improved bracket, replacing existing 
connector contacts with new contacts, and installing protective 
sleeving.

Alternative Methods of Compliance

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

    Issued in Renton, Washington, on May 23, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-13659 Filed 5-30-03; 8:45 am]
BILLING CODE 4910-13-P