[Federal Register Volume 64, Number 77 (Thursday, April 22, 1999)]
[Rules and Regulations]
[Pages 19689-19691]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-10178]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NM-44-AD; Amendment 39-11135; AD 99-09-03]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model MD-11 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain McDonnell Douglas Model MD-11 series 
airplanes. This action requires a one-time inspection of the wiring and 
wire bundles of the aft main avionics rack (MAR) to determine if the 
wires are damaged, or riding or chafing on structure, clamps, braces, 
standoffs, or clips, and to detect damaged or out of alignment rubber 
cushions inserts of the wiring clamps; and corrective actions, if 
necessary. This amendment is prompted by an incident in which the 
automatic and manual cargo door test in the cockpit was inoperative 
during dispatch of the airplane, due to the wiring of the MAR chafing 
against clamps as a result of the wire bundles being installed 
improperly during production of the airplane. The actions specified in 
this AD are intended to ensure that the wires that route from the main 
wire bundles to the MAR and associated brackets, clamps, braces, 
standoffs, and clips are installed properly. Improper installation of 
such wiring and structure could cause chafing of the wire/wire bundles, 
which could result in electrical arcing, smoke, and possible fire in 
the MAR.

DATES: Effective May 7, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 7, 1999.
    Comments for inclusion in the Rules Docket must be received on or 
before June 21, 1999.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 99-NM-44-AD, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056.
    The service information referenced in this AD 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, Transport 
Airplane Directorate, 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: Brett Portwood, Aerospace Engineer, 
ANM-130L, FAA, Transport Airplane Directorate, Los Angeles Aircraft 
Certification Office, 3960 Paramount Boulevard, Lakewood, California 
90712; telephone (562) 627-5350; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: As part of its practice of re-examining all 
aspects of the service experience of a particular aircraft whenever an 
accident occurs, the FAA has become aware of an incident in which the 
automatic and manual cargo door test in the cockpit was inoperative. 
This incident occurred on a McDonnell Douglas Model MD-11 series 
airplane during dispatch.
    Investigation revealed the insulation of a wire located on the aft 
main avionics rack (MAR) was worn through, and that the wire shorted to 
a coax cable clamp. The wires that route from the main wire bundles to 
the MAR also were found contacting clamps at other locations of the 
MAR. The cause of such chafing has been attributed to improper 
installation of the wire bundles in the MAR during production of the 
airplane. (This incident is not considered to be related to an accident 
that occurred off the coast of Nova Scotia involving a McDonnell 
Douglas Model MD-11 series airplane. The cause of that accident is 
still under investigation.)
    Improper installation of the wires that route from the main wire 
bundles to the MAR or improper installation of associated brackets, 
clamps, braces, standoffs, or clips could cause chafing of the wire/
wire bundles, which could result in electrical arcing, smoke, and 
possible fire in the MAR.

Other Related Rulemaking

    The FAA, in conjunction with Boeing and operators of Model MD-11 
series airplanes, is continuing to review all aspects of the service 
history of those airplanes to identify potential unsafe conditions and 
to take appropriate corrective actions. This airworthiness directive 
(AD) is one of a series of actions identified during that process. The 
process is continuing and the FAA may consider additional rulemaking 
actions as further results of the review become available.

Explanation of Relevant Service Information

    The FAA has reviewed and approved McDonnell Douglas Alert Service 
Bulletin MD11-24A146, dated February 1, 1999. The alert service 
bulletin describes procedures for a one-time inspection of the wiring 
and wire bundles of the aft MAR to determine if the wires are damaged, 
or riding or chafing on structure, clamps, braces, standoffs, or clips, 
and to detect damaged or out of alignment rubber cushions inserts of 
the wiring clamps; and corrective actions, if necessary. The corrective 
actions include repairing damaged wiring; routing and tying all wires/
wire bundles so that they are not in contact with adjacent wire 
bundles, clamps, or structure; installing silicone rubber coated glass 
cloth wrapping on wiring; and inspecting all brackets, clamps, braces, 
standoffs, and clips to make sure they are not bent or twisted and come 
in contact with wires/wire bundles.
    Accomplishment of the actions specified in the alert service 
bulletin is intended to adequately address the identified unsafe 
condition.

Explanation of the Requirements of the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other McDonnell Douglas Model MD-11 series 
airplanes of the same type design, this AD is being issued to ensure 
that the wires that route from the main wire bundles to the MAR and 
associated brackets, clamps, braces, standoffs, and clips are installed 
properly. Improper installation of such wiring and structure could 
cause chafing of the wire/wire bundles, which could result in 
electrical arcing, smoke, and possible fire in the MAR. This AD 
requires accomplishment of the actions specified in the alert service 
bulletin described previously, except as

[[Page 19690]]

discussed below. This AD also requires that operators submit a report 
of the inspection results to the FAA.

Differences Between the AD and the Referenced Alert Service 
Bulletin

    The alert service bulletin specifies the following corrective 
actions for certain conditions: realigning rubber cushion and replacing 
clamp. However, the alert service bulletin does not provide any 
instructions for accomplishment of those procedures or reference other 
service information. The FAA has verified with the manufacturer that 
the appropriate source of service information for accomplishment of 
those procedures is Chapter 20-30-01 of McDonnell Douglas MD-11 
Airplane Maintenance Manual (AMM), dated February 1, 1999. Therefore, 
this AD requires that those actions be accomplished in accordance with 
the AMM.
    Operators should note that, although the alert service bulletin 
recommends accomplishing the one-time inspection within 6 months (after 
the release of the service bulletin), the FAA has determined that an 
interval of 6 months would not address the identified unsafe condition 
in a timely manner. In developing an appropriate compliance time for 
this AD, the FAA considered not only the manufacturer's recommendation, 
but the degree of urgency associated with addressing the subject unsafe 
condition, the average utilization of the affected fleet, and the time 
necessary to perform the inspection (two work hours). In light of all 
of these factors, the FAA finds a 60-day compliance time for initiating 
the required actions to be warranted, in that it represents an 
appropriate interval of time allowable for affected airplanes to 
continue to operate without compromising safety.

Determination of Rule's Effective Date

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this 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 under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the 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 that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 99-NM-44-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    The regulations adopted herein will not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, 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

    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

    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:

99-09-03  McDonnell Douglas: Amendment 39-11135. Docket 99-NM-44-AD.

    Applicability: Model MD-11 series airplanes, manufacturer's 
fuselage numbers 0447 through 0464 inclusive, 466 through 0552 
inclusive, 0554 through 0596 inclusive, and 0597 through 0628 
inclusive; certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (g) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To ensure that the wires that route from the main wire bundles 
to the MAR and associated brackets, clamps, braces, standoffs, and 
clips are installed properly, accomplish the following:

One-Time Inspection

    (a) Within 60 days after the effective date of this AD, perform 
a one-time inspection of the wiring and wire bundles of the aft main 
avionics rack (MAR) to determine if the wires are damaged, or riding 
or chafing on structure, clamps, braces, standoffs, or clips, and to 
detect damaged or out of alignment rubber cushions inserts of the 
wiring clamps; in accordance with McDonnell Douglas Alert Service 
Bulletin MD11-24A146, dated February 1, 1999.

    Note 2: Where there are differences between this AD and the 
referenced alert service bulletin, the AD prevails.

[[Page 19691]]

Corrective Actions

    (b) If any damaged wiring is detected during the inspection 
required by paragraph (a) of this AD, prior to further flight, 
repair in accordance with the alert service bulletin.
    (c) If any wire/wire bundle is detected to be riding or chafing 
on the subject areas during the inspection required by paragraph (a) 
of this AD, prior to further flight, accomplish paragraphs (c)(1), 
(c)(2), and (c)(3) of this AD.

    Note 3: Operators should note that paragraph 3.A.2. of the 
Accomplishment Instructions of McDonnell Douglas Alert Service 
Bulletin MD11-24A146, dated February 1, 1999, incorrectly states, 
``* * * as outlined in paragraph 3.B.2 . . . .'' The correct 
reference is paragraph 3.A.2.

    (1) Route and tie all wires/wire bundles so that they are not in 
contact with adjacent wire bundles, clamps, or structure, and if 
necessary, install silicone rubber coated glass cloth wrapping on 
wiring; in accordance with the alert service bulletin.
    (2) Perform an inspection of all brackets, clamps, braces, 
standoffs, and clips to make sure they are not bent or twisted and 
do not come in contact with wires/wire bundles, in accordance with 
the alert service bulletin. If any of these parts is bent or twisted 
or is in contact with wires/wire bundles, prior to further flight, 
reposition in accordance with the alert service bulletin.
    (3) Perform an inspection of the clamps for proper alignment or 
for damage of the rubber cushion, in accordance with alert service 
bulletin. If any clamp is not aligned properly, prior to further 
flight, realign clamp in accordance with the alert service bulletin. 
If any rubber cushion is damaged, prior to further flight, replace 
the clamp with a new or serviceable clamp in accordance with Chapter 
20-30-01 of McDonnell Douglas MD-11 Airplane Maintenance Manual 
(AMM), dated February 1, 1999.
    (d) If any damaged rubber cushion insert is detected during the 
inspection required by paragraph (a) of this AD, prior to further 
flight, replace the clamp with a new or serviceable clamp in 
accordance with Chapter 20-30-01 of McDonnell Douglas MD-11 Airplane 
Maintenance Manual, dated February 1, 1999.
    (e) If any rubber cushion insert is out of alignment, prior to 
further flight, visually realign the cushion.

Reporting Requirement

    (f) Within 10 days after accomplishing the inspection required 
by paragraph (a) of this AD, submit a report of the inspection 
results (both positive and negative findings) to the Manager, Los 
Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane 
Directorate, 3960 Paramount Boulevard, Lakewood, California 90712-
4137; fax (562) 627-5210. Information collection requirements 
contained in this regulation have been approved by the Office of 
Management and Budget (OMB) under the provisions of the Paperwork 
Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been 
assigned OMB Control Number 2120-0056.

Alternative Methods of Compliance

    (g) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Los Angeles Aircraft Certification 
Office (ACO), FAA, Transport Airplane Directorate. Operators shall 
submit their requests through an appropriate FAA Principal 
Maintenance Inspector, who may add comments and then send it to the 
Manager, Los Angeles ACO.

    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Los Angeles ACO.

Special Flight Permits

    (h) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.

Incorporation by Reference

    (i) Except as provided by paragraphs (c)(2), (c)(3), (d), and 
(e) of this AD, the actions shall be done in accordance with 
McDonnell Douglas Alert Service Bulletin MD11-24A146, dated February 
1, 1999. 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 
Aircraft Group, Long Beach Division, 3855 Lakewood Boulevard, Long 
Beach, California 90846, Attention: Technical Publications Business 
Administration, Dept. C1-L51 (2-60). Copies may be inspected at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington; or at the FAA, Transport Airplane Directorate, 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.
    (j) This amendment becomes effective on May 7, 1999.

    Issued in Renton, Washington, on April 13, 1999.
John J. Hickey,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-10178 Filed 4-21-99; 8:45 am]
BILLING CODE 4910-13-U