[Federal Register Volume 67, Number 237 (Tuesday, December 10, 2002)]
[Proposed Rules]
[Pages 75824-75826]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-31134]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-374-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 737-600, 737-700, 737-800, 
757-200, and 757-300 Series 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 Boeing Model 737-600, 737-
700, 737-800, 757-200, and 757-300 series airplanes. This proposal 
would require replacing existing video distribution unit (VDU) 
connectors with new, improved connectors or new wire assemblies 
(jumpers), and performing related actions, as applicable. This action 
is necessary to prevent a short circuit in a VDU connector and 
consequent arcing and damage to wiring within the connector, which 
could result in damage to adjacent systems or structure and possible 
smoke or fire in the airplane cabin. This action is intended to address 
the identified unsafe condition.

DATES: Comments must be received by January 24, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-374-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-374-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 Airplane Group, P.O. Box 3707, Seattle, 
Washington 98124-2207. This information may be examined at the FAA, 
Transport

[[Page 75825]]

Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Binh V. Tran, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055-
4056; telephone (425) 227-2890; fax (425) 227-1181.

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-374-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-374-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received reports indicating that burned contacts have 
been found on certain video distribution unit (VDU) connectors 
installed on certain Boeing Model 737-700 and 737-800 series airplanes. 
In several cases, the mating connector on the VDU was damaged and, in 
one case, an insulation blanket near the connector was damaged. 
Investigation revealed that the burned contacts were caused by the 
presence of moisture and wire chafing in the backshell boot of the VDU 
connector. Moisture or chafed wiring may result in a short circuit that 
may cause internal arcing and damage to wiring within the connector. 
This condition, if not corrected, could result in damage to adjacent 
systems or structure, and possible smoke or fire in the airplane cabin.
    The same type of VDU connectors is also installed on Boeing Model 
737-600, 757-200, and 757-300 series airplanes. While the FAA has not 
received any reports of burned contacts on these airplane models, the 
VDU connectors may be subject to the same unsafe condition as those on 
Boeing Model 737-700 and -800 series airplanes.

Explanation of Relevant Service Information

    We have reviewed and approved Boeing Service Bulletin 737-23A1169, 
Revision 2, dated June 21, 2001. Part 2 of this service bulletin 
describes procedures for replacing existing VDU connectors with new, 
improved connectors having better moisture resistance and longer wires, 
and adding a drip loop to the wiring at the new VDU connectors.
    We also have reviewed and approved Boeing Alert Service Bulletin 
757-23A0060, Revision 1, dated January 11, 2001; and Boeing Alert 
Service Bulletin 757-23A0061, Revision 1, dated January 11, 2001. Part 
2 of these service bulletins describes procedures for replacing 
existing VDU connectors with new, improved connectors having better 
moisture resistance, or--if a drip loop does not exist--with new wire 
assemblies (jumpers).
    Accomplishment of the actions specified in the service bulletins 
described previously 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 bulletins described previously, except as discussed below.

Differences Between Service Bulletins and Proposed AD

    Part 1 of the Accomplishment Instructions of the referenced service 
bulletins describes various interim actions intended to detect or 
prevent conditions that may lead to a short circuit, until the VDU 
connectors are replaced with new, improved VDU connectors or wire 
assemblies, as applicable. However, this proposed AD would not require 
the interim actions in part 1 of the service bulletins, but only the 
replacement of the VDU connectors with new, improved connectors or new 
wire assemblies, as applicable, as described in part 2 of the service 
bulletins. Mandating the replacement is based on our determination that 
long-term continued operational safety will be better assured by 
modifications or design changes to remove the source of the problem, 
rather than by inspections or other interim actions. Inspections and 
interim actions may not provide the degree of safety assurance 
necessary for the transport airplane fleet. This, coupled with a better 
understanding of the human factors associated with inspections, has led 
us to consider placing less emphasis on inspections and more emphasis 
on design improvements. The proposed replacement requirement is 
consistent with these conditions.
    The service bulletins recommend that the part 2 replacement be done 
as soon as manpower, materials, and facilities are available. We find 
that such a compliance time would not ensure that the identified unsafe 
condition is addressed in a timely manner. In developing an appropriate 
compliance time for this proposed AD, we considered not only the 
manufacturer's recommendation, but also the degree of urgency 
associated with addressing the subject unsafe condition. In light of 
these factors, we find a compliance time of 18 months for completing 
the proposed actions would be warranted, in that it represents an 
appropriate interval of time allowable for affected airplanes to 
continue to operate without compromising safety.

Cost Impact

    There are approximately 280 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 28 airplanes of U.S. registry 
would be affected by this proposed AD, that it would take approximately 
16 work hours per airplane to accomplish the

[[Page 75826]]

proposed connector replacement, and that the average labor rate is $60 
per work hour. Required parts would cost between $334 and $13,944 per 
airplane. Based on these figures, the cost impact of the proposed AD on 
U.S. operators is estimated to be between $1,294 and $14,904 per 
airplane.
    The cost impact figure discussed above is 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:

Boeing: Docket 2001-NM-374-AD.

    Applicability: Model 737-600, -700, and ``800 series airplanes, 
as listed in Boeing Service Bulletin 737-23A1169, Revision 2, dated 
June 21, 2001; Model 757-200 series airplanes, as listed in Boeing 
Alert Service Bulletin 757-23A0060, Revision 1, dated January 11, 
2001; and Model 757-300 series airplanes as listed in Boeing Alert 
Service Bulletin 757-23A0061, Revision 1, dated January 11, 2001; 
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 (d) 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 prevent a short circuit in a video distribution unit (VDU) 
connector and consequent arcing and damage to wiring within the 
connector, which could result in damage to adjacent systems or 
structure and possible smoke or fire in the airplane cabin, 
accomplish the following:

Model 737-600, -700, and -800 Series Airplanes: Inspections and Follow-
on Actions

    (a) For Model 737-600, -700, and -800 series airplanes: Within 
18 months after the effective date of this AD, replace existing VDU 
connectors with new, improved connectors, and install a drip loop in 
the wiring at the new VDU connectors, per part 2 of the 
Accomplishment Instructions of Boeing Service Bulletin 737-23A1169, 
Revision 2, dated June 21, 2001.

Model 757-200 and -300 Series Airplanes: Inspections and Follow-on 
Actions

    (b) For Model 757-200 and -300 series airplanes: Within 18 
months after the effective date of this AD, replace existing VDU 
connectors with new, improved connectors, or with new wire 
assemblies (jumpers), as applicable, per part 2 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 757-
23A0060, Revision 1, dated January 11, 2001 (for Model 757-200 
series airplanes); or Boeing Alert Service Bulletin 757-23A0061, 
Revision 1, dated January 11, 2001 (for Model 757-300 series 
airplanes); as applicable.

Part Installation

    (c) As of the effective date of this AD, no person shall install 
a VDU connector, part number CAMA11W1P, on any airplane.

Alternative Methods of Compliance

    (d) 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, Seattle Aircraft Certification 
Office (ACO), FAA. Operators shall submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Seattle ACO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.

Special Flight Permits

    (e) 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.

    Issued in Renton, Washington, on December 4, 2002.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-31134 Filed 12-9-02; 8:45 am]
BILLING CODE 4910-13-P