[Federal Register: December 10, 2002 (Volume 67, Number 237)]
[Proposed Rules]
[Page 75824-75826]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr10de02-12]
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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:
9-anm-nprmcomment@faa.gov. 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]
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