[Federal Register: April 15, 2003 (Volume 68, Number 72)]
[Rules and Regulations]
[Page 18112-18114]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr15ap03-5]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-NM-386-AD; Amendment 39-13113; AD 2003-08-02]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model MD-90-30
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),
applicable to certain McDonnell Douglas Model MD-90-30 airplanes. This
action requires a one-time inspection for chafing or damage of the
cable assemblies and follow-on modification of the cable assemblies of
the powered seats located in the first-class cabin. This action is
necessary to prevent chafing and damage of the cable assemblies due to
contact between the cable and the metal retaining clip on the seat leg,
which could result in electrical arcing and consequent smoke and/or
fire in the cabin. This action is intended to address the identified
unsafe condition.
DATES: Effective April 30, 2003.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 30, 2003.
Comments for inclusion in the Rules Docket must be received on or
before June 16, 2003.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2001-NM-386-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-iarcomment@faa.gov.
Comments sent via fax or the Internet must contain ``Docket No. 2001-
NM-386-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 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;
or at the Office of the Federal Register, 800 North Capitol Street,
NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: George Mabuni, Aerospace Engineer,
Systems and Equipment Branch, ANM-130L, FAA, Los Angeles Aircraft
Certification Office, 3960 Paramount Boulevard, Lakewood, California
90712-4137; telephone (562) 627-5341; fax (562) 627-5210.
SUPPLEMENTARY INFORMATION: Boeing production personnel reported that,
while securing a first-class powered seat to the floor during routine
maintenance, the seat-to-seat power cable assembly shorted and arced
causing a small fire under the seat. Investigation revealed that the
tie-wrapped cable assembly had migrated and was contacting the metal
retaining clip on the powered seat leg. This condition, if not
corrected, could result in chafing and damage of the cable assemblies,
consequent electrical arcing, and smoke and/or fire in the cabin.
Explanation of Relevant Service Information
The FAA has reviewed and approved Boeing Alert Service Bulletin
MD90-25A056, Revision 01, dated April 30, 2002, which describes
procedures for a one-time visual inspection for chafing or damage of
the cable assemblies and follow-on modification of the cable assemblies
of the powered seats located in the first-class cabin between fuselage
stations Y=273.500 and Y=465.000. The modification includes fabrication
of identification bands for the left and right side seat plug cables,
and accomplishment of one of the following conditions:
Condition 1--If no chafing or damage is found, install cable
assemblies and mating identification bands; install protective sleeving
and wrap; install and route seat cable assemblies using improved
methods; and coil and stow the ground wire;
Condition 2--If any chafing or damage is found that is within the
limits specified in Chapter 20 of the Standard Wiring Practices Manual
(SWPM), repair the damaged cable assemblies and do a continuity check;
install cable assemblies and mating identification bands; install
protective sleeving and wrap; install and route seat cable assemblies
using improved methods; and coil and stow the ground wire; or
Condition 3--If any chafing or damage is found that is outside the
limits specified in Chapter 20 of the SWPM, replace the damaged wires
or cable assemblies with new components, and do a continuity check;
install cable assemblies and mating identification bands; install
protective sleeving and wrap; install and route seat cable assemblies
using improved methods; and coil and stow the ground wire.
The procedures for inspection and modification described above are
for Group 1 airplanes. The procedures for Group 2 airplanes are the
same, except there is no coiling and stowing of the ground wire.
Accomplishment of the actions specified in the service bulletin is
intended to adequately address the identified unsafe condition.
Explanation of Requirements of the Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design that may be
registered in the United States at some time in the future, this AD is
being issued to prevent chafing and damage of the cable assemblies due
to contact between the cable and the metal retaining clip on the seat
leg, which could result in electrical arcing and consequent smoke and/
or fire in the cabin. This AD requires a one-time inspection for
chafing or damage of the cable assemblies and follow-on modification of
the cable assemblies of the powered seats located in the first-class
cabin. The actions are required to be accomplished in
[[Page 18113]]
accordance with the service bulletin described previously.
Cost Impact
None of the Model MD-90-30 airplanes affected by this action are on
the U.S. Register. All airplanes included in the applicability of this
rule currently are operated by non-U.S. operators under foreign
registry; therefore, they are not directly affected by this AD action.
However, the FAA considers that this rule is necessary to ensure that
the unsafe condition is addressed in the event that any of these
subject airplanes are imported and placed on the U.S. Register in the
future.
Should an affected airplane be imported and placed on the U.S.
Register in the future, it would require approximately 7 work hours to
accomplish the required modification, at an average labor rate of $60
per work hour. Based on these figures, the cost impact of this AD would
be $420 per airplane.
Determination of Rule's Effective Date
Since this AD action does not affect any airplane that is currently
on the U.S. register, it has no adverse economic impact and imposes no
additional burden on any person. Therefore, prior notice and public
procedures hereon are unnecessary and the amendment may be made
effective in less than 30 days after publication in the Federal
Register.
Comments Invited
Although this action is in the form of a final rule and was not
preceded by notice and 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.
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 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 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 2001-NM-386-AD.'' The postcard will be date stamped
and returned to the commenter.
Regulatory Impact
The regulations adopted herein will 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 final rule does not have federalism
implications under Executive Order 13132.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under 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. A final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it 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
0
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
0
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]
0
2. Section 39.13 is amended by adding the following new airworthiness
directive:
2003-08-02 McDonnell Douglas: Amendment 39-13113. Docket 2001-NM-
386-AD.
Applicability: Model MD-90-30 airplanes, as listed in Boeing
Alert Service Bulletin MD90-25A056, Revision 01, dated April 30,
2002; 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 (b) 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 chafing and damage of the cable assemblies of the
powered seats located in the first-class cabin, which could result
in electrical arcing and consequent smoke and/or fire in the cabin,
accomplish the following:
One-Time Inspection/Follow-on Modification
(a) Within 6 months after the effective date of this AD: Do a
one-time general visual inspection for chafing and damage of the
cable assemblies of the powered seats located in the first-class
cabin between fuselage stations Y=273.500 and Y=465.000, per Boeing
Alert Service Bulletin MD90-25A056, Revision 01, dated April 30,
2002. Before further flight, do the applicable follow-on
modification specified in paragraph (a)(1), (a)(2), or (a)(3) of
this AD.
Note 2: 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.''
(1) If no chafing or damage is found, modify the cable
assemblies (includes
[[Page 18114]]
installing cable assemblies and mating identification bands;
installing protective sleeving and wrap; installing and routing of
seat cable assemblies using improved methods; and coiling and
stowing the ground wire if applicable) per Condition 1 of the
service bulletin.
(2) If any chafing or damage is found that is within the limits
specified in Chapter 20 of the Standard Wiring Practices Manual
(SWPM), modify the cable assemblies (includes repairing the damaged
cable assemblies and doing a continuity check; installing cable
assemblies and mating identification bands; installing protective
sleeving and wrap; installing and routing of seat cable assemblies
using improved methods; and coiling and stowing the ground wire if
applicable) per Condition 2 of the service bulletin.
(3) If any chafing or damage is found that is outside the limits
specified in Chapter 20 of the SWPM, modify the cable assemblies
(includes replacing the damaged wires or cable assemblies with new
components, and doing a continuity check; installing cable
assemblies and mating identification bands; installing protective
sleeving and wrap; installing and routing of seat cable assemblies
using improved methods; and coiling and stowing the ground wire if
applicable) per Condition 3 of the service bulletin.
Alternative Methods of Compliance
(b) 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. 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 3: 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
(c) 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
(d) The actions shall be done in accordance with Boeing Alert
Service Bulletin MD90-25A056, Revision 01, dated April 30, 2002.
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: Data and Service Management, Dept. C1-L5A (D800-
0024). Copies may be inspected 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; or at the Office of the Federal
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
Effective Date
(e) This amendment becomes effective on April 30, 2003.
Issued in Renton, Washington, on April 7, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-8892 Filed 4-14-03; 8:45 am]
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