[Federal Register Volume 67, Number 168 (Thursday, August 29, 2002)]
[Proposed Rules]
[Pages 55368-55372]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-22005]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-62-AD]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model MD-11 and -11F 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to certain McDonnell Douglas 
Model MD-11 airplanes, that currently requires, among other actions, a 
one-time inspection to detect discrepancies at certain areas around the 
entry light connector of the sliding ceiling panel above the forward 
passenger doors; repair, if necessary; and installation or modification 
of a flapper door ramp deflector on the forward entry drop ceiling 
structure. That AD also currently requires an inspection of the wire 
assembly support installation above the entry door (L1) sliding panel 
for chafing, and repair, if necessary. This action also would continue 
to require the existing requirements and require replacing the wire 
support bracket with new support clip assemblies. This action is 
necessary to prevent chafing of electrical wire assemblies above the 
forward passenger doors and above the entry door (L1) sliding panel of 
the forward drop ceiling on the passenger compartment, which could 
result in electrical arcing, and consequent electrical fire in the 
passenger compartment. This action is intended to address the 
identified unsafe condition.

[[Page 55369]]


DATES: Comments must be received by October 15, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-62-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-62-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.

FOR FURTHER INFORMATION CONTACT:
    Technical Information: Brett Portwood, Aerospace Engineer, Systems 
and Equipment Branch, ANM-130L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5350; fax (562) 627-5210.
    Other Information: Sandi Carli, Airworthiness Directive Technical 
Writer/Editor; telephone (425) 227-1120, fax (425) 227-1232. Questions 
or comments may also be sent via the Internet using the following 
address: [email protected]. Questions or comments sent via the 
Internet as attached electronic files must be formatted in Microsoft 
Word 97 for Windows or ASCII text.

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:
     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.
     For each issue, state what specific change to the proposed 
AD is being requested.
     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-62-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-62-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On November 22, 2000, the FAA issued airworthiness directive (AD) 
2000-24-11, amendment 39-12018 (65 FR 75612, December 4, 2000), 
applicable to certain McDonnell Douglas Model MD-11 airplanes, to 
require a one-time inspection to detect discrepancies at certain areas 
around the entry light connector of the sliding ceiling panel above the 
forward passenger doors, and repair, if necessary. For certain 
airplanes, that AD also requires installation or modification of a 
flapper door ramp deflector on the forward entry drop ceiling 
structure. For certain other airplanes, that AD requires inspection of 
the wire assembly support installation for evidence of chafing, and 
corrective actions, if necessary. For certain airplanes, that AD also 
requires modification of a support bracket for the ramp deflector 
assembly. That action was prompted by the FAA's determination that 
further rulemaking action was necessary to address the identified 
unsafe condition. The requirements of that AD are intended to prevent 
chafing of electrical wire assemblies above the forward passenger 
doors, which could result in an electrical fire in the passenger 
compartment.
    The incidents that prompted AD 2000-24-11 are not considered to be 
related to an accident that occurred off the coast of Nova Scotia 
involving a McDonnell Douglas Model MD-11 airplane. The cause of that 
accident is still under investigation.

Other Related Rulemaking

    The FAA, in conjunction with Boeing and operators of Model MD-11 
and -11F 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 proposed 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.

Background

    In the preamble of the notice of proposed rulemaking (NPRM) for AD 
2000-03-10, amendment 39-11569 (64 FR 57811, October 27, 1999), which 
was superseded by AD 2000-24-11, the FAA indicated that the airplane 
manufacturer had advised us that modifying the wire assembly support 
installation above the entry door (L1) sliding panel in accordance with 
McDonnell Douglas Alert Service Bulletin MD11-24A068, Revision 01, 
dated March 8, 1999, may cause further damage of the wire assembly due 
to the possibility of the wire assembly chafing on adjacent brackets. 
The manufacturer also advised that it was planning to revise the 
service bulletin to alleviate the potential chafing problem.
    As a result of this information, the FAA did NOT include the 
subject modification in the requirements of AD 2000-03-10.

Incidents Since Issuance of Previous Rule

    Since the issuance of AD 2000-24-11, the FAA has received reports 
of chafing damage to the electrical wire bundle (wire assembly ABS9202) 
located above the entry door (L1) sliding panel of the forward drop 
ceiling of the passenger compartment. These incidents occurred on 
McDonnell Douglas Model MD-11 and MD-11F airplanes on which the

[[Page 55370]]

modification specified in McDonnell Douglas Alert Service Bulletin 
MD11-24A068, Revision 01, dated March 8, 1999, has been accomplished in 
service and in production. The cause of the chafing has been attributed 
to the wire bundle coming in contact with an adjacent forward cabin 
entry work light connector due to decreased clearance caused by 
installation of a spacer per the referenced service bulletin.
    Chafing of electrical wire assemblies above the forward passenger 
doors (as identified in AD 2000-24-11) and above the entry door (L1) 
sliding panel of the forward drop ceiling on the passenger compartment, 
if not corrected, could result in electrical arcing, and consequent 
electrical fire in the passenger compartment.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletin 
MD11-24A068, Revision 02, dated May 16, 2001. The service bulletin 
describes procedures for a general visual inspection of the wire 
assembly support installation above the entry door (L1) sliding panel 
for chafing per the service bulletin; and repair, if necessary. The 
service bulletin also describes procedures for replacing the wire 
support bracket with new support clip assemblies and ensuring adequate 
clearance exists for all parts of the wire assembly, including 
breakouts to module blocks and grounds. In addition, the effectivity 
listing of Revision 02 of the service bulletin removes certain 
airplanes and adds others, which are subject to the identified unsafe 
condition.
    Accomplishment of the actions specified in Revision 02 of service 
bulletin is intended to adequately address chafing of electrical wire 
assemblies above the entry door (L1) sliding panel of the forward drop 
ceiling on the passenger compartment, which could result in electrical 
arcing, and consequent electrical fire in the passenger compartment.

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 supersede AD 2000-24-11 to continue to require, among 
other actions, a one-time inspection to detect discrepancies at certain 
areas around the entry light connector of the sliding ceiling panel 
above the forward passenger doors; repair, if necessary; and 
installation or modification of a flapper door ramp deflector on the 
forward entry drop ceiling structure. The proposed AD also would 
require accomplishment of the actions specified in Boeing Alert Service 
Bulletin MD11-24A068, Revision 02, dated May 16, 2001, described 
previously.

Explanation of Change to Applicability

    The applicability of this proposed AD references Boeing Alert 
Service Bulletin MD11-24A068, Revision 02, dated May 16, 2001, as one 
of the appropriate sources of service information for determining the 
affected Model MD-11 and -11F airplanes, rather than McDonnell Douglas 
Alert Service Bulletin MD11-24A068, Revision 01, dated March 8, 1999, 
as referenced in the applicability of AD 2000-24-11. As indicated 
above, Revision 02 includes additional airplanes that are subject to 
the requirements of this AD. Also, the applicability of this AD 
excludes airplanes listed in Boeing Alert Service Bulletin MD11-24A068, 
Revision 02, dated May 16, 2001, that have been modified from a 
passenger to a freighter configuration and have had the entry door (L1) 
sliding panel described in the service bulletin removed. In addition, 
we have revised the applicability of the existing AD to identify model 
designations as published in the most recent type certificate data 
sheet for the affected models.

Cost Impact

    1. Actions Currently Required by AD 2000-24-11 and Retained in This 
AD.
    There are approximately 110 airplanes of the affected design in the 
worldwide fleet that are affected by the actions currently required by 
AD 2000-24-11 and retained in this proposed AD. Of these 110 airplanes, 
the FAA estimates that 21 airplanes of U.S. registry would be affected 
by proposed AD.
    The inspection to detect discrepancies around the entry light 
connector of the slide ceiling panel above the forward passenger doors 
takes approximately 2 work hours per airplane to accomplish, at an 
average labor rate of $60 per work hour. Based on these figures, the 
cost impact of this currently required inspection on U.S. operators is 
estimated to be $2,520, or $120 per airplane.
    For Group 1 airplanes as specified in McDonnell Douglas Alert 
Service Bulletin MD11-25A194, Revision 06 (approximately 16 airplanes 
of U.S. registry), the installation of the flapper door ramp deflector 
takes approximately 8 work hours per airplane to accomplish, at an 
average labor rate of $60 per work hour. Required parts cost 
approximately $455 per airplane. Based on these figures, the cost 
impact of this currently required installation on U.S. operators of 
Group 1 airplanes is estimated to be $14,960, or $935 per airplane.
    For Group 2 airplanes as specified in McDonnell Douglas Alert 
Service Bulletin MD11-25A194, Revision 06 (approximately 8 airplanes of 
U.S. registry), the installation of the flapper door ramp deflector 
takes approximately 8 work hours per airplane to accomplish, at an 
average labor rate of $60 per work hour. Required parts cost 
approximately $890 per airplane. Based on these figures, the cost 
impact of this currently required installation on U.S. operators of 
Group 2 airplanes is estimated to be $10,960, or $1,370 per airplane.
    For airplanes listed in McDonnell Douglas Alert Service Bulletin 
MD11-24A068, Revision 01, dated March 8, 1999 (approximately 21 
airplanes of U.S. registry), the inspection of the wire assembly 
support installation takes approximately 1 work hour per airplane to 
accomplish, at an average labor rate of $60 per work hour. Based on 
these figures, the cost impact of this currently required inspection on 
U.S. operators is estimated to be $1,260, or $60 per airplane.
    For airplanes in Groups 1 and 3 as specified in McDonnell Douglas 
Alert Service Bulletin MD11-25A194, Revision 06 (approximately 18 
airplanes of U.S. registry), the modification takes approximately 2 
work hours per airplane to accomplish, at an average labor rate of $60 
per work hour. Based on these figures, the cost impact of this 
currently required modification on U.S. operators is estimated to be 
$2,160, or $120 per airplane.
    2. New Actions Proposed by This AD.
    There are approximately 195 Model MD-11 and -11F airplanes of the 
affected design in the worldwide fleet that are affected by the actions 
required by this proposed AD. Of these 195 airplanes, the FAA estimates 
that 64 airplanes of U.S. registry would be affected by this proposed 
AD.
    The new actions that are proposed in this AD action would take 
approximately 3 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Required parts would cost 
approximately $294 per airplane. Based on these figures, the cost 
impact of the newly proposed requirements of this AD on U.S. operators 
is estimated to be $30,336, or $474 per airplane.
    3. Cost Estimate Calculation Information.

[[Page 55371]]

    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the current or proposed 
requirements of this AD action, and that no operator would accomplish 
those actions in the future if this 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.

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 removing amendment 39-12018 (65 FR 
75612, December 4, 2000), and by adding a new airworthiness directive 
(AD), to read as follows:

McDonnell Douglas: Docket 2001-NM-62-AD. Supersedes AD 2000-24-11, 
Amendment 39-12018.

    Applicability: The following airplanes listed in Table 1 of this 
AD, certificated in any category:

                         Table 1.--Applicability
------------------------------------------------------------------------
                                                    Excluding Airplanes--
            Model                As listed in--
------------------------------------------------------------------------
MD-11 and MD-11F airplanes..  McDonnell Douglas     [reserved]
                               Alert Service
                               Bulletin MD11-
                               24A194, Revision
                               06, dated January
                               27, 2000.
MD-11 and MD-11F airplanes..  Boeing Alert Service  Modified from a
                               Bulletin MD11-        passenger to a
                               24A068, Revision      freighter
                               02, dated May 16,     configuration on
                               2001.                 which the entry
                                                     door (L1) sliding
                                                     panel described in
                                                     Boeing Alert
                                                     Service Bulletin
                                                     MD11-24A068,
                                                     Service Revision
                                                     02, dated May 16,
                                                     2001, has been
                                                     removed.
------------------------------------------------------------------------


    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 prevent chafing of electrical wire assemblies above the 
forward passenger doors and above the entry door (L1) sliding panel 
of the forward drop ceiling on the passenger compartment, which 
could result in electrical arcing, and consequent electrical fire in 
the passenger compartment, accomplish the following:

Restatement of the Requirements of AD 2000-24-11

Detailed Visual Inspection

    (a) For airplanes listed in McDonnell Douglas Alert Service 
Bulletins MD11-25A194, Revision 05, dated June 21, 1999; and MD11-
24A068, Revision 01, dated March 8, 1999: Within 10 days after 
December 28, 1998 (the effective date of AD 98-25-11 R1, amendment 
39-10988), perform a detailed visual inspection of the aircraft 
wiring to detect discrepancies that include but are not limited to 
frayed, chafed, or nicked wires and wire insulation in the areas 
specified in paragraphs (a)(1) and (a)(2) of this AD.

    Note 2: For the purposes of this AD, a detailed visual 
inspection is defined as: ``An intensive visual examination of a 
specific structural area, system, installation, or assembly to 
detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at 
intensity deemed appropriate by the inspector. Inspection aids such 
as mirror, magnifying lenses, etc., may be used. Surface cleaning 
and elaborate access procedures may be required.''

    (1) At the area of the forward drop ceiling just outboard of mod 
block S3-735, and forward and inboard of the light ballast for the 
entry light on the sliding ceiling panel above the forward left 
passenger door (1L) at station location x = 24.75, y = 435, and z = 
64.5.
    (2) At the area above the forward right passenger door (1R) at 
station location x = -30, y = 430, and z = 70 in the ramp deflector 
assembly part number 4223570-501.

Corrective Action

    (b) If any discrepancy is detected during the visual inspection 
required by paragraph (a) of this AD, prior to further flight, 
repair in accordance with Chapter 20, Standard Wiring Practices of 
the MD-11 Wiring Diagram Manual, dated January 1, 1998, or April 1, 
1998.

Inspection, Installation, and Modification

    (c) For airplanes listed in McDonnell Douglas Alert Service 
Bulletin MD11-25A194, Revision 05, dated June 21, 1999; or MD11-
24A068, Revision 01, dated March 8, 1999: Within 6 months after 
March 23, 2000 (the effective date of AD 2000-03-10, amendment 39-
11569), accomplish the actions specified in paragraphs (c)(1), 
(c)(2), (c)(3), and (c)(4) of this AD, as applicable.
    (1) For Group 1 airplanes listed in McDonnell Douglas Alert 
Service Bulletin MD11-25A194, Revision 05, dated June 21,

[[Page 55372]]

1999: Install a ramp deflector assembly on the right side forward 
entry drop ceiling structure in accordance with McDonnell Douglas 
Alert Service Bulletin MD11-25A194, Revision 05, dated June 21, 
1999; or McDonnell Douglas Alert Service Bulletin MD11-25A194, 
Revision 06, dated January 27, 2000. After the effective date of 
this AD, only Revision 06 of the alert service bulletin shall be 
used.
    (2) For Group 2 airplanes listed in McDonnell Douglas Alert 
Service Bulletin MD11-25A194, Revision 05, dated June 21, 1999: 
Install a ramp deflector assembly on the right side forward entry 
drop ceiling structure in accordance with McDonnell Douglas Alert 
Service Bulletin MD11-25A194, Revision 05, dated June 21, 1999; or 
McDonnell Douglas Alert Service Bulletin MD11-25A194, Revision 06, 
dated January 27, 2000. After the effective date of this AD, only 
Revision 06 of the alert service bulletin shall be used.

    Note 3: Installation of a ramp deflector assembly in accordance 
with McDonnell Douglas Service Bulletin MD11-25-194, dated March 15, 
1996; Revision 01, dated May 1, 1996; Revision 02, dated July 12, 
1996; Revision 03, dated December 12, 1996; or Revision 04, dated 
March 8, 1999, is acceptable for compliance with the requirements of 
paragraph (c)(2) of this AD.

    (3) For Group 3 airplanes listed in McDonnell Douglas Alert 
Service Bulletin MD11-25A194, Revision 05, dated June 21, 1999: 
Modify the previously installed ramp deflector assembly bracket in 
accordance with McDonnell Douglas Alert Service Bulletin MD11-
25A194, Revision 05, dated June 21, 1999; or McDonnell Douglas Alert 
Service Bulletin MD11-25A194, Revision 06, dated January 27, 2000. 
After the effective date of this AD, only Revision 06 of the alert 
service bulletin shall be used.
    (4) For airplanes listed in McDonnell Douglas Alert Service 
Bulletin MD11-24A068, Revision 01, dated March 8, 1999: Perform a 
general visual inspection of the wire assembly support installation 
for evidence of chafing, in accordance with the service bulletin. If 
any chafing is detected, prior to further flight, repair or replace 
any discrepant part with a new part in accordance with the service 
bulletin.

    Note 4: 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 under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or drop-light, 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.''

One-Time Inspection

    (d) For airplanes other than those identified in paragraph (a) 
of this AD: Within 10 days after January 8, 2001 (the effective date 
of AD 2000-24-11, amendment 39-12018), perform a detailed visual 
inspection of the aircraft wiring to detect discrepancies that 
include but are not limited to frayed, chafed, or nicked wires and 
wire insulation in the areas specified in paragraphs (a)(1) and 
(a)(2) of this AD. If any discrepancy is found, prior to further 
flight, repair in accordance with the requirements of paragraph (b) 
of this AD.

    Note 5: Accomplishment of the inspection required by paragraph 
(a) of AD 98-25-11 R1, amendment 39-10988, prior to the effective 
date of this AD, is acceptable for compliance with paragraph (d) of 
this AD.

Modification

    (e) For airplanes listed in Group 3 of McDonnell Douglas Alert 
Service Bulletin MD11-25A194, Revision 06, dated January 27, 2000: 
Within 6 months after January 8, 2001, modify the ramp deflector 
assembly support bracket on the right side forward entry door drop 
ceiling structure, in accordance with McDonnell Douglas Alert 
Service Bulletin MD11-25A194, Revision 06, dated January 27, 2000.

New Actions Required by This AD

Inspection, Corrective Action, if Necessary, and Replacement

    (f) For airplanes listed in Groups 1 and 2 in Boeing Alert 
Service Bulletin MD11-24A068, Revision 02, dated May 16, 2001: 
Within 6 months after the effective date of this AD, do the actions 
specified in paragraphs (f)(1) and (f)(2) of this AD.
    (1) Do a general visual inspection of the wire assembly support 
installation above the entry door (L1) sliding panel of the forward 
drop ceiling of the passenger compartment for chafing per the 
service bulletin. If any chafing is found, before further flight, 
repair per the service bulletin.
    (2) Replace the wire support bracket with new support clip 
assemblies and ensure adequate clearance exists for all parts of the 
wire assembly, including breakouts to module blacks and grounds, per 
the service bulletin.

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. 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 6: 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.

    Issued in Renton, Washington, on August 20, 2002.

Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-22005 Filed 8-28-02; 8:45 am]
BILLING CODE 4910-13-P