AD 2001-08-27

[Federal Register Volume 66, Number 82 (Friday, April 27, 2001)]
[Rules and Regulations]
[Pages 21081-21083]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-10339]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-82-AD; Amendment 39-12204; AD 2001-08-27]
RIN 2120-AA64


Airworthiness Directives; Lockheed Model L-1011 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 Lockheed Model L-1011 series airplanes. This 
action requires inspection of the windshield heat wire bundle for 
chafing or damage, and inspection of the harness clamps of the wire 
bundle for damage; and corrective actions, if necessary. For certain 
airplanes, this action also requires rerouting of the windshield heat 
wire bundle. This action is necessary to prevent chafing or damage of 
the windshield heat wire bundle, which could cause arcing and result in 
smoke and fire in the cockpit. This action is intended to address the 
identified unsafe condition.

DATES: Effective May 14, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 14, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before June 26, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-82-AD, 1601 Linda Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 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: 
<a href="/cdn-cgi/l/email-protection#1b22367a757636727a69787476767e756f5b7d7a7a357c746d"><span class="__cf_email__" data-cfemail="f5ccd8949b98d89c9487969a9898909b81b5939494db929a83">[email&#160;protected]</span></a>. Comments sent via fax or the Internet must 
contain ``Docket No. 2001-NM-82-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 this AD may be obtained from 
Lockheed Martin & Logistics Center, 120 Orion Street, Greenville, South 
Carolina 29605. This information may be examined at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at 
the FAA, Atlanta Aircraft Certification Office, One Crown Center, 1895 
Phoenix Boulevard, suite 450, Atlanta, Georgia 30349; or at the Office 
of the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

FOR FURTHER INFORMATION CONTACT: Tom Peters, Program Manager, Program

[[Page 21082]]

Management Support Branch, ACE-116A, FAA, Atlanta Aircraft 
Certification Office, One Crown Center, 1895 Phoenix Boulevard, suite 
450, Atlanta, Georgia 30349; telephone (770) 703-6063; fax (770) 703-
6097.

SUPPLEMENTARY INFORMATION: The FAA has received a report indicating 
that an in-flight electrical arcing occurred to the windshield heat 
wire bundle located above the First Officer's side window in a Lockheed 
Model L-1011-385 series airplane. The wires were smoldering and flames 
were observed by the flightcrew. After the flightcrew donned smoke 
goggles and masks, two windshield heat circuit breakers opened, and the 
flightcrew opened the remaining circuit breakers, which removed power 
from the arcing wire bundle. Investigation of the cockpit revealed that 
the windshield and window heat wire harness C-38 was arcing in the 
proximity of a wire harness clamp installed just above the First 
Officer's chart light mounting bracket. Approximately 20 wires 
sustained various degrees of damage. The investigation also revealed 
that the clamp, which had been directly over the section of burned 
wire, was broken into two pieces and the rubber insulation appeared 
carbonized. The metal of the clamp also appeared to have been exposed 
to an electrical discharge. This condition, if not corrected, could 
result in chafing and damage to the C-38 wire bundle, which could cause 
arcing and result in smoke and fire in the cockpit.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Lockheed Service Bulletin 093-30-
060, dated March 6, 2001, which describes procedures for a detailed 
visual inspection of the C-38 wire harness for any chafing or damage 
(e.g., shavings, moisture, deterioration, etc.). The service bulletin 
also describes procedures for repair and replacement of any damaged 
wiring. The FAA also reviewed and approved Lockheed Service Bulletin 
093-30-057, dated April 27, 1984. That service bulletin describes 
procedures for rerouting the C-38 windshield heat wire harness for 
certain airplanes that have a First Officer's chart light installation 
that was accomplished during production or after delivery. 
Accomplishment of the actions specified in the service bulletins 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 airplanes of the same type design, this AD is 
being issued to prevent damage to the C-38 wire bundle, which can cause 
arcing and result in smoke and fire in the cockpit. This AD requires 
accomplishment of the applicable actions specified in the service 
bulletins described previously.

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.
    Submit comments using the following format:
    <bullet> 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.
    <bullet> For each issue, state what specific change to the AD is 
being requested.
    <bullet> 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-82-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.
    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:

2001-08-27  Lockheed: Amendment 39-12204. Docket 2001-NM-82-AD.

    Applicability: Model L-1011 series airplanes, as listed in 
Lockheed Service Bulletin 093-30-060, dated March 6, 2001, and 
Lockheed Service Bulletin 093-30-057,

[[Page 21083]]

dated April 27, 1984; 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 (c) 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 damage to the windshield heat wire bundle, which 
could cause arcing and result in smoke and fire in the cockpit; 
accomplish the following:

Inspection of Wiring and Clamps, and Corrective Actions

    (a) For airplanes listed in Lockheed Service Bulletin 093-30-
060, dated March 6, 2001: Within 60 days after the effective date of 
this AD, perform the detailed visual inspections and repair or 
replacements specified in paragraph (a)(1) and (a)(2) of this AD, 
per Lockheed Service Bulletin 093-30-060, dated March 6, 2001.

    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) Remove the C-38 wire harness clamps and perform a detailed 
visual inspection of the clamps and the conforming cushions for any 
sign of deterioration, damage, or slippage on the metal band of the 
clamp. Before further flight, replace any clamp that does not meet 
the specified criteria in the service bulletin with a new or 
serviceable clamp, per the service bulletin.
    (2) Perform a detailed visual inspection of the C-38 wire 
harness for any damage from chafing or contamination (e.g., 
shavings, moisture, deterioration, etc.). Before further flight, 
repair, or replace any chafed or damaged wiring per the service 
bulletin.

Rerouting the C-38 Harness

    (b) For airplanes listed in Lockheed Service Bulletin 093-30-
057, dated April 27, 1984: Within 60 days after the effective date 
of this AD, reroute the C-38 harness and add one additional clamp to 
secure the harness away from the mounting brackets of the Flight 
Officer's chart light assembly, per the service bulletin.

Alternative Methods of Compliance

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

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Atlanta ACO.

Special Flight Permits

    (d) 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

    (e) The actions shall be done in accordance with Lockheed 
Service Bulletin 093-30-060, dated March 6, 2001; and Lockheed 
Service Bulletin 093-30-057, dated April 27, 1984, as applicable. 
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 Lockheed Martin & Logistics Center, 
120 Orion Street, Greenville, South Carolina 29605. Copies may be 
inspected at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington; Atlanta Aircraft Certification 
Office, One Crown Center, 1895 Phoenix Boulevard, suite 450, 
Atlanta, Georgia 30349; or at the Office of the Federal Register, 
800 North Capitol Street, NW., suite 700, Washington, DC.

Effective Date

    (f) This amendment becomes effective on May 14, 2001.

    Issued in Renton, Washington, on April 19, 2001.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-10339 Filed 4-26-01; 8:45 am]
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