AD Amdt-39-10730

[Federal Register Volume 63, Number 170 (Wednesday, September 2, 1998)]
[Rules and Regulations]
[Pages 46647-46648]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 98-23620]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-242-AD; Amendment 39-10730; AD 98-18-14]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 757-200 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain Boeing Model 757-200 series airplanes. This 
action requires a one-time detailed visual inspection to detect damage 
or chafing of certain electrical wire bundles, and to verify adequate 
clearance exists between the wire bundles and adjacent disconnect 
bracket; and repair, if necessary. This amendment is prompted by a 
report indicating that damaged wires caused an electrical short in the 
electrical panel, which resulted in a shower of sparks from the 
overhead panel. The actions specified in this AD are intended to 
prevent failure of essential electrical systems and a potential fire 
hazard for passengers and crewmembers, due to damage or chafing of 
electrical wire bundles.

DATES: Effective September 17, 1998.
    Comments for inclusion in the Rules Docket must be received on or 
before November 2, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 98-NM-242-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056.
    Information pertaining to this amendment may be obtained from or 
examined at the FAA, Transport Airplane Directorate, 1601 Lind Ave, 
SW., Renton, Washington 98055-4056.

FOR FURTHER INFORMATION CONTACT: Forrest Keller, Senior Engineer, 
Systems and Equipment Branch, ANM-130S, FAA, Transport Airplane 
Directorate, Seattle Aircraft Certification Office, 1601 Lind Avenue, 
SW., Renton, Washington 98055-4056; telephone (425) 227-2790; fax (425) 
227-1181.

SUPPLEMENTARY INFORMATION: The FAA has received a report indicating 
that damaged wires caused an electrical short in the P11 electrical 
panel on a Boeing Model 757-200 series airplane after takeoff, which 
resulted in a shower of sparks from the overhead panel. Subsequently, 
several erroneous flight deck indications appeared with the display of 
multiple caution messages by the engine indication and crew alerting 
system (EICAS). Investigation of the looms behind the P11 electrical 
panel revealed that certain wires were routed over the top of the 
disconnect bracket close to the bracket-bonding stud, which caused the 
wires to chafe through and resulted in an electrical short in the 
panel. In a fleetwide inspection of 13 other Boeing Model 757-200 
series airplanes, damaged wires on three additional airplanes were 
detected. This condition, if not corrected, could result in failure of 
essential electrical systems and a potential fire hazard for passengers 
and crewmembers, due to damage or chafing of electrical wire bundles.

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 failure of essential electrical systems and a 
potential fire hazard for passengers and crewmembers, due to damage or 
chafing of electrical wire bundles. This AD requires a one-time 
detailed visual inspection to detect damage or chafing of certain 
electrical wire bundles, and to verify adequate clearance exists 
between the wire bundles and adjacent disconnect bracket; and repair, 
if necessary. Accomplishment of the actions described previously is 
intended to adequately address the identified unsafe condition.

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.
    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.

[[Page 46648]]

    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 98-NM-242-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    The regulations adopted herein will not have substantial direct 
effects 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, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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, 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:
98-18-14 Boeing: Amendment 39-10730. Docket 98-NM-242-AD.
    Applicability: Model 757-200 series airplanes, certificated in any 
category; excluding the following line numbers:

2    75   221  127  130  162
180  209  212  219  388  526

    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 failure of essential electrical systems and a 
potential fire hazard for passengers and crewmembers due to damage 
or chafing of electrical wire bundles, accomplish the following:
    (a) Within 90 days after the effective date of this AD, perform 
a one-time detailed visual inspection to detect damage or chafing of 
the electrical wire bundles having part numbers W2016-0001-12 and 
W2016-0002-16, and adjacent wiring; and to verify adequate clearance 
exists between the wire bundles and adjacent disconnect bracket. Pay 
particular attention to the area located on the looms behind the P11 
panel near the AP0011 disconnect bracket.
    (1) If no damage or chafing is detected, and adequate clearance 
exists, no further action is required by this AD.
    (2) If damage or chafing is detected, and adequate clearance 
exists, prior to further flight, repair the wire bundles in 
accordance with Section 20-10-13 of the Boeing Standard Wiring 
Practices Manual.
    (3) If no damage or chafing is detected and inadequate clearance 
exists, prior to further flight, modify the wire bundles to achieve 
adequate clearance, in accordance with Section 20-10-11 and 20-10-12 
of the Boeing Standard Wiring Practices Manual.
    (4) If damage or chafing is detected and inadequate clearance 
exists, prior to further flight, repair the wire bundles in 
accordance with Section 20-10-13 of the Boeing Standard Wiring 
Practices Manual; and modify the wire bundles in accordance with 
Section 20-10-11 and 20-10-12 of the Boeing Standard Wiring 
Practices Manual.
    (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, Seattle Aircraft Certification 
Office (ACO), FAA, Transport Airplane Directorate. 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.

    (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.
    (d) This amendment becomes effective on September 17, 1998.

    Issued in Renton, Washington, on August 27, 1998.
Vi L. Lipski, Acting Manager,
Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 98-23620 Filed 9-1-98; 8:45 am]
BILLING CODE 4910-13-U