[Federal Register Volume 63, Number 65 (Monday, April 6, 1998)]
[Rules and Regulations]
[Pages 16681-16683]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-8705]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-95-AD; Amendment 39-10448; AD 98-07-26]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 767 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 Boeing Model 767 series airplanes. This action 
requires a detailed visual inspection(s) for damage or chafing of 
certain electrical wire bundles and for clearance between the wire 
bundles and adjacent forward galley air chiller; and follow-on 
corrective actions. This amendment is prompted by a report indicating 
that damaged wires caused the tripping of electrical circuit breakers 
and the display of caution messages by the engine indication and crew 
alerting system. 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 the 
wire bundles that resulted in arcing between exposed conductors and 
burning of the adjacent electrical bundles.

DATES: Effective April 21, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 21, 1998.
    Comments for inclusion in the Rules Docket must be received on or 
before June 5, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 98-NM-95-AD, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056.
    The service information referenced in this AD 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 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Elias Natsiopoulos, Aerospace 
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) 227-1279; 
fax (425) 227-1181.

SUPPLEMENTARY INFORMATION: The FAA has received a report indicating 
that, soon after takeoff on a Boeing Model 767 series airplane, the 
engine indication and crew alerting system (EICAS) displayed several 
caution messages and several circuit breakers tripped. After landing, 
the cabin crew reported smoke coming from the forward galley air 
chiller, located below the forward galley door under the floor.
    The smoke was produced by burning electrical wires. Investigation 
revealed that approximately 30 wires were damaged in bundles W272, 
W656, W782, and W254, forward of the P37 panel, adjacent to the AE0218 
disconnect panel, and above the aft side of the forward galley air 
chiller. Further investigation revealed that the wire bundles do not 
have protective taping or sleeves and that adequate clearance does not 
exist between the wire bundles and the adjacent chiller. As a result, 
during the removal or reinstallation of the forward galley air chiller, 
the wire bundles may become damaged or

[[Page 16682]]

chafed. When the insulation of the wire bundles is damaged or chafed, 
additional elements such as moisture, vibration, or conductive debris 
can result in arcing of the conductors.
    These conditions, if not corrected, could result in burning of the 
damaged wires and the adjacent electrical wire bundles and consequent 
fire hazard for passengers and crewmembers, and failure of essential 
electrical systems.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Message Number M-7200-98-
00140, dated January 11, 1998, which describes procedures for a 
detailed visual inspection(s) for damage or chafing of the electrical 
wire bundles located in the right-hand outboard electronics equipment 
bay and for adequate clearance between the wire bundles and adjacent 
forward galley air chiller; and follow-on corrective actions. Boeing 
Message Number M-7200-98-00140, dated January 11, 1998, also references 
Boeing Standard Wiring Practices Manual (SWPM) D6-54446, as an 
additional source of service information.

Explanation of the Requirement 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 arcing between exposed conductors, which could 
result in burning of the damaged wires and adjacent electrical bundles 
and consequent fire hazard for passengers and crewmembers, and failure 
of essential electrical systems. This AD requires accomplishment of the 
actions specified in the Boeing message described previously, except as 
discussed below.

Differences Between Rule and Service Bulletin

    While the Boeing Message Number M-7200-98-00140 does not describe 
procedures for repetitive inspections, this AD requires repetitive 
inspections for certain inspection results. For these certain 
inspection results, the FAA is not proposing to mandate the 
installation of protective tape or a sleeve over the wire bundles for 
several reasons:
    1. Accessing the wire bundles located forward of the P37 panel is 
easily accomplished.
    2. The subject damage or chafing is easily detectable by means of a 
detailed visual inspection.
    3. The failure of the wire bundles may adversely affect essential 
electrical systems; however, the detailed visual inspection will detect 
any damage or chafing of the wire bundles before they result in a 
hazardous 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.
    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-95-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, 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:

98-07-26 Boeing: Amendment 39-10448. Docket 98-NM-95-AD.

    Applicability: Model 767 series airplanes, line numbers 1 
through 683 inclusive, equipped with forward galley air chillers; 
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

[[Page 16683]]

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 arcing between exposed conductors, which could result 
in burning of the adjacent electrical bundles, failure of essential 
electrical systems, and consequent fire hazard for passengers and 
crewmembers, accomplish the following:
    (a) Within 30 days after the effective date of this AD, perform 
a detailed visual inspection for damage or chafing of the electrical 
wiring bundles located forward of the P37 panel adjacent to the 
AE0218 disconnect panel, and for adequate clearance between the wire 
bundles and adjacent forward galley air chiller, in accordance with 
Boeing Message Number M-7200-98-00140, dated January 11, 1998.

    Note 2: Boeing Message Number M-7200-98-00140, dated January 11, 
1998, also references Boeing Standard Wiring Practices Manual D6-
54446, as an additional source of service information.

    (1) If no damage or chafing is detected and adequate clearance 
exists, accomplish either paragraph (a)(1)(i) or (a)(1)(ii) of this 
AD.
    (i) Repeat the visual inspection required by paragraph (a) of 
this AD, thereafter, each time the forward galley air chiller is 
removed and reinstalled. Or
    (ii) Prior to further flight, install protective tape or sleeve 
over the wire bundles, in accordance with Section 20-00-11 of the 
Boeing Standard Wiring Practices Manual. Operators shall use one of 
the following materials to protect the bundles: RT876 (sleeve), TFX-
2X standard wall thickness (sleeve), P-440 (tape), Scotch 70 (tape), 
or CHR-A-2005 (tape).
    (2) If no damage or chafing is detected and inadequate clearance 
exists, prior to further flight, modify the routing of the wire 
bundles in accordance with the Boeing message, and install 
protective tape or sleeve over the wire bundles in accordance with 
Section 20-00-11 of the Boeing Standard Wiring Practices Manual. 
Operators shall use one of the following materials to protect the 
bundles: RT876 (sleeve), TFX-2X standard wall thickness (sleeve), P-
440 (tape), Scotch 70 (tape), or CHR-A-2005 (tape).
    (3) If damage or chafing is detected and adequate clearance 
exists, prior to further flight, repair the wire bundles in 
accordance with Boeing message, and accomplish either paragraph 
(a)(3)(i) or (a)(3)(ii) of this AD.
    (i) Repeat the visual inspection required by paragraph (a) of 
this AD, thereafter, each time the forward galley chiller is removed 
and reinstalled. Or
    (ii) Prior to further flight, install protective tape or sleeve 
over the wire bundles in accordance with Section 20-00-11 of the 
Boeing Standard Wiring Practices Manual. Operators shall use one of 
the following materials to protect the bundles: RT876 (sleeve), TFX-
2X standard wall thickness (sleeve), P-440 (tape), Scotch 70 (tape), 
or CHR-A-2005 (tape).
    (4) If damage or chafing is detected and inadequate clearance 
exists, prior to further flight, repair and modify the routing of 
the wire bundles in accordance with the Boeing message, and install 
protective tape or sleeve over the wire bundles in accordance with 
Section 20-00-11 of the Boeing Standard Wiring Practices Manual. 
Operators shall use one of the following materials to protect the 
bundles: RT876 (sleeve), TFX-2X standard wall thickness (sleeve), P-
440 (tape), Scotch 70 (tape), or CHR-A-2005 (tape).
    (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 3: 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) The inspections and modification shall be done in accordance 
with Boeing Message Number M-7200-98-00140, dated January 11, 1998. 
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 Airplane Group, 
P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be 
inspected at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
    (e) This amendment becomes effective on April 21, 1998.

    Issued in Renton, Washington, on March 27, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-8705 Filed 4-3-98; 8:45 am]
BILLING CODE 4910-13-U