AD 2002-17-05

[Federal Register Volume 67, Number 169 (Friday, August 30, 2002)]
[Rules and Regulations]
[Pages 55710-55712]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-22007]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-154-AD; Amendment 39-12871; AD 2002-17-05]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 727 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 all Boeing Model 727 series airplanes. This action 
requires a one-time inspection to find discrepancies of the wire 
bundles and hydraulic tubing in the aft stairwell area, and corrective 
action, if necessary. This action is necessary to find and fix such 
discrepancies, which could result in electrical arcing between the 
wiring and hydraulic tubing, and consequent fire and damage to adjacent 
structure. This action is intended to address the identified unsafe 
condition.

DATES: Effective September 16, 2002.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 16, 2002.
    Comments for inclusion in the Rules Docket must be received on or 
before October 29, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2002-NM-154-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: 
<a href="/cdn-cgi/l/email-protection#1e27337f707333777f6c7d7173737b706a5e787f7f30797168"><span class="__cf_email__" data-cfemail="1c25317d727131757d6e7f7371717972685c7a7d7d327b736a">[email&#160;protected]</span></a>. Comments sent via fax or the Internet must 
contain ``Docket No. 2002-NM-154-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 
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:
    Technical Information: Kenneth Frey, Aerospace Engineer, Systems 
and Equipment Branch, ANM-130S, FAA, Seattle Aircraft Certification 
Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone 
(425) 227-2673; fax (425) 227-1181.
    Other Information: Sandi Carli, Airworthiness Directive Technical 
Editor/Writer; telephone (425) 687-4243, fax (425) 687-4248. Questions 
or comments may also be sent via the Internet using the following 
address: <a href="/cdn-cgi/l/email-protection#295a48474d40074a485b4540694f4848074e465f"><span class="__cf_email__" data-cfemail="ec9f8d828885c28f8d9e8085ac8a8d8dc28b839a">[email&#160;protected]</span></a>. Questions or comments sent via the 
Internet as attached electronic files must be formatted in Microsoft.

SUPPLEMENTARY INFORMATION: The FAA received a report that, during a 
through-flight check shortly after the landing of a Boeing Model 727-
200F series airplane, a crew member on board the airplane saw smoke in 
the left aft stairwell area. Evidence of overheating (molten aluminum) 
and fire damage was found between body stations 1203 and 1223, in 
addition to on the upper and lower torque boxes outboard and above the 
standby hydraulic reservoir. Investigation revealed the fire was caused 
by an electrical wire bundle chafing and subsequently arcing against a 
hydraulic system ``A'' case drain return line tube. The wire bundle 
provides electrical power to the standby hydraulic pump. A hole was 
burned in the aft side of the tube and in the back of a bend on a 
hydraulic reservoir pressurization tube located four feet above the 
drain return line tube. Such discrepancies of the wire bundle, if not 
found and fixed, could result in electrical arcing between the wiring 
and hydraulic tubing, and consequent fire and damage to adjacent 
structure.

Similar Models

    All Boeing Model 727 series airplanes have the same configuration 
of the aft stairwell area as that on the affected Model 727-200F series 
airplane. Therefore, all of these models may be subject to the same 
unsafe condition.

[[Page 55711]]

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletin 
727-29A0068, dated May 30, 2002. The service bulletin describes 
procedures for a one-time inspection to find discrepancies (including 
inadequate clearance between the wire bundles and hydraulic tubing and/
or structure, missing clamps, chafing, fire damage to structure, or 
damage to wire bundles) of the wire bundles and hydraulic tubing (wire 
bundles W344 and W338, and hydraulic system ``A'' case drain line tube, 
part number 65-17844-146) in the aft stairwell area, and corrective 
action, if necessary. The corrective action includes repositioning of 
the wire bundles and clamps to ensure a minimum clearance of 0.25 inch 
between the wire bundles and hydraulic tubing and/or structure and 
installing clamps; repairing or replacing any damaged wiring and 
tubing; inspecting the adjacent structural area for fire damage, and 
repairing any damage.
    The service bulletin refers to Boeing Standard Wiring Practices 
Manuals 20-10-11, 20-10-12, and 20-10-13 for repair or replacement of 
any damaged wiring. The service bulletin also refers to the 727 
Airplane Maintenance Manual for repair or replacement of any damaged 
hydraulic tubing or structure. Accomplishment of the actions specified 
in the service bulletin 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 
requires accomplishment of the actions specified in the service 
bulletin described previously, except as discussed below.

Differences Between Service Information and This AD

    The service bulletin refers only to a ``visual inspection'' for 
discrepancies of the wire bundles and hydraulic tubing. We have 
determined that the procedures in the service bulletin should be 
described as a ``general visual inspection.'' Note 2 has been included 
in this AD to define this type of inspection.
    The service bulletin recommends doing the inspection ``at the 
earliest maintenance opportunity when facilities and manpower are 
available.'' However, we have determined that such a compliance time 
will not ensure that operators address the unsafe condition in a timely 
manner. In developing an appropriate compliance time for this AD, we 
considered not only the manufacturer's recommendation, but the degree 
of urgency associated with addressing the subject unsafe condition, the 
significant impact on scheduling and cost for the large fleet of 
airplanes which must be inspected, and adequate time and availability 
of facilities for safe and accurate accomplishment of the inspection. 
In light of all of these factors, we find a 120-day compliance time for 
doing the inspection to be warranted in that it represents an 
appropriate interval of time allowable for affected airplanes to 
continue to operate without compromising safety.

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 2002-NM-154-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.

[[Page 55712]]

Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

2002-17-05  Boeing:  Amendment 39-12871. Docket 2002-NM-154-AD.

    Applicability: All Model 727 series airplanes, 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 find and fix discrepancies of the wire bundles and hydraulic 
tubing in the aft stairwell area, which could result in electrical 
arcing between the wiring and hydraulic tubing and consequent fire 
and damage to adjacent structure, accomplish the following:

General Visual Inspection/Corrective Action

    (a) Within 120 days after the effective date of this AD: Do a 
general visual inspection to find discrepancies (including 
inadequate clearance between the wire bundles and hydraulic tubing 
and/or structure, missing clamps, chafing, fire damage to structure, 
or damage to wire bundles) of the wire bundles and hydraulic tubing 
in the aft stairwell area, per the Work Instructions of Boeing Alert 
Service Bulletin 727-29A0068, dated May 30, 2002.
    (1) If no discrepancy is found, no further action is required by 
this AD.
    (2) If any discrepancy is found, before further flight, fix the 
discrepancy (includes repositioning of the wire bundles and clamps 
to ensure a minimum clearance of 0.25 inch between the wire bundles 
and hydraulic tubing and/or structure and installing clamps; 
repairing or replacing any damaged wiring and tubing; if evidence of 
fire damage, inspecting adjacent structural area for damage, and 
repairing any damage), per Figure 1 of the service bulletin.

    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.''

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, Seattle 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, 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.

Special Flight Permits

    (c) Special flight permits may be issued in accordance with 
Secs. 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 727-29A0068, dated May 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 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.

Effective Date

    (e) This amendment becomes effective on September 16, 2002.


    Issued in Renton, Washington, on August 22, 2002.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-22007 Filed 8-29-02; 8:45 am]
BILLING CODE 4910-13-U