[Federal Register Volume 68, Number 41 (Monday, March 3, 2003)]
[Proposed Rules]
[Pages 9947-9950]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-4842]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-259-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 767 Series 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 Boeing Model 767 
series airplanes, that currently requires a one-time inspection to 
detect abrasion damage and installation discrepancies of the wire 
bundles located below the P37 panel, and corrective action if 
necessary. For airplanes already subject to the existing AD, this 
action would require inspecting to determine whether the existing 
location of a certain wire support standoff is adequate, relocating the 
wire support standoff if necessary, installing protective sleeving over 
the wire bundles, and installing wire bundle support clamps if 
necessary. This action also would expand the applicability of the 
existing AD to include additional airplanes, and require inspecting the 
sleeving on certain wire bundles, and accomplishing corrective action 
if necessary, on those airplanes. The actions specified in this 
proposed AD are intended to detect and prevent abrasion damage and 
correct installation discrepancies of the wire bundles located below 
the P37 panel, which could result in arcing to structure and consequent 
fire or loss of function of affected systems.

DATES: Comments must be received by April 17, 2003.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-259-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-259-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 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.

FOR FURTHER INFORMATION CONTACT: Elias Natsiopoulos, Aerospace 
Engineer, Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055-
4056; telephone (425) 917-6478; fax (425) 917-6590.

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:
    [sbull] 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.
    [sbull] For each issue, state what specific change to the proposed 
AD is being requested.
    [sbull] 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-259-AD.''

[[Page 9948]]

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-259-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On November 15, 2001, the FAA issued AD 2001-17-28 R1, amendment 
39-12510 (66 FR 58924, November 26, 2001), applicable to certain Boeing 
Model 767 series airplanes, to require a one-time inspection to detect 
abrasion damage and installation discrepancies of the wire bundles 
located below the P37 panel, and corrective action if necessary. That 
action was prompted by findings of abrasion damage and installation 
discrepancies of these wire bundles on certain Boeing Model 767 series 
airplanes. The requirements of that AD are intended to detect and 
correct such abrasion damage and installation discrepancies, which 
could result in arcing to structure and consequent fire or loss of 
function of affected systems.
    In the preamble to AD 2001-17-28 R1, we indicated that the actions 
required by that AD were considered ``interim action'' and that further 
rulemaking action was being considered to add requirements to relocate 
the wire support standoff and install protective sleeving over the wire 
bundles, and to expand the applicability of the AD to include certain 
additional airplanes. We have now determined that further rulemaking 
action is indeed necessary, and this proposed AD follows from that 
determination.

Explanation of Relevant Service Information

    We have previously reviewed and approved Boeing Alert Service 
Bulletins 767-24A0134 (for Model 767-200 and -300 series airplanes) and 
767-24A0135 (for Model 767-400ER series airplanes), both Revision 1, 
both dated October 18, 2001. AD 2001-17-28 R1 refers to those alert 
service bulletins as appropriate sources of service information for the 
actions required by that AD. Those alert service bulletins identify two 
``Work Packages,'' and two groups of airplanes. Work Package 1 
describes procedures for the actions that are currently required by AD 
2001-17-28 R1 for airplanes listed in Group 1 in the alert service 
bulletins. Work Package 2, for Group 1 airplanes, describes procedures 
for performing an inspection to determine whether the existing location 
of a certain wire support standoff is adequate and whether a grommet is 
installed and not damaged (e.g., chafed), installing a new grommet if 
not already installed or if the existing grommet is damaged, relocating 
the wire support standoff if necessary, installing protective sleeving 
over certain wire bundles, and installing wire bundle support clamps. 
Work Package 2, for Group 2 airplanes, describes procedures for 
inspecting certain wire bundles to determine the type of protective 
sleeving that is installed and the location of that sleeving, 
relocating protective sleeving or replacing it with new sleeving if 
necessary, and installing wire bundle support clamps if necessary. The 
alert service bulletins specify to make sure that wire bundles are 
installed inboard/above the insulation blankets when wire bundle 
support clamps are installed. Accomplishment of the actions specified 
in the applicable alert service bulletin is intended to adequately 
address the identified unsafe condition.

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 2001-17-28 R1 to continue to require a 
one-time inspection to detect abrasion damage and installation 
discrepancies of the wire bundles located below the P37 panel, and 
corrective action if necessary. The proposed AD would also require, for 
airplanes already subject to the existing AD, inspecting to determine 
whether the existing location of a certain wire support standoff is 
adequate, relocating the wire support standoff if necessary, and 
installing protective sleeving over the wire bundles. On airplanes not 
included in the applicability of the existing AD, the proposed AD would 
require inspecting the protective sleeving on certain wire bundles, and 
corrective action if necessary. The actions would be required to be 
accomplished in accordance with the alert service bulletin described 
previously, except as discussed under the heading, ``Difference Between 
Proposed AD and Alert Service Bulletins.''
    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 
average utilization of the affected fleet, and the time necessary to 
perform the proposed actions. In light of all of these factors, we find 
an 18-month compliance time for completing the new proposed actions to 
be warranted, in that it represents an appropriate interval of time 
allowable for affected airplanes to continue to operate without 
compromising safety.

Explanation of Change Made To Existing Requirements

    We have changed all references to a ``detailed visual inspection'' 
in the existing AD to ``detailed inspection'' in this proposed AD.
    Also, we have changed the alert service bulletin citations 
throughout this proposed AD to exclude the Evaluation Form. The 
airplane manufacturer intends for operators to complete and submit this 
form to provide input on the quality of the alert service bulletin. 
However, this proposed AD would not include such a requirement.

Difference Between Proposed AD and Alert Service Bulletins

    Operators should note that the instructions under Work Package 2 in 
the alert service bulletins do not specify what type of inspection is 
needed to determine whether the existing location of a certain wire 
support standoff is adequate (Group 1 airplanes), or to determine the 
type of protective sleeving that is installed and the location of that 
sleeving (Group 2 airplanes). We have determined that a detailed 
inspection is necessary to make these determinations.

Cost Impact

    There are approximately 839 airplanes of the affected design in the 
worldwide fleet. We estimate that 325 airplanes of U.S. registry would 
be affected by this proposed AD.
    The inspection that is currently required by AD 2001-17-28 R1 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 the currently required actions on U.S. operators is estimated 
to be $39,000, or $120 per airplane.
    For airplanes in both Groups 1 and 2 as listed in the alert service 
bulletins, the new proposed actions would take approximately 2 work 
hours per airplane to accomplish, at an average labor rate of $60 per 
work hour. The cost of required parts would be negligible. Based on 
these figures, the cost impact of the new proposed requirements on U.S. 
operators is estimated to be $39,000, or $120 per airplane.

[[Page 9949]]

    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the proposed requirements 
of this AD action, and that no operator would accomplish those actions 
in the future if this proposed 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 39-12510 (66 FR 
58924, November 26, 2001), and by adding a new airworthiness directive 
(AD), to read as follows:

Boeing: Docket 2001-NM-259-AD. Supersedes AD 2001-17-28 R1, 
amendment 39-12510.

    Applicability: Model 767 airplanes, certificated in any 
category, line numbers (L/Ns) 1 through 853 inclusive.

    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)(1) 
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 detect and prevent abrasion damage and correct installation 
discrepancies of the wire bundles located below the P37 panel, which 
could result in arcing to structure and consequent fire or loss of 
function of affected systems, accomplish the following:

Requirements of AD 2001-17-28 R1

Inspection for Damage and Installation Discrepancies

    (a) For airplanes with L/Ns 1 through 815 inclusive: Within 90 
days after September 13, 2001 (the effective date of AD 2001-17-28, 
amendment 39-12419), perform a one-time detailed inspection of the 
wire bundles located below the P37 panel to detect abrasion damage 
and wire installation discrepancies (including missing standoffs; 
missing, chafed, or loose cable clamps; chafed grommets; and wire 
bundles located beneath an insulation blanket), in accordance with 
Boeing Alert Service Bulletin 767-24A0134, excluding Evaluation 
Form, dated March 15, 2001, or Revision 1, excluding Evaluation 
Form, dated October 18, 2001 (for Model 767-200 and -300 series 
airplanes); or 767-24A0135, excluding Evaluation Form, dated March 
15, 2001, or Revision 1, excluding Evaluation Form, dated October 
18, 2001 (for Model 767-400ER series airplanes). If any damage or 
other discrepancy is found, prior to further flight, perform 
corrective actions in accordance with the applicable alert service 
bulletin. After December 11, 2001 (the effective date of AD 2001-17-
28 R1, amendment 39-12510), only Revision 1 of the alert service 
bulletins may be used.

    Note 2: For the purposes of this AD, a detailed 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.''

New Requirements of This AD

    (b) Within 18 months after the effective date of this AD, do all 
actions in Work Package 2 of Boeing Alert Service Bulletin 767-
24A0134 (for Model 767-200 and -300 series airplanes) or 767-24A0135 
(for Model 767-400ER series airplanes), both Revision 1, both 
excluding Evaluation Form, both dated October 18, 2001, as 
applicable, in accordance with the Accomplishment Instructions of 
the applicable alert service bulletin. For Group 1 airplanes, the 
procedures in Work Package 2 include performing a detailed 
inspection to determine whether the location of the wire support 
standoff for wire bundle W298 is adequate and whether a grommet is 
installed and not damaged (e.g., chafed), installing a new grommet 
if not already installed or if the existing grommet is damaged, 
relocating the wire support standoff as applicable, installing 
protective sleeving over certain wire bundles, and installing wire 
bundle support clamps. When installing wire bundle support clamps, 
make sure that wire bundles are installed inboard/above the 
insulation blankets. For Group 2 airplanes, the procedures in Work 
Package 2 include performing a detailed inspection of the sleeving 
on wire bundles W298, W235, and W2130, as applicable, to determine 
the type of protective sleeving installed and the location of that 
sleeving, relocating the sleeving or replacing the sleeving with new 
sleeving as applicable, and installing wire bundle support clamps as 
applicable. When installing wire bundle support clamps, make sure 
that wire bundles are installed inboard/above the insulation 
blankets.

Alternative Methods of Compliance

    (c)(1) 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.
    (2) Alternative methods of compliance, approved previously in 
accordance with AD 2001-17-28 R1, amendment 39-12510, are approved 
as alternative methods of compliance with the corresponding 
requirements of this AD.

    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

    (d) Special flight permits may be issued in accordance with 
Sec. Sec.  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.


[[Page 9950]]


    Issued in Renton, Washington, on February 24, 2003.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-4842 Filed 2-28-03; 8:45 am]
BILLING CODE 4910-13-P