[Federal Register: March 3, 2003 (Volume 68, Number 41)]
[Proposed Rules]
[Page 9947-9950]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr03mr03-24]
=======================================================================
-----------------------------------------------------------------------
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).
-----------------------------------------------------------------------
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:
9-anm-nprmcomment@faa.gov. 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