[Federal Register: September 19, 2003 (Volume 68, Number 182)]
[Proposed Rules]
[Page 54864-54866]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr19se03-29]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-306-AD]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model DC-9-10, DC-9-
20, DC-9-30, DC-9-40, and DC-9-50 Series Airplanes; and Model DC-9-81
(MD-81) and DC-9-82 (MD-82) 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 McDonnell Douglas
transport category airplanes, that currently requires an inspection for
chafing and/or abrasion, repair if necessary, and modification of the
power feeder cable installation. This action would require inspection
for proper installation, damage, or abrasion of the power feeder cables
and trough installations; proper installation of caterpillar grommets
in the lightening holes; and repair if necessary. This action also
would require modification of the power feeder cable installation and
add airplanes to the applicability of the AD. The actions specified by
the proposed AD are intended to prevent a possible loss of electrical
bus power, which could result in a potential fire ignition source and
consequent fire in the cabin. This action is intended to address the
identified unsafe condition.
DATES: Comments must be received by November 3, 2003.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2002-NM-306-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. 2002-NM-306-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 or 2000 or
ASCII text.
The service information referenced in the proposed rule may be
obtained from Boeing Commercial Aircraft Group, Long Beach Division,
3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data
and Service Management, Dept. C1-L5A (D800-0024). This information may
be examined at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft
Certification Office, 3960 Paramount Boulevard, Lakewood, California.
FOR FURTHER INFORMATION CONTACT: Elvin Wheeler, Aerospace Engineer,
Systems and Equipment Branch, ANM-130L, FAA, Los Angeles Aircraft
Certification Office, 3960 Paramount Boulevard, Lakewood, California
90712-4137; telephone (562) 627-5344; fax (562) 627-5210.
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
[[Page 54865]]
statement is made: ``Comments to Docket Number 2002-NM-306-AD.'' 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. 2002-NM-306-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
On January 10, 1986, the FAA issued AD 85-25-06, amendment 39-5177
(50 FR 49833, December 5, 1985), applicable to certain McDonnell
Douglas Model DC-9 and C-9 (military) series airplanes, to require
inspection of the power feeder cable installation, repair if necessary,
and modification of the power feeder cable installation between the
electrical power center and the respective generators. That action was
prompted by reports of chafing and/or abrasion of the power feeder
cables and six instances of shorted 1 power feeder cables. The chafing
and/or abrasion was attributed to power feeder cables riding against
bulkhead feedthroughs, floor panel clipnuts, and lightening holes in
transition areas below floor level. The requirements of that AD are
intended to eliminate a potential fire ignition source from the
generator power feeder cable installation.
Actions Since Issuance of Previous Rule
Since the issuance of that AD, the manufacturer has advised the FAA
that additional airplanes have been identified that also may be subject
to the identified unsafe condition.
Explanation of Relevant Service Information
The FAA has reviewed and approved McDonnell Douglas Alert Service
Bulletin (ASB) DC9-24A078, Revision 04, dated May 25, 2000, which
describes procedures for a general visual inspection for damage such as
sharp object penetration or abrasion damage of the power feeder cables,
a general visual inspection of the power feeder cables, troughs and
associated hardware for secure and proper installation, and repair if
necessary. That ASB also describes procedures for installing grommets
on all lightening holes where the power feeder cables pass through, and
performing a generator control relay test on any repaired power feeder
cables. For certain airplanes, that ASB also describes modification of
the power feeder cable installation (including installing lightening
hole grommets, replacing clipnuts with clipnuts specified in the ASB,
as applicable, and performing a generator circuit relay test).
Additionally, that ASB adds airplanes to the effectivity of the ASB.
Accomplishment of the actions specified in the ASB 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 85-25-06 to require general visual
inspections for proper installation, damage, or abrasion of the power
feeder cables and trough installations; proper installation of
caterpillar grommets in the lightening holes; and repair if necessary.
For certain airplanes, this proposed AD would require modification, as
described previously, of the power feeder cable installation. The
actions would be required to be accomplished in accordance with the
service bulletin described previously.
Explanation of Change to Applicability
The FAA has revised the applicability of this proposed AD to
reference the appropriate models as listed in the current published
Type Certification Data Sheet.
Changes to 14 CFR Part 39/Effect on the Proposed AD
On July 10, 2002, the FAA issued a new version of 14 CFR part 39
(67 FR 47997, July 22, 2002), which governs the FAA's airworthiness
directives system. The regulation now includes material that relates to
altered products, special flight permits, and alternative methods of
compliance (AMOCs). Because we have now included this material in part
39, only the office authorized to approve AMOCs is identified in each
individual AD.
Change to Labor Rate Estimate
We have reviewed the figures we have used over the past several
years to calculate AD costs to operators. To account for various
inflationary costs in the airline industry, we find it necessary to
increase the labor rate used in these calculations from $60 per work
hour to $65 per work hour. The cost impact information, below, reflects
this increase in the specified hourly labor rate.
Cost Impact
There are approximately 1,050 airplanes of the affected design in
the worldwide fleet. The FAA estimates that 475 airplanes of U.S.
registry would be affected by this proposed AD.
The new actions that are proposed in this AD action would take
approximately (depending on the applicable airplane group specified in
the service bulletin) from 1 work hour per airplane to 25 work hours
per airplane to accomplish, at an average labor rate of $65 per work
hour. Certain airplane groups (1, 2, and 7) do not require parts. For
certain other airplane groups (5 and 6), required parts would cost
approximately $291 to $428 per airplane. Based on these figures, the
cost impact of the proposed requirements of this AD on U.S. operators
is estimated to be between $65 per airplane for certain airplane
groups, and $2,053 per airplane for certain other airplane groups.
The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of the current or proposed
requirements of this AD action, and that no operator would accomplish
those actions in the future if this 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.
[[Page 54866]]
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 39-5177 (50 FR
49833, December 5, 1985), and by adding a new airworthiness directive
(AD), to read as follows:
McDonnell Douglas: Docket 2002-NM-306-AD. Supersedes AD 85-25-06,
Amendment 39-5177.
Applicability: Model DC-9-11, DC-9-12, DC-9-13, DC-9-14, DC-9-
15, and DC-9-15F airplanes; Model DC-9-21 airplanes; Model DC-9-31,
DC-9-32, DC-9-32 (VC-9C), DC-9-32F, DC-9-32F (C-9A and C-9B), DC-9-
33F, DC-9-34 and DC-9-34F airplanes; Model DC-9-41 airplanes; Model
DC-9-51 airplanes; and Model DC-9-81 (MD-81) and DC-9-82 (MD-82)
airplanes; as specified in McDonnell Douglas Alert Service Bulletin
DC9-24A078, Revision 04, dated May 25, 2000; certificated in any
category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent a possible loss of electrical bus power due to
chafing and/or abrasion of the power feeder cable installation,
which could result in a potential fire ignition source and
consequent fire in the cabin; accomplish the following:
Inspection
(a) Within 2 years after the effective date of this AD, perform
a general visual inspection for proper installation, damage (e.g.,
evidence of sharp object penetration), or abrasion of the power
feeder cables and trough installations, and for proper installation
of caterpillar grommets in the lightening holes; per the Work
Instructions of McDonnell Douglas Alert Service Bulletin (ASB) DC9-
24A078, Revision 04, dated May 25, 2000.
Note 1: 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.''
Note 2: It is not necessary to inspect power feeder cables that
are contained in conduit.
(b) If any abrasion or damage is found on the power feeder
cables and troughs or any improper installation of the caterpillar
grommets in the lightening holes is detected during the inspections
required by paragraph (a) of this AD, before further flight, repair
per the Work Instructions of McDonnell Douglas ASB DC9-24A078,
Revision 04, dated May 25, 2000.
(c) Within 2 years after the effective date of this AD, modify
the power feeder cable installation (including installing lightening
hole grommets, replacing clipnuts with clipnuts specified in
McDonnell Douglas ASB DC9-24A078, Revision 04, dated May 25, 2000,
as applicable, and performing a generator circuit relay test), per
the Work Instructions of McDonnell Douglas ASB DC9-24A078, Revision
04, dated May 25, 2000.
Acceptable Methods of Compliance
(d) Accomplishment of the actions specified in McDonnell Douglas
DC-9 Service Bulletin 24-78, dated April 9, 1985; Revision 1, dated
December 9, 1985; Revision 2, dated March 20, 1986; or Revision 3,
dated July 17, 1987; before the effective date of this AD, is
acceptable as a method of compliance with the requirements of this
AD.
Alternative Methods of Compliance
(e) In accordance with 14 CFR 39.19, the Manager, Los Angeles
Aircraft Certification Office (ACO), FAA, is authorized to approve
alternative methods of compliance for this AD.
Issued in Renton, Washington, on September 15, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-23938 Filed 9-18-03; 8:45 am]
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