[Federal Register: June 2, 2004 (Volume 69, Number 106)]
[Rules and Regulations]
[Page 31002-31005]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr02jn04-4]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-202-AD; Amendment 39-13648; AD 2004-11-03]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-400 and -400F Series
Airplanes Equipped With Rolls Royce Engines
AGENCY: Federal Aviation Administration, DOT.
[[Page 31003]]
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Boeing Model 747-400 and -400F series airplanes.
This action requires repetitive inspections for damage or arcing of the
power feeder cables and conduit of the integrated drive generator (IDG)
in the forward section of all four struts, and repair if necessary.
This action also requires repetitive inspections for chafing damage or
arcing of the adjacent hydraulic lines in the aft section of the
outboard struts. Additionally, this action requires eventual
terminating actions for the repetitive inspections. This action is
necessary to prevent damage and arcing to the conduit and power feeder
cables of the IDG, which could result in a fire in the engine strut;
and to prevent damage to the adjacent hydraulic lines in the aft
section of the outboard struts, which could result in reduced
controllability of the airplane. This action is intended to address the
identified unsafe condition.
DATES: Effective June 17, 2004.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 17, 2004.
Comments for inclusion in the Rules Docket must be received on or
before August 2, 2004.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2003-NM-202-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-iarcomment@faa.gov. Comments sent via fax or the Internet must
contain ``Docket No. 2003-NM-202-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 this AD may be obtained from
Boeing Commercial Airplanes, 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
National Archives and Records Administration (NARA). For information on
the availability of this material at NARA, call (202) 741-6030, or go
to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
FOR FURTHER INFORMATION CONTACT: Sulmo Mariano, Aerospace Engineer,
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone
(425) 917-6501; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION: The FAA has received a report of power
feeder cables of the integrated drive generator (IDG) chafing against
an adjacent hydraulic case drain line in the number 4 strut of certain
Boeing Model 747-400 and -400F series airplanes. The chafing caused
arcing from the power feeder cable that resulted in a leak in the
hydraulic line. Investigation revealed that excessive slack in the
power feeder cables could potentially cause a chafing condition with
the hydraulic case drain line or the hydraulic pressure line. We also
received reports indicating a chafed power feeder cable located inside
the conduit of the forward section of the engine strut, damage to the
cables and protective sleeve inside the conduit, and damage to the
cable insulation. We received a report of an additional indication of a
chafed power feeder cable inside the conduit, in which the resulting
arcing between the cable and conduit appeared to have caused molten
metal to drip onto the adjacent fuel tube and to burn a small hole in
the tube. The engine struts have no provision for detection or
containment of a fire. Such damage and arcing to the conduit and power
feeder cables of the IDG, could result in an uncontrolled fire in the
engine strut; and cause damage to the adjacent hydraulic lines in the
aft section of the outboard struts, and consequent reduced
controllability of the airplane. This action is intended to address the
identified unsafe condition.
Explanation of Relevant Service Information
We have reviewed and approved the following Boeing Service
Bulletins (SBs) and Alert Service Bulletins (ASBs):
SB 747-24A2240, Revision 1, dated February 20, 2003, which
describes procedures for general visual inspections of the power feeder
cables and conduit of the integrated drive generator (IDG) for damage
or arcing and repair if necessary, on all four engine struts.
ASB 747-24A2247, dated July 10, 2003, which describes
procedures for general visual inspections of the power feeder cables of
the IDG and hydraulic lines on each outboard strut aft of the block
clamp for chafing and arcing damage, and repair if necessary.
SB 747-24A2242, Revision 1, dated August 14, 2003, which
describes procedures for removing the conduit, installing a new shield/
bracket assembly, and replacing two hydraulic lines in each engine
strut. Those actions will prevent chafing inside the conduit and
prevent chafing of the power feeder cables with the hydraulic lines.
Accomplishment of those actions eliminates the need to continue the
repetitive inspections described in SB 747-24A2240.
ASB 747-24A2243, dated October 31, 2002, which describes
procedures for replacing the wiring and tubing support bracket with a
new bracket. Such replacement provides improved separation between the
power feeder cables of the IDG and the hydraulic case drain line in the
outboard struts, and eliminates the need to continue the repetitive
inspections described in ASB 747-24A2247.
Accomplishment of the actions specified in the SBs and ASBs is
intended to adequately address the identified unsafe condition.
Explanation of 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 that may be
registered in the United States at some time in the future, this AD is
being issued to prevent damage and arcing to the conduit and power
feeder cables of the IDG, which could result in a fire in the engine
strut; and to prevent damage to the adjacent hydraulic lines in the aft
section of the outboard struts, which could result in reduced
controllability of the airplane. This AD requires accomplishment of the
actions specified in the service bulletins described previously.
Cost Impact
None of the airplanes affected by this action are on the U.S.
Register. All airplanes included in the applicability of this rule
currently are operated by non-U.S. operators under foreign registry;
therefore, they are not directly affected by this AD action. However,
the FAA considers that this rule is necessary to ensure that the unsafe
condition is addressed in the event that any of these subject airplanes
are imported and placed on the U.S. Register in the future.
Should an affected airplane be imported and placed on the U.S.
Register in the future, it would require
[[Page 31004]]
approximately 14 work hours per airplane to accomplish the required
inspections, at an average labor rate of $65 per work hour. The
estimated cost for the required inspections is estimated to cost $910,
per airplane, per inspection cycle.
It would also require between 52 and 56 work hours, per airplane,
to accomplish the terminating actions required by this AD, at an
average labor rate of $65 per work hour. Required parts to accomplish
the terminating actions are estimated to cost approximately $14,188.
Based on these figures, the cost impact of this AD would be between
$24,588 and $25,628, per airplane, to accomplish the terminating
actions.
Determination of Rule's Effective Date
Since this AD action does not affect any airplane that is currently
on the U.S. Register, it has no adverse economic impact and imposes no
additional burden on any person. Therefore, prior notice and public
procedures hereon are unnecessary and the amendment may be made
effective in less than 30 days after publication in the Federal
Register.
Comments Invited
Although this action is in the form of a final rule and was not
preceded by notice and 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:
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.
For each issue, state what specific change to the AD is
being requested.
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 2003-NM-202-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.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it 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
0
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
0
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]
0
2. Section 39.13 is amended by adding the following new airworthiness
directive:
2004-11-03 Boeing: Amendment 39-13648. Docket 2003-NM-202-AD.
Applicability: Model 747-400 and -400F series airplanes having
line numbers 696 through 1310 inclusive and equipped with Rolls
Royce engines; certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent damage and arcing to the conduit and power feeder
cables of the integrated drive generator (IDG), which could result
in a fire in the engine strut; and to prevent damage to the adjacent
hydraulic lines in the aft section of the outboard struts, which
could result in reduced controllability of the airplane; accomplish
the following:
Inspection for Damage or Arcing
(a) Within 90 days after the effective date of this AD, perform
a general visual inspection for damage or arcing of the power feeder
cables of the integrated drive generator (IDG) and the cable
conduit, per the Accomplishment Instructions of Boeing Service
Bulletin (SB) 747-24A2240, Revision 1, dated February 20, 2003.
Before further flight, repair any damage per the SB. Thereafter,
repeat the inspection at intervals not to exceed 10,000 flight
hours, until the actions required by paragraph (c) of this AD are
accomplished.
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.''
Inspection for Chafing and Arcing Damage
(b) Within 90 days after the effective date of this AD, perform
a general visual inspection for chafing and arcing damage of the
power feeder cables of the IDG and hydraulic lines on each outboard
strut aft of the block clamp, per the Accomplishment Instructions of
Boeing Alert Service Bulletin (ASB) 747-24A2247, dated July 10,
2003. Before further flight, repair any chafing or arcing damage per
the ASB. Thereafter, repeat the inspection at intervals not to
exceed 10,000 flight hours until the actions required by paragraph
(d) of this AD are accomplished.
Terminating Requirements for Paragraph (a) of This AD
(c) Within 48 months after the effective date of this AD, remove
the conduit, install a new shield/bracket assembly, and replace two
hydraulic lines with two new hydraulic
[[Page 31005]]
lines in each engine strut, per the Accomplishment Instructions of
Boeing SB 747-24A2242, Revision 1, dated August 14, 2003. Before
further flight, perform related investigative actions and corrective
actions per the Accomplishment Instructions of the SB.
Accomplishment of these actions terminates the inspection
requirements of paragraph (a) of this AD.
Terminating Requirements for Paragraph (b) of This AD
(d) Within 48 months after the effective date of this AD,
replace the wiring and hydraulic tubing support bracket per the
Accomplishment Instructions of Boeing ASB 747-24A2243, dated October
31, 2002. Accomplishment of these actions terminates the inspection
requirements of paragraph (b) of this AD.
Alternative Methods of Compliance (AMOC)
(e) In accordance with 14 CFR 39.19, the Manager, Seattle
Aircraft Certification Office (ACO), FAA, is authorized to approve
alternative methods of compliance (AMOCs) for this AD.
Incorporation by Reference
(f) The actions shall be done in accordance with Boeing Service
Bulletin 747-24A2240, Revision 1, dated February 20, 2003; Boeing
Service Bulletin 747-24A2242, Revision 1, dated August 14, 2003;
Boeing Alert Service Bulletin 747-24A2243, dated October 31, 2002;
and Boeing Alert Service Bulletin 747-24A2247, dated July 10, 2003,
as applicable. 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
Airplanes, 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 National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
Effective Date
(g) This amendment becomes effective on June 17, 2004.
Issued in Renton, Washington, on May 18, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-11957 Filed 6-1-04; 8:45 am]
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