[Federal Register: June 23, 2004 (Volume 69, Number 120)]
[Proposed Rules]
[Page 34966-34969]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr23jn04-24]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-NM-89-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 777-200 and -300 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Supplemental notice of proposed rulemaking; reopening of
comment period.
-----------------------------------------------------------------------
SUMMARY: This document revises an earlier proposed airworthiness
directive (AD), applicable to certain Boeing Model 777-200 and -300
series airplanes. The proposed AD would have required a one-time
inspection of the clevis end of the vertical tie rods that support the
center stowage bins to measure the exposed thread, installation of
placards that advise of weight limits for certain electrical racks, a
one-time inspection and records check to determine the amount of weight
currently installed in those electrical racks, corrective actions, and
replacement of the vertical tie rods for the center stowage bins or
electrical racks with new improved tie rods, as applicable. This new
action revises the proposed rule by proposing to require, for certain
airplanes, inspections of additional tie rod part numbers and
additional locations. This new action also proposes to revise an
inspection method. The actions specified by this new proposed AD are
intended to prevent failure of the tie rods supporting certain
electrical racks and the center stowage bins, which could cause the
racks or stowage bins to fall onto passenger seats below during an
emergency landing, impeding an emergency evacuation or injuring
passengers. This action is intended to address the identified unsafe
condition.
DATES: Comments must be received by July 19, 2004.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 2001-NM-89-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-89-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 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.
FOR FURTHER INFORMATION CONTACT: Robert Kaufman, Aerospace Engineer,
Cabin Safety and Environmental Systems Branch, ANM-150S, FAA, Seattle
Aircraft Certification Office, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056; telephone (425) 917-6433; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
[[Page 34967]]
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:
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 proposed
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 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-89-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. 2001-NM-89-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
A proposal to amend part 39 of the Federal Aviation Regulations (14
CFR part 39) to add an airworthiness directive (AD), applicable to
certain Boeing Model 777-200 and -300 series airplanes, was published
as a notice of proposed rulemaking (NPRM) in the Federal Register on
September 9, 2003 (68 FR 53055). That NPRM would have required, for all
airplanes, installation of a placard that advises of weight limits for
a certain electrical rack, accomplishment of a one-time inspection and
records check to determine the amount of weight currently installed in
that rack, and removal of equipment from that rack if necessary. For
certain airplanes, that NPRM also would have required a one-time
inspection of the clevis end of the vertical tie rods that support the
center stowage bins to measure the exposed thread, installation of
placards that advise of weight limits for certain other electrical
racks, a one-time inspection and records check to determine the amount
of weight currently installed in certain other electrical racks,
corrective actions, and replacement of the vertical tie rods for the
center stowage bins or electrical racks with new improved tie rods, as
applicable. That NPRM was prompted by a report indicating that, under
certain conditions on Boeing Model 777-200 and -300 series airplanes,
the vertical tie rods that attach the center stowage bins and
electrical racks to the airplane structure can break. That condition,
if not corrected, could result in the racks or stowage bins falling
onto passenger seats below during an emergency landing, impeding an
emergency evacuation or injuring passengers.
Explanation of New Relevant Service Information
Since the issuance of that NPRM, the FAA has reviewed and approved
Boeing Special Attention Service Bulletin 777-25-0144, Revision 2,
dated January 15, 2004. (The NPRM referred to Boeing Service Bulletin
777-25-0144, Revision 1, dated January 10, 2002, as the appropriate
source of service information for accomplishing the proposed actions.)
Among other things, for certain airplanes, Revision 2 of the service
bulletin includes additional affected tie rod part numbers and
additional locations that are subject to the one-time inspection to
measure the exposed thread of the clevis end of the vertical tie rods
supporting the center stowage bins, and installation of a threaded
sleeve if necessary. Revision 2 of the service bulletin also divides
the Accomplishment Instructions into Parts 1, 2, and 3, with Parts 2
and 3 of the Accomplishment Instructions providing instructions for
airplanes in certain groups that were modified per the original issue
or Revision 1 of the service bulletins. (Parts 2 and 3 specify
inspecting the clevis end of the vertical support tie rod for the
center stowage bin in certain locations to determine whether a threaded
sleeve was installed, and installing a threaded sleeve and re-torquing
the jam nuts, as applicable.)
Also, while the instructions in Revision 1 of the service bulletin
for replacing the vertical support tie rods for the center stowage bin
specify inspecting through the witness hole to make sure tie rod
threads are visible, Revision 2 of the service bulletin revises this
instruction to specify inserting a pin in the witness hole to ensure
that the witness hole is blocked by the clevis shank.
Accomplishment of the actions specified in the service bulletin is
intended to adequately address the identified unsafe condition.
Explanation of Additional Changes to Supplemental NPRM
We have revised paragraph (b) of this supplemental NPRM to specify
corrective actions that may be necessary as a result of findings from
the inspection in that paragraph. The corrective actions were not
specifically identified in the original NPRM.
Paragraph (e) of the original NPRM specifies that, where the
service bulletin specifies to contact Boeing for appropriate action,
repair would be required per a method approved by the FAA, or per data
approved by an authorized Boeing Company Designated Engineering
Representative. The instruction to contact Boeing has been removed from
Revision 2 of the service bulletin, so paragraph (e) of the original
NPRM is not included in this supplemental NPRM.
Conclusion
Since certain changes described previously expand the scope of the
originally proposed rule, the FAA has determined that it is necessary
to reopen the comment period to provide additional opportunity for
public comment.
Cost Impact
There are approximately 282 airplanes of the affected design in the
worldwide fleet. The FAA estimates that 84 airplanes of U.S. registry
would be affected by this proposed AD.
For all airplanes: The records check and inspection to determine
the weight currently installed in electrical rack E7 would take
approximately 1 work hour per airplane to accomplish, at an average
labor rate of $65 per work hour. Based on these figures, the cost
impact of this proposed records check and inspection on U.S. operators
is estimated to be $5,460, or $65 per airplane.
For all airplanes: It would take approximately 1 work hour to
[[Page 34968]]
accomplish the proposed installation of a placard specifying weight
limits for electrical rack E7, at an average labor rate of $65 per work
hour. Required parts would cost approximately $29. Based on these
figures, the cost impact of this proposed placard installation on U.S.
operators is estimated to be $7,896, or $94 per electrical rack.
For airplanes subject to the records check and inspection to
determine the weight currently installed in electrical rack E9, E11,
E13, or E15: It would take approximately 1 work hour per electrical
rack (up to 4 racks per airplane) to accomplish, at an average labor
rate of $65 per work hour. Based on these figures, the cost impact of
this proposed records check and inspection is estimated to be as much
as $260 per airplane.
For airplanes subject to the installation of a placard specifying
weight limits for electrical rack E9, E11, E13, or E15: It would take
approximately 1 work hour per electrical rack to accomplish, at an
average labor rate of $65 per work hour. Required parts would cost
approximately $29 per electrical rack. Based on these figures, the cost
impact of this proposed installation is estimated to be as much as $376
per airplane.
For airplanes subject to the inspection of the clevis end of the
vertical support tie rod for the center stowage bin to measure the
exposed thread: It would take as much as 3 work hours per airplane
(0.25 work hour per tie rod, with up to 12 subject tie rods per
airplane) at an average labor rate of $65 per work hour. Based on these
figures, the cost impact of this proposed inspection is estimated to be
as much as $195 per airplane.
For airplanes subject to the replacement of the vertical tie rods
that support the center stowage bins: It would take as much as 6 work
hours per airplane (0.5 work hour per tie rod, with up to 12 subject
tie rods per airplane) at an average labor rate of $65 per work hour.
Required parts would cost as much as $3,020 per airplane. Based on
these figures, this proposed replacement is estimated to be as much as
$3,410 per airplane.
For airplanes subject to the replacement of the vertical tie rods
that support the electrical racks: It would take as much as 2 work
hours per airplane (0.5 work hour per tie rod with up to 4 subject tie
rods per airplane) at an average labor rate of $65 per work hour.
Required parts would cost as much as $3,012 per airplane. Based on
these figures, this proposed replacement is estimated to be as much as
$3,142 per airplane.
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 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 adding the following new
airworthiness directive:
Boeing: Docket 2001-NM-89-AD.
Applicability: Model 777-200 and -300 series airplanes; line
numbers 002 through 151 inclusive, 153 through 157 inclusive, 159
through 195 inclusive, 197 through 211 inclusive, 213 through 237
inclusive, 239 through 241 inclusive, and 243 through 282 inclusive;
certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent failure of the vertical tie rods that attach the
center stowage bins and electrical racks to the airplane structure,
which could cause the center stowage bins and electrical racks to
fall onto passenger seats below, impeding an emergency evacuation or
injuring passengers, accomplish the following:
Inspection To Determine Weight and Placard Installation
(a) For airplanes in the groups listed in the table under
paragraph 3.B.1.b.(3) of the Accomplishment Instructions of Boeing
Special Attention Service Bulletin 777-25-0144, Revision 2, dated
January 15, 2004: Within 5 years after the effective date of this
AD, do the applicable actions in paragraphs (a)(1) and (a)(2) of
this AD.
(1) Install placards that show weight limits for electrical
racks E7, E11, and E15; as applicable; per the Accomplishment
Instructions of the service bulletin.
(2) For each electrical rack on which a placard was installed
per paragraph (a)(1) of this AD: Before further flight after
installing the placard, perform a one-time inspection and records
check to determine the weight of equipment installed in that
electrical rack. This records review and inspection must include
determining what extra equipment, if any, has been installed in the
subject rack of the airplane, performing a detailed inspection to
determine whether this equipment is installed on the airplane,
calculating the total weight of the installed equipment, and
comparing that total to the weight limit specified on the placard
installed per paragraph (a)(1) of this AD. If the weight is outside
the limits specified in the placard to be installed per the service
bulletin, before further flight, remove equipment from the rack to
meet the weight limit specified in the placard.
Note 1: 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.''
Inspection To Measure Exposed Thread and Corrective Actions
(b) For airplanes in the groups listed in the table under
paragraph 3.B.1.b.(1) of the
[[Page 34969]]
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 777-25-0144, Revision 2, dated January 15, 2004: Within 5
years after the effective date of this AD, perform a detailed
inspection of the clevis end of the vertical support tie rod for the
center stowage bin to measure the exposed thread, per the
Accomplishment Instructions of the service bulletin. If the
measurement of the exposed thread is outside the limits specified in
Figure 2 of the service bulletin, before further flight, perform all
corrective actions specified in steps 2 through 14 inclusive of
Figure 2 of the service bulletin (including installing a threaded
sleeve, torquing the jam nuts, inserting a pin in the witness hole
to ensure that the witness hole is blocked by the clevis shank, and
making any applicable adjustment of the clevis). Perform the
corrective actions per the Accomplishment Instructions of the
service bulletin, except as provided by paragraph (e) of this AD.
Replacement of Tie Rods for Center Stowage Bin
(c) For airplanes in Group 21, as listed in the Airplane Group
column of the table under 3.B.1.b.(2) of the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 777-25-
0144, Revision 2, dated January 15, 2004: Within 5 years after the
effective date of this AD, replace the vertical support tie rods for
the center stowage bin with new improved tie rods (including
replacing the existing tie rod with a new improved tie rod, torquing
the jam nuts, inserting a pin in the witness hole to ensure that the
witness hole is blocked by the clevis shank, and making any
applicable adjustment of the clevis) by doing all actions specified
in steps 1 through 8 of Figure 3 of the service bulletin. Do these
actions per the Accomplishment Instructions of the service bulletin.
Any required adjustment of the clevis must be done before further
flight.
Inspection To Determine Weight, Tie Rod Replacement, and Placard
Installation
(d) For airplanes in the groups listed in the table under
paragraph 3.B.1.b.(4) of the Accomplishment Instructions of Boeing
Special Attention Service Bulletin 777-25-0144, Revision 2, dated
January 15, 2004: Do the actions in paragraphs (d)(1), (d)(2), and
(d)(3) of this AD.
(1) Within 5 years after the effective date of this AD, replace
the vertical support tie rods for electrical racks E9, E11, and E13
(including replacing the existing tie rods with new improved tie
rods, replacing an existing tie rod clamp with a new improved tie
rod clamp, performing a free-play inspection of certain electrical
racks, adjusting jam nuts as applicable, performing a general visual
inspection through the witness hole to make sure tie rod threads are
visible, and making any applicable adjustment to ensure tie rod
threads are visible) by doing all actions specified in Figures 5, 6,
7, and 9 of the service bulletin; as applicable. Do these actions
per the Accomplishment Instructions of the service bulletin. Any
required adjustment must be done before further flight.
(2) Before further flight after accomplishing paragraph (d)(1)
of this AD, install placards that show weight limits for electrical
racks E9, E11, and E13; as applicable; per the Accomplishment
Instructions of the service bulletin.
(3) For each electrical rack on which a placard was installed
per paragraph (d)(2) of this AD: Before further flight after
accomplishing paragraphs (d)(1) and (d)(2) of this AD, perform a
one-time inspection and records check to determine the weight of
equipment installed in that electrical rack. This records review and
inspection must include determining what, if any, extra equipment
has been installed in the subject racks of the airplane, performing
a detailed inspection to determine that this equipment is installed
on the airplane, calculating the total weight of the installed
equipment, and comparing that total to the weight limit specified on
the placard installed per paragraph (d)(2) of this AD. If the weight
is outside the limits specified in the placard, before further
flight, remove equipment from the rack to meet the weight limit
specified in the placard.
Actions Accomplished Previously
(e) Actions accomplished before the effective date of this AD
per the Accomplishment Instructions of Boeing Service Bulletin 777-
25-0144, dated January 25, 2001; or Revision 1, dated January 10,
2002; are acceptable for compliance with the corresponding actions
required by this AD, provided that the additional actions specified
in Part 2 or 3 of the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 777-25-0144, Revision 2, dated January
15, 2004, are accomplished within the compliance time specified in
this AD.
Alternative Methods of Compliance
(f) In accordance with 14 CFR 39.19, the Manager, Seattle
Aircraft Certification Office, FAA, is authorized to approve
alternative methods of compliance for this AD.
Issued in Renton, Washington, on June 16, 2004.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-14183 Filed 6-22-04; 8:45 am]
BILLING CODE 4910-13-P