[Federal Register: September 9, 2003 (Volume 68, Number 174)]
[Proposed Rules]
[Page 53055-53058]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr09se03-24]
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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: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to certain Boeing Model 777-200 and -
300 series airplanes. For all airplanes, this proposal would require
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, this proposal also would require 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. This action is necessary 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 October 24, 2003.
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 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: 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:
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-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
The FAA has received 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. Multiple broken tie rods
could allow the center stowage bins and electrical racks to fall onto
the passenger seats below during an emergency landing. This condition,
if not corrected, could impede an emergency evacuation or result in
injury to passengers.
Explanation of Relevant Service Information
We have reviewed and approved Boeing Service Bulletin 777-25-0144,
Revision 1, dated January 10, 2002. For all airplanes, the service
bulletin describes procedures for installing a placard showing weight
limits for electrical rack E7. For certain airplanes, the service
bulletin also describes procedures for additional actions, as follows:
[sbull] A one-time inspection of the clevis end of the vertical tie
rods that support
[[Page 53056]]
the center stowage bins to measure the exposed thread, and installation
of a threaded sleeve if necessary.
[sbull] Replacement of the vertical tie rods that support the
center stowage bins with new improved tie rods (including replacing the
existing tie rod with a new improved tie rod, torquing the jam nuts,
and inspecting through the witness hole to make sure tie rod threads
are visible).
[sbull] Replacement of the vertical tie rods that support
electrical racks E9, E11, and E13 (including replacing the existing tie
rod with a new improved tie rod, replacing an existing tie rod clamp
with a new improved tie rod clamp, inspecting certain electrical racks
for ``free play,'' adjusting jam nuts if necessary, and inspecting
through the witness hole to make sure tie rod threads are visible); as
applicable.
[sbull] Installation of placards showing weight limits for
electrical racks E9, E11, E13, and E15; as applicable.
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 require accomplishment of the applicable actions
specified in the service bulletin described previously, except as
discussed below under the heading ``Differences Between Proposed Rule
and Service Bulletin.'' The proposed AD would also require a one-time
records review and inspection to verify that the weight of equipment
currently installed in certain electrical racks meets specified weight
limits. This records review and inspection would involve determining
what extra equipment has been installed in the subject racks of the
airplane, performing a detailed inspection to determine that the
subject 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. If the weight of the equipment
exceeds the limit specified on the placard, equipment must be removed
from the rack to meet the requirement.
In developing an appropriate compliance time for this action, we
considered not only the degree of urgency associated with addressing
the subject unsafe condition, but the normal maintenance schedules for
the majority of affected operators. In consideration of these factors,
we have determined that 5 years represents an appropriate interval of
time allowable wherein the proposed actions can be accomplished during
scheduled maintenance intervals for the majority of affected operators.
We find that this will ensure an acceptable level of safety.
Clarification of Inspection Types
The service bulletin refers to an inspection of the clevis end of
the vertical support tie rod to determine whether a threaded sleeve is
required. We find that, since the inspection involves measuring the
length of the exposed thread, the procedures for this inspection
constitute a detailed inspection. This type of inspection is defined in
Note 1 of this proposed AD.
As part of the procedures for replacing the vertical support tie
rods, the service bulletin specifies to inspect through the witness
hole to ensure that tie rod threads are visible. We find that this
inspection constitutes a general visual inspection. This type of
inspection is defined in Note 2 of the proposed AD.
Differences Between Proposed AD and Service Bulletin
Operators should note that, although the service bulletin specifies
that the manufacturer may be contacted for disposition of certain
conditions, this proposal would require the disposition of those
conditions per a method approved by the FAA.
Operators also should note that, as explained previously, this
proposed AD would require a one-time records review and an inspection
that are not included in the service bulletin. We find that these
additional actions are necessary to ensure that the weight of equipment
currently installed in certain electrical racks is within the limits
specified in the placards to be installed per the service bulletin
referenced in this proposed AD.
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 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
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 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.
[[Page 53057]]
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 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. The manufacturer may
cover the cost of parts associated with certain actions in this
proposed AD, subject to warranty conditions. Manufacturer warranty
remedies may also be available for labor costs associated with certain
actions in this proposed AD. As a result, the costs attributable to the
proposed AD may be less than stated above.
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., Part 1, paragraph E., of the Accomplishment
Instructions of Boeing Service Bulletin 777-25-0144, Revision 1,
dated January 10, 2002: 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: 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 has been installed, if any, in the
subject rack 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 (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
(b) For airplanes in the groups listed in the table under
paragraph 3., Part 1, paragraph C., of the Accomplishment
Instructions of Boeing Service Bulletin 777-25-0144, Revision 1,
dated January 10, 2002: 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
15 inclusive of Figure 2 of the service bulletin. 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 paragraph 3., Part 1, paragraph D., of the
Accomplishment Instructions of Boeing Service Bulletin 777-25-0144,
Revision 1, dated January 10, 2002: 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, performing a general visual inspection through the
witness hole to make sure tie rod threads are visible, 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, except as provided by paragraph (e) of this AD. Any
required adjustment of the clevis must be done before further
flight.
Note 2:
For the purposes of this AD, a general visual inspection is
defined as: ``A visual examination of an interior or exterior
[[Page 53058]]
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 To Determine Weight, Tie Rod Replacement, and Placard
Installation
(d) For airplanes in the groups listed in the table under
paragraph 3., Part 1, paragraph F., of the Accomplishment
Instructions of Boeing Service Bulletin 777-25-0144, Revision 1,
dated January 10, 2002: 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.
Exception to Service Bulletin Instructions
(e) Where the service bulletin specifies to contact Boeing for
appropriate action, before further flight, repair per a method
approved by the Manager, Seattle Aircraft Certification Office
(ACO), FAA; or per data meeting the type certification basis of the
airplane approved by a Boeing Company Designated Engineering
Representative who has been authorized by the Manager, Seattle ACO,
to make such findings. For a repair method to be approved, the
approval must specifically reference this AD.
Alternative Methods of Compliance
(f) In accordance with 14 CFR 39.19, the Manager, Seattle ACO,
is authorized to approve alternative methods of compliance for this
AD.
Issued in Renton, Washington, on September 2, 2003.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 03-22890 Filed 9-8-03; 8:45 am]
BILLING CODE 4910-13-P