[Federal Register: June 27, 2005 (Volume 70, Number 122)]
[Rules and Regulations]
[Page 36826-36829]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr27jn05-9]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2001-NM-89-AD; Amendment 39-14165; AD 2005-13-28]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 777-200 and -300 Series
Airplanes
AGENCY: Federal Aviation Administration, Department of Transportation
(DOT).
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Boeing Model 777-200 and -300 series airplanes.
This AD requires 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. The actions specified by this AD are
intended to prevent failure of the vertical tie rods supporting certain
electrical racks and the center stowage bins, which could cause the
center stowage bins or electrical racks 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: Effective August 1, 2005.
The incorporation by reference of a certain publication listed in
the regulations is approved by the Director of the Federal Register as
of August 1, 2005.
ADDRESSES: 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 Federal
Aviation Administration (FAA), Transport Airplane Directorate, Rules
Docket, 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: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to certain Boeing Model 777-200 and -
300 series airplanes was published as a supplemental notice of proposed
rulemaking (NPRM) in the Federal Register on January 5, 2005 (70 FR
737). That action proposed to 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 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.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
Support for the Supplemental NPRM
Two commenters support the supplemental NPRM. One of these
commenters states that the applicable requirements for its 19 affected
airplanes will take 13 work hours to accomplish, with a parts cost of
$2,072 per airplane. This is consistent with the costs estimated in the
supplemental NPRM.
Request To Extend Compliance Time for Weight Inspection/Records Check
One commenter requests that we revise paragraph (d)(3) of the
supplemental NPRM to extend the compliance time for accomplishing the
inspection and records check to determine the weight of equipment
installed in the subject electrical racks. The commenter notes that, by
the time the AD is issued, it will have accomplished the actions
specified in paragraphs (d)(1) and (d)(2) of the supplemental NPRM in
accordance with the referenced service bulletin. However, it will not
have accomplished the actions specified in paragraph (d)(3) of the
supplemental NPRM because those actions are not specified in the
service bulletin. The commenter requests that compliance time language
similar to that in paragraph (a)(2)(i) of the supplemental NPRM be
added to paragraph (d)(3). (Paragraph (a)(2)(i) of the supplemental
NPRM gives a compliance time of up to 12 months after the effective
date of the AD for checking the weight installed in certain electrical
racks on airplanes on which the placard installation specified in
paragraph (a)(1) has been accomplished before the effective date of the
AD.)
We concur. The actions in paragraph (d)(3) of this AD are similar
to those in paragraph (a)(2), and the compliance time should also be
similar. Accordingly, we have revised paragraph (d)(3) of this AD, and
added paragraphs (d)(3)(i) and (d)(3)(ii) to this AD, to allow up to 12
months for accomplishing the weight check on airplanes on which the
actions in paragraphs (d)(1) and (d)(2) of this AD have been
accomplished before the effective date of this AD.
Request To Clarify Credit for Actions Accomplished Previously
The same commenter states that paragraph (e), ``Actions
Accomplished Previously,'' contradicts the rest of the supplemental
NPRM. The commenter states that paragraph (e) implies that no further
work is necessary if a previous revision of the service bulletin was
accomplished before the effective date of the AD. The commenter states
that this would mean that the weighing of electrical racks, which is
not referenced in the service bulletins, would not be done.
We do not agree. Paragraph (e) states that actions accomplished
before the
[[Page 36827]]
effective date of the AD per an earlier revision of the service
bulletin are acceptable for compliance with corresponding actions
required by this AD. For example, if placards were installed on
electrical racks E7, E11, and E15, in accordance with the original
issue of the referenced service bulletin, the placards would not have
to be reinstalled in accordance with Revision 2 of the service
bulletin. Because the procedures in the original issue of the service
bulletin for accomplishing the placard installation are exactly the
same as the procedures in Revision 2, there is no need to repeat the
installation of placards to establish compliance with the AD. However,
as paragraph (e) states, any actions in Revision 2 of the service
bulletin (e.g., in Part 2 or 3 of the Accomplishment Instructions) that
were not included in the original issue of the service bulletin must
still be done in accordance with Revision 2. Likewise, the weighing of
equipment that is specified in this AD is still required.
However, we agree that it is possible to clarify paragraph (e) of
this AD in this regard. Therefore, we have added a sentence to
paragraph (e) of this AD to state that the weighing requirements in
paragraphs (a)(2) and (d)(3) of the AD must be accomplished at the
applicable times identified in those paragraphs.
Request To Refer to Revised Service Information
One commenter notes that information that it received from Boeing
indicates that Boeing would be revising the service bulletin referenced
in the supplemental NPRM. The commenter states that Boeing has
indicated that Figure 8 of the service bulletin does not need to be
done if the crew rest has been modified. The commenter states that, if
Boeing doesn't update the service bulletin in time, operators of
airplanes with the modified crew rest may have to request an
alternative method of compliance (AMOC).
We infer that the commenter is requesting that we delay issuance of
the final rule until Boeing has released the revised service bulletin.
We do not concur. The revision of the service bulletin to which the
commenter refers is not yet available. We find that it would be
inappropriate to delay the issuance of this final rule to wait for the
service bulletin to be revised. The commenter may request approval of
an AMOC for the relevant requirements of this AD. The request must
include data substantiating that the AMOC would provide an acceptable
level of safety. We have not changed the final rule in this regard.
Explanation of Editorial Change to Final Rule
We have revised paragraphs (a), (b), (c), and (d)(1) of this final
rule to state the compliance times in months (i.e., 60 months) instead
of years (i.e., 5 years).
Conclusion
After careful review of the available data, including the comments
noted above, we have determined that air safety and the public interest
require the adoption of the rule with the changes previously described.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.
Cost Impact
There are approximately 282 airplanes of the affected design in the
worldwide fleet. We estimate that 84 airplanes of U.S. registry will be
affected by this AD.
For all airplanes: The records check and inspection to determine
the weight currently installed in electrical rack E7 will 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 records check and inspection on U.S. operators is
estimated to be $5,460, or $65 per airplane.
For all airplanes: It will take approximately 1 work hour to
accomplish the installation of a placard specifying weight limits for
electrical rack E7, at an average labor rate of $65 per work hour.
Required parts will cost approximately $29 per airplane. Based on these
figures, the cost impact of this 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 will 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
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 will take
approximately 1 work hour per electrical rack to accomplish, at an
average labor rate of $65 per work hour. Required parts will cost
approximately $29 per electrical rack. Based on these figures, the cost
impact of this 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 will 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 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 will 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 will cost as much as $3,020 per airplane. Based on these
figures, this 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 will 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 will cost as much as $3,012 per airplane. Based on these figures,
this 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 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.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation
[[Page 36828]]
is within the scope of that authority because it addresses an unsafe
condition that is likely to exist or develop on products identified in
this rulemaking action.
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:
2005-13-28 Boeing: Amendment 39-14165. Docket 2001-NM-89-AD.
Applicability: Model 777-200 and -300 series airplanes;
certificated in any category; line numbers 002 through 283
inclusive.
Compliance: Required as indicated, unless accomplished
previously.
To prevent failure of the vertical tie rods supporting certain
electrical racks and the center stowage bins, which could cause the
center stowage bins or electrical racks to fall onto passenger seats
below during an emergency landing, 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 60 months 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: At the applicable compliance time
specified in paragraph (a)(2)(i) or (a)(2)(ii) of this AD, perform a
one-time inspection and records review 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.
(i) For airplanes on which the actions required by paragraph
(a)(1) of this AD were done before the effective date of this AD:
Within 12 months after the effective date of this AD.
(ii) For airplanes on which the actions required by paragraph
(a)(1) of this AD are done after the effective date of this AD:
Before further flight after installing the placards.
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 Accomplishment Instructions of Boeing
Special Attention Service Bulletin 777-25-0144, Revision 2, dated
January 15, 2004: Within 60 months 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 60 months 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 60 months 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: At the applicable compliance time
specified in paragraph (d)(3)(i) or (d)(3)(ii) of
[[Page 36829]]
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.
(i) For airplanes on which the actions required by paragraphs
(d)(1) and (d)(2) of this AD were done before the effective date of
this AD: Within 12 months after the effective date of this AD.
(ii) For airplanes on which the actions required by paragraphs
(d)(1) and (d)(2) of this AD are done after the effective date of
this AD: Before further flight after installing the placards.
Actions Accomplished Previously
(e) Actions accomplished before the effective date of this AD
per the Accomplishment Instructions of Boeing Special Attention
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. The weighing requirements
in paragraphs (a)(2) and (d)(3) of this AD must be accomplished at
the applicable times identified in those paragraphs.
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 (AMOCs) for this AD.
Incorporation by Reference
(g) Unless otherwise specified in this AD, the actions must be
done in accordance with Boeing Special Attention Service Bulletin
777-25-0144, Revision 2, dated January 15, 2004. 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. To get copies of
this service information, go to Boeing Commercial Airplanes, P.O.
Box 3707, Seattle, Washington 98124-2207. To inspect copies of this
service information, go to the FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington; or to the National
Archives and Records Administration (NARA). For information on the
availability of this material at the NARA, call (202) 741-6030, or
go to http://www.archives.gov/ federal--register/code-- of--
federal--regulations/ ibr--locations.html.
Effective Date
(h) This amendment becomes effective on August 1, 2005.
Issued in Renton, Washington, on June 15, 2005.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-12510 Filed 6-24-05; 8:45 am]
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