Airworthiness Directives; Boeing Model 777-200, -300, and -300ER Series Airplanes, 3715-3718 [E7-1081]
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Federal Register / Vol. 72, No. 17 / Friday, January 26, 2007 / Rules and Regulations
TABLE 1.—AIRBUS SERVICE INFORMATION—Continued
For all model—
Use Airbus Service
Bulletin—
Revision
level—
A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R, F4–605R, F4–622R, and
C4–605R Variant F airplanes.
A300–32–6094 ......
01
Note 1: The Airbus service bulletins refer
to Messier-Bugatti Service Bulletin C24264–
32–848, dated February 15, 2006, as an
additional source of service information for
modifying the parking brake pressure limiter.
Actions Accomplished According to
Previously Issued Service Information
(g) Actions accomplished before the
effective date of this AD according to the
Date—
October 2, 2006.
applicable service bulletin specified in Table
2 of this AD are considered acceptable for
compliance with the corresponding action
specified in this AD.
TABLE 2.—PREVIOUSLY ISSUED SERVICE INFORMATION
Model
Airbus Service
Bulletin
Dated
A300 airplanes ...........................................................................................................................................
A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R, F4–605R, F4–622R, and C4–605R
Variant F airplanes.
A300–32–0448 ...
A300–32–6094 ...
February 22, 2006.
February 22, 2006.
Parts Installation
(h) As of the effective date of this AD, no
person may install, on the parking brake
system of any airplane, a pressure limiter
having P/N C24264–302 or C24264004.
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, International Branch,
ANM–116, FAA, has the authority to approve
AMOCs for this AD, if requested in
accordance with the procedures found in 14
CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Related Information
(j) European Aviation Safety Agency
(EASA) airworthiness directive 2006–0178,
dated June 26, 2006, also addresses the
subject of this AD.
Material Incorporated by Reference
(k) You must use the applicable service
information specified in Table 3 of this AD
to perform the actions that are required by
this AD, unless the AD specifies otherwise.
The Director of the Federal Register approved
the incorporation by reference of these
documents in accordance with 5 U.S.C.
552(a) and 1 CFR part 51. Contact Airbus, 1
Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France, for a copy of this service
information. You may review copies at the
Docket Management Facility, U.S.
Department of Transportation, 400 Seventh
Street, SW., Room PL–401, Nassif Building,
Washington, DC; on the Internet at https://
dms.dot.gov; or at 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 https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
TABLE 3.—MATERIAL INCORPORATED BY REFERENCE
Airbus Service Bulletin
Revision level
A300–32–0448 ..............................................................................................................................................
A300–32–6094 ..............................................................................................................................................
Issued in Renton, Washington, on January
12, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–1079 Filed 1–25–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24891; Directorate
Identifier 2006–NM–080–AD; Amendment
39–14910; AD 2007–02–23]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 777–200, –300, and –300ER
Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
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01
01
Date
October 2, 2006.
October 2, 2006.
Boeing Model 777–200, –300, and
–300ER series airplanes. This AD
requires replacement of the gimbal
plates of the left and right outboard
trailing edge flaps with improved
gimbal plates and other specified
actions. This AD results from a broken
pivot link found on the inboard support
for the outboard trailing edge flap. We
are issuing this AD to prevent
disconnection of the drive arm from its
drive gimbal, due to a broken pivot link
on an outboard flap support, which
could result in unexpected roll of the
airplane and loss of control of the
airplane.
This AD becomes effective
March 2, 2007.
The Director of the Federal Register
approved the incorporation by reference
DATES:
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of a certain publication listed in the AD
as of March 2, 2007.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Gary
Oltman, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington
98057–3356; telephone (425) 917–6443;
fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to certain Boeing Model 777–200,
–300, and –300ER series airplanes. That
NPRM was published in the Federal
Register on May 26, 2006 (71 FR 30338).
That NPRM proposed to require
replacement of the gimbal plates of the
left and right outboard trailing edge
flaps with improved gimbal plates and
other specified actions.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
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Support for the NPRM
Boeing, British Airways, American
Airlines, and the Air Transport
Association (ATA) support the intent of
the NPRM.
Request To Use Existing Gimbal Plates
Delta Airlines requests that we either
have Boeing revise Alert Service
Bulletin 777–27A0073, dated March 30,
2006, or that we revise paragraph (f) of
the NPRM to allow operators to deviate
from the referenced service bulletin.
The commenter would like to continue
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to use existing gimbal plates having part
numbers (P/Ns) 113W1112–3,
113W1112–4, 113W1212–3, and
113W1212–4. As justification, the
commenter states the service bulletin
specifies installing improved gimbal
plates having P/Ns 113W1112–7,
113W1112–8, 113W1212–7, and
113W1212–8, but it does not specify to
replace or remove the existing parts.
The commenter also cites paragraph (g)
of the NPRM, which allows installation
of the existing parts if an airplane is
modified in accordance with paragraph
(f) of the NPRM.
We do not agree to allow use of the
existing gimbal plates. Although the
existing gimbal plate part numbers are
not identified explicitly in the service
bulletin, we confirmed with Boeing that
they are P/Ns 113W1112–3, 113W1112–
4, 113W1212–3, and 113W1212–4.
Further, the effectivity of Boeing Alert
Service Bulletin 777–27A0073 identifies
Model 777–200, –300, and –300ER
series airplanes that have the existing
gimbal plates installed and approved as
part of their type design. The intent of
the service bulletin is to replace the
existing gimbal plates with new,
improved gimbal plates having P/Ns
113W1112–7, 113W1112–8, 113W1212–
7, and 113W1212–8. These new,
improved gimbal plates are identified
clearly in the service bulletin and must
be installed to adequately address the
unsafe condition of this AD. We
acknowledge that paragraph (g) of the
NPRM is confusing in that it contains
the phrase ‘‘* * * unless it has been
modified in accordance with paragraph
(f) of this AD.’’ However, that phrase is
not accurate and was inadvertently
included in the NPRM. We have deleted
that phrase from paragraph (g) of this
AD.
Request for Clarification on Improved
Gimbal Plates
Delta Airlines requests clarification
on the new, improved gimbal plates.
The commenter states that the NPRM
and Boeing Alert Service Bulletin 777–
27A0073, dated March 30, 2006, do not
appear to be in agreement regarding use
of existing gimbal plate P/Ns
113W1112–3, 113W1112–4, 113W1212–
3, and 113W1212–4. The commenter
also states that these part numbers are
not referenced in the service bulletin.
The commenter further requests that we
provide more information regarding
usage of the new, improved P/Ns
113W1112–7, 113W1112–8, 113W1212–
7, and 113W1212–8.
We acknowledge that paragraph (g) of
the NPRM has caused confusion
regarding the existing and new,
improved part numbers. As stated
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previously, we have deleted a certain
phrase to clarify that the existing parts
may no longer be installed on the
affected airplanes. Installation of the
new, improved parts is necessary to
adequately address the unsafe condition
of this AD. No further change has been
made to this AD in this regard.
Request To Extend Compliance Time
British Airways requests that we
extend the compliance time of the
NPRM to 30 months. The commenter
states that the maintenance planning
document schedules zonal inspections
at intervals of 6,000 flight cycles or
1,125 days, and that the commenter
currently performs these inspections at
intervals of 750 days (corresponding to
just under 25 months). The commenter
contends that the proposed compliance
time could cause it to accomplish the
gimbal replacement during minor
maintenance. The commenter states that
extending the compliance time would
allow it to accomplish the gimbal
replacement at a heavy maintenance
facility.
We do not agree with the commenter’s
request to extend the compliance time.
In developing an appropriate
compliance time for this action, we
considered the safety implications, parts
availability, and normal maintenance
schedules for the timely
accomplishment of the replacement. In
consideration of these items, we have
determined that a compliance time of 24
months will ensure an acceptable level
of safety and allow the modifications to
be done during scheduled maintenance
intervals for most affected operators.
However, under the provisions of
paragraph (h) of this AD, we may
approve requests for adjustments to the
compliance time if data are submitted to
substantiate that such an adjustment
would provide an acceptable level of
safety. We have not revised this AD in
this regard.
Request To Revise Compliance Time to
Flight Cycles
British Airways requests that we
express the compliance time in units of
flight cycles. The commenter asserts
that calendar time is an inappropriate
unit of life control. As justification, the
commenter states that flap operations
would primarily influence the failure
experienced. The commenter proposes
6,000 flight cycles as a more appropriate
compliance time.
We disagree with revising the
compliance time. Although failure of
the pivot link is primarily affected by
airplane flight cycles, the original
design of the flap system was certified
to withstand such a failure. A design
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deficiency exists in the gimbal plate
structure within the flap system. This
design deficiency is not fatigue related
and accordingly not flight-cycle related.
Therefore, it is appropriate to use a
calendar time to express the compliance
time. The compliance time of 24 months
was selected to allow replacement of the
gimbal plates during a routine
maintenance visit. We have not revised
this AD in this regard.
Request To Revise the Costs of
Compliance
American Airlines requests that we
adjust the costs estimated in the NPRM.
American Airlines states that it has
accomplished the gimbal plate
replacement in accordance with Boeing
Alert Service Bulletin 777–27A0073,
dated March 30, 2006, on 2 of its 45
affected airplanes. American Airlines
estimates that the cost impact for
accomplishing the NPRM will be
approximately $84,200 per airplane, or
$3,789,000 for its entire fleet. We infer
the commenter would like us to revise
the Cost of Compliance paragraph in
this AD.
We disagree. The cost information in
this AD describes only the direct costs
of the specific actions required by this
AD. Based on the best data available, the
manufacturer provided the number of
work hours (153) necessary to do the
required actions. This number
represents the time necessary to perform
only the actions actually required by
this AD. We recognize that, in doing the
actions required by an AD, operators
may incur incidental costs in addition
to the direct costs. The cost analysis in
AD rulemaking actions, however,
typically does not include incidental
costs such as the time required to gain
access and close up, time necessary for
planning, or time necessitated by other
administrative actions. Those incidental
costs, which may vary significantly
among operators, are almost impossible
to calculate. We have not changed this
AD in this regard.
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New Note Added to Paragraph (f)
We have added a note to paragraph (f)
of this AD informing operators to pay
particular attention that grease or
lubricant is not applied to the gimbal
plate bolts, bushings, washers, or nuts.
Yielding or failure of the bolts could
occur due to overtorquing a lubricated
attachment that was intended to be
installed without lubricant.
Conclusion
We have carefully reviewed the
available data, including the comments
received, and determined that air safety
and the public interest require adopting
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the AD with the changes described
previously. We have determined that
these changes will neither increase the
economic burden on any operator nor
increase the scope of the AD.
Costs of Compliance
There are about 546 airplanes of the
affected design in the worldwide fleet.
This AD affects about 145 airplanes of
U.S. registry. The required actions take
about 153 work hours per airplane, at an
average labor rate of $80 per work hour.
Required parts cost about $69,850 per
airplane. Based on these figures, the
estimated cost of the AD for U.S.
operators is $11,903,050, or $82,090 per
airplane.
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
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 Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD 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.
For the reasons discussed above, I
certify that this AD:
(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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
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3717
See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
I
2007–02–23 Boeing: Amendment 39–14910.
Docket No. FAA–2006–24891;
Directorate Identifier 2006–NM–080–AD.
Effective Date
(a) This AD becomes effective March 2,
2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 777–
200, –300, and –300ER series airplanes,
certificated in any category; as identified in
Boeing Alert Service Bulletin 777–27A0073,
dated March 30, 2006.
Unsafe Condition
(d) This AD results from a broken pivot
link found on the inboard support for the
outboard trailing edge flap. We are issuing
this AD to prevent disconnection of the drive
arm from its drive gimbal, due to a broken
pivot link on an outboard flap support,
which could result in unexpected roll of the
airplane and loss of control of the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Replacement of Gimbal Plates
(f) Within 24 months after the effective
date of this AD, replace the gimbal plates of
the left and right outboard trailing edge flaps
with improved gimbal plates, and do the
other specified actions before further flight
after the replacement, by accomplishing all
the actions specified in the Accomplishment
Instructions of Boeing Alert Service Bulletin
777–27A0073, dated March 30, 2006.
Note 1: Pay particular attention that grease
or lubricant is not applied to the gimbal plate
bolts, bushings, washers, or nuts. Yielding or
failure of the bolts could occur due to
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Federal Register / Vol. 72, No. 17 / Friday, January 26, 2007 / Rules and Regulations
overtorquing a lubricated attachment that
was intended to be installed without
lubricant.
DEPARTMENT OF TRANSPORTATION
Parts Installation
14 CFR Part 39
Federal Aviation Administration
(g) As of the effective date of this AD, no
person may install a gimbal plate, part
numbers 113W1112–3, 113W1112–4,
113W1212–3, and 113W1212–4, on any
airplane.
[Docket No. FAA–2006–25087; Directorate
Identifier 2006–NM–053–AD; Amendment
39–14882; AD 2007–01–10]
RIN 2120–AA64
Alternative Methods of Compliance
(AMOCs)
Airworthiness Directives; Boeing
Model 747 Airplanes
(h)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by an
Authorized Representative for the Boeing
Commercial Airplanes Delegation Option
Authorization Organization who has been
authorized by the Manager, Seattle ACO, to
make those findings. For a repair method to
be approved, the repair must meet the
certification basis of the airplane, and the
approval must specifically refer to this AD.
Material Incorporated by Reference
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(i) You must use Boeing Alert Service
Bulletin 777–27A0073, dated March 30,
2006, to perform the actions that are required
by this AD, unless the AD specifies
otherwise. The Director of the Federal
Register approved the incorporation by
reference of this document in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Boeing Commercial Airplanes, P.O.
Box 3707, Seattle, Washington 98124–2207,
for a copy of this service information. You
may review copies at the Docket Management
Facility, U.S. Department of Transportation,
400 Seventh Street, SW., Room PL–401,
Nassif Building, Washington, DC; on the
Internet at https://dms.dot.gov; or at 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 https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on January
17, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–1081 Filed 1–25–07; 8:45 am]
BILLING CODE 4910–13–P
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Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to all Boeing Model 747
airplanes. That AD currently requires a
one-time inspection to determine
whether the outer cylinder of the wing
landing gear has certain part numbers,
and replacement of the outer cylinder of
the wing landing gear with a new,
improved, or reworked part if necessary.
That AD also requires removal of the
load evening system, if such a system is
installed. This new AD requires, for
certain airplanes, an additional one-time
inspection to determine whether the
outer cylinder has a certain other part
number. For those certain airplanes, this
new AD also requires replacement of the
outer cylinder with a reworked or new,
improved part and related investigative
and corrective actions, if necessary. This
AD results from identification of an
additional unsafe part. We are issuing
this AD to prevent fracture of the outer
cylinder of the wing landing gear, which
could result in collapse of the wing
landing gear.
DATES: This AD becomes effective
March 2, 2007.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of March 2, 2007.
On September 14, 2004 (69 FR 48359,
August 10, 2004), the Director of the
Federal Register approved the
incorporation by reference of Boeing
Service Bulletin 747–32–2472, dated
November 30, 2000; and Boeing Service
Bulletin 747–32–2131, Revision 2, dated
March 15, 1974.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
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Washington 98124–2207, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT:
Steve Fox, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6425; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that
supersedes AD 2004–16–05, amendment
39–13761 (69 FR 48359, August 10,
2004). The existing AD applies to all
Boeing Model 747 airplanes. That
NPRM was published in the Federal
Register on June 21, 2006 (71 FR 35581).
That NPRM proposed to continue to
require a one-time inspection to
determine whether the outer cylinder of
the wing landing gear has certain part
numbers, and replacement of the outer
cylinder of the wing landing gear with
a new, improved, or reworked part if
necessary. That NPRM also proposed to
require, for certain airplanes, an
additional one-time inspection to
determine whether the outer cylinder
has a certain other part number. For
those certain airplanes, that NPRM also
proposed to require replacement of the
outer cylinder with a reworked or new,
improved part and related investigative/
corrective actions, if necessary.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments that have
been received on the NPRM.
Request To Delete Compliance Time
Boeing requests that we revise
paragraph (j) of the NPRM so that it
reads similar to paragraph (g) of the
NPRM. Boeing states that the
compliance time of ‘‘before further flight
after the replacement’’ is confusing;
Boeing is unclear as to whether that
phrase applies to a removed outer
cylinder or to an airplane on which an
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]]>Agencies
[Federal Register Volume 72, Number 17 (Friday, January 26, 2007)]
[Rules and Regulations]
[Pages 3715-3718]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-1081]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24891; Directorate Identifier 2006-NM-080-AD;
Amendment 39-14910; AD 2007-02-23]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 777-200, -300, and -300ER
Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Boeing Model 777-200, -300, and -300ER series airplanes. This
AD requires replacement of the gimbal plates of the left and right
outboard trailing edge flaps with improved gimbal plates and other
specified actions. This AD results from a broken pivot link found on
the inboard support for the outboard trailing edge flap. We are issuing
this AD to prevent disconnection of the drive arm from its drive
gimbal, due to a broken pivot link on an outboard flap support, which
could result in unexpected roll of the airplane and loss of control of
the airplane.
DATES: This AD becomes effective March 2, 2007.
The Director of the Federal Register approved the incorporation by
reference
[[Page 3716]]
of a certain publication listed in the AD as of March 2, 2007.
ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for service information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Gary Oltman, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6443; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness directive (AD) docket on the
Internet at https://dms.dot.gov or in person at the Docket Management
Facility office between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Management Facility office
(telephone (800) 647-5227) is located on the plaza level of the Nassif
Building at the street address stated in the ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that would apply to certain Boeing Model
777-200, -300, and -300ER series airplanes. That NPRM was published in
the Federal Register on May 26, 2006 (71 FR 30338). That NPRM proposed
to require replacement of the gimbal plates of the left and right
outboard trailing edge flaps with improved gimbal plates and other
specified actions.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Support for the NPRM
Boeing, British Airways, American Airlines, and the Air Transport
Association (ATA) support the intent of the NPRM.
Request To Use Existing Gimbal Plates
Delta Airlines requests that we either have Boeing revise Alert
Service Bulletin 777-27A0073, dated March 30, 2006, or that we revise
paragraph (f) of the NPRM to allow operators to deviate from the
referenced service bulletin. The commenter would like to continue to
use existing gimbal plates having part numbers (P/Ns) 113W1112-3,
113W1112-4, 113W1212-3, and 113W1212-4. As justification, the commenter
states the service bulletin specifies installing improved gimbal plates
having P/Ns 113W1112-7, 113W1112-8, 113W1212-7, and 113W1212-8, but it
does not specify to replace or remove the existing parts. The commenter
also cites paragraph (g) of the NPRM, which allows installation of the
existing parts if an airplane is modified in accordance with paragraph
(f) of the NPRM.
We do not agree to allow use of the existing gimbal plates.
Although the existing gimbal plate part numbers are not identified
explicitly in the service bulletin, we confirmed with Boeing that they
are P/Ns 113W1112-3, 113W1112-4, 113W1212-3, and 113W1212-4. Further,
the effectivity of Boeing Alert Service Bulletin 777-27A0073 identifies
Model 777-200, -300, and -300ER series airplanes that have the existing
gimbal plates installed and approved as part of their type design. The
intent of the service bulletin is to replace the existing gimbal plates
with new, improved gimbal plates having P/Ns 113W1112-7, 113W1112-8,
113W1212-7, and 113W1212-8. These new, improved gimbal plates are
identified clearly in the service bulletin and must be installed to
adequately address the unsafe condition of this AD. We acknowledge that
paragraph (g) of the NPRM is confusing in that it contains the phrase
``* * * unless it has been modified in accordance with paragraph (f) of
this AD.'' However, that phrase is not accurate and was inadvertently
included in the NPRM. We have deleted that phrase from paragraph (g) of
this AD.
Request for Clarification on Improved Gimbal Plates
Delta Airlines requests clarification on the new, improved gimbal
plates. The commenter states that the NPRM and Boeing Alert Service
Bulletin 777-27A0073, dated March 30, 2006, do not appear to be in
agreement regarding use of existing gimbal plate P/Ns 113W1112-3,
113W1112-4, 113W1212-3, and 113W1212-4. The commenter also states that
these part numbers are not referenced in the service bulletin. The
commenter further requests that we provide more information regarding
usage of the new, improved P/Ns 113W1112-7, 113W1112-8, 113W1212-7, and
113W1212-8.
We acknowledge that paragraph (g) of the NPRM has caused confusion
regarding the existing and new, improved part numbers. As stated
previously, we have deleted a certain phrase to clarify that the
existing parts may no longer be installed on the affected airplanes.
Installation of the new, improved parts is necessary to adequately
address the unsafe condition of this AD. No further change has been
made to this AD in this regard.
Request To Extend Compliance Time
British Airways requests that we extend the compliance time of the
NPRM to 30 months. The commenter states that the maintenance planning
document schedules zonal inspections at intervals of 6,000 flight
cycles or 1,125 days, and that the commenter currently performs these
inspections at intervals of 750 days (corresponding to just under 25
months). The commenter contends that the proposed compliance time could
cause it to accomplish the gimbal replacement during minor maintenance.
The commenter states that extending the compliance time would allow it
to accomplish the gimbal replacement at a heavy maintenance facility.
We do not agree with the commenter's request to extend the
compliance time. In developing an appropriate compliance time for this
action, we considered the safety implications, parts availability, and
normal maintenance schedules for the timely accomplishment of the
replacement. In consideration of these items, we have determined that a
compliance time of 24 months will ensure an acceptable level of safety
and allow the modifications to be done during scheduled maintenance
intervals for most affected operators. However, under the provisions of
paragraph (h) of this AD, we may approve requests for adjustments to
the compliance time if data are submitted to substantiate that such an
adjustment would provide an acceptable level of safety. We have not
revised this AD in this regard.
Request To Revise Compliance Time to Flight Cycles
British Airways requests that we express the compliance time in
units of flight cycles. The commenter asserts that calendar time is an
inappropriate unit of life control. As justification, the commenter
states that flap operations would primarily influence the failure
experienced. The commenter proposes 6,000 flight cycles as a more
appropriate compliance time.
We disagree with revising the compliance time. Although failure of
the pivot link is primarily affected by airplane flight cycles, the
original design of the flap system was certified to withstand such a
failure. A design
[[Page 3717]]
deficiency exists in the gimbal plate structure within the flap system.
This design deficiency is not fatigue related and accordingly not
flight-cycle related. Therefore, it is appropriate to use a calendar
time to express the compliance time. The compliance time of 24 months
was selected to allow replacement of the gimbal plates during a routine
maintenance visit. We have not revised this AD in this regard.
Request To Revise the Costs of Compliance
American Airlines requests that we adjust the costs estimated in
the NPRM. American Airlines states that it has accomplished the gimbal
plate replacement in accordance with Boeing Alert Service Bulletin 777-
27A0073, dated March 30, 2006, on 2 of its 45 affected airplanes.
American Airlines estimates that the cost impact for accomplishing the
NPRM will be approximately $84,200 per airplane, or $3,789,000 for its
entire fleet. We infer the commenter would like us to revise the Cost
of Compliance paragraph in this AD.
We disagree. The cost information in this AD describes only the
direct costs of the specific actions required by this AD. Based on the
best data available, the manufacturer provided the number of work hours
(153) necessary to do the required actions. This number represents the
time necessary to perform only the actions actually required by this
AD. We recognize that, in doing the actions required by an AD,
operators may incur incidental costs in addition to the direct costs.
The cost analysis in AD rulemaking actions, however, typically does not
include incidental costs such as the time required to gain access and
close up, time necessary for planning, or time necessitated by other
administrative actions. Those incidental costs, which may vary
significantly among operators, are almost impossible to calculate. We
have not changed this AD in this regard.
New Note Added to Paragraph (f)
We have added a note to paragraph (f) of this AD informing
operators to pay particular attention that grease or lubricant is not
applied to the gimbal plate bolts, bushings, washers, or nuts. Yielding
or failure of the bolts could occur due to overtorquing a lubricated
attachment that was intended to be installed without lubricant.
Conclusion
We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
There are about 546 airplanes of the affected design in the
worldwide fleet. This AD affects about 145 airplanes of U.S. registry.
The required actions take about 153 work hours per airplane, at an
average labor rate of $80 per work hour. Required parts cost about
$69,850 per airplane. Based on these figures, the estimated cost of the
AD for U.S. operators is $11,903,050, or $82,090 per airplane.
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 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 Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD 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.
For the reasons discussed above, I certify that this AD:
(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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 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. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
adding the following new airworthiness directive (AD):
2007-02-23 Boeing: Amendment 39-14910. Docket No. FAA-2006-24891;
Directorate Identifier 2006-NM-080-AD.
Effective Date
(a) This AD becomes effective March 2, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 777-200, -300, and -300ER
series airplanes, certificated in any category; as identified in
Boeing Alert Service Bulletin 777-27A0073, dated March 30, 2006.
Unsafe Condition
(d) This AD results from a broken pivot link found on the
inboard support for the outboard trailing edge flap. We are issuing
this AD to prevent disconnection of the drive arm from its drive
gimbal, due to a broken pivot link on an outboard flap support,
which could result in unexpected roll of the airplane and loss of
control of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Replacement of Gimbal Plates
(f) Within 24 months after the effective date of this AD,
replace the gimbal plates of the left and right outboard trailing
edge flaps with improved gimbal plates, and do the other specified
actions before further flight after the replacement, by
accomplishing all the actions specified in the Accomplishment
Instructions of Boeing Alert Service Bulletin 777-27A0073, dated
March 30, 2006.
Note 1: Pay particular attention that grease or lubricant is not
applied to the gimbal plate bolts, bushings, washers, or nuts.
Yielding or failure of the bolts could occur due to
[[Page 3718]]
overtorquing a lubricated attachment that was intended to be
installed without lubricant.
Parts Installation
(g) As of the effective date of this AD, no person may install a
gimbal plate, part numbers 113W1112-3, 113W1112-4, 113W1212-3, and
113W1212-4, on any airplane.
Alternative Methods of Compliance (AMOCs)
(h)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested in
accordance with the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD, if it is approved by an
Authorized Representative for the Boeing Commercial Airplanes
Delegation Option Authorization Organization who has been authorized
by the Manager, Seattle ACO, to make those findings. For a repair
method to be approved, the repair must meet the certification basis
of the airplane, and the approval must specifically refer to this
AD.
Material Incorporated by Reference
(i) You must use Boeing Alert Service Bulletin 777-27A0073,
dated March 30, 2006, to perform the actions that are required by
this AD, unless the AD specifies otherwise. The Director of the
Federal Register approved the incorporation by reference of this
document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for a copy of this service information. You
may review copies at the Docket Management Facility, U.S. Department
of Transportation, 400 Seventh Street, SW., Room PL-401, Nassif
Building, Washington, DC; on the Internet at https://dms.dot.gov; or
at 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 https://www.archives.gov/federal_register/
code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on January 17, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-1081 Filed 1-25-07; 8:45 am]
BILLING CODE 4910-13-P
