Airworthiness Directives; Boeing Model 777 Airplanes, 64139-64143 [E7-21999]
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64139
Federal Register / Vol. 72, No. 220 / Thursday, November 15, 2007 / Rules and Regulations
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
Material Incorporated by Reference
(l) You must use the service information
identified in Table 2 of this AD to perform
the actions that are required by this AD,
unless the AD specifies otherwise. If you
accomplish the optional actions specified in
this AD, you must use Cessna Alert Service
Letter ASL560–34–34, Revision 1, dated
October 2, 2007, including Attachments; or
Cessna Alert Service Letter ASL560–34–35,
Revision 1, dated October 2, 2007, including
Attachments; as applicable; 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 Cessna Aircraft Co., P.O. Box
7706, Wichita, Kansas 67277, for a copy of
this service information. You may review
copies at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
Washington; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
TABLE 2.—MATERIAL INCORPORATED BY REFERENCE
Service information
Cessna
Cessna
Cessna
Cessna
Cessna
Cessna
Cessna
Cessna
Cessna
Cessna
Cessna
Cessna
Cessna
Cessna
Cessna
Cessna
Cessna
Cessna
Cessna
Cessna
Cessna
Cessna
Cessna
Cessna
Cessna
Cessna
Service Bulletin SB560–34–143, including Attachment and Service Bulletin Supplemental Data ...........................
Temporary Change 56FMA TC–R11–16 to the Cessna Model 560 Citation Ultra Airplane Flight Manual .............
Temporary Change 56FMA TC–R11–17 to the Cessna Model 560 Citation Ultra Airplane Flight Manual .............
Temporary Change 56FMA TC–R11–19 to the Cessna Model 560 Citation Ultra Airplane Flight Manual .............
Temporary Change 56FMA TC–R11–20 to the Cessna Model 560 Citation Ultra Airplane Flight Manual .............
Temporary Change 56FMA TC–R11–21 to the Cessna Model 560 Citation Ultra Airplane Flight Manual .............
Temporary Change 56FMA TC–R11–23 to the Cessna Model 560 Citation Ultra Airplane Flight Manual .............
Temporary Change 56FMA TC–R11–24 to the Cessna Model 560 Citation Ultra Airplane Flight Manual .............
Temporary Change 56FMA TC–R11–25 to the Cessna Model 560 Citation Ultra Airplane Flight Manual .............
Temporary Change 56FMA TC–R11–26 to the Cessna Model 560 Citation Ultra Airplane Flight Manual .............
Temporary Change 56FMA TC–R11–27 to the Cessna Model 560 Citation Ultra Airplane Flight Manual .............
Temporary Change 56FMA TC–R11–28 to the Cessna Model 560 Citation Ultra Airplane Flight Manual .............
Temporary Change 56FMA TC–R11–29 to the Cessna Model 560 Citation Ultra Airplane Flight Manual .............
Temporary Change 56FMA TC–R11–30 to the Cessna Model 560 Citation Ultra Airplane Flight Manual .............
Temporary Change 560FM TC–R13–08 to the Cessna Model 560 Citation V Airplane Flight Manual ...................
Temporary Change 560FM TC–R13–09 to the Cessna Model 560 Citation V Airplane Flight Manual ...................
Temporary Change 560FM TC–R13–10 to the Cessna Model 560 Citation V Airplane Flight Manual ...................
Temporary Change 560FM TC–R13–12 to the Cessna Model 560 Citation V Airplane Flight Manual ...................
Temporary Change 560FM TC–R13–13 to the Cessna Model 560 Citation V Airplane Flight Manual ...................
Temporary Change 560FM TC–R13–14 to the Cessna Model 560 Citation V Airplane Flight Manual ...................
Temporary Change 560FM TC–R13–15 to the Cessna Model 560 Citation V Airplane Flight Manual ...................
Temporary Change 560FM TC–R13–16 to the Cessna Model 560 Citation V Airplane Flight Manual ...................
Temporary Change 560FM TC–R13–17 to the Cessna Model 560 Citation V Airplane Flight Manual ...................
Temporary Change 560FM TC–R13–18 to the Cessna Model 560 Citation V Airplane Flight Manual ...................
Temporary Change 560FM TC–R13–19 to the Cessna Model 560 Citation V Airplane Flight Manual ...................
Temporary Change 560FM TC–R13–20 to the Cessna Model 560 Citation V Airplane Flight Manual ...................
Issued in Renton, Washington, on
November 5, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–22179 Filed 11–14–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27619; Directorate
Identifier 2005–NM–164–AD; Amendment
39–15257; AD 2007–23–11]
RIN 2120–AA64
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Date
Airworthiness Directives; Boeing
Model 777 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
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SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Boeing Model 777 airplanes. This AD
requires repetitive measurements of the
freeplay of certain joints of the trailing
edge flap supports; repetitive
lubrication of the support joints; and
related investigative and corrective
actions if necessary. This AD also
provides for modifying certain
components of the trailing edge flap
supports, which extends the intervals
for the repetitive measurements, and
revising the maintenance practices of
the maintenance planning data
document. This AD results from reports
of excessive wear of the pins, bushings,
and bearings, and corrosion at the joints
of the outboard trailing edge flap
supports. We are issuing this AD to
prevent wear and corrosion at the flap
support joints, which could result in
loss of the trailing edge flap and
possible loss of control of the airplane.
DATES: This AD becomes effective
December 20, 2007.
The Director of the Federal Register
approved the incorporation by reference
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September 7, 2007.
August 31, 2007.
August 31, 2007.
August 31, 2007.
August 31, 2007.
August 31, 2007.
October 2, 2007.
October 2, 2007.
October 2, 2007.
October 2, 2007.
October 2, 2007.
October 2, 2007.
October 2, 2007.
October 2, 2007.
August 31, 2007.
August 31, 2007.
August 31, 2007.
August 31, 2007.
August 31, 2007.
October 2, 2007.
October 2, 2007.
October 2, 2007.
October 2, 2007.
October 2, 2007.
October 2, 2007.
October 2, 2007.
of certain publications listed in the AD
as of December 20, 2007.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207.
Examining the Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is the Document Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Gary
Oltman, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
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Federal Register / Vol. 72, No. 220 / Thursday, November 15, 2007 / Rules and Regulations
Avenue SW., Renton, Washington
98057–3356; telephone (425) 917–6443;
fax (425) 917–6590.
paragraph (c), ‘‘Applicability,’’ of the
NPRM. We have made no change to the
AD in this regard.
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
airplanes. That NPRM was published in
the Federal Register on March 20, 2007
(72 FR 13048). That NPRM proposed to
require repetitive measurements of the
freeplay of certain joints of the trailing
edge flap supports; repetitive
lubrication of the support joints; and
related investigative and corrective
actions if necessary. That NPRM also
provides for modifying certain
components of the trailing edge flap
supports, which extends the intervals
for the repetitive measurements, and
revising the maintenance practices of
the maintenance planning data
document.
Request To Change Description of
Relevant Service Information Section
Air France asks that certain language
specified in the Relevant Service
Information section of the NPRM be
changed. Air France states that the last
paragraph of the description of Service
Bulletin 777–27A0066, Revision 1,
specifies that accomplishing the actions
in Boeing Alert Service Bulletin 777–
27A0071, Revision 1, dated October 16,
2006, eliminates the need for the
repetitive measurements and
lubrications of certain trailing edge flap
supports. Air France notes that Alert
Service Bulletin 777–27A0071, Revision
1, does not eliminate the need for the
repetitive inspections, but only extends
the interval for the repetitive
inspections.
We acknowledge the commenter’s
concern; however, that section of the
preamble does not reappear in the final
rule. We have provided clarification as
follows: Service Bulletin 777–27A0071,
Revision 1, specifies that accomplishing
the modification in that service bulletin
constitutes terminating action for the
actions specified in Service Bulletin
777–27A0066, Revision 1, for the
associated trailing edge flap support
only. The actions required by paragraph
(l) of the AD require continuing periodic
inspections and maintenance of the
support joints of the trailing edge flap,
which is part of the maintenance
inspection program. Those are the
inspections that are not terminated by
the AD. As part of the maintenance
program, those inspections would
generally be accomplished at the same
time or in combination with normally
scheduled airplane inspections and
other maintenance program tasks. In
light of these facts, we have made no
change to the AD.
Japan Airlines International (JAL) asks
that the NPRM be changed to allow
modification of the flap support
mechanism by incorporating Service
Bulletin 777–27A0071, Revision 1,
dated October 16, 2006, instead of doing
a support teardown inspection or
temporary return to service inspection.
JAL refers to the Relevant Service
Information section of the NPRM, which
describes procedures for disassembling
any joint that exceeds the freeplay limits
specified in Service Bulletin 777–
27A0066, Revision 1, and doing the
related investigative and corrective
actions in the ‘‘support teardown
inspection.’’ JAL also refers to the
teardown inspections required by
paragraphs (h)(1), (h)(2), and (h)(3) of
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Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Request To Change Paragraph (f)(1) of
the NPRM
Boeing asks that paragraph (f)(1) be
changed to read ‘‘For airplanes that have
accumulated 6,000 total flight cycles or
more on or before the effective date of
this AD and on which a teardown
inspection has not been accomplished
before the effective date of this AD.’’
Boeing states that with the use of the
word ‘‘or’’ in place of the word ‘‘and’’
as noted above, the NPRM could
include ‘‘For airplanes on which a
teardown inspection has not been
accomplished before the effective date
of this AD’’ and could be interpreted as
including new airplanes. Boeing adds
that this may be confusing as the NPRM
provides coverage for airplanes that
have accumulated fewer than 6,000
cycles, or new airplanes.
We agree with changing ‘‘or’’ to ‘‘and’’
as requested by Boeing because the use
of the word ‘‘or’’ could be interpreted as
applying to all Model 777 airplanes in
the applicability, regardless of the total
flight cycles, if a teardown inspection
has not been done. We have changed
paragraph (f)(1) of this AD accordingly.
We disagree with the interpretation
that the AD applicability could include
new airplanes, because Boeing Service
Bulletin 777–27A0066, Revision 1,
dated May 18, 2006, clearly identifies
affected airplanes as having line
numbers 1 through 546 only, and we
refer to that service bulletin in
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the NPRM. JAL notes that as an option
to the support teardown inspection, for
certain airplanes, the service bulletin
describes procedures for a ‘‘temporary
return to service’’ inspection.
We agree with JAL that allowing
operators to accomplish the
modification specified in Alert Service
Bulletin 777–27A0071, Revision 1,
instead of the teardown inspection or
temporary return to service is an
acceptable option. However, we do not
agree to change the AD because that
option is already specified in this AD.
We have made no change to the AD in
this regard.
Requests To Clarify Actions in
Paragraph (k) of the NPRM
Air France asks that we include in
paragraph (k) of the NPRM the
extension interval of 16,000 flight cycles
for the repetitive measurements allowed
by the application of Alert Service
Bulletin 777–27A0071, Revision 1,
dated October 16, 2006. Air France
notes that paragraph (k) should specify
accomplishing the actions in Alert
Service Bulletin 777–27A0071, Revision
1; or make a reference to maintenance
review board (MRB) and maintenance
planning document (MPD) item 27–
460–01, which is the item created in the
MRB and MPD; or take into account
airplanes on which Service Bulletin
777–27A0071, Revision 1, has been
accomplished at the extended 16,000
flight cycle intervals.
JAL states that paragraph (k) of the
NPRM should be clarified to include the
extended interval of 16,000 flight cycles.
We agree with the commenters that
paragraph (k) of the AD should provide
the extended interval for the repetitive
measurements so it corresponds with
the interval specified in paragraph (j) of
the AD. We have included that interval
in paragraph (k) for clarification.
Air France also asks that paragraph (k)
of the NPRM include terminating action.
Air France states that paragraph (k) does
not specify that application of Alert
Service Bulletin 777–27A0071, Revision
1, is terminating action for the actions
specified in paragraphs (f), (g), (h), and
(i) of the NPRM, for the associated
trailing edge flap support only. Air
France adds that paragraph (k) should
correspond with paragraph (j) of the
NPRM.
We agree with Air France for the
reasons provided, and we have included
the terminating action in paragraph (k)
of the AD for clarification.
Request To Change Compliance Times
JAL asks that the compliance times
specified in paragraph (h)(1)(i) and
(h)(3) of the NPRM be extended from 12
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to 18 months after the first freeplay
measurement of 0.020 inch to 0.100
inch inclusive, and that the repetitive
freeplay inspection (measurement)
interval be reduced to 500 flight cycles.
JAL provides the following reasons for
the request:
• All flap support mechanisms are
modified at the same time to avoid
complexity and save time with the
freeplay inspection interval. There are
many Model 777 airplanes planned for
flap-related modifications, but once the
freeplay value exceeds 0.020 inch, the
actions must be done within 12 months.
The 12-month compliance time makes it
difficult to schedule additional
airplanes because of inflexibility;
however, 18 months provides more
flexibility for scheduling flap
modifications. Reducing the freeplay
inspection interval to 500 flight cycles
would support the compliance time
extension.
• Since the freeplay inspection
procedure is not precise, it frequently
measures freeplay data containing
human errors. If the freeplay
measurement value exceeds 0.020 inch
the actions should be done within 12
months. The teardown inspection must
be done before further flight if the
freeplay value exceeds 0.020 inch. On
the next measurement the value can get
within 0.020 inch, but the actions must
still be done within 12 months. This is
not economical and JAL should be
allowed an additional 6-month buffer
for flexibility.
• Since repetitive inspections are
done at intervals of 500 flight cycles,
JAL monitors the freeplay data for the
joints. Due to the freeplay (wear) value
of all joints being monitored, the trend
of the freeplay value of specific joints is
known. For Model 777 airplanes
utilized for domestic flight (high
utilization in terms of flight cycles), the
500 flight-cycle freeplay inspection is
done within 3 months, and the normal
1,000 flight-cycle freeplay inspection is
done at around 6 months.
In developing an appropriate
compliance time for these actions, we
considered the urgency associated with
the subject unsafe condition, the
availability of required parts, and the
practical aspect of accomplishing the
required modification within a period of
time that corresponds to the normal
scheduled maintenance for most
affected operators. Additionally, the
compliance times were in part based on
observed wear properties of the
applicable parts. We recognize that JAL
may have data to show that its wear
64141
rates are different than that used in the
manufacturer’s analysis. If this is the
case, we recommend that JAL submit its
data in the form of an alternative
method of compliance because JAL
provides no technical justification for
changing the compliance times.
According to the provisions of
paragraph (n) of the AD, we may
approve requests to adjust the
compliance time if the request includes
data that show that the new compliance
time would provide an acceptable level
of safety. We have made no change to
the AD in this regard.
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.
The following table provides the
estimated costs for U.S. operators to
comply with this AD.
ESTIMATED COSTS
Action
Work
hours
Freeplay measurement .......
Lubrication ...........................
Modification for flap support
No. 3 and 6.
Average
labor rate
per hour
28
2
135
$80
80
80
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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
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Parts cost
0
0
$58,521
$2,240, per cycle ...............
$160, per cycle ..................
$69,321 ..............................
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
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Number of
U.S.registered
airplanes
Cost per airplane
Sfmt 4700
145
145
145
Fleet cost
$324,800, per cycle.
$23,200 per cycle.
$10,051,545.
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
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
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Federal Register / Vol. 72, No. 220 / Thursday, November 15, 2007 / Rules and Regulations
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
2007–23–11 Boeing: Amendment 39–15257.
Docket No. FAA–2007–27619;
Directorate Identifier 2005–NM–164–AD.
Effective Date
(a) This AD becomes effective December
20, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 777–
200, –200LR, –300, and –300ER series
airplanes, certificated in any category; as
identified in Boeing Service Bulletin 777–
27A0066, Revision 1, dated May 18, 2006.
Unsafe Condition
(d) This AD results from reports of
excessive wear of the pins, bushings, and
bearings, and corrosion at the joints of the
outboard trailing edge flap supports. We are
issuing this AD to prevent wear and
corrosion at the flap support joints, which
could result in loss of the trailing edge flap
and possible loss of control of the airplane.
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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.
Initial Freeplay Measurement
(f) At the applicable time in paragraph
(f)(1) or (f)(2) of this AD: Measure the
freeplay of support joints A, B, C, and D of
the trailing edge flap supports, numbers 1
through 3 inclusive and 6 through 8
inclusive, and of joint B of the trailing edge
flap supports, numbers 4 and 5; in
accordance with the Accomplishment
Instructions of Boeing Service Bulletin 777–
27A0066, Revision 1, dated May 18, 2006.
(1) For airplanes that have accumulated
6,000 total flight cycles or more on or before
the effective date of this AD and on which
a teardown inspection has not been
accomplished before the effective date of this
AD: At the earlier of the times in paragraph
(f)(1)(i) or (f)(1)(ii) of this AD.
(i) Prior to the accumulation of 10,000 total
flight cycles, or within 9 months after the
effective date of this AD, whichever occurs
later.
(ii) Within 30 months after the effective
date of this AD.
(2) For airplanes that have accumulated
fewer than 6,000 total flight cycles on or
before the effective date of this AD: At the
later of the times in paragraph (f)(2)(i) or
(f)(2)(ii) of this AD.
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(i) Prior to the accumulation of 6,000 total
flight cycles, or within 120 months after the
date of issuance of the original standard
airworthiness certificate or the date of
issuance of the original export certificate of
airworthiness, whichever occurs first.
(ii) Within 30 months after the effective
date of this AD.
Repetitive Intervals if the Freeplay
Measurement is Less Than 0.020 Inch
(g) If, during any freeplay measurement
required by paragraph (f), (g), or (h) of this
AD, the freeplay measurement is less than
0.020 inch: Repeat the freeplay measurement
required by paragraph (f) of this AD at the
applicable interval in paragraph (g)(1) or
(g)(2) of this AD. Accomplishing the actions
specified in paragraph (j) or (k) of this AD,
as applicable, extends the intervals for the
repetitive measurements for the associated
flap support only.
(1) At intervals not to exceed 1,000 flight
cycles.
(2) At intervals not to exceed 6,000 flight
cycles or 120 months, whichever occurs first,
if a review of airplane maintenance records
can conclusively determine that the joints
have been lubricated with only BMS 3–33
grease at the earlier of intervals not to exceed
1,000 flight cycles or 240 days since the last
support teardown inspection, or since the
date of issuance of the original standard
airworthiness certificate or the date of
issuance of the original export certificate of
airworthiness.
Related Investigative and Corrective
Actions, and Repetitive Intervals if the
Freeplay Measurement is 0.020 Inch or
Greater
(h) If, during any freeplay measurement
required by paragraph (f), (g), or (h) of this
AD, the freeplay measurement is 0.020 inch
or greater: Do the applicable action in
paragraph (h)(1), (h)(2), or (h)(3) of this AD.
Accomplishing the actions specified in
paragraph (j) or (k) of this AD, as applicable,
extends the intervals for repetitive
measurements for the associated flap support
only. Do all actions in accordance with the
Accomplishment Instructions and note (e) of
Table 1 in paragraph 1.E., ‘‘Compliance.’’ of
Boeing Service Bulletin 777–27A0066,
Revision 1, dated May 18, 2006.
(1) For airplanes that have accumulated
6,000 total flight cycles or more as of the
effective date of this AD, and for which the
freeplay measurement is 0.020 inch to 0.100
inch inclusive: Repeat the freeplay
measurement required by paragraph (f) of
this AD thereafter at intervals not to exceed
500 flight cycles until the support teardown
inspection in paragraph (h)(1)(i) or (h)(1)(ii)
of this AD is done.
(i) Within 12 months after the first freeplay
measurement of 0.020 inch to 0.100 inch
inclusive, do the applicable related
investigative and corrective actions specified
in the service bulletin as the ‘‘Support
Teardown Inspection,’’ and repeat the
freeplay measurement required by paragraph
(f) of this AD thereafter at intervals not to
exceed 6,000 flight cycles or 120 months,
whichever occurs first.
(ii) Before further flight after the first
freeplay measurement of 0.020 inch to 0.100
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inch inclusive, do the applicable related
investigative and corrective actions specified
in the service bulletin as the ‘‘Temporary
Return to Service Inspection’’ and, within 24
months after the first freeplay measurement
of 0.020 inch to 0.100 inch inclusive, do the
applicable related investigative and
corrective actions specified in the service
bulletin as the ‘‘Support Teardown
Inspection.’’ Repeat the freeplay
measurement required by paragraph (f) of
this AD thereafter at intervals not to exceed
6,000 flight cycles, or 120 months, whichever
occurs first.
(2) For airplanes that have accumulated
6,000 total flight cycles or more as of the
effective date of this AD, and the freeplay
measurement is greater than 0.100 inch: Do
the action in paragraph (h)(2)(i) or (h)(2)(ii)
of this AD.
(i) Before further flight after the first
freeplay measurement of greater than 0.100
inch, do the applicable related investigative
and corrective actions specified in the service
bulletin as the ‘‘Support Teardown
Inspection.’’ Repeat the freeplay
measurement required by paragraph (f) of
this AD thereafter at intervals not to exceed
6,000 flight cycles or 120 months, whichever
occurs first.
(ii) Before further flight after the first
freeplay measurement of greater than 0.100
inch, do applicable related investigative and
corrective actions in the ‘‘Temporary Return
to Service Inspection,’’ and within 6 months
after the first freeplay measurement of greater
than 0.100 inch, do the applicable related
investigative and corrective actions in the
‘‘Support Teardown Inspection.’’ Repeat the
freeplay measurement required by paragraph
(f) of this AD thereafter at intervals not to
exceed 6,000 flight cycles or 120 months,
whichever occurs first.
(3) For airplanes that have accumulated
fewer than 6,000 total flight cycles as of the
effective date of this AD: Before further flight
after the first freeplay measurement of 0.020
inch or greater, do the related investigative
and corrective actions specified in the service
bulletin as the ‘‘Support Teardown
Inspection.’’ Repeat the freeplay
measurement required by paragraph (f) of
this AD thereafter at intervals not to exceed
6,000 flight cycles or 120 months, whichever
occurs first.
Repetitive Lubrications
(i) Within 12 months after the effective
date of this AD: Lubricate the joints of the
trailing edge flap supports using BMS 3–33
grease. Repeat the lubrication thereafter at
intervals not to exceed 1,000 flight cycles, or
240 days, whichever occurs first. Do all
actions in accordance with the
Accomplishment Instructions, and note (d) of
Table 1 in paragraph 1.E., ‘‘Compliance,’’ of
Boeing Service Bulletin 777–27A0066,
Revision 1, dated May 18, 2006.
Modification/Repetitive Freeplay
Measurements for Flap Support Numbers 3
and 6
(j) Before the accumulation of 23,000 total
flight cycles or within 24 months after the
effective date of this AD, whichever is later:
Replace the pins, ball sets, and bushings on
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15NOR1
Federal Register / Vol. 72, No. 220 / Thursday, November 15, 2007 / Rules and Regulations
the joints of the trailing edge flap at support
numbers 3 and 6 with new, improved
components by doing all the applicable
actions, including all applicable corrective
actions, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 777–27A0071, Revision 1,
dated October 16, 2006. Before further flight
after doing the actions, do a detailed
inspection of the components that interface
with the flap support pins for discrepancies
(corrosion, damage, or excessive wear), and
a general visual inspection for any blocked
lubrication paths; and do all applicable
corrective actions. Repeat the freeplay
measurements for the associated trailing edge
flap support at intervals not to exceed 16,000
flight cycles in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 777–27A0071, Revision 1,
dated October 16, 2006. Accomplishing the
actions in this paragraph constitutes
terminating action for the actions specified in
paragraphs (f), (g), (h), and (i) of this AD, for
the associated trailing edge flap support only.
Optional Modification for Flap Support
Numbers 1, 2, 4, 5, 7, and 8
(k) Accomplishing the actions specified in
paragraph (j) of this AD at support numbers
1, 2, 4, 5, 7, and 8, extends the repetitive
intervals for the freeplay measurements
required by paragraph (g) of this AD to an
interval not to exceed 16,000 flight cycles for
the associated trailing edge flap support.
Accomplishing the actions in this paragraph
constitutes terminating action for the actions
specified in paragraphs (f), (g), (h), and (i) of
this AD, for the associated trailing edge flap
support only.
Revise Maintenance Planning Data (MPD)
Document
(l) Within 12 months after the effective
date of this AD: Revise the maintenance
practices for performing periodic inspections
and maintenance of the support joints of the
trailing edge flap for the maintenance
inspection program of the Boeing 777 MPD
Document by doing the actions specified in
paragraphs 1 and 3 only of Part 7 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 777–27A0071, Revision 1,
dated October 16, 2006.
rfrederick on PROD1PC67 with RULES
Actions Accomplished Previously
(m) Actions done before the effective date
of this AD in accordance with Boeing Alert
Service Bulletin 777–27A0066, dated July 28,
2005, are acceptable for compliance with the
actions specified in paragraphs (f), (g), (h),
and (i) of this AD, as applicable. Actions
done before the effective date of this AD in
accordance with Boeing Alert Service
Bulletin 777–27A0071, dated March 30,
2006, are acceptable for compliance with the
actions specified in paragraphs (j), (k), and (l)
of this AD, as applicable.
Alternative Methods of Compliance
(AMOCs)
(n)(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.
VerDate Aug<31>2005
15:27 Nov 14, 2007
Jkt 214001
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(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
(o) You must use Boeing Service Bulletin
777–27A0066, Revision 1, dated May 18,
2006; and Boeing Alert Service Bulletin 777–
27A0071, Revision 1, dated October 16, 2006;
as applicable, 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 Boeing Commercial Airplanes, P.O.
Box 3707, Seattle, Washington 98124–2207,
for a copy of this service information. You
may review copies at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW.,
Renton, Washington; or at the National
Archives and Records Administration
(NARA). For information on the availability
of this material at NARA, call 202–741–6030,
or go to: https://www.archives.gov/federalregister/cfr/ibr-locations.html.
Issued in Renton, Washington, on
November 2, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–21999 Filed 11–14–07; 8:45 am]
BILLING CODE 4910–13–P
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27740; Directorate
Identifier 2006–NM–290–AD; Amendment
39–15256; AD 2007–23–10]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–600, –700, –700C, –800 and
–900 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Frm 00025
Fmt 4700
Boeing Model 737–600, –700, –700C,
–800 and –900 series airplanes. This AD
requires an inspection of the fillet
sealant at the inboard and outboard
sides of the receptacles in the wheel
wells of the main landing gear, and
related investigative/corrective actions
if necessary. This AD results from
reports of in-production airplanes with
missing or insufficient fillet sealant
around the receptacles at the disconnect
bracket. We are issuing this AD to
prevent corrosion damage due to
missing or insufficient fillet sealant.
Such corrosion could result in
insufficient electrical bonding between
the connectors and the disconnect
bracket, and consequent loss of the
shielding that protects the wire bundles
from lightning, electromagnetic
interference (EMI), and high intensity
radiated field (HIRF). Loss of lightning,
EMI, and HIRF protection at those
receptacles could cause failure of
multiple electrical systems and
subsequent loss of several critical
control systems that are necessary for
safe flight. In addition, a lightning strike
could cause arcing in the fuel tank; this
potential ignition source, in
combination with flammable fuel
vapors, could result in a fuel tank
explosion and consequent loss of the
airplane.
This AD becomes effective
December 20, 2007.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of December 20, 2007.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207.
DATES:
Examining the AD Docket
DEPARTMENT OF TRANSPORTATION
PO 00000
64143
Sfmt 4700
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is the Document Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Binh Tran, Aerospace Engineer, Systems
and Equipment Branch, ANM–130S,
FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton,
E:\FR\FM\15NOR1.SGM
15NOR1
]]>Agencies
[Federal Register Volume 72, Number 220 (Thursday, November 15, 2007)]
[Rules and Regulations]
[Pages 64139-64143]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-21999]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-27619; Directorate Identifier 2005-NM-164-AD;
Amendment 39-15257; AD 2007-23-11]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 777 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 airplanes. This AD requires repetitive
measurements of the freeplay of certain joints of the trailing edge
flap supports; repetitive lubrication of the support joints; and
related investigative and corrective actions if necessary. This AD also
provides for modifying certain components of the trailing edge flap
supports, which extends the intervals for the repetitive measurements,
and revising the maintenance practices of the maintenance planning data
document. This AD results from reports of excessive wear of the pins,
bushings, and bearings, and corrosion at the joints of the outboard
trailing edge flap supports. We are issuing this AD to prevent wear and
corrosion at the flap support joints, which could result in loss of the
trailing edge flap and possible loss of control of the airplane.
DATES: This AD becomes effective December 20, 2007.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of December 20,
2007.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
Examining the Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (telephone 800-647-5527) is the Document Management
Facility, U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Gary Oltman, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind
[[Page 64140]]
Avenue SW., Renton, Washington 98057-3356; telephone (425) 917-6443;
fax (425) 917-6590.
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 airplanes. That NPRM was published in the Federal Register on March
20, 2007 (72 FR 13048). That NPRM proposed to require repetitive
measurements of the freeplay of certain joints of the trailing edge
flap supports; repetitive lubrication of the support joints; and
related investigative and corrective actions if necessary. That NPRM
also provides for modifying certain components of the trailing edge
flap supports, which extends the intervals for the repetitive
measurements, and revising the maintenance practices of the maintenance
planning data document.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Request To Change Paragraph (f)(1) of the NPRM
Boeing asks that paragraph (f)(1) be changed to read ``For
airplanes that have accumulated 6,000 total flight cycles or more on or
before the effective date of this AD and on which a teardown inspection
has not been accomplished before the effective date of this AD.''
Boeing states that with the use of the word ``or'' in place of the word
``and'' as noted above, the NPRM could include ``For airplanes on which
a teardown inspection has not been accomplished before the effective
date of this AD'' and could be interpreted as including new airplanes.
Boeing adds that this may be confusing as the NPRM provides coverage
for airplanes that have accumulated fewer than 6,000 cycles, or new
airplanes.
We agree with changing ``or'' to ``and'' as requested by Boeing
because the use of the word ``or'' could be interpreted as applying to
all Model 777 airplanes in the applicability, regardless of the total
flight cycles, if a teardown inspection has not been done. We have
changed paragraph (f)(1) of this AD accordingly.
We disagree with the interpretation that the AD applicability could
include new airplanes, because Boeing Service Bulletin 777-27A0066,
Revision 1, dated May 18, 2006, clearly identifies affected airplanes
as having line numbers 1 through 546 only, and we refer to that service
bulletin in paragraph (c), ``Applicability,'' of the NPRM. We have made
no change to the AD in this regard.
Request To Change Description of Relevant Service Information Section
Air France asks that certain language specified in the Relevant
Service Information section of the NPRM be changed. Air France states
that the last paragraph of the description of Service Bulletin 777-
27A0066, Revision 1, specifies that accomplishing the actions in Boeing
Alert Service Bulletin 777-27A0071, Revision 1, dated October 16, 2006,
eliminates the need for the repetitive measurements and lubrications of
certain trailing edge flap supports. Air France notes that Alert
Service Bulletin 777-27A0071, Revision 1, does not eliminate the need
for the repetitive inspections, but only extends the interval for the
repetitive inspections.
We acknowledge the commenter's concern; however, that section of
the preamble does not reappear in the final rule. We have provided
clarification as follows: Service Bulletin 777-27A0071, Revision 1,
specifies that accomplishing the modification in that service bulletin
constitutes terminating action for the actions specified in Service
Bulletin 777-27A0066, Revision 1, for the associated trailing edge flap
support only. The actions required by paragraph (l) of the AD require
continuing periodic inspections and maintenance of the support joints
of the trailing edge flap, which is part of the maintenance inspection
program. Those are the inspections that are not terminated by the AD.
As part of the maintenance program, those inspections would generally
be accomplished at the same time or in combination with normally
scheduled airplane inspections and other maintenance program tasks. In
light of these facts, we have made no change to the AD.
Japan Airlines International (JAL) asks that the NPRM be changed to
allow modification of the flap support mechanism by incorporating
Service Bulletin 777-27A0071, Revision 1, dated October 16, 2006,
instead of doing a support teardown inspection or temporary return to
service inspection. JAL refers to the Relevant Service Information
section of the NPRM, which describes procedures for disassembling any
joint that exceeds the freeplay limits specified in Service Bulletin
777-27A0066, Revision 1, and doing the related investigative and
corrective actions in the ``support teardown inspection.'' JAL also
refers to the teardown inspections required by paragraphs (h)(1),
(h)(2), and (h)(3) of the NPRM. JAL notes that as an option to the
support teardown inspection, for certain airplanes, the service
bulletin describes procedures for a ``temporary return to service''
inspection.
We agree with JAL that allowing operators to accomplish the
modification specified in Alert Service Bulletin 777-27A0071, Revision
1, instead of the teardown inspection or temporary return to service is
an acceptable option. However, we do not agree to change the AD because
that option is already specified in this AD. We have made no change to
the AD in this regard.
Requests To Clarify Actions in Paragraph (k) of the NPRM
Air France asks that we include in paragraph (k) of the NPRM the
extension interval of 16,000 flight cycles for the repetitive
measurements allowed by the application of Alert Service Bulletin 777-
27A0071, Revision 1, dated October 16, 2006. Air France notes that
paragraph (k) should specify accomplishing the actions in Alert Service
Bulletin 777-27A0071, Revision 1; or make a reference to maintenance
review board (MRB) and maintenance planning document (MPD) item 27-460-
01, which is the item created in the MRB and MPD; or take into account
airplanes on which Service Bulletin 777-27A0071, Revision 1, has been
accomplished at the extended 16,000 flight cycle intervals.
JAL states that paragraph (k) of the NPRM should be clarified to
include the extended interval of 16,000 flight cycles.
We agree with the commenters that paragraph (k) of the AD should
provide the extended interval for the repetitive measurements so it
corresponds with the interval specified in paragraph (j) of the AD. We
have included that interval in paragraph (k) for clarification.
Air France also asks that paragraph (k) of the NPRM include
terminating action. Air France states that paragraph (k) does not
specify that application of Alert Service Bulletin 777-27A0071,
Revision 1, is terminating action for the actions specified in
paragraphs (f), (g), (h), and (i) of the NPRM, for the associated
trailing edge flap support only. Air France adds that paragraph (k)
should correspond with paragraph (j) of the NPRM.
We agree with Air France for the reasons provided, and we have
included the terminating action in paragraph (k) of the AD for
clarification.
Request To Change Compliance Times
JAL asks that the compliance times specified in paragraph (h)(1)(i)
and (h)(3) of the NPRM be extended from 12
[[Page 64141]]
to 18 months after the first freeplay measurement of 0.020 inch to
0.100 inch inclusive, and that the repetitive freeplay inspection
(measurement) interval be reduced to 500 flight cycles. JAL provides
the following reasons for the request:
All flap support mechanisms are modified at the same time
to avoid complexity and save time with the freeplay inspection
interval. There are many Model 777 airplanes planned for flap-related
modifications, but once the freeplay value exceeds 0.020 inch, the
actions must be done within 12 months. The 12-month compliance time
makes it difficult to schedule additional airplanes because of
inflexibility; however, 18 months provides more flexibility for
scheduling flap modifications. Reducing the freeplay inspection
interval to 500 flight cycles would support the compliance time
extension.
Since the freeplay inspection procedure is not precise, it
frequently measures freeplay data containing human errors. If the
freeplay measurement value exceeds 0.020 inch the actions should be
done within 12 months. The teardown inspection must be done before
further flight if the freeplay value exceeds 0.020 inch. On the next
measurement the value can get within 0.020 inch, but the actions must
still be done within 12 months. This is not economical and JAL should
be allowed an additional 6-month buffer for flexibility.
Since repetitive inspections are done at intervals of 500
flight cycles, JAL monitors the freeplay data for the joints. Due to
the freeplay (wear) value of all joints being monitored, the trend of
the freeplay value of specific joints is known. For Model 777 airplanes
utilized for domestic flight (high utilization in terms of flight
cycles), the 500 flight-cycle freeplay inspection is done within 3
months, and the normal 1,000 flight-cycle freeplay inspection is done
at around 6 months.
In developing an appropriate compliance time for these actions, we
considered the urgency associated with the subject unsafe condition,
the availability of required parts, and the practical aspect of
accomplishing the required modification within a period of time that
corresponds to the normal scheduled maintenance for most affected
operators. Additionally, the compliance times were in part based on
observed wear properties of the applicable parts. We recognize that JAL
may have data to show that its wear rates are different than that used
in the manufacturer's analysis. If this is the case, we recommend that
JAL submit its data in the form of an alternative method of compliance
because JAL provides no technical justification for changing the
compliance times. According to the provisions of paragraph (n) of the
AD, we may approve requests to adjust the compliance time if the
request includes data that show that the new compliance time would
provide an acceptable level of safety. We have made no change to the AD
in this regard.
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. The following table provides the estimated costs for
U.S. operators to comply with this AD.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of
Work Average Cost per U.S.-
Action hours labor rate Parts cost airplane registered Fleet cost
per hour airplanes
----------------------------------------------------------------------------------------------------------------
Freeplay measurement........ 28 $80 0 $2,240, per 145 $324,800, per
cycle. cycle.
Lubrication................. 2 80 0 $160, per cycle 145 $23,200 per
cycle.
Modification for flap 135 80 $58,521 $69,321........ 145 $10,051,545.
support No. 3 and 6.
----------------------------------------------------------------------------------------------------------------
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:
[[Page 64142]]
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):
2007-23-11 Boeing: Amendment 39-15257. Docket No. FAA-2007-27619;
Directorate Identifier 2005-NM-164-AD.
Effective Date
(a) This AD becomes effective December 20, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 777-200, -200LR, -300, and -
300ER series airplanes, certificated in any category; as identified
in Boeing Service Bulletin 777-27A0066, Revision 1, dated May 18,
2006.
Unsafe Condition
(d) This AD results from reports of excessive wear of the pins,
bushings, and bearings, and corrosion at the joints of the outboard
trailing edge flap supports. We are issuing this AD to prevent wear
and corrosion at the flap support joints, which could result in loss
of the trailing edge flap and possible 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.
Initial Freeplay Measurement
(f) At the applicable time in paragraph (f)(1) or (f)(2) of this
AD: Measure the freeplay of support joints A, B, C, and D of the
trailing edge flap supports, numbers 1 through 3 inclusive and 6
through 8 inclusive, and of joint B of the trailing edge flap
supports, numbers 4 and 5; in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 777-27A0066, Revision 1,
dated May 18, 2006.
(1) For airplanes that have accumulated 6,000 total flight
cycles or more on or before the effective date of this AD and on
which a teardown inspection has not been accomplished before the
effective date of this AD: At the earlier of the times in paragraph
(f)(1)(i) or (f)(1)(ii) of this AD.
(i) Prior to the accumulation of 10,000 total flight cycles, or
within 9 months after the effective date of this AD, whichever
occurs later.
(ii) Within 30 months after the effective date of this AD.
(2) For airplanes that have accumulated fewer than 6,000 total
flight cycles on or before the effective date of this AD: At the
later of the times in paragraph (f)(2)(i) or (f)(2)(ii) of this AD.
(i) Prior to the accumulation of 6,000 total flight cycles, or
within 120 months after the date of issuance of the original
standard airworthiness certificate or the date of issuance of the
original export certificate of airworthiness, whichever occurs
first.
(ii) Within 30 months after the effective date of this AD.
Repetitive Intervals if the Freeplay Measurement is Less Than 0.020
Inch
(g) If, during any freeplay measurement required by paragraph
(f), (g), or (h) of this AD, the freeplay measurement is less than
0.020 inch: Repeat the freeplay measurement required by paragraph
(f) of this AD at the applicable interval in paragraph (g)(1) or
(g)(2) of this AD. Accomplishing the actions specified in paragraph
(j) or (k) of this AD, as applicable, extends the intervals for the
repetitive measurements for the associated flap support only.
(1) At intervals not to exceed 1,000 flight cycles.
(2) At intervals not to exceed 6,000 flight cycles or 120
months, whichever occurs first, if a review of airplane maintenance
records can conclusively determine that the joints have been
lubricated with only BMS 3-33 grease at the earlier of intervals not
to exceed 1,000 flight cycles or 240 days since the last support
teardown inspection, or since the date of issuance of the original
standard airworthiness certificate or the date of issuance of the
original export certificate of airworthiness.
Related Investigative and Corrective Actions, and Repetitive Intervals
if the Freeplay Measurement is 0.020 Inch or Greater
(h) If, during any freeplay measurement required by paragraph
(f), (g), or (h) of this AD, the freeplay measurement is 0.020 inch
or greater: Do the applicable action in paragraph (h)(1), (h)(2), or
(h)(3) of this AD. Accomplishing the actions specified in paragraph
(j) or (k) of this AD, as applicable, extends the intervals for
repetitive measurements for the associated flap support only. Do all
actions in accordance with the Accomplishment Instructions and note
(e) of Table 1 in paragraph 1.E., ``Compliance.'' of Boeing Service
Bulletin 777-27A0066, Revision 1, dated May 18, 2006.
(1) For airplanes that have accumulated 6,000 total flight
cycles or more as of the effective date of this AD, and for which
the freeplay measurement is 0.020 inch to 0.100 inch inclusive:
Repeat the freeplay measurement required by paragraph (f) of this AD
thereafter at intervals not to exceed 500 flight cycles until the
support teardown inspection in paragraph (h)(1)(i) or (h)(1)(ii) of
this AD is done.
(i) Within 12 months after the first freeplay measurement of
0.020 inch to 0.100 inch inclusive, do the applicable related
investigative and corrective actions specified in the service
bulletin as the ``Support Teardown Inspection,'' and repeat the
freeplay measurement required by paragraph (f) of this AD thereafter
at intervals not to exceed 6,000 flight cycles or 120 months,
whichever occurs first.
(ii) Before further flight after the first freeplay measurement
of 0.020 inch to 0.100 inch inclusive, do the applicable related
investigative and corrective actions specified in the service
bulletin as the ``Temporary Return to Service Inspection'' and,
within 24 months after the first freeplay measurement of 0.020 inch
to 0.100 inch inclusive, do the applicable related investigative and
corrective actions specified in the service bulletin as the
``Support Teardown Inspection.'' Repeat the freeplay measurement
required by paragraph (f) of this AD thereafter at intervals not to
exceed 6,000 flight cycles, or 120 months, whichever occurs first.
(2) For airplanes that have accumulated 6,000 total flight
cycles or more as of the effective date of this AD, and the freeplay
measurement is greater than 0.100 inch: Do the action in paragraph
(h)(2)(i) or (h)(2)(ii) of this AD.
(i) Before further flight after the first freeplay measurement
of greater than 0.100 inch, do the applicable related investigative
and corrective actions specified in the service bulletin as the
``Support Teardown Inspection.'' Repeat the freeplay measurement
required by paragraph (f) of this AD thereafter at intervals not to
exceed 6,000 flight cycles or 120 months, whichever occurs first.
(ii) Before further flight after the first freeplay measurement
of greater than 0.100 inch, do applicable related investigative and
corrective actions in the ``Temporary Return to Service
Inspection,'' and within 6 months after the first freeplay
measurement of greater than 0.100 inch, do the applicable related
investigative and corrective actions in the ``Support Teardown
Inspection.'' Repeat the freeplay measurement required by paragraph
(f) of this AD thereafter at intervals not to exceed 6,000 flight
cycles or 120 months, whichever occurs first.
(3) For airplanes that have accumulated fewer than 6,000 total
flight cycles as of the effective date of this AD: Before further
flight after the first freeplay measurement of 0.020 inch or
greater, do the related investigative and corrective actions
specified in the service bulletin as the ``Support Teardown
Inspection.'' Repeat the freeplay measurement required by paragraph
(f) of this AD thereafter at intervals not to exceed 6,000 flight
cycles or 120 months, whichever occurs first.
Repetitive Lubrications
(i) Within 12 months after the effective date of this AD:
Lubricate the joints of the trailing edge flap supports using BMS 3-
33 grease. Repeat the lubrication thereafter at intervals not to
exceed 1,000 flight cycles, or 240 days, whichever occurs first. Do
all actions in accordance with the Accomplishment Instructions, and
note (d) of Table 1 in paragraph 1.E., ``Compliance,'' of Boeing
Service Bulletin 777-27A0066, Revision 1, dated May 18, 2006.
Modification/Repetitive Freeplay Measurements for Flap Support Numbers
3 and 6
(j) Before the accumulation of 23,000 total flight cycles or
within 24 months after the effective date of this AD, whichever is
later: Replace the pins, ball sets, and bushings on
[[Page 64143]]
the joints of the trailing edge flap at support numbers 3 and 6 with
new, improved components by doing all the applicable actions,
including all applicable corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 777-
27A0071, Revision 1, dated October 16, 2006. Before further flight
after doing the actions, do a detailed inspection of the components
that interface with the flap support pins for discrepancies
(corrosion, damage, or excessive wear), and a general visual
inspection for any blocked lubrication paths; and do all applicable
corrective actions. Repeat the freeplay measurements for the
associated trailing edge flap support at intervals not to exceed
16,000 flight cycles in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 777-27A0071, Revision
1, dated October 16, 2006. Accomplishing the actions in this
paragraph constitutes terminating action for the actions specified
in paragraphs (f), (g), (h), and (i) of this AD, for the associated
trailing edge flap support only.
Optional Modification for Flap Support Numbers 1, 2, 4, 5, 7, and 8
(k) Accomplishing the actions specified in paragraph (j) of this
AD at support numbers 1, 2, 4, 5, 7, and 8, extends the repetitive
intervals for the freeplay measurements required by paragraph (g) of
this AD to an interval not to exceed 16,000 flight cycles for the
associated trailing edge flap support. Accomplishing the actions in
this paragraph constitutes terminating action for the actions
specified in paragraphs (f), (g), (h), and (i) of this AD, for the
associated trailing edge flap support only.
Revise Maintenance Planning Data (MPD) Document
(l) Within 12 months after the effective date of this AD: Revise
the maintenance practices for performing periodic inspections and
maintenance of the support joints of the trailing edge flap for the
maintenance inspection program of the Boeing 777 MPD Document by
doing the actions specified in paragraphs 1 and 3 only of Part 7 of
the Accomplishment Instructions of Boeing Alert Service Bulletin
777-27A0071, Revision 1, dated October 16, 2006.
Actions Accomplished Previously
(m) Actions done before the effective date of this AD in
accordance with Boeing Alert Service Bulletin 777-27A0066, dated
July 28, 2005, are acceptable for compliance with the actions
specified in paragraphs (f), (g), (h), and (i) of this AD, as
applicable. Actions done before the effective date of this AD in
accordance with Boeing Alert Service Bulletin 777-27A0071, dated
March 30, 2006, are acceptable for compliance with the actions
specified in paragraphs (j), (k), and (l) of this AD, as applicable.
Alternative Methods of Compliance (AMOCs)
(n)(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) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(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
(o) You must use Boeing Service Bulletin 777-27A0066, Revision
1, dated May 18, 2006; and Boeing Alert Service Bulletin 777-
27A0071, Revision 1, dated October 16, 2006; as applicable, 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 Boeing Commercial
Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207, for a copy
of this service information. You may review copies at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton,
Washington; or at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-
register/cfr/ibr-locations.html.
Issued in Renton, Washington, on November 2, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-21999 Filed 11-14-07; 8:45 am]
BILLING CODE 4910-13-P
