Airworthiness Directives; McDonnell Douglas Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, MD-10-30F, MD-11, and MD-11F Airplanes, 6669-6673 [06-1148]
Download as PDF
Federal Register / Vol. 71, No. 27 / Thursday, February 9, 2006 / Rules and Regulations
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
2006–03–11 BAE Systems (Operations)
Limited (Formerly British Aerospace
Regional Aircraft): Amendment 39–
14475. Docket No. FAA–2006–23799;
Directorate Identifier 2004–NM–141–AD.
Effective Date
(a) This AD becomes effective February 24,
2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all BAE Systems
(Operations) Limited Model HS 748 series 2A
and series 2B airplanes, certificated in any
category.
Unsafe Condition
(d) This AD results from incidents where
an elevator gust lock re-engaged without
input from the flightcrew, and may have
caused a flight control restriction. We are
issuing this AD to prevent uncommanded reengagement of the elevator gust lock, which
could result in restriction of the elevator’s
movement and consequent reduced
controllability 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.
cprice-sewell on PROD1PC66 with RULES
Installation and Repetitive Inspections
(f) Within 9 months after the effective date
of this AD, install a baulking actuator system
for the elevator gust lock in accordance with
the Accomplishment Instructions of BAE
Systems (Operations) Limited Service
Bulletin HS748–27–135, Revision 2, dated
October 2, 2003.
Note 1: BAE Systems (Operations) Limited
Service Bulletin HS748–27–135, Revision 2,
dated October 2, 2003, refers to BAE Systems
(Operations) Limited Alert Service Bulletin
HS748–A27–128, Revision 1, dated
December 10, 2002; and BAE Systems
(Operations) Limited Service Bulletin
HS748–A27–76, Revision 3, dated December
20, 1996; as additional sources of service
information for doing the installation.
(g) At the later of the times specified in
paragraphs (g)(1) or (g)(2), test the actuator
system for correct operation in accordance
with Appendix 2 of BAE Systems
(Operations) Limited Service Bulletin
HS748–27–135, Revision 2, dated October 2,
2003. Repeat the inspection thereafter at
intervals not to exceed 750 flight hours or
240 days, whichever occurs first. Correct any
operation errors before further flight in
accordance with a method approved by the
FAA or the Civil Aviation Authority (CAA)
(or its delegated agent).
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12:39 Feb 08, 2006
Jkt 208001
(1) 750 flight hours or 240 days after
installation of the actuator system, whichever
occurs first.
(2) 750 flight hours or 240 days after the
effective date of this AD, whichever occurs
first.
Inspection of Any Installation Done in
Accordance With Older Service Bulletin
(h) For airplanes with a baulking actuator
system installed in accordance with the
Accomplishment Instructions of BAE
Systems (Operations) Limited Service
Bulletin HS748–27–135, Revision 1, dated
December 10, 2002: Within 750 flight hours
or 240 days after the effective date of this AD,
whichever occurs first, do the actions
specified in paragraphs (h)(1) and (h)(2) of
this AD.
(1) Do a general visual inspection of the
actuator system for correct wiring in
accordance with the Accomplishment
Instructions of BAE Systems (Operations)
Limited Service Bulletin HS748–27–135,
Revision 2, dated October 2, 2003. Reroute
any wiring as applicable before further flight
in accordance with the service bulletin.
(2) Do a functional test of the actuator
system in accordance with Appendix 1 of
BAE Systems (Operations) Limited Service
Bulletin HS748–27–135, Revision 2, dated
October 2, 2003.
Note 2: For the purposes of this AD, a
general visual inspection is: ‘‘A visual
examination of an interior or exterior area,
installation, or assembly to detect obvious
damage, failure, or irregularity. This level of
inspection is made from within touching
distance unless otherwise specified. A mirror
may be necessary to ensure visual access to
all surfaces in the inspection area. This level
of inspection is made under normally
available lighting conditions such as
daylight, hangar lighting, flashlight, or
droplight and may require removal or
opening of access panels or doors. Stands,
ladders, or platforms may be required to gain
proximity to the area being checked.’’
Previous Actions
(i) Actions done before the effective date of
this AD in accordance with BAE Systems
(Operations) Limited Service Bulletin
HS748–27–135, Revision 1, dated December
10, 2002, are considered acceptable for
compliance with paragraphs (f) and (g) of this
AD.
Alternative Methods of Compliance
(AMOCs)
(j)(1) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
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
(k) British airworthiness directives G–
2004–0002, dated February 18, 2004, and
003–12–2002, also address the subject of this
AD.
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6669
Material Incorporated by Reference
(l) You must use BAE Systems (Operations)
Limited Service Bulletin HS748–27–135,
Revision 2, dated October 2, 2003, 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 British Aerospace Regional
Aircraft American Support, 13850 Mclearen
Road, Herndon, Virginia 20171, 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
26, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 06–1149 Filed 2–8–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22503; Directorate
Identifier 2005–NM–062–AD; Amendment
39–14477; AD 2006–03–13]
RIN 2120–AA64
Airworthiness Directives; McDonnell
Douglas Model DC–10–10, DC–10–10F,
DC–10–15, DC–10–30, DC–10–30F (KC–
10A and KDC–10), DC–10–40, DC–10–
40F, MD–10–10F, MD–10–30F, MD–11,
and MD–11F 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
McDonnell Douglas transport category
airplanes. This AD requires an initial
ultrasonic inspection for cracks of the
studbolts of the inboard and outboard
hinge fittings of the left and right
outboard flaps of the wings. Based on
the inspection results, this AD also
requires doing repetitive ultrasonic
inspections, replacing upper and/or
lower studbolts with new or serviceable
studbolts, doing a detailed inspection
for corrosion of the upper studbolts,
doing a magnetic particle inspection for
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Federal Register / Vol. 71, No. 27 / Thursday, February 9, 2006 / Rules and Regulations
part 39 to include an AD that would
apply to certain McDonnell Douglas
Model DC–10–10, DC–10–10F, DC–10–
15, DC–10–30, DC–10–30F (KC–10A
and KDC–10), DC–10–40, DC–10–40F,
MD–10–10F, MD–10–30F, MD–11, and
MD–11F airplanes. That NPRM was
published in the Federal Register on
September 22, 2005 (70 FR 55598). That
NPRM proposed to require an initial
ultrasonic inspection for cracks of the
studbolts of the inboard and outboard
hinge fittings of the left and right
outboard flaps of the wings. Based on
the inspection results, that NPRM also
proposed to require doing repetitive
ultrasonic inspections, replacing upper
and/or lower studbolts with new or
serviceable studbolts, doing a detailed
inspection for corrosion of the upper
studbolts, doing a magnetic particle
inspection for cracks of studbolts, and
changing the protection treatment; as
applicable.
cracks of studbolts, and changing the
protection treatment; as applicable. This
AD results from reports of corrosion and
failures of the upper and lower
studbolts of the outboard flaps inboard
and outboard hinge fittings. We are
issuing this AD to prevent corrosion and
subsequent cracking of studbolts, which
could result in failure of the flap hinge
fittings and their possible separation
from the wing rear spar, and consequent
reduced controllability of the airplane.
DATES: This AD becomes effective
March 16, 2006.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of March 16, 2006.
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, Long Beach Division, 3855
Lakewood Boulevard, Long Beach,
California 90846, Attention: Data and
Service Management, Dept. C1–L5A
(D800–0024), for service information
identified in this AD.
FOR FURTHER INFORMATION CONTACT:
Maureen Moreland, Aerospace
Engineer, Airframe Branch, ANM–120L,
FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard,
Lakewood, California 90712–4137;
telephone (562) 627–5238; fax (562)
627–5210.
SUPPLEMENTARY INFORMATION:
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
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
Request To Consider Parts Availability
One commenter requests that we
consider parts availability before setting
an effective date for the AD. The
commenter states that there are no kits
available to do the proposed
replacement. The commenter also states
that most quantities of studbolts are
minimal (less than 50 available) with
additional orders coming in from
suppliers in the first half of 2006.
We agree to consider parts
availability, but do not agree that there
is a shortage of parts. The AD specifies
several options for continued operation
with existing studbolts that are found
not to be cracked. Options include
installing new bolts with increased
corrosion protections; treating existing
studbolts with corrosion protection in
accordance with a method approved by
us; and replacing the studbolts with
equivalent studbolts with follow-on
repetitive inspections.
In addition, the airplane manufacturer
has informed us that they have
developed corrosion protection
methodologies and will pursue approval
from us once the final rule is issued. We
will support this effort. The airplane
manufacturer also has informed us that
they are scheduled to receive studbolts
in March of 2006 to support the
required replacement of failed studbolts.
For operators that initiate a program to
replace all the studbolts as terminating
action, the airplane manufacturer
recommends placing a specific purchase
order for the part numbers and
quantities of studbolts required, along
with a time frame that supports their
replacement program.
In light of these findings, we have
determined that no change to the final
rule is necessary.
Clarification of Alternative Method of
Compliance (AMOC) Paragraph
We have revised this action to clarify
the appropriate procedure for notifying
the principal inspector before using any
approved AMOC on any airplane to
which the AMOC applies.
Clarification of Replacement
In paragraph (j)(4) of the NPRM, we
inadvertently omitted the reference to
the service bulletin. We have revised
that paragraph to include the phrase ‘‘in
accordance with the service bulletin.’’
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 change described
previously. We have determined that
this change will neither increase the
economic burden on any operator nor
increase the scope of the AD.
Costs of Compliance
There are about 594 airplanes of the
affected design in the worldwide fleet.
This AD will affect about 297 U.S.registered Model DC–10–10, DC–10–
10F, DC–10–15, DC–10–30, DC–10–30F
(KC–10A and KDC–10), DC–10–40, DC–
10–40F, MD–10–10F, and MD–10–30F
airplanes; and 69 Model MD–11 and
–11F airplanes.
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ESTIMATED COSTS FOR REQUIRED ACTIONS
Action
Work
hours
Average labor
rate per hour
Parts
Cost per
airplane
Number of
U.S.-registered
airplanes
Fleet cost
Initial ultrasonic inspection ......................
16
$65
None .......................
$1,040
366
$380,640
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Federal Register / Vol. 71, No. 27 / Thursday, February 9, 2006 / Rules and Regulations
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.
6671
the FAA amends 14 CFR part 39 as
follows:
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
2006–03–13 McDonnell Douglas:
Amendment 39–14477. Docket No.
FAA–2005–22503; Directorate Identifier
2005–NM–062–AD.
Effective Date
(a) This AD becomes effective March 16,
2006.
Affected ADs
(b) None.
Applicability
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
I
(c) This AD applies to McDonnell Douglas
airplanes identified in Table 1 of this AD,
certificated in any category.
TABLE 1.—APPLICABILITY
Model—
As identified in—
(1) DC–10–10, DC–10–10F, DC–10–15, DC–10–30, DC–10–30F (KC–
10A and KDC–10), DC–10–40, DC–10–40F, MD–10–10F and MD–
10–30F airplanes.
(2) MD–11 and MD–11F airplanes ...........................................................
Boeing Service Bulletin DC10–57–154, dated February 2, 2005.
Unsafe Condition
(d) This AD was prompted by reports of
corrosion and failures of the upper and lower
studbolts of the outboard flaps inboard and
outboard hinge fittings. We are issuing this
AD to prevent corrosion and subsequent
cracking of studbolts, which could result in
failure of the flap hinge fittings and their
possible separation from the wing rear spar,
and consequent reduced controllability 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.
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Service Bulletins
(f) The term ‘‘service bulletin,’’ as used in
this AD, means the Accomplishment
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12:39 Feb 08, 2006
Jkt 208001
Boeing Service Bulletin MD11–57–076, dated February 2, 2005.
Instructions of the applicable service bulletin
listed in Table 1 of this AD.
Ultrasonic Inspection
(g) Do an ultrasonic inspection for cracks
of the upper and lower studbolts (upper
studbolts only for Model MD–11 and –11F
airplanes) of the inboard and outboard hinge
fittings of the left and right outboard flaps of
the wings, in accordance with the service
bulletin. Inspect within 72 months from the
time the studbolts were last replaced, or
within 24 months after the effective date of
this AD, whichever occurs later.
Condition 1: No Cracked Studbolts
(h) If no cracked upper or lower studbolt
is detected during any ultrasonic inspection
required by paragraph (g) of this AD, do the
actions specified in paragraph (i), (j), or (k)
of this AD.
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Fmt 4700
Sfmt 4700
Condition 1, Option 1: Repetitive Inspections
(i) Repeat the ultrasonic inspection
required by paragraph (g) of this AD
thereafter at intervals not to exceed 24
months, until the action in paragraph (j)(1),
(j)(2), (k)(1), (k)(2)(i), (o)(1), or (o)(2)(i) of this
AD is done.
Condition 1, Option 2: Replacement
(j) Within 72 months from the time the
studbolts were last replaced, or within 24
months after the effective date of this AD,
whichever occurs later, do any one of the
replacements in Table 2 of this AD.
Thereafter, at the times specified in Table 2,
repeat the ultrasonic inspection required by
paragraph (g) of this AD (if applicable).
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Federal Register / Vol. 71, No. 27 / Thursday, February 9, 2006 / Rules and Regulations
TABLE 2.—REPLACEMENT PARTS
Replace the upper and lower studbolts (as applicable) of the inboard and outboard hinge fittings with—
And repeat the ultrasonic inspection required
by paragraph (g) of this AD thereafter—
Accomplishing this replacement terminates—
(1) New studbolts that have increased corrosion
protection in accordance with the service bulletin.
(2) Studbolts changed with protective treatment
in accordance with a method approved by
the Manager, Los Angeles Aircraft Certification (ACO), FAA.
(3) Equivalent studbolts in accordance with the
service bulletin.
(4) Kept serviceable studbolts wet with sealant
in accordance with the service bulletin.
None .................................................................
The repetitive inspection requirements of
paragraph (i), (j)(3), and (j)(4) of this AD.
None .................................................................
The repetitive inspection requirements of
paragraph (i), (j)(3), and (j)(4) of this AD.
At intervals not to exceed 24 months ..............
None.
At intervals not to exceed 24 months ..............
None.
Condition 1, Option 3: Removal,
Inspection(s), and Corrective Actions
(k) Within 72 months from the time the
studbolts were last replaced, or within 24
months after the effective date of this AD,
whichever occurs later, remove the upper
and lower studbolts (as applicable) of the
inboard and outboard hinge fittings, and do
a detailed inspection for corrosion of the
upper and lower studbolts (as applicable), in
accordance with the service bulletin.
cprice-sewell on PROD1PC66 with RULES
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
(1) If no corroded studbolt is found, before
further flight, change the protective treatment
of all upper and lower studbolts (as
applicable) to give increased corrosion
protection, in accordance with a method
approved by the Manager, Los Angeles ACO,
FAA. Accomplishing this change ends the
repetitive inspection requirements of
paragraph (i) of this AD.
(2) If any corroded studbolt is found, before
further flight, install any studbolt identified
in and in accordance with Table 2 of this AD,
thereafter do the repetitive inspections (if
applicable) in accordance with Table 2 of this
AD, and do a magnetic particle inspection for
cracks in any remaining studbolt in
accordance with the service bulletin.
(i) If no cracked studbolt is found, before
further flight, change the protective treatment
of all remaining studbolts to give increased
corrosion protection, in accordance with a
method approved by the Manager, Los
Angeles ACO, FAA. Accomplishing this
change ends the repetitive inspection
requirements of paragraph (i) of this AD.
(ii) If any cracked studbolt is found, before
further flight, install any studbolt identified
in and in accordance with Table 2 of this AD,
and thereafter do the repetitive inspections
(if applicable) in accordance with Table 2 of
this AD.
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12:39 Feb 08, 2006
Jkt 208001
Condition 2: Cracked Studbolts
(l) If any cracked studbolt is detected
during any ultrasonic inspection required by
paragraph (g) of this AD, before further flight,
do the actions specified in paragraph (m), (n),
or (o) of this AD.
Condition 2, Option 1: Removal,
Inspection(s), and Corrective Actions
(m) Remove any cracked upper and lower
studbolt (as applicable) of the inboard and
outboard hinge fittings, install any studbolt
identified in and in accordance with Table 2
of this AD, do the repetitive inspections (if
applicable) in accordance with Table 2 of this
AD, and do a detailed inspection for
corrosion of any remaining studbolts in
accordance with the service bulletin.
(1) If no corroded studbolt is found, before
further flight, do a magnetic particle
inspection for cracks in any remaining
studbolt in accordance with the service
bulletin. If any crack is found, before further
flight, install any studbolt identified in and
in accordance with Table 2 of this AD and
do the repetitive inspections (if applicable) in
accordance with Table 2 of this AD.
(2) If any corroded studbolt is found, before
further flight, install any studbolt identified
in and in accordance with Table 2 of this AD,
do the repetitive inspections (if applicable) in
accordance with Table 2 of this AD, and do
a magnetic particle inspection for cracks in
any remaining studbolt in accordance with
the service bulletin.
(i) If no cracked studbolt is found, before
further flight, install any studbolt identified
in and in accordance with Table 2 of this AD,
and do the repetitive inspections (if
applicable) in accordance with Table 2 of this
AD.
(ii) If any cracked studbolt is found, before
further flight, install any studbolt identified
in and in accordance with Table 2 of this AD,
and do the repetitive inspections (if
applicable) in accordance with Table 2 of this
AD.
Condition 2, Option 2: Replacement
(n) Replace all studbolts in accordance
with paragraph (j) of this AD.
Condition 2, Option 3: Removal, Inspections,
and Installation
(o) Remove any cracked studbolt, install
any studbolt identified in and in accordance
with Table 2 of this AD, do the repetitive
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Fmt 4700
Sfmt 4700
inspections (if applicable) in accordance with
Table 2 of this AD, and do a detailed
inspection for corrosion of any remaining
studbolt in accordance with the service
bulletin.
(1) If no corroded studbolt is found, before
further flight, do a magnetic particle
inspection for cracks in any remaining
studbolt in accordance with the service
bulletin, and change the protective treatment
of all remaining upper and lower studbolts
(as applicable) to give increased corrosion
protection in accordance with a method
approved by the Manager, Los Angeles ACO,
FAA. Accomplishing this change ends the
repetitive inspection requirements of
paragraph (i) of this AD.
(2) If any corroded studbolt is found, before
further flight, install any studbolt identified
in and in accordance with Table 2 of this AD,
do the repetitive inspections (if applicable) in
accordance with Table 2 of this AD, and do
a magnetic particle inspection for cracks in
any remaining studbolt in accordance with
the service bulletin.
(i) If no cracked studbolt is found, before
further flight, change the protective treatment
of all remaining studbolts to give increased
corrosion protection in accordance with a
method approved by the Manager, Los
Angeles ACO, FAA. Accomplishing this
change ends the repetitive inspection
requirements of paragraph (i) of this AD.
(ii) If any cracked studbolt is found, before
further flight, install any studbolt identified
in and in accordance with Table 2 of this AD,
and do the repetitive inspections (if
applicable) in accordance with Table 2 of this
AD.
Alternative Methods of Compliance
(AMOCs)
(p)(1) The Manager, Los Angeles 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.
Material Incorporated by Reference
(q) You must use the applicable service
bulletin in table 3 of this AD to perform the
actions that are required by this AD, unless
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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, Long Beach Division,
3855 Lakewood Boulevard, Long Beach,
California 90846, Attention: Data and Service
Management, Dept. C1–L5A (D800–0024), 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
Service Bulletin
Boeing Service Bulletin DC10–57–154.
Boeing Service Bulletin MD11–57–076.
Date
February 2, 2005.
February 2, 2005.
Dated: Issued in Renton, Washington, on
January 30, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 06–1148 Filed 2–8–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–23279; Directorate
Identifier 2005–NE–44–AD; Amendment 39–
14478; AD 2006–03–14]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
plc RB211 Trent 500 Series Turbofan
Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
cprice-sewell on PROD1PC66 with RULES
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for Rolls
Royce plc (RR) RB211 Trent 500 series
turbofan engines. This AD requires
initial and repetitive borescope
inspections of the high pressure-andintermediate pressure (HP–IP) turbine
oil vent tubes and bearing chambers for
coking and carbon buildup and
VerDate Aug<31>2005
12:39 Feb 08, 2006
Jkt 208001
replacing the vent tubes if necessary.
This AD results from a report of an
RB211 Trent 700 series engine that
experienced a disk shaft separation,
overspeed of the IP turbine rotor, and
multiple blade release of IP turbine
blades. Since the design arrangement in
the Trent 500 series engines is similar
to that of the Trent 700 series engines,
the same failure could occur in the
Trent 500 series engines. We are issuing
this AD to prevent internal oil fires
caused by coking and carbon buildup,
that could result in uncontained engine
failure and damage to the airplane.
DATES: Effective February 24, 2006. The
Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the
regulations as of February 24, 2006.
We must receive any comments on
this AD by April 10, 2006.
ADDRESSES: Use one of the following
addresses to comment on this AD:
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact Rolls-Royce plc, Technical
Publications, P.O. Box 31, Derby, DE24
8BJ, UK; telephone: 011–44–1332–
242424; fax: 011–44–1332–249936, for
the service information identified in this
AD.
FOR FURTHER INFORMATION CONTACT:
Christopher Spinney, Aerospace
Engineer, Engine Certification Office,
FAA, Engine and Propeller Directorate,
12 New England Executive Park,
Burlington, MA 01803–5299; telephone
(781) 238–7175; fax (781) 238–7199.
SUPPLEMENTARY INFORMATION: The Civil
Aviation Authority (CAA), which is the
airworthiness authority for the United
Kingdom (UK) recently notified us that
an unsafe condition might exist on RR
RB211 Trent 500 Series turbofan
engines. The CAA advises that a
previous service incident in a Trent 700
engine indicates that carbon restriction
in the vent tube can cause overpressurization of the HP–IP bearing
chamber leading to oil ejection from the
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
6673
rear of the chamber. If this oil spray
ignites, the fire can cause an IPT shaft
failure, leading to overspeed and
uncontained failure of the IPT disc.
Since the design arrangement in the
Trent 500 engines is similar to that of
the Trent 700 engines, the same failure
could occur in the Trent 500 series
engines. We are issuing this AD to
prevent internal oil fires caused by
coking and carbon buildup, that could
result in uncontained engine failure and
damage to the airplane.
Relevant Service Information
We have reviewed and approved the
technical contents of RR Alert Service
Bulletin (ASB) RB.211–72–AE836,
Revision 1, dated October 5, 2005. That
ASB describes procedures for initial and
repetitive borescope inspection and
assessment of the HP–IP turbine oil vent
tubes and bearing chamber. The CAA
classified this service bulletin as
mandatory and issued AD No. G–2005–
0029, dated October 4, 2005, in order to
ensure the airworthiness of these RR
Trent 500 series engines in the U.K.
Bilateral Airworthiness Agreement
These RB211 Trent 500 series
turbofan engines are manufactured in
the U.K. and are type certificated for
operation in the United States under the
provisions of section 21.29 of the
Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral
airworthiness agreement. Under this
bilateral airworthiness agreement, the
CAA kept the FAA informed of the
situation described above. We have
examined the findings of the CAA,
reviewed all available information, and
determined that AD action is necessary
for products of this type design that are
certificated for operation in the United
States.
FAA’s Determination and Requirements
of This AD
Although no airplanes that are
registered in the United States use these
engines, the possibility exists that the
engines could be used on airplanes that
are registered in the United States in the
future. The unsafe condition described
previously is likely to exist or develop
on other RR RB211 Trent 500 series
turbofan engines of the same type
design. This AD requires initial and
repetitive borescope inspections of the
HP–IP turbine bearing oil vent tubes and
bearing chambers for coking and carbon
buildup; and replacement of the tubes if
necessary.
We are issuing this AD to prevent
internal oil fires from coking and carbon
buildup that could cause uncontained
engine failure and damage to the
E:\FR\FM\09FER1.SGM
09FER1
Agencies
[Federal Register Volume 71, Number 27 (Thursday, February 9, 2006)]
[Rules and Regulations]
[Pages 6669-6673]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-1148]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22503; Directorate Identifier 2005-NM-062-AD;
Amendment 39-14477; AD 2006-03-13]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model DC-10-10, DC-
10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40,
DC-10-40F, MD-10-10F, MD-10-30F, MD-11, and MD-11F 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 McDonnell Douglas transport category airplanes. This AD
requires an initial ultrasonic inspection for cracks of the studbolts
of the inboard and outboard hinge fittings of the left and right
outboard flaps of the wings. Based on the inspection results, this AD
also requires doing repetitive ultrasonic inspections, replacing upper
and/or lower studbolts with new or serviceable studbolts, doing a
detailed inspection for corrosion of the upper studbolts, doing a
magnetic particle inspection for
[[Page 6670]]
cracks of studbolts, and changing the protection treatment; as
applicable. This AD results from reports of corrosion and failures of
the upper and lower studbolts of the outboard flaps inboard and
outboard hinge fittings. We are issuing this AD to prevent corrosion
and subsequent cracking of studbolts, which could result in failure of
the flap hinge fittings and their possible separation from the wing
rear spar, and consequent reduced controllability of the airplane.
DATES: This AD becomes effective March 16, 2006.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of March 16,
2006.
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, Long Beach Division, 3855
Lakewood Boulevard, Long Beach, California 90846, Attention: Data and
Service Management, Dept. C1-L5A (D800-0024), for service information
identified in this AD.
FOR FURTHER INFORMATION CONTACT: Maureen Moreland, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137;
telephone (562) 627-5238; fax (562) 627-5210.
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 McDonnell
Douglas Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-
10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, MD-10-30F, MD-11, and
MD-11F airplanes. That NPRM was published in the Federal Register on
September 22, 2005 (70 FR 55598). That NPRM proposed to require an
initial ultrasonic inspection for cracks of the studbolts of the
inboard and outboard hinge fittings of the left and right outboard
flaps of the wings. Based on the inspection results, that NPRM also
proposed to require doing repetitive ultrasonic inspections, replacing
upper and/or lower studbolts with new or serviceable studbolts, doing a
detailed inspection for corrosion of the upper studbolts, doing a
magnetic particle inspection for cracks of studbolts, and changing the
protection treatment; as applicable.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Request To Consider Parts Availability
One commenter requests that we consider parts availability before
setting an effective date for the AD. The commenter states that there
are no kits available to do the proposed replacement. The commenter
also states that most quantities of studbolts are minimal (less than 50
available) with additional orders coming in from suppliers in the first
half of 2006.
We agree to consider parts availability, but do not agree that
there is a shortage of parts. The AD specifies several options for
continued operation with existing studbolts that are found not to be
cracked. Options include installing new bolts with increased corrosion
protections; treating existing studbolts with corrosion protection in
accordance with a method approved by us; and replacing the studbolts
with equivalent studbolts with follow-on repetitive inspections.
In addition, the airplane manufacturer has informed us that they
have developed corrosion protection methodologies and will pursue
approval from us once the final rule is issued. We will support this
effort. The airplane manufacturer also has informed us that they are
scheduled to receive studbolts in March of 2006 to support the required
replacement of failed studbolts. For operators that initiate a program
to replace all the studbolts as terminating action, the airplane
manufacturer recommends placing a specific purchase order for the part
numbers and quantities of studbolts required, along with a time frame
that supports their replacement program.
In light of these findings, we have determined that no change to
the final rule is necessary.
Clarification of Alternative Method of Compliance (AMOC) Paragraph
We have revised this action to clarify the appropriate procedure
for notifying the principal inspector before using any approved AMOC on
any airplane to which the AMOC applies.
Clarification of Replacement
In paragraph (j)(4) of the NPRM, we inadvertently omitted the
reference to the service bulletin. We have revised that paragraph to
include the phrase ``in accordance with the service bulletin.''
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 change described previously.
We have determined that this change will neither increase the economic
burden on any operator nor increase the scope of the AD.
Costs of Compliance
There are about 594 airplanes of the affected design in the
worldwide fleet. This AD will affect about 297 U.S.-registered Model
DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10),
DC-10-40, DC-10-40F, MD-10-10F, and MD-10-30F airplanes; and 69 Model
MD-11 and -11F airplanes.
Estimated Costs for Required Actions
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work hours Average labor Parts Cost per registered Fleet cost
rate per hour airplane airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Initial ultrasonic inspection............. 16 $65 None........................ $1,040 366 $380,640
--------------------------------------------------------------------------------------------------------------------------------------------------------
[[Page 6671]]
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):
2006-03-13 McDonnell Douglas: Amendment 39-14477. Docket No. FAA-
2005-22503; Directorate Identifier 2005-NM-062-AD.
Effective Date
(a) This AD becomes effective March 16, 2006.
Affected ADs
(b) None.
Applicability
(c) This AD applies to McDonnell Douglas airplanes identified in
Table 1 of this AD, certificated in any category.
Table 1.--Applicability
------------------------------------------------------------------------
Model-- As identified in--
------------------------------------------------------------------------
(1) DC-10-10, DC-10-10F, DC-10-15, DC- Boeing Service Bulletin DC10-57-
10-30, DC-10-30F (KC-10A and KDC-10), 154, dated February 2, 2005.
DC-10-40, DC-10-40F, MD-10-10F and MD-
10-30F airplanes.
(2) MD-11 and MD-11F airplanes......... Boeing Service Bulletin MD11-57-
076, dated February 2, 2005.
------------------------------------------------------------------------
Unsafe Condition
(d) This AD was prompted by reports of corrosion and failures of
the upper and lower studbolts of the outboard flaps inboard and
outboard hinge fittings. We are issuing this AD to prevent corrosion
and subsequent cracking of studbolts, which could result in failure
of the flap hinge fittings and their possible separation from the
wing rear spar, and consequent reduced controllability 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.
Service Bulletins
(f) The term ``service bulletin,'' as used in this AD, means the
Accomplishment Instructions of the applicable service bulletin
listed in Table 1 of this AD.
Ultrasonic Inspection
(g) Do an ultrasonic inspection for cracks of the upper and
lower studbolts (upper studbolts only for Model MD-11 and -11F
airplanes) of the inboard and outboard hinge fittings of the left
and right outboard flaps of the wings, in accordance with the
service bulletin. Inspect within 72 months from the time the
studbolts were last replaced, or within 24 months after the
effective date of this AD, whichever occurs later.
Condition 1: No Cracked Studbolts
(h) If no cracked upper or lower studbolt is detected during any
ultrasonic inspection required by paragraph (g) of this AD, do the
actions specified in paragraph (i), (j), or (k) of this AD.
Condition 1, Option 1: Repetitive Inspections
(i) Repeat the ultrasonic inspection required by paragraph (g)
of this AD thereafter at intervals not to exceed 24 months, until
the action in paragraph (j)(1), (j)(2), (k)(1), (k)(2)(i), (o)(1),
or (o)(2)(i) of this AD is done.
Condition 1, Option 2: Replacement
(j) Within 72 months from the time the studbolts were last
replaced, or within 24 months after the effective date of this AD,
whichever occurs later, do any one of the replacements in Table 2 of
this AD. Thereafter, at the times specified in Table 2, repeat the
ultrasonic inspection required by paragraph (g) of this AD (if
applicable).
[[Page 6672]]
Table 2.--Replacement Parts
------------------------------------------------------------------------
And repeat the
Replace the upper and lower ultrasonic Accomplishing this
studbolts (as applicable) of inspection required replacement
the inboard and outboard by paragraph (g) of terminates--
hinge fittings with-- this AD thereafter--
------------------------------------------------------------------------
(1) New studbolts that have None................ The repetitive
increased corrosion inspection
protection in accordance requirements of
with the service bulletin. paragraph (i),
(j)(3), and (j)(4)
of this AD.
(2) Studbolts changed with None................ The repetitive
protective treatment in inspection
accordance with a method requirements of
approved by the Manager, paragraph (i),
Los Angeles Aircraft (j)(3), and (j)(4)
Certification (ACO), FAA. of this AD.
(3) Equivalent studbolts in At intervals not to None.
accordance with the service exceed 24 months.
bulletin.
(4) Kept serviceable At intervals not to None.
studbolts wet with sealant exceed 24 months.
in accordance with the
service bulletin.
------------------------------------------------------------------------
Condition 1, Option 3: Removal, Inspection(s), and Corrective Actions
(k) Within 72 months from the time the studbolts were last
replaced, or within 24 months after the effective date of this AD,
whichever occurs later, remove the upper and lower studbolts (as
applicable) of the inboard and outboard hinge fittings, and do a
detailed inspection for corrosion of the upper and lower studbolts
(as applicable), in accordance with the service bulletin.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
(1) If no corroded studbolt is found, before further flight,
change the protective treatment of all upper and lower studbolts (as
applicable) to give increased corrosion protection, in accordance
with a method approved by the Manager, Los Angeles ACO, FAA.
Accomplishing this change ends the repetitive inspection
requirements of paragraph (i) of this AD.
(2) If any corroded studbolt is found, before further flight,
install any studbolt identified in and in accordance with Table 2 of
this AD, thereafter do the repetitive inspections (if applicable) in
accordance with Table 2 of this AD, and do a magnetic particle
inspection for cracks in any remaining studbolt in accordance with
the service bulletin.
(i) If no cracked studbolt is found, before further flight,
change the protective treatment of all remaining studbolts to give
increased corrosion protection, in accordance with a method approved
by the Manager, Los Angeles ACO, FAA. Accomplishing this change ends
the repetitive inspection requirements of paragraph (i) of this AD.
(ii) If any cracked studbolt is found, before further flight,
install any studbolt identified in and in accordance with Table 2 of
this AD, and thereafter do the repetitive inspections (if
applicable) in accordance with Table 2 of this AD.
Condition 2: Cracked Studbolts
(l) If any cracked studbolt is detected during any ultrasonic
inspection required by paragraph (g) of this AD, before further
flight, do the actions specified in paragraph (m), (n), or (o) of
this AD.
Condition 2, Option 1: Removal, Inspection(s), and Corrective Actions
(m) Remove any cracked upper and lower studbolt (as applicable)
of the inboard and outboard hinge fittings, install any studbolt
identified in and in accordance with Table 2 of this AD, do the
repetitive inspections (if applicable) in accordance with Table 2 of
this AD, and do a detailed inspection for corrosion of any remaining
studbolts in accordance with the service bulletin.
(1) If no corroded studbolt is found, before further flight, do
a magnetic particle inspection for cracks in any remaining studbolt
in accordance with the service bulletin. If any crack is found,
before further flight, install any studbolt identified in and in
accordance with Table 2 of this AD and do the repetitive inspections
(if applicable) in accordance with Table 2 of this AD.
(2) If any corroded studbolt is found, before further flight,
install any studbolt identified in and in accordance with Table 2 of
this AD, do the repetitive inspections (if applicable) in accordance
with Table 2 of this AD, and do a magnetic particle inspection for
cracks in any remaining studbolt in accordance with the service
bulletin.
(i) If no cracked studbolt is found, before further flight,
install any studbolt identified in and in accordance with Table 2 of
this AD, and do the repetitive inspections (if applicable) in
accordance with Table 2 of this AD.
(ii) If any cracked studbolt is found, before further flight,
install any studbolt identified in and in accordance with Table 2 of
this AD, and do the repetitive inspections (if applicable) in
accordance with Table 2 of this AD.
Condition 2, Option 2: Replacement
(n) Replace all studbolts in accordance with paragraph (j) of
this AD.
Condition 2, Option 3: Removal, Inspections, and Installation
(o) Remove any cracked studbolt, install any studbolt identified
in and in accordance with Table 2 of this AD, do the repetitive
inspections (if applicable) in accordance with Table 2 of this AD,
and do a detailed inspection for corrosion of any remaining studbolt
in accordance with the service bulletin.
(1) If no corroded studbolt is found, before further flight, do
a magnetic particle inspection for cracks in any remaining studbolt
in accordance with the service bulletin, and change the protective
treatment of all remaining upper and lower studbolts (as applicable)
to give increased corrosion protection in accordance with a method
approved by the Manager, Los Angeles ACO, FAA. Accomplishing this
change ends the repetitive inspection requirements of paragraph (i)
of this AD.
(2) If any corroded studbolt is found, before further flight,
install any studbolt identified in and in accordance with Table 2 of
this AD, do the repetitive inspections (if applicable) in accordance
with Table 2 of this AD, and do a magnetic particle inspection for
cracks in any remaining studbolt in accordance with the service
bulletin.
(i) If no cracked studbolt is found, before further flight,
change the protective treatment of all remaining studbolts to give
increased corrosion protection in accordance with a method approved
by the Manager, Los Angeles ACO, FAA. Accomplishing this change ends
the repetitive inspection requirements of paragraph (i) of this AD.
(ii) If any cracked studbolt is found, before further flight,
install any studbolt identified in and in accordance with Table 2 of
this AD, and do the repetitive inspections (if applicable) in
accordance with Table 2 of this AD.
Alternative Methods of Compliance (AMOCs)
(p)(1) The Manager, Los Angeles 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.
Material Incorporated by Reference
(q) You must use the applicable service bulletin in table 3 of
this AD to perform the actions that are required by this AD, unless
[[Page 6673]]
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, Long Beach Division, 3855 Lakewood Boulevard,
Long Beach, California 90846, Attention: Data and Service
Management, Dept. C1-L5A (D800-0024), 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
------------------------------------------------------------------------
Service Bulletin Date
------------------------------------------------------------------------
Boeing Service Bulletin DC10-57-154....... February 2, 2005.
Boeing Service Bulletin MD11-57-076....... February 2, 2005.
------------------------------------------------------------------------
Dated: Issued in Renton, Washington, on January 30, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-1148 Filed 2-8-06; 8:45 am]
BILLING CODE 4910-13-P