[Federal Register Volume 77, Number 190 (Monday, October 1, 2012)]
[Rules and Regulations]
[Pages 59728-59732]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-23049]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-0327; Directorate Identifier 2011-NM-125-AD;
Amendment 39-17198; AD 2012-19-03]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for certain The Boeing Company 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. That AD currently requires installing or
replacing with improved parts, as applicable, the bonding straps
between the metallic frame of the fillet and the wing leading edge
ribs, on both the left and right sides of the airplane; and for certain
airplanes, repositioning or replacing two bonding straps, doing a
bonding-resistance check and an inspection to determine correct
installation of certain bonding straps, and applicable corrective
actions. This new AD adds airplanes to the applicability and, depending
on the airplane configuration, requires installing new braided bonding
straps, inspecting to determine if a certain strap is installed and
replacing with or installing a braided bonding strap if necessary,
measuring the electrical resistance of the bonding straps, verifying
that brackets have an acceptable fillet seal, and doing corrective
actions if necessary. This AD
[[Page 59729]]
was prompted by fuel system reviews conducted by the manufacturer, and
our determination that additional actions are necessary to address the
identified unsafe condition. We are issuing this AD to reduce the
potential of ignition sources inside fuel tanks in the event of a
severe lightning strike, which, in combination with flammable fuel
vapors, could result in fuel tank explosions and consequent loss of the
airplane.
DATES: This AD is effective November 5, 2012.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of November 5,
2012.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
February 4, 2010 (74 FR 69268, December 31, 2009).
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD of September
7, 2006 (71 FR 43962, August 3, 2006).
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
3855 Lakewood Boulevard, MC D800-0019, Long Beach, California 90846-
0001; telephone 206-544-5000, extension 2; fax 206-766-5683; Internet
https://www.myboeingfleet. You may review copies of the referenced
service information at the FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For information on the availability of
this material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at http://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 (phone: 800-647-5527) is 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: Samuel Lee, Aerospace Engineer,
Propulsion Branch, ANM-140L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137;
phone: 562-627-5262; fax: 562-627-5210; email: [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2009-26-17, Amendment 39-16156 (74 FR 69268,
December 31, 2009). That AD applies to the specified products. The NPRM
published in the Federal Register on March 28, 2012 (77 FR 18719). That
NPRM proposed to continue to require installing or replacing with
improved parts, as applicable, the bonding straps between the metallic
frame of the fillet and the wing leading edge ribs, on both the left
and right sides of the airplane. That NPRM also proposed to continue to
require, for certain airplanes, repositioning or replacing two bonding
straps, doing a bonding-resistance check and an inspection to determine
correct installation of certain bonding straps, and applicable
corrective actions. That NPRM also proposed to add airplanes to the
applicability, and depending on the airplane configuration, installing
new braided bonding straps, inspecting to determine if a certain strap
is installed and replacing with or installing a braided bonding strap
if necessary, measuring the electrical resistance of the bonding
straps, verifying that brackets have an acceptable fillet seal, and
doing corrective actions if necessary.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
(77 FR 18719, March 28, 2012) and the FAA's response to each comment.
Request To Add Credit for Previous Actions
FedEx requested that previous actions accomplished on 51 of its
airplanes using Boeing Service Bulletin DC10-53-111, Revision 4, dated
September 21, 2006; or Boeing Service Bulletin DC10-53-111, Revision 7,
dated March 16, 2011; be acceptable as terminating action for the
actions specified in paragraph (j) of the NPRM (77 FR 18719, March 28,
2012).
We partially agree. We agree that the actions are acceptable, but
do not agree to change the AD. We disagree that credit for previous
actions should be added to the AD. Paragraphs (m)(3) and (m)(4) of this
AD already allow previous accomplishment of the actions specified in
paragraphs (g), (h), (i), and (j) of this AD, if those actions were
done using alternative methods of compliance (AMOCs) approved in
accordance with AD 2006-16-03, Amendment 39-14703 (71 FR 43962, August
3, 2006); and AD 2009-26-17, Amendment 39-16156 (74 FR 69268, December
31, 2009). Boeing Service Bulletin DC10-53-111, Revision 4, dated
September 21, 2006, states that it is approved as an AMOC for AD 2006-
16-03. We have not changed the final rule in this regard.
Request To Combine Paragraphs
FedEx suggested that paragraphs (l)(3) and (l)(4) of the NPRM (77
FR 18719, March 28, 2012) be combined since they state the same thing.
We do not agree to combine paragraphs (l)(3) and (l)(4) of this AD,
because those paragraphs state different requirements for different
airplanes. We have not changed the final rule in this regard.
Request To Correct Effectivity
FedEx stated that Boeing Service Bulletin DC10-53-111, Revision 7,
dated March 16, 2011, incorrectly specifies that the reason for the
revision was to add fuselage 317 to the effectivity of that service
bulletin. FedEx stated that fuselage 317 was not and does not need to
be added to the effectivity of that service bulletin, because fuselage
317 is in the effectivity of Boeing Service Bulletin DC10-53-109,
Revision 8, dated March 10, 2011.
We infer that FedEx is requesting that Boeing Service Bulletin
DC10-53-111, Revision 7, dated March 16, 2011, be revised to correct
the discrepancy in the stated reason for the revision of that service
bulletin. We do not agree. Boeing issued Service Bulletin Information
Notice DC10-53-111 IN 02, dated June 17, 2011, to clarify that fuselage
317 was not added to the effectivity of Boeing Service Bulletin DC10-
53-111, Revision 7, dated March 16, 2011. No change to this final rule
is necessary in this regard.
Explanation of Additional Changes Made To This AD
We have revised certain headings throughout this AD.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD as proposed except for minor editorial changes. We have
determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (77 FR 18719, March 28, 2012) for correcting the unsafe condition;
and
[[Page 59730]]
Do not add any additional burden upon the public than was
already proposed in the NPRM (77 FR 18719, March 28, 2012).
Costs of Compliance
We estimate that this AD affects 208 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Installation, inspection, and Up to 17 work- Up to $4,169...... Up to $5,614...... Up to $1,167,712.
resistance measurement hours x $85 per
[retained actions from hour = $1,445.
existing AD 2009-26-17,
Amendment 39[dash]16156 (74 FR
69268, December 31, 2009)].
Installation, inspection, and Up to 16 work- Up to $33,230..... Up to $34,590..... Up to $7,194,720.
resistance measurement [new hours x $85 per
action]. hour = $1,360.
----------------------------------------------------------------------------------------------------------------
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),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
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:
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 FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2009-26-17, Amendment 39-16156 (74 FR 69268, December 31, 2009), and
adding the following new AD:
2012-19-03 The Boeing Company: Amendment 39-17198; Docket No. FAA-
2012-0327; Directorate Identifier 2011-NM-125-AD.
(a) Effective Date
This airworthiness directive (AD) is effective November 5, 2012.
(b) Affected ADs
This AD supersedes AD 2009-26-17, Amendment 39-16156 (74 FR
69268, December 31, 2009).
(c) Applicability
This AD applies to The Boeing Company Model DC-10-10, DC-10-10F,
DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, and DC-
10-40F airplanes, and Model MD-10-10F and MD-10-30F airplanes that
have been converted from Model DC-10 series airplanes; certificated
in any category; as identified in paragraphs (c)(1) and (c)(2) of
this AD, as applicable.
(1) Boeing Service Bulletin DC10-53-109, Revision 8, dated March
10, 2011 (for airplanes with extended wing-to-fuselage fillets).
(2) Boeing Service Bulletin DC10-53-111, Revision 7, dated March
16, 2011 (for airplanes with conventional wing-to-fuselage fillets).
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by fuel system reviews conducted by the
manufacturer, and our determination that additional actions are
necessary to address the identified unsafe condition. We are issuing
this AD to reduce the potential of ignition sources inside fuel
tanks in the event of a severe lightning strike, which, in
combination with flammable fuel vapors, could result in fuel tank
explosions and consequent loss of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Requirements for Installation or Replacement for Certain
Airplanes, With New Service Information
This paragraph restates the installation or replacement
requirements of paragraph (g) of AD 2009-26-17, Amendment 39-16156
(74 FR 69268, December 31, 2009), with new service information. For
airplanes with manufacturer's fuselage numbers identified in the
applicable service bulletin listed in paragraph (g)(1) of this AD:
Within 7,500 flight hours or 60 months after September 7, 2006 (the
effective date of AD 2006-16-03, Amendment 39-14703 (71 FR 43962,
August 3, 2006)), whichever occurs earlier: Install or replace with
improved parts, as applicable, the bonding straps between the
metallic frame of the fillet and the wing leading edge ribs, on both
the left and right sides of the airplane, in accordance with the
Accomplishment Instructions of the applicable service bulletin
identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. After
February 4, 2010 (the effective date of AD 2009-26-17), use the
applicable service bulletin identified in paragraph (g)(2) or (g)(3)
of this AD. After the effective date of this AD, use only the
applicable service bulletin identified in paragraph (g)(3) of this
[[Page 59731]]
AD to do the actions required by this paragraph.
(1) McDonnell Douglas DC-10 Service Bulletin 53-109, Revision 4,
dated October 7, 1992 (for airplanes with extended wing-to-fuselage
fillets); or McDonnell Douglas DC-10 Service Bulletin 53-111,
Revision 3, dated August 24, 1992 (for airplanes with conventional
wing-to-fuselage fillets).
(2) Boeing Service Bulletin DC10-53-109, Revision 7, dated March
3, 2009 (for airplanes with extended wing-to-fuselage fillets); or
Boeing Service Bulletin DC10-53-111, Revision 6, dated March 3, 2009
(for airplanes with conventional wing-to-fuselage fillets).
(3) Boeing Service Bulletin DC10-53-109, Revision 8, dated March
10, 2011 (for airplanes with extended wing-to-fuselage fillets); or
Boeing Service Bulletin
DC10-53-111, Revision 7, dated March 16, 2011 (for airplanes
with conventional wing-to-fuselage fillets).
(h) Retained Requirements for Installation or Replacement for Certain
Other Airplanes, With New Service Information
This paragraph restates the installation or replacement
requirements of paragraph (h) of AD 2009-26-17, Amendment 39-16156
(74 FR 69268, December 31, 2009), with new service information. For
airplanes with fuselage numbers identified in the applicable service
bulletin listed in paragraph (g)(2) of this AD that are not also
identified in the applicable service bulletin listed in paragraph
(g)(1) of this AD, except for airplanes identified in paragraph (i)
or (j) of this AD: Within 7,500 flight hours or 60 months, whichever
occurs first after February 4, 2010 (the effective date of AD 2009-
26-17), install or replace with improved parts, as applicable, the
bonding straps between the metallic frame of the fillet and the wing
leading edge ribs, on both the left and right sides of the airplane.
Do the actions in accordance with the Accomplishment Instructions of
the applicable service bulletin identified in paragraph (g)(2) or
(g)(3) of this AD. After the effective date of this AD, use only the
applicable service bulletin identified in paragraph (g)(3) of this
AD to do the actions required by this paragraph.
(i) Retained Requirements for Strap Repositioning for Certain
Airplanes, With New Service Information
This paragraph restates the strap repositioning requirements of
paragraph (i) of AD 2009-26-17, Amendment 39-16156 (74 FR 69268,
December 31, 2009), with new service information. For Group 1-4,
Configuration 3 airplanes, as identified in Boeing Service Bulletin
DC10-53-109, Revision 7, dated March 3, 2009: Within 7,500 flight
hours or 60 months after February 4, 2010 (the effective date of AD
2009-26-17), whichever occurs first, do the actions specified in
paragraphs (i)(1) and (i)(2) of this AD.
(1) Remove two braided bonding straps and install two longer
braided bonding straps between the metallic frame of the fillet and
the wing leading edge ribs, in accordance with the Accomplishment
Instructions of Boeing Service Bulletin DC10-53-109, Revision 7,
dated March 3, 2009; or Boeing Service Bulletin DC10-53-109,
Revision 8, dated March 10, 2011. After the effective date of this
AD, use only Boeing Service Bulletin DC10-53-109, Revision 8, dated
March 10, 2011, to do the actions required by this paragraph.
(2) Measure the resistance of the previously installed bonding
straps and, before further flight, do all applicable corrective
actions, in accordance with the Accomplishment Instructions of
Boeing Service Bulletin DC10-53-109, Revision 7, dated March 3,
2009; or Boeing Service Bulletin DC10-53-109, Revision 8, dated
March 10, 2011. After the effective date of this AD, use only Boeing
Service Bulletin DC10-53-109, Revision 8, dated March 10, 2011, to
do the actions required by this paragraph.
(j) Retained Requirements for Inspection and Corrective Action for
Certain Airplanes, With New Service Information
This paragraph restates the inspection requirements of paragraph
(j) of AD 2009-26-17, Amendment 39-16156 (74 FR 69268, December 31,
2009), with new service information. For Group 1-2, Configuration 2
airplanes, as identified in Boeing Service Bulletin DC10-53-111,
Revision 6, dated March 3, 2009: Within 7,500 flight hours or 60
months after February 4, 2010 (the effective date of AD 2009-26-17),
whichever occurs first, do the actions specified in paragraphs
(j)(1) and (j)(2) of this AD.
(1) Do a general visual inspection to verify correct
installation of the braided bonding straps (one left-hand wing and
one right-hand wing) as shown in Sheet 7 in Figure 3 of Boeing
Service Bulletin DC10-53-111, Revision 6, dated March 3, 2009, or
Boeing Service Bulletin DC10-53-111, Revision 7, dated March 16,
2011; and, before further flight, do all applicable corrective
actions, in accordance with the Accomplishment Instructions of
Boeing Service Bulletin DC10-53-111, Revision 6, dated March 3,
2009, or Boeing Service Bulletin DC10-53-111, Revision 7, dated
March 16, 2011. After the effective date of this AD, use only Boeing
Service Bulletin DC10-53-111, Revision 7, dated March 16, 2011, to
do the actions required by this paragraph.
(2) Measure the resistance of the previously installed bonding
straps and, before further flight, do all applicable corrective
actions, in accordance with the Accomplishment Instructions of
Boeing Service Bulletin DC10-53-111, Revision 6, dated March 3,
2009; or Boeing Service Bulletin DC10-53-111, Revision 7, dated
March 16, 2011. After the effective date of this AD, use only Boeing
Service Bulletin DC10-53-111, Revision 7, dated March 16, 2011, to
do the actions required by this paragraph.
(k) Credit for Previous Actions
This paragraph provides credit for the actions required by
paragraphs (g), (h), (i), and (j) this AD, if those actions were
accomplished before February 4, 2010 (the effective date of AD 2009-
26-17, Amendment 39-16156 (74 FR 69268, December 31, 2009)), using
Boeing Service Bulletin DC10-53-111, Revision 5, dated March 19,
2008; or Boeing Service Bulletin DC10-53-109, Revision 6, dated July
10, 2008; as applicable; which are not incorporated by reference.
(l) New Installation and Corrective Actions for Certain Airplanes
Within 7,500 flight hours or 60 months after the effective date
of this AD, whichever comes first: Do the applicable actions
specified in paragraphs (l)(1) through (l)(6) of this AD, as
applicable.
(1) For Group 1-4, Configurations 1 and 2 airplanes, as
identified in Boeing Service Bulletin DC10-53-109, Revision 8, dated
March 10, 2011, except airplanes that are identified in paragraph
(g) of this AD: Remove any solid metal bonding straps and install
seven new braided bonding straps, in accordance with the
Accomplishment Instructions of Boeing Service Bulletin DC10-53-109,
Revision 8, dated March 10, 2011.
(2) For Group 1-4, Configurations 1 and 2 airplanes, as
identified in Boeing Service Bulletin DC10-53-109, Revision 8, dated
March 10, 2011, that are also identified in paragraph (g) of this
AD: Remove any solid metal bonding straps not removed during the
actions required by paragraph (g) of this AD and install a 7th new
braided bonding strap (paragraph (g) of this AD requires installing
6 straps), in accordance with the Accomplishment Instructions of
Boeing Service Bulletin DC10-53-109, Revision 8, dated March 10,
2011.
(3) For Group 1-4, Configuration 3 airplanes, as identified in
Boeing Service Bulletin DC10-53-109, Revision 8, dated March 10,
2011, except airplanes identified in paragraph (i) of this AD: Do
the actions specified in paragraphs (l)(3)(i) and (l)(3)(ii) of this
AD.
(i) Replace one strap with new braided bonding strap, inspect to
determine the existence of an installed solid metal bonding strap
and replace any missing strap and any solid metal bonding strap with
a new braided bonding strap, in accordance with the Accomplishment
Instructions of Boeing Service Bulletin DC10-53-109, Revision 8,
dated March 10, 2011.
(ii) Measure the electrical resistance across each bonding joint
of the six previously-installed braided strap assemblies and verify
that brackets have an acceptable fillet seal, and do all applicable
corrective actions, in accordance with the Accomplishment
Instructions of Boeing Service Bulletin DC10-53-109, Revision 8,
dated March 10, 2011. Do all applicable corrective actions before
further flight.
(4) For Group 1-4, Configuration 3 airplanes, as identified in
Boeing Service Bulletin DC10-53-109, Revision 8, dated March 10,
2011, that are also identified in paragraph (i) of this AD: Do the
actions specified in paragraphs (l)(4)(i) and (l)(4)(ii) of this AD.
(i) Inspect to determine the existence of an installed solid
metal bonding strap and replace any missing strap and any solid
metal bonding strap with a new braided bonding strap, in accordance
with the Accomplishment Instructions of Boeing Service Bulletin
DC10-53-109, Revision 8, dated March 10, 2011.
[[Page 59732]]
(ii) Measure the electrical resistance across each bonding joint
of the six previously-installed braided strap assemblies and verify
that brackets have an acceptable fillet seal, and do all applicable
corrective actions, in accordance with the Accomplishment
Instructions of Boeing Service Bulletin DC10-53-109, Revision 8,
dated March 10, 2011. Do all applicable corrective actions before
further flight.
(5) For Group 1-4, Configuration 4 airplanes, as identified in
Boeing Service Bulletin DC10-53-109, Revision 8, dated March 10,
2011: Do the actions specified in paragraphs (l)(5)(i) and
(l)(5)(ii) of this AD.
(i) Inspect to determine the existence of an installed solid
metal bonding strap, and replace any missing strap and any solid
metal bonding strap with a new braided bonding strap, in accordance
with the Accomplishment Instructions of Boeing Service Bulletin
DC10-53-109, Revision 8, dated March 10, 2011.
(ii) Measure the electrical resistance across each bonding joint
of the six previously-installed braided strap assemblies and verify
that brackets have an acceptable fillet seal, and do all applicable
corrective actions, in accordance with the Accomplishment
Instructions of Boeing Service Bulletin DC10-53-109, Revision 8,
dated March 10, 2011. Do all applicable corrective actions before
further flight.
(6) For Group 1-4, Configuration 5 airplanes, as identified in
Boeing Service Bulletin DC10-53-109, Revision 8, dated March 10,
2011: Inspect to determine the existence of an installed solid metal
bonding strap, and replace any missing strap and any solid metal
bonding strap with a new braided bonding strap, in accordance with
the Accomplishment Instructions of Boeing Service Bulletin DC10-53-
109, Revision 8, dated March 10, 2011.
(m) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles Aircraft Certification Office
(ACO), FAA, has the authority to approve AMOCs for this AD, if
requested using the procedures found in 14 CFR 39.19. In accordance
with 14 CFR 39.19, send your request to your principal inspector or
local Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in the Related Information
section of this AD.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) AMOCs approved previously in accordance with AD 2006-16-03,
Amendment 39-14703 (71 FR 43962, August 3, 2006), are approved as
AMOCs for the corresponding provisions of paragraphs (g), (h), (i),
and (j) of this AD.
(4) AMOCs approved previously in accordance with AD 2009-26-17,
Amendment 39-16156 (74 FR 69268, December 31, 2009), are approved as
AMOCs for the corresponding provisions of paragraphs (g), (h), (i),
and (j) of this AD.
(n) Related Information
(1) For more information about this AD, contact Samuel Lee,
Aerospace Engineer, Propulsion Branch, ANM-140L, FAA, Los Angeles
Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood,
California 90712-4137; phone: 562-627-5262; fax: 562-627-5210;
email: [email protected].
(2) For service information specified in this AD that is not
incorporated by reference, contact Boeing Commercial Airplanes,
Attention: Data & Services Management, 3855 Lakewood Boulevard, MC
D800-0019, Long Beach, California 90846-0001; telephone 206-544-
5000, extension 2; fax 206-766-5683; Internet https://www.myboeingfleet.
(o) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(3) The following service information was approved for IBR on
November 5, 2012.
(i) Boeing Service Bulletin DC10-53-109, Revision 8, dated March
10, 2011.
(ii) Boeing Service Bulletin DC10-53-111, Revision 7, dated
March 16, 2011.
(4) The following service information was approved for IBR on
February 4, 2010 (74 FR 69268, December 31, 2009).
(i) Boeing Service Bulletin DC10-53-109, Revision 7, dated March
3, 2009.
(ii) Boeing Service Bulletin DC10-53-111, Revision 6, dated
March 3, 2009.
(5) The following service information was approved for IBR on
September 7, 2006 (71 FR 43962, August 3, 2006).
(i) McDonnell Douglas DC-10 Service Bulletin 53-109, Revision 4,
dated October 7, 1992.
(ii) McDonnell Douglas DC-10 Service Bulletin 53-111, Revision
3, dated August 24, 1992.
(6) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
3855 Lakewood Boulevard, MC D800-0019, Long Beach, California 90846-
0001; telephone 206-544-5000, extension 2; fax 206-766-5683;
Internet https://www.myboeingfleet.
(7) You may review copies of the referenced service information
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the availability of this material at
the FAA, call 425-227-1221.
(8) You may also review copies of the service information that
is incorporated by reference 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: http://www.archives.gov/federal-register/cfr/ibr_locations.html.
Issued in Renton, Washington, on September 11, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-23049 Filed 9-28-12; 8:45 am]
BILLING CODE 4910-13-P