[Federal Register Volume 77, Number 60 (Wednesday, March 28, 2012)]
[Proposed Rules]
[Pages 18719-18722]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-7386]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0327; Directorate Identifier 2011-NM-125-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede an existing airworthiness directive 
(AD) that applies to 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. The existing 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. The existing AD also requires, 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. Since we 
issued that AD, we have determined that additional actions are 
necessary to address the identified unsafe condition. This proposed AD 
would add airplanes to the applicability and retain the requirements of 
the existing AD. This proposed AD would also require, 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 corrective actions if necessary. We 
are proposing 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: We must receive comments on this proposed AD by May 14, 2012.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
    <bullet> Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed 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; email 
<a href="/cdn-cgi/l/email-protection#ceaabdabe0aca1abada1a38eaca1aba7a0a9e0ada1a3"><span class="__cf_email__" data-cfemail="d2b6a1b7fcb0bdb7b1bdbf92b0bdb7bbbcb5fcb1bdbf">[email protected]</span></a>; Internet https://www.myboeingfleet. You may 
review copies of the referenced service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
Washington. 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 proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

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: <a href="/cdn-cgi/l/email-protection#f0a3919d85959cdebc9595b0969191de979f86"><span class="__cf_email__" data-cfemail="4112202c34242d6f0d2424012720206f262e37">[email protected]</span></a>.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2012-0327; 
Directorate Identifier 2011-NM-125-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On December 17, 2009, we issued AD 2009-26-17, Amendment 39-16156 
(74 FR 69268, December 31, 2009), for certain Boeing Model DC-10-10, 
DC-

[[Page 18720]]

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 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. That AD 
also requires, for certain airplanes, repositioning or replacing two 
bonding straps, and doing a bonding-resistance check and an inspection 
to determine correct installation of certain bonding straps, and 
applicable corrective actions. That AD resulted from fuel system 
reviews conducted by the manufacturer. We issued that 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.

Actions Since Existing AD 2009-26-17, Amendment 39-16156 (74 FR 69268, 
December 31, 2009) Was Issued

    Since we issued AD 2009-26-17, Amendment 39-16156 (74 FR 69268, 
December 31, 2009), Boeing has issued new service information that 
specifies additional actions that are necessary to address the 
identified unsafe condition.

Relevant Service Information

    We reviewed Boeing Service Bulletin DC10-53-111, Revision 7, dated 
March 16, 2011, which makes minor corrections and adds part number 
substitutions.
    We also reviewed Boeing Service Bulletin DC10-53-109, Revision 8, 
dated March 10, 2011. This service information reinstates airplanes 
inadvertently omitted from the prior revision of this service 
information, and describes new additional actions. This service 
information describes:
    <bullet> New procedures for installing new braided bonding straps, 
depending on the airplane configuration.
    <bullet> Inspecting to determine if a certain strap is installed, 
and replacing with or installing a braided bonding strap if necessary.
    <bullet> Measuring the electrical resistance of the bonding straps.
    <bullet> Verifying that brackets have an acceptable fillet seal.
    <bullet> Corrective actions if necessary.
    Corrective actions include cleaning braided bonding straps, and 
repairing damaged or missing fillet seals.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would retain all requirements of AD 2009-26-17, 
Amendment 39-16156 (74 FR 69268, December 31, 2009). This proposed AD 
would also require accomplishing the additional actions specified in 
the service information described previously.

Changes to Existing AD 2009-26-17, Amendment 39-16156 (74 FR 69268, 
December 31, 2009)

    Since AD 2009-26-17, Amendment 39-16156 (74 FR 69268, December 31, 
2009), was issued, the AD format has been revised, and certain 
paragraphs have been rearranged. As a result, the service bulletins 
listed in Table 1 of AD 2009-26-17 are listed in paragraph (g)(2) of 
this proposed AD, and the service bulletins listed in Table 2 of AD 
2009-26-17 are listed in paragraph (g)(1) of this proposed AD.
    We also revised paragraph (h) of this proposed AD to describe the 
affected airplanes. Paragraph (h) of AD 2009-26-17, Amendment 39-16156 
(74 FR 69268, December 31, 2009), specifies that it is ``for airplanes 
with fuselage numbers not identified in Table 2 of this AD * * *.'' 
Since this proposed AD adds airplanes, we have revised that sentence as 
follows: ``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 * * *.''
    In addition, we have revised the wording of paragraph (k) of AD 
2009-26-17, Amendment 39-16156 (74 FR 69268, December 31, 2009); 
however, the intent of that paragraph has not changed.

Costs of Compliance

    We estimate that this proposed AD affects 208 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed 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 existing   hour = $1,445.
 AD 2009-26-17, Amendment 39-
 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
 proposed 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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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.

[[Page 18721]]

    For the reasons discussed above, I certify that the proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    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]

    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:

The Boeing Company: Docket No. FAA-2012-0327; Directorate Identifier 
2011-NM-125-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by May 14, 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 paragraph (c)(1) or (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. 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) Restatement of Requirements of AD 2006-16-03, Amendment 39-14703 
(71 FR 43962, August 3, 2006), With New Service Information: Install or 
Replace

    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, Amendment 39-16156 (74 FR 69268, December 31, 2009)), 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 
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) Restatement of Requirements of AD 2009-26-17, Amendment 39-16156 
(74 FR 69268, December 31, 2009), With New Service Information: Install 
or Replace

    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, Amendment 39-16156 (74 FR 69268, December 31, 
2009)), 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) Restatement of Requirements of AD 2009-26-17, Amendment 39-16156 
(74 FR 69268, December 31, 2009), With New Service Information: Strap 
Repositioning for Certain Airplanes

    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, Amendment 39-16156 (74 FR 
69268, December 31, 2009)), 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) Restatement of Requirements of AD 2009-26-17, Amendment 39-16156 
(74 FR 69268, December 31, 2009), With New Service Information: 
Inspection and Corrective Action for Certain Airplanes

    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, Amendment 39-16156 (74 FR 
69268, December 31, 2009)), whichever occurs first, do the actions 
specified in paragraphs (j)(1) and (j)(2) of this AD.

[[Page 18722]]

    (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.

(l) New Requirements of This AD: 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 7 
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 6 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.
    (ii) Measure the electrical resistance across each bonding joint 
of the 6 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 6 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: <a href="/cdn-cgi/l/email-protection#81d2e0ecf4e4edafcde4e4c1e7e0e0afe6eef7"><span class="__cf_email__" data-cfemail="0251636f77676e2c4e6767426463632c656d74">[email protected]</span></a>.
    (2) 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; email 
<a href="/cdn-cgi/l/email-protection#680c1b0d460a070d0b0705280a070d01060f460b0705"><span class="__cf_email__" data-cfemail="462235236824292325292b062429232f28216825292b">[email protected]</span></a>; Internet https://www.myboeingfleet.com. You 
may review copies of the referenced service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221.

    Issued in Renton, Washington, on March 16, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-7386 Filed 3-27-12; 8:45 am]
BILLING CODE 4910-13-P


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