Document ID: FAA-2007-0186-0008
Agency: faa
Document Type: Rule
Title: 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, and MD-10-30F Airplanes
Posted Date: 2009-09-01T04:00Z

[Federal Register: September 1, 2009 (Volume 74, Number 168)]
[Proposed Rules]               
[Page 45135-45139]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr01se09-14]                         

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0186; Directorate Identifier 2007-NM-226-AD]
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, and MD-10-30F Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of 
comment period.

-----------------------------------------------------------------------

SUMMARY: We are revising an earlier proposed airworthiness directive 
(AD) for 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, and MD-10-30F airplanes. That action (the first supplemental NPRM) 
would have superseded an existing AD that currently requires installing 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 first 
supplemental NPRM proposed to add a requirement to reposition or 
replace two bonding straps for certain airplanes. This action resulted 
from fuel system reviews conducted by the manufacturer. This second 
supplemental NPRM would add, for certain airplanes, a bonding-
resistance check and an inspection to determine correct installation of 
certain bonding straps, and applicable corrective actions. We are 
proposing this second supplemental NPRM 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 supplemental NPRM by September 
28, 2009.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     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.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, 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; e-mail 
dse.boecom@boeing.com; 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 or 425-227-1152.

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 (telephone 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; 
telephone (562) 627-5262; fax (562) 627-5210.

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-2007-0186; 
Directorate Identifier 2007-NM-226-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

    We issued a notice of proposed rulemaking (NPRM) (the ``first 
supplemental NPRM'') to amend 14 CFR part 39 to include an 
airworthiness directive (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, and MD-10-30F 
airplanes. The first supplemental NPRM was published in the Federal 
Register on November 26, 2008 (73 FR 71957).
    The first supplemental NPRM would have superseded an existing AD 
that 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 first supplemental NPRM proposed to add a requirement to 
reposition or replace two bonding straps for certain airplanes.

Actions Since First Supplemental NPRM Was Issued

    Since we issued the first supplemental NPRM, Boeing has issued 
Service Bulletin DC10-53-109, Revision 7, dated March 3, 2009; and 
Service Bulletin DC10-53-111, Revision 6, dated March 3, 2009. We cited 
Boeing Service Bulletin DC10-53-109, Revision 6, dated July 10, 2008; 
and Boeing Service Bulletin DC10-53-111, Revision 5, dated March 19, 
2008; in the first supplemental NPRM. The newly revised service 
bulletins contain the same procedures as the earlier revisions along 
with the following changes:
     Boeing Service Bulletin DC10-53-109, Revision 7, dated 
March 3, 2009, provides instructions to measure the electrical 
resistance of certain previously installed braided bonding straps and 
correct any failed resistance checks. The corrective action includes 
cleaning and installing the braided bonding strap assembly.
     Boeing Service Bulletin DC10-53-111, Revision 6, dated 
March 3, 2009, incorporates comments from operators

[[Page 45136]]

to clarify service bulletin instructions, including instructions for 
Group 1-2 airplanes, Configuration 2, to check the electrical 
resistance for bonding straps previously installed and correct any 
failed resistance checks. The corrective action includes cleaning and 
installing the braided bonding strap assembly. This service bulletin 
also includes an inspection to determine correct installation of 
braided bonding straps, and corrective action if necessary, for Group 
1-2 airplanes, Configuration 2. The corrective action is repositioning 
braided bonding straps and replacing fasteners.
    We have also approved the revised service bulletins as alternative 
methods of compliance (AMOCs) for the requirements of AD 2006-16-03.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comments received from the sole commenter, 
FedEx Express (FedEx).

Support for the NPRM

    FedEx applauds the FAA's decision to include ``AMOCs approved 
previously in accordance with AD 2006-16-03 * * * as AMOCs for the 
corresponding provisions of this AD.'' This statement allows FedEx to 
use its previously obtained AMOC, dated May 24, 2007, for compliance 
with the bulk of the proposed requirements, without the need for 
additional FAA approval. Any additional work required by the AD can be 
incorporated into FedEx's existing modification program using the AD as 
approval.

Request To Provide Additional Information

    FedEx requests that the section of the first supplemental NPRM 
titled ``Actions Since Original NPRM Was Issued'' include the following 
statement: ``[Boeing] Service Bulletin DC10-53-109, Revision 5, now 
includes an action to reposition two bonding straps by using new 
bonding straps that are less susceptible to cracking.'' FedEx notes 
that while this statement comes directly from the service bulletin 
section titled ``Reason for Revision,'' an examination of the changes 
to Boeing Service Bulletin DC10-53-109, Revision 5, dated March 19, 
2008, indicates that the straps in question, which were installed 
according to McDonnell Douglas DC-10 Service Bulletin 53-109, Revision 
4, dated October 7, 1992, are identical to the straps that replace them 
in Revision 5, except the replacement straps are 2 inches longer. 
Revision 6, dated July 10, 2008, of this service bulletin corrects the 
previous statement in the ``Reason'' section as follows: ``Revision 5 
was sent to incorporate engineering released subsequent to Revision 4 
of this service bulletin, which replaces an existing braided bonding 
strap (each side) with a new longer braided bonding strap that is less 
susceptible to chafing structure.''
    To avoid confusion, FedEx requests that we revise corresponding 
language in the AD to something similar to the following: ``[Boeing] 
Service Bulletin DC10-53-109, Revision 5, now includes an action to 
remove and replace two bonding straps installed via Revision 4 of the 
service bulletin with longer bonding straps.''
    We acknowledge FedEx's concern that this language may be confusing. 
However, the section of the AD preamble referenced by the commenter 
does not appear in this second supplemental NPRM. In addition, as 
stated previously, this second supplemental NPRM refers to Revision 7 
of Boeing Service Bulletin DC10-53-109, dated March 3, 2009, which 
contains the correct information in regard to this issue.

Request To Change ``Reason for Revision''

    FedEx requests that we revise the reason for using Boeing Service 
Bulletin DC10-53-109, Revision 6, dated July 10, 2008, in the first 
supplemental NPRM to read ``Revision 6 of Service Bulletin DC10-53-109 
provides a faster and easier method of replacing the two bonding straps 
that require replacement per Revision 5, and corrects some part number 
errors.'' FedEx also suggests that we revise the reason for using 
Boeing Service Bulletin DC10-53-111, Revision 5, dated March 19, 2008, 
as noted in the first supplemental NPRM, to read ``In addition to the 
effectivity correction, Revision 5 of Service Bulletin DC10-53-111 
requires the repositioning of two braided bonding straps installed on 
certain aircraft configuration via Revision 4 and all configurations 
via Service Bulletin revisions released prior to Revision 4.''
    We acknowledge FedEx's suggestions that the prior revisions of the 
service bulletins need to be clarified. However, the section of the AD 
preamble referenced by the commenter does not appear in this second 
supplemental NPRM. In addition, this second supplemental NPRM refers to 
Boeing Service Bulletin DC10-53-109, Revision 7, dated March 3, 2009; 
and Boeing Service Bulletin DC10-53-111, Revision 6, dated March 3, 
2009; which contain the correct information in regard to this issue.

Request To Revise Paragraph (h) of the First Supplemental NPRM

    FedEx requests that we revise paragraph (h) of the first 
supplemental NPRM to indicate that the action is to ``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 lieu of ``reposition two bonding straps.''
    We concur with FedEx, and the requested changes in paragraph (h) of 
the first supplemental NPRM are incorporated in the new reidentified 
paragraph (i)(1) of this second supplemental NPRM.
    In addition, FedEx believes that additional work is required for 
all airplanes previously modified in accordance with McDonnell Douglas 
DC-10 Service Bulletin 53-109, Revision 4, dated October 7, 1992.
    We agree with FedEx's request to provide clarification. Airplanes 
that were modified in accordance with McDonnell Douglas DC-10 Service 
Bulletin 53-109, Revision 4, dated October 7, 1992, also require an 
electrical resistance measurement of previously installed braided 
bonding straps to be in compliance with the proposed requirements of 
this second supplemental NPRM. Revision 7 of McDonnell Douglas DC-10 
Service Bulletin 53-109, dated March 3, 2009, clarifies the additional 
work required. We have revised paragraph (h) of the first supplemental 
NPRM (now paragraph (i) of this second supplmenetal NPRM) to specify 
the additional work required and that the additional work be 
accomplished in accordance with McDonnell Douglas DC-10 Service 
Bulletin 53-109, Revision 7, dated March 3, 2009.

Request To Clarify Procedures in Service Bulletin DC10-53-111, Revision 
5

    FedEx notes the following issues in Boeing Service Bulletin DC10-
53-111, Revision 5, dated March 19, 2008:
     In Figure 3, the requirement to remove and install all 
strap brackets should be removed. Only require a conductivity check of 
the previously installed strap (with the exception of the single strap 
that will need to be relocated) with any additional rework based on the 
results of the conductivity check. Also include the strap to fillet 
seal and encapsulate with sealant all strap attach points.
     The groups and configurations callouts should be revised 
to distinguish airplanes that did or did not receive metal bonding 
straps in production and distinguish those on which a previous

[[Page 45137]]

version of Boeing Service Bulletin DC10-53-111 was or was not done.
     The fastener pattern in Figure 1 should be corrected by 
removing the middle rivet of the three rivets indicated by ``2'' in the 
figure and the rivet to the left of those three rivets. This would 
leave the figure with six evenly spaced rivets on the edge of the 
stiffener that receives the installation. It also makes the figure 
match the work instruction.
     The compliance section should be revised so that steps 6 
through 13 of Figure 3 of Boeing Service Bulletin DC10-53-111, Revision 
5, dated March 19, 2008, must be done on all airplanes that have been 
modified per Figures 1 or 2 of Boeing Service Bulletin DC10-53-111, 
Revision 4, dated September 21, 2006.
    We infer that FedEx wants us to revise this second supplemental 
NPRM to provide the correct information. We agree. As stated 
previously, this second supplemental NPRM refers to Boeing Service 
Bulletin DC10-53-111, Revision 6, dated March 3, 2009, which contains 
the correct information in regard to these issues.

Request To Clarify Procedures in Service Bulletin DC10-53-109

    FedEx requests the following clarifications of configurations and 
electrical bonding requirements in Boeing Service Bulletin DC10-53-109, 
Revision 6, dated July 10, 2008:
     Configuration 3 should apply only to airplanes previously 
accomplished per Boeing Service Bulletin DC10-53-109, Revision 5, dated 
March 19, 2008, instead of McDonnell Douglas DC-10 Service Bulletin 53-
109, Revision 4, dated October 7, 1992.
     Configurations accomplished in accordance with McDonnell 
Douglas DC-10 Service Bulletin 53-109, Revision 1, dated August 14, 
1981; McDonnell Douglas DC-10 Service Bulletin 53-109, Revision 2, 
dated October 28, 1983; McDonnell Douglas DC-10 Service Bulletin 53-
109, Revision 3, dated November 14, 1986; and McDonnell Douglas DC-10 
Service Bulletin 53-109, Revision 4, dated October 7, 1992; should each 
have their own specific configuration.
    All previous braided straps are removed and reinstalled using 
proper electrical bonding procedures.
     All references to actions taken for Configuration 3 
airplanes should refer to removing braided bonding straps and 
installing new, longer braided bonding straps.
    We concur with FedEx's comments that the proper electrical bonding 
procedures and/or clarifications be provided in the associated Boeing 
service bulletins. As stated previously, this second supplemental NPRM 
now refers to Boeing Service Bulletin DC10-53-109, Revision 7, dated 
March 3, 2009, which contains instructions for conductivity checks for 
all previously installed braided bonding straps, as requested by FedEx. 
In addition, we note that Configuration 3 applies only to aircraft 
previously modified per McDonnell Douglas DC-10 Service Bulletin 53-
109, Revision 4, dated October 7, 1992, of this service bulletin, not 
Boeing Service Bulletin DC10-53-109, Revision 5, dated March 19, 2008, 
as FedEx commented.

Explanation of Additional Paragraph in the Supplemental NPRM

    We have added a new paragraph (d) to this supplemental NPRM to 
provide the Air Transport Association (ATA) of America code. This code 
is added to make this supplemental NPRM parallel with other new AD 
actions. We have reidentified subsequent paragraphs accordingly.

FAA's Determination and Proposed Requirements of the Supplemental NPRM

    We are proposing this second supplemental NPRM because we evaluated 
all pertinent information and determined an unsafe condition exists and 
is likely to exist or develop on other products of the same type 
design. Certain changes described above expand the scope of the first 
supplemental NPRM. As a result, we have determined that it is necessary 
to reopen the comment period to provide additional opportunity for the 
public to comment on this second supplemental NPRM.

Costs of Compliance

    We estimate that this proposed AD would affect 280 airplanes of 
U.S. registry. The following table provides the estimated costs for 
U.S. operators to comply with this proposed AD.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                     Number of U.S.-
   Work hours      Average labor        Parts           Cost per        registered            Fleet cost
                   rate per hour                        product         airplanes
----------------------------------------------------------------------------------------------------------------
2-17............             $80   Up to $4,169...  Up to $5,529...             281   Up to $1,553,649.
----------------------------------------------------------------------------------------------------------------

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 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.
    For the reasons discussed above, I certify this 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), 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.
    You can find our regulatory evaluation and the estimated costs of 
compliance in the AD Docket.

[[Page 45138]]

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 amendment 39-14703 (71 FR 
43962, August 3, 2006) and adding the following new AD:

McDonnell Douglas: Docket No. FAA-2007-0186; Directorate Identifier 
2007-NM-226-AD.

Comments Due Date

    (a) We must receive comments by September 28, 2009.

Affected ADs

    (b) This AD supersedes AD 2006-16-03.

Applicability

    (c) This AD applies to 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, 
and DC-10-40F airplanes, and MD-10-10F and MD-10-30F airplanes that 
have been converted from Model DC-10 series airplanes; certificated 
in any category; with manufacturer's fuselage numbers as identified 
in the applicable service bulletin listed in Table 1 of this AD.

                                             Table 1--Applicability
----------------------------------------------------------------------------------------------------------------
       Boeing Service  Bulletin--           Revision--              Dated--              For airplanes with--
----------------------------------------------------------------------------------------------------------------
DC10-53-109.............................               7  March 3, 2009.............  Extended wing-to-fuselage
                                                                                       fillets.
DC10-53-111.............................               6  March 3, 2009.............  Conventional wing-to-
                                                                                       fuselage fillets.
----------------------------------------------------------------------------------------------------------------

Subject

    (d) Air Transport Association (ATA) of America Code 53: 
Fuselage.

Unsafe Condition

    (e) This AD results from 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.

Compliance

    (f) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Restatement of Requirements of AD 2006-16-03 With New Service 
Information

Installation or Replacement

    (g) For airplanes with manufacturer's fuselage numbers 
identified in the applicable service bulletin listed in Table 2 of 
this AD: Within 7,500 flight hours or 60 months after September 7, 
2006 (the effective date of AD 2006-16-03), 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 Table 2 of this AD or Table 1 of this 
AD. After the effective date of this AD, use the applicable service 
bulletin identified in Table 1 of this AD.

                               Table 2--Fuselage Numbers Affected by AD 2006-16-03
----------------------------------------------------------------------------------------------------------------
  McDonnell Douglas DC[dash]10 Service
               Bulletin--                   Revision--              Dated--              For airplanes with--
----------------------------------------------------------------------------------------------------------------
53[dash]109.............................               4  October 7, 1992...........  Extended wing-to-fuselage
                                                                                       fillets.
53-111..................................               3  August 24, 1992...........  Conventional wing-to-
                                                                                       fuselage fillets.
----------------------------------------------------------------------------------------------------------------

New Requirements of This AD

Installation or Replacement

    (h) For airplanes with fuselage numbers not identified in Table 
2 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 the effective date of this AD, 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, and reposition two bonding 
straps. Do the actions in accordance with the Accomplishment 
Instructions of the applicable service bulletin identified in Table 
1 of this AD.

Strap Repositioning for Certain Airplanes

    (i) 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 the effective 
date of this AD, 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.
    (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.

Inspection and Corrective Action for Certain Airplanes

    (j) 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 the effective 
date of this AD, 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 strap, and, before further 
flight, do all applicable corrective actions, in accordance with 
Accomplishment Instructions of Boeing Service Bulletin DC10-53-111, 
Revision 6, dated March 3, 2009.
    (2) Measure the resistance of the previously installed bonding 
straps and, before further flight, do all applicable corrective 
actions, in accordance with Accomplishment Instructions of Boeing 
Service Bulletin DC10-53-111, Revision 6, dated March 3, 2009.

[[Page 45139]]

Credit for Actions Accomplished In Accordance With Previous Service 
Information

    (k) Actions accomplished before the effective date of this AD 
according to Boeing Service Bulletin DC10-53-111, Revision 5, dated 
March 19, 2008; and Boeing Service Bulletin DC10-53-109, Revision 6, 
dated July 10, 2008; are considered acceptable for compliance with 
the corresponding action specified in this AD.

Alternative Methods of Compliance (AMOCs)

    (l)(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. Send 
information to ATTN: Samuel Lee, Aerospace Engineer, Propulsion 
Branch, ANM-140L, FAA, Los Angeles Aircraft Certification Office, 
3960 Paramount Boulevard, Lakewood, California 90712-4137; telephone 
(562) 627-5262; fax (562) 627-5210.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office. 
The AMOC approval letter must specifically reference this AD.
    (3) AMOCs approved previously in accordance with AD 2006-16-03 
are approved as AMOCs for the corresponding provisions of this AD.

    Issued in Renton, Washington, on August 17, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-20994 Filed 8-31-09; 8:45 am]

BILLING CODE 4910-13-P