[Federal Register Volume 70, Number 30 (Tuesday, February 15, 2005)]
[Proposed Rules]
[Pages 7683-7687]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-2837]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20349; Directorate Identifier 2003-NM-108-AD]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model MD-11 and -11F 
Airplanes; Model DC-10-10 and DC-10-10F Airplanes; Model DC-10-15 
Airplanes; Model DC-10-30 and DC-10-30F (KC-10A and KDC-10) Airplanes; 
Model DC-10-40 and DC-10-40F Airplanes; and Model MD-10-10F and MD-10-
30F Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to certain McDonnell Douglas Model MD-11 
and -11F airplanes. The existing AD currently requires a one-time 
inspection to detect loose preload-indicating (PLI) washers or cracked 
or corroded nuts of the lower bolts of the inboard flap outboard hinge, 
and replacement with new parts if necessary. This proposed AD would 
require replacement with new, improved parts of the inboard flap, 
outboard hinge, forward attach bracket, and lower attach bolt 
assemblies. This proposed AD also would add certain other McDonnell 
Douglas transport category airplanes and require an inspection for 
certain parts, and related investigative and corrective actions if 
necessary. This proposed AD is prompted by a report indicating that the 
left-hand inboard flap outboard hinge pulled away from the wing 
structure. We are proposing this AD to prevent loose PLI washers or 
cracked or corroded nuts of the lower bolts of the inboard flap 
outboard hinge, which could result in separation of the inboard flap 
outboard hinge from the wing structure and consequent reduced 
controllability of the airplane.

DATES: We must receive comments on this proposed AD by April 1, 2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://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.
     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.
    For service information identified in this proposed AD, contact 
Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood 
Boulevard, Long Beach, California 90846, Attention: Data and Service 
Management, Dept. C1-L5A (D800-0024).
    You can examine the contents of this AD docket on the Internet at 
http://dms.dot.gov, or at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street SW., room PL-401, on 
the plaza level of the Nassif Building, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Ronald Atmur, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5224; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: 

Docket Management System (DMS)

    The FAA has implemented new procedures for maintaining AD dockets 
electronically. As of May 17, 2004, new AD actions are posted on DMS 
and assigned a docket number. We track each action and assign a 
corresponding directorate identifier. The DMS AD docket number is in 
the form ``Docket No. FAA-2005-99999.'' The Transport Airplane 
Directorate identifier is in the form ``Directorate Identifier 2005-NM-
999-AD.'' Each DMS AD docket also lists the directorate identifier 
(``Old Docket Number'') as a cross-reference for searching purposes.

Comments Invited

    We invite you to submit any written relevant data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2005-20349; 
Directorate Identifier 2003-NM-108-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of our 
docket web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You can review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
can visit http://dms.dot.gov.
    We are reviewing the writing style we currently use in regulatory 
documents. We are interested in your comments on whether the style of 
this document is clear, and your suggestions to improve the clarity of 
our communications that affect you. You can get more information about 
plain language at http://www.faa.gov/language and http://www.plainlanguage.gov.

Examining the Docket

    You can examine the AD docket on the Internet at http://dms.dot.gov, or in person at the Docket Management

[[Page 7684]]

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 DOT street address stated in the ADDRESSES section. 
Comments will be available in the AD docket shortly after the DMS 
receives them.

Discussion

    On July 10, 2002, we issued AD 2002-14-03, amendment 39-12803 (67 
FR 47254, July 18, 2002), for certain McDonnell Douglas Model MD-11 and 
MD-11F airplanes. That AD requires a one-time inspection to detect 
loose preload-indicating (PLI) washers or cracked or corroded nuts of 
the lower bolts of the inboard flap outboard hinge, and replacement 
with new parts if necessary. That AD was prompted by a report 
indicating that the left-hand inboard flap outboard hinge pulled away 
from the wing structure where it attaches with two upper and two lower 
bolts. We issued that AD to detect and correct loose PLI washers or 
cracked or corroded nuts of the lower bolts of the inboard flap 
outboard hinge, which could result in separation of the inboard flap 
outboard hinge from the wing structure and consequent reduced 
controllability of the airplane.

Actions Since Existing AD Was Issued

    Since the existing AD was issued, we have determined that the upper 
and lower attach bolt assemblies specified on Model MD-11 and MD-11F 
airplanes affected by AD 2002-14-03 are identical to the attach bolt 
assemblies on certain Model DC-10-10 and DC-10-10F airplanes; Model DC-
10-15 airplanes; Model DC-10-30 and DC-10-30F (KC-10A and KDC-10) 
airplanes; Model DC-10-40 and DC-10-40F airplanes; and Model MD-10-10F 
and MD-10-30F airplanes. Therefore, all these models may be subject to 
the same unsafe condition.
    Additionally, in the preamble to AD 2002-14-03, we indicated that 
the actions required by that AD were considered ``interim action'' and 
that further rulemaking action was being considered. We now have 
determined that further rulemaking action is indeed necessary, and this 
proposed AD follows from that determination.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin (ASB) MD11-57A067, 
Revision 01, including Appendices A and B, dated April 8, 2003 (for 
Model MD-11 and -11F airplanes). The ASB describes various procedures 
for different groups of airplanes, based on the composition of the nuts 
on the lower bolts of the inboard flap outboard hinge. (Boeing ASB 
MD11-57A067, including Appendices A and B, dated July 10, 2002, is the 
appropriate source of service information for AD 2002-14-03.)
    Group 1 airplanes specified in Revision 01 have alloy steel nuts, 
and Group 2 airplanes specified in Revision 01 have Inconel nuts. The 
procedures for these airplane groups include removing sealant from the 
head and nut sides of both bolt assemblies, using a wiggle tool to 
detect looseness of the preload-indicating (PLI) washers, and visually 
inspecting the nut for corrosion and cracking. Based on the results of 
the inspection, related investigative and corrective actions include 
doing a magnetic particle inspection of the bolt to detect cracking and 
corrosion, replacing discrepant parts with new Inconel and/or alloy 
steel bolts and nuts and new PLI washers, and applying sealant.
    We also have reviewed Boeing Service Bulletin MD-1157A068, Revision 
1, dated April 8, 2003 (for Model MD-11 and MD-11F airplanes). That 
service bulletin describes procedures for replacing the bolts and nuts 
of the inboard flap, outboard hinge, forward attach bracket, and the 
lower attach bolt assemblies with Inconel bolts and nuts.
    Additionally, we reviewed Boeing Service Bulletin DC10-57A149, 
Revision 1, dated April 8, 2003 (for Model DC-10-10 and DC-10-10F 
airplanes; Model DC-10-15 airplanes; Model DC-10-30 and DC-10-30F (KC-
10A and KDC-10) airplanes; Model DC-10-40 and DC-10-40F airplanes; and 
Model MD-10-10F and MD-10-30F airplanes). That service bulletin 
describes procedures for inspecting the maintenance records to 
determine if new Inconel bolts and nuts have been installed in 
accordance with Boeing Service Bulletin DC10-57-116. For certain 
airplanes, the service bulletin describes encapsulating both nut sides 
of the bolt assemblies with sealant, and inspecting for cracking of the 
nuts of the upper and lower attach bolt assemblies. The service 
bulletin also describes procedures for replacing the PLI washers with 
new washers, and for replacing both upper and lower attach bolt 
assemblies with Inconel nuts and bolts.
    Accomplishment of the actions specified in the above service 
bulletins is intended to adequately address the identified unsafe 
condition.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other products 
of this same type design. Therefore, we are proposing this AD, which 
would supersede AD 2002-14-03. For certain airplanes, this proposed AD 
would continue to require the one-time inspection to detect loose PLI 
washers or cracked or corroded nuts of the lower bolts of the inboard 
flap outboard hinge, and replacement with new parts if necessary. This 
proposed AD would also require eventual replacement of the steel bolts 
and nuts with Inconel material. This proposed AD would require you to 
use the applicable service information described previously to perform 
these actions except as discussed under ``Differences Between the 
Proposed AD and the Relevant Service Information.''

Differences Between the Proposed AD and the Relevant Service 
Information

    Boeing Alert Service Bulletin MD11-57A067, Revision 01, dated April 
8, 2003, specifies that operators may test for looseness of the PLI 
washers by use of a wiggle tool, ``or equivalent.'' However, this 
proposed AD would require that any alternative to the wiggle-tool test 
be accomplished in accordance with a method approved by the FAA. Use of 
an equivalent tool or test procedure is allowed only if approved as an 
alternative method of compliance in accordance with the requirements of 
paragraph (e) of this proposed AD.
    Although Boeing Service Bulletin DC10-57A149, Revision 1, dated 
April 8, 2003, specifies inspection of the maintenance records to 
determine if new Inconel bolts and nuts have been installed in 
accordance with Boeing Service Bulletin DC10-57-116, this proposed AD 
specifies inspection of the maintenance records to determine if new 
Inconel bolts and nuts have been installed in accordance with Boeing 
Service Bulletin DC10-57-116, Revision 01, dated November 25, 1993; 
Revision 02, dated December 22, 1998; or Revision 03, dated May 12, 
1999.
    Further, although Boeing Alert Service Bulletin MD11-57A067 
specifies that the manufacturer may be contacted for disposition of 
``additional examination recommendations,'' this proposed AD would 
require the actions to be accomplished in accordance with a method 
approved by the FAA.
    Although Boeing Service Bulletin DC10-57A149 specifies sending a 
report

[[Page 7685]]

and discrepant parts to the manufacturer, this proposed AD would not 
require those actions.

Change to Existing AD

    This proposed AD would retain certain requirements of AD 2002-14-
03. Since AD 2002-14-03 was issued, the AD format has been revised, and 
certain paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers have changed in this proposed AD, as listed in 
the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                          Corresponding  requirement in
      Requirement in AD 2002-14-03              this  proposed AD
------------------------------------------------------------------------
Paragraph (a)..........................  Paragraph (f).
Paragraph (b)..........................  Paragraph (g).
Paragraph (c)..........................  Paragraph (h).
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Costs of Compliance

    There are about 593 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this proposed AD. The average labor rate 
is considered to be $65 per hour.

                                                                     Estimated Costs
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                                                                                                                 Number of
                                                                                                                   U.S.-
               Action                          Work hours              Parts           Cost per airplane         registered           Fleet cost
                                                                                                                 airplanes
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Inspection of Model MD-11 and -11F   10 to 12.....................  ...........  $650 to $780.................           66  Between $42,900 and
 airplanes (required by AD 2002-14-                                                                                           $51,480.
 03).
Replacing parts for Model MD-11 and  13...........................       $2,041  $2,886.......................           66  $190,476.
 -11F airplanes (new proposed
 action).
Inspection of Model DC-10-10, and    1............................            0  $65..........................          297  $19,305.
 DC-10-10F airplanes; Model DC-10-
 15 airplanes; Model DC-10-30 and
 DC-10-30F (KC-10A and KDC-10)
 airplanes; Model DC-10-40 and DC-
 10-40F airplanes; Model MD-10-10F
 and MD-10-30F airplanes.
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Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on 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.
    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); 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 proposed AD. 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, 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 39-12803 (67 FR 
47254, July 18, 2002) and adding the following new airworthiness 
directive (AD):

McDonnell Douglas: Docket No. FAA-2005-20349; Directorate Identifier 
2003-NM-108-AD.

Comments Due Date

    (a) The Federal Aviation Administration must receive comments on 
this airworthiness directive (AD) action by April 1, 2005.

Affected ADs

    (b) This AD supersedes AD 2002-14-03, amendment 39-12803.

Applicability

    (c) This AD applies to the airplanes listed in Table 1 of this 
AD, certificated in any category.

[[Page 7686]]



                         Table 1.--Applicability
------------------------------------------------------------------------
        McDonnell Douglas Model                As listed in Boeing
------------------------------------------------------------------------
(1) DC-10-10, and DC-10-10F airplanes;   Service Bulletin DC10-57A149,
 DC-10-15 airplanes; DC-10-30 and DC-10-  Revision 1, dated April 8,
 30F (KC-10A and KDC-10) airplanes; DC-   2003.
 10-40 and DC-10-40F airplanes; MD-10-
 10F and MD-10-30F airplanes.
(2) MD-11 and MD-11F airplanes.........  Alert Service Bulletin MD11-
                                          57A067, including Appendix A
                                          and B; Revision 01, dated
                                          April 8, 2003; and Service
                                          Bulletin MD11-57A068, Revision
                                          1, dated April 8, 2003.
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD is prompted by a report indicating that the left-
hand inboard flap outboard hinge pulled away from the wing 
structure. We are issuing this AD to prevent loose preload-
indicating (PLI) washers or cracked or corroded nuts of the lower 
bolts of the inboard flap outboard hinge, which could result in 
separation of the inboard flap outboard hinge from the wing 
structure 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.
    Certain Requirements of AD 2002-14-03:

Inspection

    (f) For airplanes listed in Boeing Alert Service Bulletin MD11-
57A067, dated July 10, 2002: At the applicable time specified in 
paragraph (f)(1) or (f)(2) of this AD, do a detailed inspection 
(including removing sealant from the head and nut sides of both bolt 
assemblies) of the nuts and PLI washers of the lower bolts of the 
inboard flap outboard hinge to detect discrepancies (including loose 
PLI washers or cracked or corroded nuts, as applicable), in 
accordance with Boeing Alert Service Bulletin MD11-57A067, including 
Appendices A and B, dated July 10, 2002, except as required by 
paragraphs (g) and (h) of this AD. Before further flight thereafter, 
do applicable related investigative and corrective actions 
(including performing a magnetic particle inspection of the bolt to 
detect cracking and corrosion, replacing discrepant parts with new 
Inconel and/or alloy steel bolts and nuts and new PLI washers, and 
applying sealant, as applicable); and, within 600 flight cycles, 
replace discrepant bolts, nuts, and washers with new parts, as 
applicable; in accordance with the alert service bulletin.
    (1) For Group 1 airplanes: Inspect within 30 days after August 
2, 2002 (the effective date of AD 2002-14-03, amendment 39-12803).
    (2) For Group 2 airplanes: Inspect within 60 days after August 
2, 2002.

    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.''

Exceptions to Paragraph (f) Requirements

    (g) Where Boeing Alert Service Bulletin MD11-57A067, including 
Appendices A and B, dated July 10, 2002, specifies that testing for 
looseness of the PLI washers may be accomplished by the use of a 
wiggle tool, ``or equivalent'': Either the wiggle tool must be used, 
or the test must be accomplished in accordance with a method 
approved by the Manager, Los Angeles Aircraft Certification Office 
(ACO), FAA.
    (h) Where Boeing Alert Service Bulletin MD11-57A067, including 
Appendices A and B, dated July 10, 2002, specifies to contact Boeing 
for ``additional examination recommendations'': Before further 
flight, these actions, if accomplished, must be performed in 
accordance with a method approved by the Manager, Los Angeles ACO. 
For such a method to be approved by the Manager, Los Angeles ACO, as 
required by this paragraph, the Manager's approval letter must 
specifically refer to this AD.

New Requirements of This AD:

Replacement of Steel Bolts and Nuts

    (i) For Model MD-11 and ``MD-11F airplanes specified in 
Condition 2 of the Accomplishment Instructions of Boeing Alert 
Service Bulletin MD11-57A068, dated Revision 1, dated April 8, 2003: 
Within 18 months after the effective date of this AD, replace the 
bolts and nuts of the inboard flap, outboard hinge, forward attach 
bracket, and lower attach bolt assemblies with bolts and nuts made 
from Inconel material; and install new PLI washers, by accomplishing 
all the actions in the Accomplishment Instructions of Boeing Service 
Bulletin MD11-57068, dated January 7, 2003, or Revision 1, dated 
April 8, 2003.
    (j) For Model MD-11 and MD-11F airplanes specified in Condition 
3 of the Accomplishment Instructions of Boeing Alert Service 
Bulletin MD11-57A068, Revision 1, dated April 8, 2003: Within 36 
months after the effective date of this AD, replace the bolts and 
nuts of the inboard flap, outboard hinge, forward attach bracket, 
and lower attach bolt assemblies with bolts and nuts made from 
Inconel material and install new PLI washers, in accordance with 
Boeing Service Bulletin MD11-57068, dated January 7, 2003 or 
Revision 1, dated April 8, 2003.
    (k) For Model MD-11 and MD-11F airplanes specified in Condition 
4 of the Accomplishment Instructions of Boeing Alert Service 
Bulletin MD11-57A068, Revision 1, dated April 8, 2003: Within 60 
months after the effective date of this AD, replace the bolts and 
nuts of the inboard flap, outboard hinge, forward attach bracket, 
and lower attach bolt assemblies with bolts and nuts made from 
Inconel material and new PLI washers, in accordance with Boeing 
Service Bulletin MD11-57068, dated January 7, 2003, or Revision 1, 
dated April 8, 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.''

Inspection of Certain Parts or Maintenance Records

    (l) For Model DC-10-10, and DC-10-10F airplanes; Model DC-10-15 
airplanes; Model DC-10-30 and DC-10-30F (KC-10A and KDC-10) 
airplanes; Model DC-10-40 and DC-10-40F airplanes; and Model MD-10-
10F and MD-10-30F airplanes: Within 6 months after the effective 
date of this AD, perform a general visual inspection of the inboard 
flap, outboard hinge, forward attach bracket, and upper and lower 
attach bolt assemblies to determine if those parts have been 
replaced with Inconel bolt assemblies in accordance with Boeing 
Service Bulletin DC10-57-116, Revision 01, dated November 25, 1993; 
Revision 02, dated December 22, 1998; or Revision 03, dated May 12, 
1999. Instead of performing a general visual inspection of those 
parts, a review of airplane maintenance records is acceptable if 
replacement of the Inconnel bolt assemblies in accordance with 
Boeing Service Bulletin DC10-57-116, Revision 01, dated November 25, 
1993; Revision 02, dated December 22, 1998; or Revision 03, dated 
May 12, 1999, can be positively determined from that review.
    (1) If it can positively be determined that the Inconcel bolt 
assemblies are installed, no further action is required by this 
paragraph.
    (2) If the Inconel bolt assemblies are not installed, before 
further flight, do a detailed inspection for cracking of the 
external area of each nut of the inboard flap, outboard hinge, 
forward attach bracket, lower attach bolt assembly, in accordance 
with Boeing Service Bulletin DC10-57A149, Revision 1, dated April 8, 
2003.
    (i) If no cracking is detected, before further flight, 
encapsulate both nut sides of the bolt assembly installations with 
sealant; and,

[[Page 7687]]

within 24 months after the effective date of this AD, replace both 
upper and lower attach bolt assemblies with bolts and nuts made from 
Inconel; in accordance with the service bulletin.
    (ii) If any cracking is detected, do the actions specified in 
either paragraph (l)(2)(ii)(A) or (l)(2)(ii)(B) of this AD, at the 
times specified, in accordance with the service bulletin.
    (A) Prior to further flight, replace both upper and lower attach 
bolt assemblies with bolts and nuts made from Inconel and new 
washers;
    (B) Prior to further flight, replace both lower attach bolt 
assemblies with bolts and nuts made from Inconel and new washers, 
and within 24 months after the effective date of this AD, replace 
both upper attach bolt assemblies with bolts and nuts made from 
Inconel and new washers.

No Reporting Requirement

    (m) Although certain service information referenced in this AD 
specifies to submit a report and discrepant parts to the 
manufacturer, this AD does not include those requirements.

Alternative Methods of Compliance (AMOCs)

    (n)(1) The Manager, Los Angeles Aircraft Certification Office 
(ACO), FAA, has the authority to approve AMOCs for this AD, if 
requested in accordance with the procedures found in 14 CFR 39.19.
    (2) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD, if it is approved by an 
Authorized Representative for the Boeing Delegation Option 
Authorization Organization who has been authorized by the Manager, 
Los Angeles ACO, to make those findings. For a repair method to be 
approved, the approval must specifically refer to this AD.

    Issued in Renton, Washington, on February 3, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-2837 Filed 2-14-05; 8:45 am]
BILLING CODE 4910-13-P