FR Doc 05-2837

[Federal Register: February 15, 2005 (Volume 70, Number 30)]
[Proposed Rules]
[Page 7683-7687]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr15fe05-19]

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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

[[Page 7686]]

Table 1.--Applicability
------------------------------------------------------------------------
McDonnell Douglas Model As listed in Boeing
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(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