[Federal Register Volume 69, Number 230 (Wednesday, December 1, 2004)]
[Proposed Rules]
[Pages 69838-69842]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-26494]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19753; Directorate Identifier 2002-NM-264-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 767-200, -300, and -300F 
Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) for certain Boeing Model 767-200, -300, and -300F series 
airplanes. That AD currently requires inspections for fatigue cracking 
of the horizontal stabilizer pivot bulkhead, and repetitive inspections 
or other follow-on actions. That action also provides a permanent 
repair, which is optional for airplanes with no cracks, and, if 
accomplished, ends the repetitive inspections. This proposed AD would 
require, for airplanes on which the permanent repair is not installed, 
repetitive inspections of the same and additional inspection locations 
at new inspection intervals; a one-time torque test; and related 
investigative and corrective actions. For airplanes on which the 
permanent repair is installed, this proposed AD would require 
repetitive inspections of the repaired area and, if necessary, 
corrective action. This proposed AD is prompted by reports of loose 
tension bolts and crack indications in the fuselage skin. We are 
proposing this AD to find and fix fatigue cracking of the horizontal 
stabilizer pivot bulkhead and adjacent structure, which could result in 
loss of the horizontal stabilizer.

DATES: We must receive comments on this proposed AD by January 18, 
2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
    <bullet> DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
    <bullet> Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
    <bullet> Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401, 
Washington, DC 20590.
    <bullet> Fax: (202) 493-2251.
    <bullet> 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.
    You can get the service information identified in this proposed AD 
from Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 
98124-2207.
    You may 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:
    Technical information: Suzanne Masterson, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6441; fax (425) 917-6590.
    Plain language information: Marcia Walters, <a href="/cdn-cgi/l/email-protection#660b0714050f074811070a120314152600070748010910"><span class="__cf_email__" data-cfemail="eb868a9988828ac59c8a879f8e9998ab8d8a8ac58c849d">[email protected]</span></a>.

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-2004-99999.'' The Transport Airplane 
Directorate identifier is in the form ``Directorate Identifier 2004-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-2004-19753; 
Directorate Identifier 2002-NM-264-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 may review the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may 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

[[Page 69839]]

http://www.faa.gov/language and http://www.plainlanguage.gov.

Examining the Docket

    You may examine the AD docket in person at the Docket Management 
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 April 27, 2001, we issued AD 2001-09-13, amendment 39-12220 (66 
FR 23538, May 9, 2001), for certain Boeing Model 767-200, -300, and -
300F series airplanes. That AD requires inspections for fatigue 
cracking of the horizontal stabilizer pivot bulkhead, and repetitive 
inspections or other follow-on actions. That AD also provides a 
permanent repair, which is optional for airplanes with no cracks, and, 
if accomplished, ends the repetitive inspections. That AD was prompted 
by reports of fatigue cracking of the horizontal stabilizer pivot 
bulkhead on several affected airplanes. We issued that AD to find and 
fix fatigue cracking of the horizontal stabilizer pivot bulkhead and 
adjacent structure, which could result in loss of the horizontal 
stabilizer.

Actions Since Existing AD Was Issued

    Since we issued AD 2001-09-13, an airplane operator reported three 
incidents of loose tension bolts at stringer 12A. Another operator 
reported that there were indications of cracks in the fuselage skin at 
``Area 1'' as shown on Sheet 2 of Figure 2 of Boeing Alert Service 
Bulletin 767-53A0078, Revision 4, dated September 26, 2002.
    In addition, the preamble to AD 2001-09-13 said that we were 
considering further action to require the permanent repair that was an 
option in that AD. However, further information shows that operators 
have found cracks at the repaired area. Therefore, we are not requiring 
the permanent repair from AD 2001-09-13 as a preventive modification in 
this proposed AD.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 767-53A0078, 
Revision 4, dated September 26, 2002.
    The alert service bulletin describes the following procedures for 
airplanes on which the permanent repair, described in previous 
revisions of the service bulletin, was not installed:
    <bullet> Inspections for cracks of the forward and aft outer chord, 
the splice fitting, the tension fitting, the aft mid chord, and the 
upper and lower intercostals. The inspection methods include the 
following, as applicable: Repetitive detailed inspections, surface high 
frequency eddy current (HFEC) inspections, open-hole HFEC inspections, 
and low frequency eddy current (LFEC) inspections.
    <bullet> Corrective action and related investigative action if 
cracks are found in the forward outer chord. The corrective action is 
installing a permanent repair. The related investigative action is 
repetitive inspections of the repaired area.
    <bullet> Installing a time-limited repair as an alternative to the 
permanent repair, which includes the related investigative and 
corrective actions of an additional visual inspection for cracks, and 
installation of the permanent repair either before further flight after 
this inspection if cracks are found, or within 3,000 flight cycles or 
18 months after the inspection (whichever occurs first), if no cracks 
are found.
    <bullet> A torque check of the bolt in the tension fitting, and 
related investigative and corrective actions. The related investigative 
action is doing a visual inspection of the bolt and bolt-hole for 
damage, and an HFEC inspection of the bolt-hole for damage. The 
corrective action is to contact Boeing for repair data.
    <bullet> If any crack is found in the aft outer chord, the aft mid 
chord, the splice fitting, the tension fitting, or the intercostal, the 
service bulletin recommends that operators contact Boeing for repair 
data.
    For airplanes on which the permanent repair was installed using 
previous revisions of the service bulletin, Revision 4 of the service 
bulletin describes procedures for repetitive inspections of the 
repaired area. The service bulletin recommends that operators contact 
Boeing for any necessary corrective action.
    We have determined that accomplishment of the actions specified in 
the service information will adequately address the 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 2001-09-13. This proposed AD would continue to 
require inspections for fatigue cracking of the horizontal stabilizer 
pivot bulkhead, and repetitive inspections or other follow-on actions. 
For airplanes with cracks, this proposed AD also would continue to 
require a permanent repair, which is optional for airplanes with no 
cracks. This proposed AD would require, for airplanes on which the 
permanent repair is not installed, repetitive inspections of the same 
and additional inspection locations at new inspection intervals; a one-
time torque test; and other related corrective and investigative 
actions. For airplanes on which the permanent repair is installed, this 
proposed AD would require repetitive inspections of the repaired area, 
and corrective action if necessary. This proposed AD would require you 
to use the service information described previously to perform these 
actions, except as discussed under ``Difference Between the Proposed AD 
and the Service Bulletin.''

Difference Between the Proposed AD and the Service Bulletin

    The service bulletin specifies that you may contact the 
manufacturer for instructions on how to repair certain conditions, but 
this proposed AD would require you to repair those conditions in one of 
the following ways:
    <bullet> Using a method that we approve; or
    <bullet> Using data that meet the type certification basis of the 
airplane, and that have been approved by a Boeing Company Designated 
Engineering Representative who has been authorized by the FAA to make 
such findings.

Changes to Existing AD

    This proposed AD would retain all requirements of AD 2001-09-13 
with revised repetitive inspection intervals. Since AD 2001-09-13 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
       Requirement in AD 2001-09-13             in this  proposed AD
------------------------------------------------------------------------
Paragraph (a).............................  paragraph (f).
Paragraph (b).............................  paragraph (g).
Paragraph (c).............................  paragraph (h).
Paragraph (d).............................  paragraph (i).
Paragraph (e).............................  paragraph (j).
Paragraph (f).............................  paragraph (p).
------------------------------------------------------------------------


[[Page 69840]]

    In addition, we have changed all references to a ``detailed visual 
inspection'' in the AD 2001-09-13 to ``detailed inspection'' in this 
proposed AD, which is defined in Note 1.
    We have also changed the applicability of the proposed AD to refer 
to Revision 4 of the service bulletin rather than to Revision 2, which 
we referenced in the applicability of AD 2001-09-13. Both revisions of 
the service bulletin refer to the same airplane line numbers, so 
airplanes have not been added to the applicability.

Costs of Compliance

    This proposed AD would affect about 699 Boeing Model 767-200, -300, 
and -300F series airplanes worldwide. The following table provides the 
estimated costs for U.S. operators to comply with this proposed AD.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Number of U.S.-
            Action                Work hours     Average labor     Parts    Cost per airplane      registered
                                                 rate per hour                                     airplanes
----------------------------------------------------------------------------------------------------------------
Inspection (required by AD                   1             $65  None......  $65 (per           287.
 2001-09-13).                                                                inspection
                                                                             cycle).
Inspection and torque check                  4              65  None......  260 (per           287.
 (new proposed action).                                                      inspection
                                                                             cycle).
Post-modification inspection                 6              65  None......  390..............  Those with the
 (new proposed action).                                                                         permanent repair
                                                                                                installed using
                                                                                                this proposed AD
                                                                                                or AD 2001-09-
                                                                                                13.
----------------------------------------------------------------------------------------------------------------

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 39-12220 (66 FR 
23538, May 9, 2001) and adding the following new airworthiness 
directive (AD):

Boeing: Docket No. FAA-2004-19753; Directorate Identifier 2002-NM-
264-AD.

Comments Due Date

    (a) The Federal Aviation Administration must receive comments on 
this airworthiness directive (AD) action by January 18, 2005.

Affected ADs

    (b) This AD supersedes AD 2001-09-13, amendment 39-12220.

Applicability

    (c) This AD applies to Boeing Model 767-200, -300, and -300F 
series airplanes, as listed in Boeing Alert Service Bulletin 767-
53A0078, Revision 4, dated September 26, 2002; certificated in any 
category.

Unsafe Condition

    (d) This AD was prompted by reports of loose tension bolts, and 
crack indications in the fuselage skin. We are issuing this AD to 
find and fix fatigue cracking of the horizontal stabilizer pivot 
bulkhead and adjacent structure, which could result in loss of the 
horizontal stabilizer.

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.

Requirements of AD 2001-09-13, Restated

Initial Inspections

    (f) Prior to the accumulation of 8,000 total flight cycles, or 
within 90 days after May 24, 2001 (the effective date of AD 2001-09-
13), whichever occurs later, perform detailed, surface high 
frequency eddy current (HFEC), and low frequency eddy current (LFEC) 
inspections, as applicable, for cracking of the forward and aft 
outer chord, aft mid chord, and upper and lower intercostals of the 
Station 1809.5 bulkhead. Do the inspections per Boeing Service 
Bulletin 767-53-0078, Revision 2, dated April 19, 2001; or Boeing 
Alert Service Bulletin 767-53-0078, Revision 3, dated November 15, 
2001.

    Note 1: For the purposes of this AD, a detailed inspection is: 
``An intensive visual examination of a specific structural area, 
system, installation, or assembly to detect damage, failure, or 
irregularity. Available lighting is normally supplemented with a 
direct source of good lighting at intensity deemed appropriate by 
the inspector. Inspection aids such as mirror, magnifying lenses, 
etc., may be used. Surface cleaning and elaborate access procedures 
may be required.''

Repetitive Inspections

    (g) For areas where no cracking is found during the inspection 
per paragraph (f) of this AD: Repeat the inspections in paragraph 
(f) thereafter at the intervals specified in paragraphs (g)(1) and 
(g)(2) of this AD, per Boeing Service Bulletin 767-53-0078, Revision 
2, dated April 19, 2001; or Boeing Alert Service Bulletin 767-53-
0078, Revision 3, dated November 15, 2001; until paragraph (i), 
(l)(1), or (m) of this AD has been done.
    (1) Repeat the detailed inspection every 3,000 flight cycles, or 
18 months, whichever comes first.
    (2) Repeat the surface HFEC and LFEC inspections every 6,000 
flight cycles or 36 months, whichever comes first.

Repair and Follow-On Actions

    (h) If any cracking is found during any inspection required by 
paragraph (f) or (g) of this AD, before further flight, repair per 
paragraph (h)(1) or (h)(2) of this AD, as applicable.
    (1) For cracking of the aft outer chord, aft mid chord, or any 
intercostal: Repair per a method approved by the Manager, Seattle 
Aircraft Certification Office (ACO), FAA. For a repair method to be 
approved by the Manager, Seattle ACO, as required by this paragraph, 
the Manager's approval letter must specifically reference this AD.

[[Page 69841]]

    (2) For cracking of the forward outer chord: Repair per Boeing 
Service Bulletin 767-53-0078, Revision 2, dated April 19, 2001; 
Revision 3, dated November 15, 2001; or Revision 4, dated September 
26, 2002; except as provided by paragraph (j) of this AD. Procedures 
for repair include open-hole HFEC inspections for cracking of 
certain fastener holes of the chord and longeron fitting, detailed 
inspections for cracking of adjacent structure, and installation of 
new chords, splices, fairings, and brackets. If the time-limited 
repair is done per the service bulletin, do a detailed inspection of 
the repaired area within 1,500 flight cycles or 9 months after 
installation of the temporary repair, whichever comes first, and do 
paragraph (h)(2)(i) or (h)(2)(ii) of this AD, per the service 
bulletin. As of the effective date of this AD, inspect only in 
accordance with Boeing Alert Service Bulletin 767-53-0078, Revision 
4, dated September 26, 2002.
    (i) If no cracking is found during the inspection of the 
repaired area: Within 3,000 flight cycles or 18 months after 
installation of the time-limited repair, whichever comes first, do 
paragraph (i), ``Permanent Repair,'' of this AD.
    (ii) If any cracking is found during the inspection of the 
repaired area: Before further flight, do paragraph (i), ``Permanent 
Repair,'' of this AD.

Permanent Repair

    (i) Except as provided by paragraph (j) of this AD, installation 
of the permanent repair of the forward outer chord, including 
accomplishment of all actions specified in Part 4 of the 
Accomplishment Instructions of Boeing Service Bulletin 767-53-0078, 
Revision 2, dated April 19, 2001; Boeing Service Bulletin 767-53-
0078, Revision 3, dated November 15, 2001; or Boeing Alert Service 
Bulletin 767-53-0078, Revision 4, dated September 26, 2002; 
terminates the repetitive inspections required by paragraph (g) of 
this AD. As of the effective date of this AD, install the permanent 
repair only in accordance with Boeing Alert Service Bulletin 767-53-
0078, Revision 4, dated September 26, 2002.

    Note 2: Installation of the permanent repair before the 
effective date of this AD in accordance with Boeing Service Bulletin 
767-53-0078, dated October 15, 1998; Revision 1, dated September 9, 
1999; is acceptable for compliance with paragraph (i) of this AD.

Exception to Repair Instructions

    (j) For repairs of the forward outer chord: Where the service 
bulletin specifies to ask Boeing for repair data, repair per a 
method approved by the Manager, Seattle ACO, or per data meeting the 
type certification basis of the airplane approved by a Boeing 
Company Designated Engineering Representative who has been 
authorized by the Manager, Seattle ACO, to make such findings. For a 
repair method to be approved by the Manager, Seattle ACO, as 
required by this paragraph, the Manager's approval letter must 
specifically reference this AD.

New Requirements of This AD

Initial and Repetitive Inspections, and Torque Test for Airplanes 
Without the Permanent Repair

    (k) For airplanes that have not had the permanent repair 
installed in accordance with paragraph (i) of this AD, at the later 
of the times in paragraphs (k)(1) and (k)(2) of this AD, do all the 
actions in paragraph (l) of this AD.
    (1) Within 3,000 flight cycles or 18 months after the effective 
date of this AD, whichever occurs first.
    (2) Prior to the accumulation of 8,000 total flight cycles.
    (l) Do all the actions in paragraphs (l)(1) and (l)(2) of this 
AD in accordance with ``Part 1--Inspection'' of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 767-53A0078, Revision 
4, dated September 26, 2002.
    (1) Do detailed, LFEC, and applicable HFEC inspections for 
cracking of the forward and aft outer chord, splice fitting, aft mid 
chord, aft intercostal, tension fitting, and fuselage skin, and 
repeat the applicable inspections at the applicable time in 
paragraph (l)(1)(i) and (l)(1)(ii) of this AD. This inspection 
terminates the repetitive inspections required by paragraphs (f) and 
(g) of this AD.
    (i) Except as provided by paragraph (l)(1)(ii) of this AD: 
Repeat the inspections, at intervals not to exceed 3,000 flight 
cycles until the permanent repair in paragraph (m)(2) of this AD has 
been done.
    (ii) For airplanes that meet the criteria in flag note 1 of 
Figure 1 of Boeing Alert Service Bulletin 767-53A0078, Revision 4, 
dated September 26, 2002 (close ream fasteners, external doubler, 
rub strip or wear plate installed): Repeat the open-hole HFEC 
inspections for cracking of the forward outer chord, splice fitting, 
tension fitting, and fuselage skin in Step 7, Figure 2 of the 
service bulletin at intervals not to exceed 9,000 flight cycles 
until the permanent repair in paragraph (m)(2) of this AD has been 
done.
    (2) Do a one-time torque test and related investigative and 
corrective actions of the tension bolt at lower stringer 12A. If any 
corrosion or damage is found in the bolt hole, and the service 
bulletin specifies to contact Boeing for appropriate action: Before 
further flight, repair per a method approved by the Manager, Seattle 
Aircraft Certification Office (ACO), FAA; or per data meeting the 
type certification basis of the airplane approved by a Boeing 
Company Designated Engineering Representative who has been 
authorized by the Manager, Seattle ACO, to make such findings. For a 
repair method to be approved, the approval must specifically 
reference this AD.

Corrective Actions

    (m) If any cracking is found during any inspection required by 
paragraph (l), (n) and (o) of this AD, before further flight, repair 
in accordance with paragraph (m)(1) or (m)(2) of this AD, as 
applicable.
    (1) For cracks found during the inspection required by paragraph 
(n) or (o) of this AD, or for cracks found in the aft outer chord, 
tension fitting, splice fitting, aft mid chord, or any intercostal: 
Before further flight, repair per a method approved by the Manager, 
Seattle Aircraft Certification Office (ACO), FAA; or per data 
meeting the type certification basis of the airplane approved by a 
Boeing Company Designated Engineering Representative who has been 
authorized by the Manager, Seattle ACO, to make such findings. For a 
repair method to be approved, the approval must specifically 
reference this AD.
    (2) For cracks in the forward outer chord: Prior to further 
flight, do the time limited repair in paragraph (h)(2) of this AD, 
or do the permanent repair in paragraph (i) of this AD. If the time 
limited repair is done, do the other applicable actions in paragraph 
(h)(2) of this AD at the times specified in that paragraph. As of 
the effective date of this AD, only repairs done per Boeing Alert 
Service Bulletin 767-53A0078, Revision 4, dated September 26, 2002, 
are acceptable for compliance with the requirements of this 
paragraph.

Repetitive Inspection of Repaired Area

    (n) For any airplane on which the permanent repair in paragraph 
(i) or (m)(2) of this AD is installed, at the later of the times in 
paragraph (n)(1) and (n)(2) of this AD: Do detailed, LFEC, and 
applicable HFEC inspections of the forward and aft outer chords, 
tension fitting, splice fitting, and splice angle for cracks; and a 
detailed inspection of the aft mid chord and aft upper and lower 
intercostals for cracks. Do the inspections in accordance with 
``Part 6--After Modification or After-Repair Inspection Program'' of 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
767-53A0078, Revision 4, dated September 26, 2002. Repeat each 
inspection, except as provided by paragraph (o) of this AD, 
thereafter at intervals not to exceed 6,000 flight cycles, or 36 
months, whichever occurs first.
    (1) Within 12,000 flight cycles or 72 months after the repair 
accomplished in accordance with paragraph (i) or (m)(2) of this AD.
    (2) Prior to the accumulation of 25,000 total flight cycles.
    (o) For any airplane on which the permanent repair in paragraph 
(i) or (m)(2) of this AD is installed, and that meets the criteria 
(close ream fasteners, external doubler, rub strip or wear plate 
installed) in flag note 1 of Figure 9 of Boeing Alert Service 
Bulletin 767-53A0078, Revision 4, dated September 26, 2002: After 
the initial inspection in paragraph (n) of this AD, repeat the open-
hole HFEC inspection in Step 7 of Figure 10 of the service bulletin, 
at intervals not to exceed 12,000 flight cycles, or 72 months, 
whichever occurs first.

Alternative Methods of Compliance

    (p)(1) In accordance with 14 CFR 39.19, the Manager, Seattle 
Aircraft Certification Office (ACO), FAA, is authorized to approve 
alternative methods of compliance (AMOCs) for the corresponding 
provisions of this AD.
    (2) AMOCs, approved previously per AD 2001-09-13, amendment 39-
12220, are approved as AMOCs with the corresponding provisions of 
this AD.

[[Page 69842]]

    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD, if it is approved by a 
Boeing Company Designated Engineering Representative who has been 
authorized by the Manager, Seattle ACO, to make such findings.

    Issued in Renton, Washington, on November 17, 2004.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-26494 Filed 11-30-04; 8:45 am]
BILLING CODE 4910-13-P


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