[Federal Register Volume 68, Number 101 (Tuesday, May 27, 2003)]
[Rules and Regulations]
[Pages 28703-28707]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-12844]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-10-AD; Amendment 39-13156; AD 2003-10-11]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Boeing Model 767-200 and -300 series 
airplanes, that currently requires repetitive inspections to find 
discrepancies of the barrel nuts that attach the vertical fin to body 
section 48, and follow-on actions. For certain airplanes, the existing 
AD requires replacement of certain bolts with new bolts. The existing 
AD also provides for optional terminating actions for the repetitive 
inspections. This amendment reduces the compliance time for the 
inspections; changes the torque specification; and mandates eventual 
replacement of all H-11 steel alloy barrel nuts and bolts with Inconel 
nuts and bolts, which ends the repetitive inspections. The actions 
specified by this AD are intended to find and fix corroded, cracked, or

[[Page 28704]]

broken barrel nuts that attach the vertical fin to body section 48, 
which could result in reduced structural integrity of the vertical fin 
attachment joint, loss of the vertical fin, and consequent loss of 
controllability of the airplane. This action is intended to address the 
identified unsafe condition.

DATES: Effective July 1, 2003.
    The incorporation by reference of Boeing Service Bulletin 767-
53A0085, Revision 2, dated May 2, 2002; and Boeing Service Bulletin 
767-53A0085, Revision 3, dated November 21, 2002; as listed in the 
regulations; is approved by the Director of the Federal Register as of 
July 1, 2003.
    The incorporation by reference of Boeing Service Bulletin 767-53-
0085, dated May 14, 1998; and Boeing Alert Service Bulletin 767-
53A0085, Revision 1, dated July 1, 1999; as listed in the regulations; 
was approved previously by the Director of the Federal Register as of 
October 9, 2001 (66 FR 48538, September 21, 2001).

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, 
Washington 98124-2207. This information may be examined at the Federal 
Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of 
the Federal Register, 800 North Capitol Street, NW., Suite 700, 
Washington, DC.

FOR FURTHER INFORMATION CONTACT: 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.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 2001-19-04, 
amendment 39-12444 (66 FR 48538, September 21, 2001), which is 
applicable to certain Boeing Model 767-200 and -300 series airplanes, 
was published in the Federal Register on August 16, 2002 (67 FR 53529). 
The action proposed to continue to require repetitive inspections to 
find discrepancies of the barrel nuts that attach the vertical fin to 
body section 48, and follow-on actions. For certain airplanes, the 
action proposed to continue to require replacement of certain bolts 
with new bolts. The action also proposed to continue to provide for 
optional terminating actions for the repetitive inspections. The new 
action proposed to reduce the compliance time for the inspections; 
change the torque specification; and mandate eventual replacement of 
all H-11 steel alloy barrel nuts and bolts with Inconel nuts and bolts, 
which would end the repetitive inspections.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Request To Reference Revision 3 of the Service Bulletin

    One commenter, the manufacturer, states that it is in the process 
of issuing Boeing Service Bulletin 767-53A0085, Revision 3 (Boeing 
Service Bulletin 767-53A0085, Revision 2, dated May 2, 2002, was 
referenced in the proposed AD as the source of service information for 
accomplishment of certain actions). The commenter would like the FAA to 
review Revision 3 and add it to the proposed AD. The commenter states 
that the changes in Revision 3 will correct the compliance statement 
specified in Revision 2 to align it with the proposed AD, and will also 
update the tooling information specified in Revision 2.
    The FAA has reviewed and approved Boeing Service Bulletin 767-
53A0085, Revision 3, dated November 21, 2002. We find that the changes 
incorporated in Revision 3 of the service bulletin are not substantive, 
meaning that airplanes modified per Boeing Service Bulletin 767-53-
0085, dated May 14, 1998; Revision 1, dated July 1, 1999; or Revision 
2, dated May 2, 2002; are not subject to any additional work under 
Revision 3 of the service bulletin. Revision 3 specifies a minor change 
to the compliance time recommended in Revision 2, but we have already 
extended the compliance time in this final rule, in order to avoid 
undue hardship on operators, per a comment we received (see discussion 
below). We have added Revision 3 of the service bulletin to this final 
rule as another source of service information for the accomplishment of 
certain actions.

Request To Add Credit Note for Terminating Action

    Several commenters ask that a credit note be added for previous 
accomplishment of the replacements required by paragraph (e) of the 
proposed AD per Boeing Service Bulletin 767-53-0085, dated May 14, 
1998; or Boeing Alert Service Bulletin 767-53A0085, Revision 1, dated 
July 1, 1999. One commenter would like credit to be given regardless of 
the revision level of the service bulletin, or any other approved 
maintenance procedures used to do the replacements, including the use 
of the production drawing. One commenter asks that credit be given for 
the replacements (terminating action) required by paragraph (e) of the 
proposed AD that were done before the required inspections and before 
the effective date of the AD.
    We partially agree with the commenters' requests, as follows.
    We agree that there are no significant changes among Boeing Service 
Bulletin 767-53-0085, dated May 14, 1998; Boeing Alert Service Bulletin 
767-53A0085, Revision 1, dated July 1, 1999; and Boeing Service 
Bulletin 767-53A0085, Revision 2, dated May 2, 2002; for the bolt and 
barrel nut installation method. Therefore, we have added the original 
issue and Revision 1 of the service bulletin as additional sources of 
service information for accomplishment of the terminating action 
required by paragraph (f) of this final rule (paragraph (e) of the 
proposed AD). In addition, credit is given as allowed by the phrase, 
``unless accomplished previously,'' and if the terminating action has 
already been accomplished per any of the service bulletin revisions 
specified in the final rule, this AD does not require that it be 
repeated.
    We do not agree to give credit regardless of the revision level of 
the service bulletin, or any approved procedures including the 
production drawing because they are not FAA-approved. To use the 
phrase, ``or later FAA-approved revisions,'' in an AD when referring to 
the service document, violates Office of the Federal Register (OFR) 
regulations regarding approval of materials ``incorporated by 
reference'' in rules. In general terms, these OFR regulations require 
that either the service document contents be published as part of the 
actual AD language; or the service document be submitted for approval 
by the OFR as ``referenced'' material, in which case it may be only 
referred to in the text of an AD. The AD may refer only to the service 
document that was submitted and approved by the OFR for ``incorporation 
by reference.'' In order for operators to use later revisions of the 
referenced document (issued after the publication of the AD), either 
the AD must be revised to reference the specific later revisions, or 
operators must request the approval of the use of them as an 
alternative method of compliance with this AD under the provisions of 
paragraph (h)(1) of this final rule.

[[Page 28705]]

Requests To Change Paragraph (d)

    Two commenters ask that paragraph (d) of the proposed AD be changed 
to specify that the new inspections are not required at the fastener 
locations where the H-11 steel bolts and nuts have been replaced with 
Inconel bolts and nuts.
    We agree with the commenters. We have changed paragraph (d) of this 
final rule, for clarification, to specify inspection of only the 
locations having ``H-11 steel alloy bolts and nuts.''
    Two commenters ask that paragraph (d) of the proposed AD be changed 
for clarification. One commenter states that paragraph (d) specifies 
doing internal and external inspections and a torque check within 18 
months after doing the initial inspections required by paragraph (a) of 
the existing AD, or within 90 days after the effective date of the AD. 
The commenter notes that it already performed the inspections required 
by paragraph (a) on two of its airplanes per Boeing Alert Service 
Bulletin 767-53A0085, Revision 1, dated July 1, 1999, and adds that the 
repeat inspections were done in the first half of 2002. The commenter 
asks that paragraph (d) be changed to specify, ``Within 18 months after 
the doing initial or the last repeated inspections required by 
paragraphs (a) and (b) * * *.'' Another commenter asks that ``until 
paragraph (e) of this AD is done,'' be added at the end of the 
compliance time specified in paragraph (d) of the proposed AD.
    We agree with the commenters to some extent. We have extended the 
compliance time specified in paragraph (d) of this final rule, per 
another comment (discussed below), to specify, ``Within 36 months after 
the last inspections done per paragraphs (a) and (b) of this AD * * 
*.'' However, paragraph (d) of this final rule already specifies that 
the inspections are repeated until accomplishment of paragraph (f) of 
the AD, so no change is necessary in this regard.

Request To Change Compliance Time

    One commenter asks that the compliance time specified in paragraph 
(d) of the proposed AD be changed to, ``Within 36 months after the 
initial inspections required by paragraph (a) of this AD or by June 
2003, whichever is later.'' The commenter states that the current 
compliance wording in paragraph (d) would result in inspecting its 28 
airplanes within 90 days, which would require taking those airplanes 
out-of-service to do the inspections. The commenter adds that the 
inspections could be done on an overnight visit, but any findings would 
require replacement of the barrel nut/bolt. The commenter notes that 
replacement at a field station is not practical due to the tooling 
involved and the need to ensure the safety of personnel, as there have 
been reports of injuries while removing/replacing barrel nuts using 
tooling other than a torque multiplier.
    We partially agree with the commenter. We do not agree to use a 
calendar date in the AD because the compliance time in this case is a 
function of fleet utilization, which is unrelated to calendar dates. 
However, we do agree to change the compliance time required by 
paragraph (d) of the final rule somewhat to avoid undue hardship on 
operators. Increasing the compliance time to, ``Within 36 months after 
the last inspections done per paragraphs (a) and (b) of this AD, or 
within 180 days after the effective date of this AD, whichever is 
later,'' will provide an acceptable level of safety. Paragraph (d) of 
this final rule has been changed accordingly.
    Another commenter asks that the compliance time specified in 
paragraph (d) of the proposed AD be changed to ``Within 18 months after 
the last inspection done per maintenance planning document (MPD) Items 
5380-311-02I and 5380-312-02I. The commenter states that paragraph (d) 
should clearly identify airplanes that would require the 90-day 
compliance time, and adds that, under the new requirements, it appears 
that the airplanes on which the MPD inspections specified in paragraph 
(a) of the proposed AD were done would require that the inspections 
specified in paragraph (d) be done within 90 days.
    We do not agree with the commenter. We have determined that the MPD 
inspections were inadequate and did not detect corroded barrel nuts and 
bolts. Operators have reported finding cracked bolts that passed the 
2,000-inch pound torque check specified in MPD Items 5380-311-02I and 
5380-312-02I. The MPD inspections are inadequate because they do not 
include a visual inspection of the barrel nut holes for sealant damage 
or signs of corrosion. Therefore, the compliance time cannot be changed 
to include inspections done per the MPD; however, the compliance time 
in paragraph (d) of this final rule has been changed somewhat for 
clarification, per another comment discussed previously.

Request To Change Cost Impact Section

    One commenter asks that the Cost Impact section of the proposed AD 
be changed. The commenter states that the hours required to do the 
actions, as specified in the referenced service bulletin, should be 
changed to show a more accurate cost impact. The commenter also states 
that the hours required for inspections and torque checks, and for the 
replacement of the 16 vertical stabilizer attachment nuts and bolts, as 
listed in the referenced service bulletin, are not sufficient. The 
commenter adds that an experienced crew with adequate tooling would 
require 24 work hours to do the replacement, and estimates the total 
work hours for replacement to be approximately 72 work hours. The 
commenter also adds that the rental cost of tooling would be $12,051 
per day. The commenter states that the proposed AD should be changed to 
reflect the significant cost of the tooling required to do the 
replacement.
    We do not agree with the commenter. The cost impact information 
describes only the costs of the specific actions required by this AD. 
The number of work hours necessary to accomplish the actions, specified 
in the cost impact information, was provided by the manufacturer based 
on the best data available to date. This number represents the time 
necessary to perform only the actions actually required by this AD. We 
recognize that, in accomplishing the requirements of any AD, operators 
may incur ``incidental'' costs in addition to the ``direct'' costs. The 
cost analysis in AD rulemaking actions, however, typically does not 
include incidental costs, such as tooling costs, the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions. Because incidental costs may vary significantly 
from operator to operator, they are almost impossible to calculate. No 
change to the final rule is necessary in this regard.

Additional Changes to Final Rule

    We have removed the reference to replacement of ``all 16'' H-11 
steel bolts specified in paragraph (f) of this final rule (paragraph 
(e) of the proposed AD), as some of the replacements may have been made 
before the effective date of this final rule. Paragraph (f) now 
specifies replacement of ``all'' H-11 steel bolts.
    There is a typographical error in the reference to the Maintenance 
Planning Document (MPD) Item numbers specified in paragraphs (a)(1) and 
(a)(2) of AD 2001-19-04 and restated in the proposed AD. MPD Items 
5380-311-021 and 5380-312-021, as specified in both paragraphs, should 
be referenced as MPD Items 5380-311-02I and 5380-312-02I. Paragraphs 
(a)(1) and (a)(2) of this final rule have been changed accordingly.

[[Page 28706]]

    Paragraph (g)(2) of the proposed AD (paragraph (h)(2) of this final 
rule) should have included a reference to paragraphs (a) and (b) in the 
approval of previously granted alternative methods of compliance with 
AD 2001-19-04, amendment 39-12444. Paragraph (h)(2) of this final rule 
has been changed accordingly.
    Because the language in Note 3 of the proposed AD is regulatory in 
nature, that note has been redesignated as paragraph (e) of this final 
rule, and subsequent paragraphs have been reordered accordingly.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes previously 
described. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    There are approximately 549 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 221 airplanes of U.S. registry 
will be affected by this AD.
    The actions that are currently required by AD 2001-19-04 take 
approximately 2 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Based on these figures, the cost 
impact of the currently required actions is estimated to be $120 per 
airplane.
    The inspections that are required in this AD action take 
approximately 1 work hour per airplane to accomplish, at an average 
labor rate of $60 per work hour. Based on these figures, the cost 
impact of the inspections on U.S. operators is estimated to be $13,260, 
or $60 per airplane.
    The replacement that is required in this AD action takes 
approximately 8 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Required parts will cost approximately 
$6,528 per airplane. Based on these figures, the cost impact of the 
replacement on U.S. operators is estimated to be $1,548,768, or $7,008 
per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the requirements of this 
AD action, and that no operator would accomplish those actions in the 
future if this AD were not adopted. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

Regulatory Impact

    The regulations adopted herein will 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under 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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. Section 39.13 is amended by removing amendment 39-12444 (66 FR 
48538, September 21, 2001), and by adding a new airworthiness directive 
(AD), amendment 39-13156, to read as follows:

2003-10-11 Boeing: Amendment 39-13156. Docket 2002-NM-10-AD. 
Supersedes AD 2001-19-04, Amendment 39-12444.

    Applicability: Model 767-200 and -300 series airplanes, line 
numbers 1 through 574 inclusive; certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (h)(1) 
of this AD. The request should include an assessment of the effect 
of the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To find and fix corroded, cracked, or broken barrel nuts that 
attach the vertical fin to body section 48, which could result in 
reduced structural integrity of the vertical fin attachment joint, 
loss of the vertical fin, and consequent loss of controllability of 
the airplane; accomplish the following:

Restatement of Requirements of AD 2001-19-04

Internal/External Detailed Inspections

    (a) Do internal and external detailed inspections of the barrel 
nuts at the 16 locations that attach the vertical fin to body 
section 48 to find discrepancies (i.e., cracked or damaged sealant, 
signs of corrosion damage, cracked or broken barrel nuts). Do the 
inspections at the times specified in paragraphs (a)(1) and (a)(2) 
of this AD, as applicable; per Part 1 of the Accomplishment 
Instructions of Boeing Service Bulletin 767-53-0085, dated May 14, 
1998; Boeing Alert Service Bulletin 767-53A0085, Revision 1, dated 
July 1, 1999; or Boeing Service Bulletin 767-53A0085, Revision 2, 
dated May 2, 2002.

    Note 2: For the purposes of this AD, a detailed inspection is 
defined as: ``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.''

    (1) For airplanes on which the inspections specified in 
paragraph (a) of this AD have been done within the last 3 years per 
Boeing 767 Maintenance Planning Document (MPD) D622T001, Items 5380-
311-02I and 5380-312-02I: Do the inspections at the later of the 
times specified in paragraphs (a)(1)(i) and (a)(1)(ii) of this AD.
    (i) Within 3 years or 6,000 flight cycles after doing the most 
recent inspection per the MPD, whichever comes first.
    (ii) Within 45 days after October 9, 2001 (the effective date AD 
2001-19-04, amendment 39-12444).
    (2) For airplanes on which the inspections specified in 
paragraph (a) of this AD have not been done within the last 3 years 
per Boeing 767 MPD D622T001, Items 5380-311-02I and 5380-312-02I: Do 
the inspections within 45 days after October 9, 2001.

[[Page 28707]]

Follow-On Actions

    (b) If no discrepancy is found during any inspection specified 
in paragraph (a) of this AD: Before further flight, do a torque 
check of each of the 16 bolts in the barrel nuts that attach the 
vertical fin to body section 48 to determine if any bolt turns, per 
Part 2 of the Accomplishment Instructions of Boeing Service Bulletin 
767-53-0085, dated May 14, 1998; Boeing Alert Service Bulletin 767-
53A0085, Revision 1, dated July 1, 1999; or Boeing Service Bulletin 
767-53A0085, Revision 2, dated May 2, 2002.
    (1) If no bolt turns: Repeat the inspections required by 
paragraph (a) of this AD (and applicable follow-on actions) every 3 
years or 6,000 flight cycles, whichever comes first; until 
paragraphs (d) and (e) of this AD are done.
    (2) If any bolt turns: Before further flight, do the actions 
specified in paragraphs (b)(2)(i) and (b)(2)(ii) of this AD, as 
applicable. Then repeat the inspections required by paragraph (a) of 
this AD (and applicable follow-on actions) every 3 years or 6,000 
flight cycles, whichever comes first; until paragraphs (d) and (e) 
of this AD are done.
    (i) For all airplanes: Replace the barrel nut at that bolt with 
a new, Inconel barrel nut per Part 3 of the Accomplishment 
Instructions of the service bulletin. No further action is required 
for that barrel nut only.
    (ii) For Group 1 airplanes: If an H-11 steel alloy bolt is 
installed with the affected barrel nut, replace the bolt with a new, 
Inconel bolt per Figure 5 of the Accomplishment Instructions of the 
service bulletin. No further action is required for that bolt only.
    (c) If any discrepancy of any barrel nut is found during any 
inspection specified in paragraph (a) or (d) of this AD: Before 
further flight, do the actions specified in paragraphs (c)(1) and 
(c)(2) of this AD, as applicable.
    (1) For all airplanes: Replace the affected barrel nut with a 
new, Inconel barrel nut per Part 3 of the Accomplishment 
Instructions of Boeing Service Bulletin 767-53-0085, dated May 14, 
1998; Boeing Alert Service Bulletin 767-53A0085, Revision 1, dated 
July 1, 1999; or Boeing Service Bulletin 767-53A0085, Revision 2, 
dated May 2, 2002. No further action is required for that barrel nut 
only.
    (2) For Group 1 airplanes: If an H-11 steel alloy bolt is 
installed with the affected barrel nut, replace the bolt with a new, 
Inconel bolt per Figure 5 of the Accomplishment Instructions of the 
service bulletin. No further action is required for that bolt only.

New Requirements of This AD

Detailed Inspection/Torque Check

    (d) Within 36 months after the last inspections done per 
paragraphs (a) and (b) of this AD, or within 180 days after the 
effective date of this AD, whichever is later: Do internal and 
external detailed inspections and a torque check (between 3,700 and 
4,100 inch-pounds of torque) of the 16 locations that attach the 
vertical fin to body section 48, and that have H-11 steel alloy 
barrel nuts or bolts, to find discrepancies (i.e., cracked or 
damaged sealant, signs of corrosion damage, and cracked or broken 
barrel nuts), per Boeing Service Bulletin 767-53A0085, Revision 2, 
dated May 2, 2002; or Revision 3, dated November 21, 2002. Repeat 
the inspections and check after that at least every 18 months until 
paragraph (f) of this AD is done.

Credit for Actions Done Previously

    (e) Accomplishment of inspections and torque checks before the 
effective date of this AD per Boeing Service Bulletin 767-53-0085, 
dated May 14, 1998; or Boeing Alert Service Bulletin 767-53A0085, 
Revision 1, dated July 1, 1999; is considered acceptable for 
compliance with the applicable actions specified in paragraphs (a) 
and (b) of this AD only.

Terminating Action

    (f) Within 36 months after the effective date of this AD: 
Replace all H-11 steel alloy barrel nuts and bolts that attach the 
vertical fin to body section 48 with Inconel barrel nuts and bolts, 
per Boeing Service Bulletin 767-53-0085, dated May 14, 1998; Boeing 
Alert Service Bulletin 767-53A0085, Revision 1, dated July 1, 1999; 
Boeing Service Bulletin 767-53A0085, Revision 2, dated May 2, 2002; 
or Revision 3, dated November 21, 2002. Such replacement ends the 
repetitive inspections required by this AD.

Part Installation

    (g) As of the effective date of this AD: No person shall 
install, on any airplane, an Inconel vertical fin attach bolt, 
unless an Inconel barrel nut is installed at the same location; nor 
shall any person install an H-11 steel alloy attachment nut or bolt 
on the vertical fin on any airplane.

Alternative Methods of Compliance

    (h)(1) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Seattle Aircraft Certification 
Office (ACO), FAA. Operators shall submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Seattle ACO.
    (2) Alternative methods of compliance, approved previously in 
accordance with AD 2001-19-04, amendment 39-12444, are approved as 
alternative methods of compliance with paragraphs (a) and (b) of 
this AD.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.

Special Flight Permits

    (i) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.

Incorporation by Reference

    (j) Unless otherwise specified in this AD, the actions shall be 
done in accordance with Boeing Service Bulletin 767-53-0085, dated 
May 14, 1998; Boeing Alert Service Bulletin 767-53A0085, Revision 1, 
dated July 1, 1999; Boeing Service Bulletin 767-53A0085, Revision 2, 
dated May 2, 2002; or Boeing Service Bulletin 767-53A0085, Revision 
3, dated November 21, 2002; as applicable.
    (1) The incorporation by reference of Boeing Service Bulletin 
767-53A0085, Revision 2, dated May 2, 2002; and Boeing Service 
Bulletin 767-53A0085, Revision 3, dated November 21, 2002; is 
approved by the Director of the Federal Register in accordance with 
5 U.S.C. 552(a) and 1 CFR part 51.
    (2) The incorporation by reference of Boeing Service Bulletin 
767-53-0085, dated May 14, 1998; and Boeing Alert Service Bulletin 
767-53A0085, Revision 1, dated July 1, 1999; was approved previously 
by the Director of the Federal Register as of October 9, 2001 (66 FR 
48538, September 21, 2001).
    (3) Copies may be obtained from Boeing Commercial Airplane 
Group, P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be 
inspected at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., Suite 700, Washington, DC.

Effective Date

    (k) This amendment becomes effective on July 1, 2003.

    Issued in Renton, Washington, on May 16, 2003.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-12844 Filed 5-23-03; 8:45 am]
BILLING CODE 4910-13-P