[Federal Register Volume 69, Number 158 (Tuesday, August 17, 2004)]
[Rules and Regulations]
[Pages 51002-51007]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-17984]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-NM-186-AD; Amendment 39-13768; AD 2004-16-12]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes three existing airworthiness 
directives (AD); applicable to certain Boeing Model 767-200, -300, and 
-300F series airplanes. One AD currently requires modification of the 
nacelle strut and wing structure for certain Boeing Model 767-200, --
300, and --300F series airplanes powered by Pratt & Whitney engines. 
The second AD currently requires a similar modification for certain 
Boeing Model 767-200, -300, and -300F series airplanes powered by 
General Electric engines. The third AD currently requires repetitive 
inspections for cracking of the outboard pitch load fittings of the 
wing front spar, and corrective action if necessary, for certain Boeing 
Model 767-200 series airplanes. The third AD also provides a 
terminating action for the repetitive inspections, which is optional 
for uncracked pitch load fittings. This amendment requires, for 
airplanes subject to the first and second existing ADs on which certain 
modifications have been accomplished previously, reworking the aft 
pitch load fitting, and installing a new diagonal brace fuse pin. This 
amendment also requires, for airplanes subject to the third existing 
AD, replacing the outboard pitch load fitting of the wing front spar 
with a new, improved fitting, which terminates certain currently 
required repetitive inspections. The actions specified by this 
amendment are intended to prevent fatigue cracking in primary strut 
structure, which could result in separation of the strut and engine 
from the airplane. This action is intended to address the identified 
unsafe condition.

DATES: Effective September 21, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 21, 2004.
    The incorporation by reference of Boeing Service Bulletin 767-
57A0070, Revision 1, dated November 16, 2000, was approved previously 
by the Director of the Federal Register as of May 14, 2001 (66 FR 
21069, April 27, 2001).
    The incorporation by reference of Boeing Service Bulletin 767-54-
0081, dated July 29, 1999, was approved previously by the Director of 
the Federal Register as of May 7, 2001 (66 FR 17492, April 2, 2001).
    The incorporation by reference of certain publications, as listed 
in the regulations, was approved previously by the Director of the 
Federal Register as of March 5, 2001 (66 FR 8085, January 29, 2001).
    The incorporation by reference of certain other publications, as 
listed in the regulations, was approved previously by the Director of 
the Federal Register as of October 17, 2000 (65 FR 58641, October 2, 
2000).
    The incorporation by reference of Boeing Service Bulletin 767-57-
0053, Revision 2, dated September 23, 1999, was approved previously by 
the Director of the Federal Register as of July 24, 2000 (65 FR 37843, 
June 19, 2000).

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Airplanes, 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 National 
Archives and Records Administration (NARA). For information on the 
availability of this material at NARA, call (202) 741-6030, or go to: 
http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

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 the following ADs 
was published in the Federal Register on February 11, 2004 (69 FR 
6587):
     AD 2001-02-07, amendment 39-12091 (66 FR 8085, January 29, 
2001), which is applicable to certain Boeing Model 767-200, -300, and -
300F series airplanes powered by Pratt & Whitney engines.
     AD 2001-06-12, amendment 39-12159 (66 FR 17492, April 2, 
2001), applicable to certain Boeing Model 767-200, -300, and -300F 
series airplanes powered by General Electric engines.

[[Page 51003]]

     AD 2001-08-23, amendment 39-12200 (66 FR 21069, April 27, 
2001), applicable to certain Boeing Model 767-200 series airplanes.
    The action proposed to continue to require modification of the 
nacelle strut and wing structure, as currently required by AD 2001-02-
07 and AD 2001-06-12. The action also proposed to continue to require 
repetitive inspections for cracking of the outboard pitch load fittings 
of the wing front spar, and corrective action if necessary, as 
currently required by AD 2001-08-23. The action also proposed to 
continue to provide a terminating action for the repetitive 
inspections, which is optional for uncracked pitch load fittings. For 
certain airplanes on which certain modifications have been accomplished 
previously, the action proposed to add new requirements for reworking 
the aft load pitch fitting, and installing a new diagonal brace fuse 
pin. For certain other airplanes, the action proposed to add a new 
requirement for replacing the outboard pitch load fitting of the wing 
front spar with a new, improved fitting on the left- and right-hand 
sides of the airplane, which would terminate repetitive inspections 
currently required by AD 2001-08-23.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. The FAA has duly considered the single 
comment received.

Request To Clarify Required Actions

    The commenter states that the Accomplishment Instructions of Boeing 
Service Bulletin 767-54-0081, Revision 1, dated February 7, 2002, 
specify installing a new pitch load fitting with a new part number. The 
commenter states that the Accomplishment Instructions do not specify 
reworking the aft load pitch fitting, as stated in the ``Differences 
Between Proposed AD and Service Bulletins'' section of the proposed AD. 
The commenter requests that we revise the proposed AD to clarify that 
any operator that has accomplished the strut improvement modification 
per the original issue of Boeing Service Bulletin 767-54-0081, dated 
July 29, 1999, must accomplish the additional rework in Boeing Service 
Bulletin 767-54-0081, Revision 1. The commenter notes that this is 
supported by ``Note 7 (1)'' of the proposed AD, which indicates that no 
further action is needed if aft pitch load fittings with certain part 
numbers are installed.
    We do not agree with the commenter's statement that the 
Accomplishment Instructions in Revision 1 of the service bulletin do 
not specify reworking the aft load pitch fitting. The commenter is 
correct that the Accomplishment Instructions do specify installing a 
new pitch load fitting with a new part number for airplanes not 
modified per the original issue of the service bulletin. However, 
Paragraph CB. under ``Additional Work Required--Group 3 through 12 
Airplanes'' in the Accomplishment Instructions of the service bulletin 
specifies reworking the affected aft pitch load fitting and installing 
the diagonal brace with a new fuse pin for airplanes with an aft pitch 
load fitting with certain part numbers.
    However, we agree that clarifying paragraph (l) of this AD would be 
helpful. (We note that the paragraph that the commenter identifies as 
``Note 7 (1)'' is actually paragraph (l) of this AD--with a (lower-
case) letter ``L,'' not with a number ``1.'' Paragraph (l) is 
independent from Note 7.) Paragraph (d) of this AD requires that strut 
modifications performed after the effective date of this AD be done per 
Revision 1 of that service bulletin. The requirements of paragraph (l) 
of this AD should apply only to airplanes that have been modified 
before the effective date of this AD per the original issue of Boeing 
Service Bulletin 767-54-0081. We recognize that the wording in 
paragraph (l) of the proposed AD could inadvertently require extra work 
for any operator who accomplished Revision 1 of the service bulletin 
before the effective date of this AD. This was not our intent. 
Therefore, for clarification, we have revised paragraph (l) of this AD 
to apply only to subject airplanes ``on which the modification required 
by paragraph (d) of this AD has been accomplished per the original 
issue of Boeing Service Bulletin 767-54-0081. * * *''

Conclusion

    After careful review of the available data, including the comment 
noted above, we have determined that air safety and the public interest 
require the adoption of the rule as proposed.

Cost Impact

    There are approximately 619 airplanes of the affected design in the 
worldwide fleet. We estimate that 255 airplanes of U.S. registry will 
be affected by this AD.
    The following table shows the estimated costs associated with the 
actions currently required by ADs 2001-02-07, 2001-06-12, and 2001-08-
23, at an average labor rate of $65 per work hour:

                                                    Estimated Cost Impact--Actions Currently Required
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                               Number of
                                                affected
     Actions in Boeing service bulletin          U.S.-       Work hours               Parts cost            Cost per airplane          Fleet cost
                                               registered
                                               airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
76-54-0080..................................           86  \1\1,423-1,519  Free...........................    $92,495-$98,735      $7,954,570-$8,491,210
767-54-0081.................................          169        \1\1,474  Free...........................             95,810                 16,191,890
767-54-0069.................................          249             106  Free...........................              6,890                  1,715,610
767-54-0083.................................          228               1  Free...........................                 65                     14,820
767-54-0088.................................          255               2  Free...........................                130                     33,150
767-54A0094.................................          117              20  Free...........................              1,300                    152,100
767-57-0053.................................          255               5  None...........................                325                     82,875
767-29-0057.................................          200              16  Free...........................              1,040                    208,000
767-57A0070.................................           67               4  None...........................             \2\260                 \2\17,420
--------------------------------------------------------------------------------------------------------------------------------------------------------
\1\ Including time for gaining access and closing up.)
\2\ Per inspection cycle.

    For affected airplanes, the new inspection to determine the part 
number of the aft load pitch fittings that is required by this AD will 
take approximately 1 work hour per airplane to accomplish, at an 
average labor rate of $65 per work hour. Based on these figures, the 
cost impact of this

[[Page 51004]]

requirement is estimated to be $65 per airplane.
    For affected airplanes, the new replacement of the outboard pitch 
load fittings that is required by this AD takes approximately 14 work 
hours per airplane to accomplish, at an average labor rate of $65 per 
work hour. Required parts cost approximately $14,438 per airplane. 
Based on these figures, the cost impact of this requirement is 
estimated to be $15,348 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the current or proposed 
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; however, as noted 
previously, time to gain access and close up has been included for 
certain actions in this AD.

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 amendments 39-12091 (66 FR 
8085, January 29, 2001), 39-12159 (66 FR 17492, April 2, 2001), and 39-
12200 (66 FR 21069, April 27, 2001); and by adding a new airworthiness 
directive (AD), amendment 39-13768, to read as follows:

2004-16-12 Boeing: Amendment 39-13768. Docket 2002-NM-186-AD. 
Supersedes AD 2001-02-07, Amendment 39-12091; AD 2001-06-12, 
Amendment 39-12159; and AD 2001-08-23, Amendment 39-12200.

    Applicability: Model 767-200, -300, and -300F series airplanes; 
certificated in any category; line numbers (L/Ns) 1 through 663 
inclusive; powered by Pratt & Whitney or General Electric engines.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent fatigue cracking in primary strut structure, which 
could result in separation of the strut and engine from the 
airplane, accomplish the following:

Requirements of AD 2001-02-07

Modifications

    (a) For Model 767-200, -300, and -300F series airplanes powered 
by Pratt & Whitney engines, L/Ns 1 through 663 inclusive: When the 
airplane has reached the flight cycle threshold as defined by the 
flight cycle threshold formula described in Figure 1 of Boeing 
Service Bulletin 767-54-0080, dated October 7, 1999, or Revision 1, 
dated May 9, 2002; or within 20 years since the date of manufacture; 
whichever occurs first; modify the nacelle strut and wing structure 
on both the left-hand and right-hand sides of the airplane, in 
accordance with the service bulletin. Use of the flight cycle 
threshold formula described in Figure 1 of the service bulletin is 
an acceptable alternative to the 20-year threshold, provided the 
corrosion prevention and control program inspections, as described 
in paragraphs 1 and 2 of Figure 1, have been met. As of the 
effective date of this AD, only Revision 1 of the service bulletin 
may be used.
    (b) For Model 767-200, -300, and -300F series airplanes powered 
by Pratt & Whitney engines, L/Ns 1 through 663 inclusive: Prior to 
or concurrently with the accomplishment of the modification of the 
nacelle strut and wing structure required by paragraph (a) of this 
AD; as specified in paragraph 1.D., Table 2, of Boeing Service 
Bulletin 767-54-0080, dated October 7, 1999, or Revision 1, dated 
May 9, 2002; accomplish the actions specified in Boeing Service 
Bulletins 767-54-0069, Revision 1, dated January 29, 1998, or 
Revision 2, dated August 31, 2000; 767-54-0083, dated September 17, 
1998; 767-54-0088, Revision 1, dated July 29, 1999; 767-54A0094, 
Revision 1, dated September 16, 1999, or Revision 2, dated February 
7, 2002; 767-57-0053, Revision 2, dated September 23, 1999; and 767-
29-0057, dated December 16, 1993, including Notice of Status Change 
NSC 1, dated November 23, 1994; or Revision 1, dated August 14, 
2003; as applicable; in accordance with those service bulletins. 
Accomplishment of this paragraph constitutes terminating action for 
the repetitive inspections required by AD 94-11-02, amendment 39-
8918; AD 2000-07-05, amendment 39-11659; and AD 2000-12-17, 
amendment 39-11795.

    Note 1: Paragraph (b) of this AD specifies prior or concurrent 
accomplishment of Boeing Service Bulletin 767-57-0053, Revision 2, 
dated September 23, 1999; however, Table 2 of Boeing Service 
Bulletin 767-54-0080, dated October 7, 1999, specifies prior or 
concurrent accomplishment of the original issue of the service 
bulletin. Therefore, accomplishment of the applicable actions 
specified in Boeing Service Bulletin 767-57-0053, dated June 27, 
1996, or Revision 1, dated October 31, 1996, prior to the effective 
date of this AD, is considered acceptable for compliance with the 
actions in Boeing Service Bulletin 767-57-0053 required by paragraph 
(b) of this AD.

Repair

    (c) For Model 767-200, -300, and -300F series airplanes powered 
by Pratt & Whitney engines, L/Ns 1 through 663 inclusive: If any 
damage (corrosion or cracking) to the airplane structure is found 
during the accomplishment of the modification required by paragraph 
(a) of this AD; and the service bulletin specifies to contact Boeing 
for appropriate action: Prior to further flight, repair in 
accordance with a method approved by the Manager, Seattle Aircraft 
Certification Office (ACO), FAA; or in accordance with data meeting 
the type certification basis of the airplane approved by a Boeing 
Company Designated Engineering Representative (DER) who has been 
authorized by the FAA 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.

Requirements of AD 2001-06-12

Modification

    (d) For Model 767-200, -300, and -300F series airplanes powered 
by General Electric engines, L/Ns 1 through 663 inclusive: Modify 
the nacelle strut and wing structure on both the left-hand and 
right-hand sides of the airplane, in accordance with Boeing Service 
Bulletin 767-54-0081, dated July 29, 1999; or Revision 1, dated 
February 7, 2002; at the later of the times specified in paragraphs 
(d)(1) and (d)(2) of this AD. After the effective date of this AD, 
only Revision 1 may be used.

[[Page 51005]]

    (1) Prior to the accumulation of 37,500 total flight cycles, or 
within 20 years since date of manufacture, whichever occurs first. 
Use of the optional threshold formula described in Figure 1 of the 
service bulletin is an acceptable alternative to the 20-year 
threshold provided that the conditions specified in Figure 1 of the 
service bulletin are met. For the optional threshold formula in 
Figure 1 to be used, actions in the service bulletins listed in Item 
2 of Figure 1 must be accomplished no later than 20 years since the 
airplane's date of manufacture.
    (2) Within 3,000 flight cycles after May 7, 2001 (the effective 
date of AD 2001-06-12).
    (e) For Model 767-200, -300, and -300F series airplanes powered 
by General Electric engines, L/Ns 1 through 663 inclusive: Prior to 
or concurrently with the accomplishment of the modification of the 
nacelle strut and wing structure required by paragraph (d) of this 
AD; as specified in paragraph 1.D., Table 2, ``Prior or Concurrent 
Service Bulletins,'' of Boeing Service Bulletin 767-54-0081, dated 
July 29, 1999; or Revision 1, dated February 7, 2002; accomplish the 
actions specified in Boeing Service Bulletin 767-29-0057, dated 
December 16, 1993, or Revision 1, dated August 14, 2003; Boeing 
Service Bulletin 767-54-0069, Revision 1, dated January 29, 1998, or 
Revision 2, dated August 31, 2000; Boeing Service Bulletin 767-54-
0083, dated September 17, 1998; Boeing Service Bulletin 767-54-0088, 
Revision 1, dated July 29, 1999; Boeing Service Bulletin 767-
54A0094, Revision 1, dated September 16, 1999, or Revision 2, dated 
February 7, 2002; and Boeing Service Bulletin 767-57-0053, Revision 
2, dated September 23, 1999; as applicable, in accordance with those 
service bulletins.

    Note 2: AD 2000-12-17, amendment 39-11795, requires 
accomplishment of Boeing Service Bulletin 767-57-0053, Revision 2, 
dated September 23, 1999. However, inspections and rework 
accomplished in accordance with Boeing Service Bulletin 767-57-0053, 
Revision 1, dated October 31, 1996, are acceptable for compliance 
with the applicable actions required by paragraph (e) of this AD.


    Note 3: AD 2000-07-05, amendment 39-11659, requires 
accomplishment of Boeing Service Bulletin 767-54A0094, dated May 22, 
1998. Inspections and rework accomplished in accordance with Boeing 
Service Bulletin 767-54A0094, dated May 22, 1998, are acceptable for 
compliance with the applicable actions required by paragraph (e) of 
this AD.


    Note 4: AD 2001-02-07, amendment 39-12091, requires 
accomplishment of Boeing Service Bulletin 767-54-0069, Revision 1, 
dated January 29, 1998, or Revision 2, dated August 31, 2000. 
Inspections and rework accomplished in accordance with those service 
bulletins are acceptable for compliance with the applicable actions 
required by paragraph (e) of this AD.

Repairs

    (f) For Model 767-200, -300 and -300F series airplanes powered 
by General Electric engines, L/Ns 1 through 663 inclusive: If any 
damage to the airplane structure is found during the accomplishment 
of the modification required by paragraph (d) of this AD, and the 
service bulletin specifies to contact Boeing for appropriate action, 
prior to further flight, repair in accordance with a method approved 
by the Manager, Seattle ACO, or a Boeing Company DER who has been 
authorized by the FAA 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.

Requirements of AD 2001-08-23

Initial and Repetitive Inspections

    (g) For Model 767-200 series airplanes, as listed in Boeing 
Service Bulletin 767-57A0070, Revision 1, dated November 16, 2000: 
Within 30 days after May 14, 2001 (the effective date of AD 2001-08-
23, amendment 39-12200), perform a high frequency eddy current 
(HFEC) inspection for cracking of the outboard pitch load fitting of 
the wing front spar, on the left-hand and right-hand sides of the 
airplane, according to Boeing Service Bulletin 767-57A0070, Revision 
1, dated November 16, 2000; Revision 2, dated August 2, 2001; or 
Revision 3, dated November 8, 2001. If no cracking is found, repeat 
the inspection at intervals not to exceed 3,000 flight cycles or 18 
months, whichever occurs first, until paragraph (i) or (m) of this 
AD is done.

    Note 5: Inspections done prior to the effective date of this AD, 
in accordance with Boeing Service Bulletin 767-57A0070, dated March 
2, 2000, as revised by Information Notice 767-57A0070 IN 01, dated 
March 23, 2000, are considered acceptable for compliance with 
paragraph (g) of this AD.

Corrective Action

    (h) For Model 767-200 series airplanes, as listed in Boeing 
Service Bulletin 767-57A0070, Revision 1, dated November 16, 2000: 
If any cracking is found during any inspection per paragraph (g) of 
this AD, prior to further flight, do paragraph (h)(1) or (h)(2) of 
this AD.
    (1) Rework the cracked outboard pitch load fitting according to 
a method approved by the Manager, Seattle ACO, or according to data 
meeting the type certification basis of the airplane approved by a 
Boeing Company DER who has been authorized by the Manager, Seattle 
ACO, to make such findings. For a rework method to be approved by 
the Manager, Seattle ACO, as required by this paragraph, the 
Manager's approval letter must specifically reference this AD.
    (2) Replace the cracked outboard pitch load fitting with a new, 
improved fitting (including removing the existing fittings, 
performing an HFEC inspection for damage of fastener holes, 
repairing damaged fastener holes, and installing new fittings of 
improved design), according to Boeing Service Bulletin 767-57A0070, 
Revision 1, dated November 16, 2000; Revision 2, dated August 2, 
2001; or Revision 3, dated November 8, 2001. Such replacement 
terminates the repetitive inspections required by paragraph (g) of 
this AD for the replaced fitting.

    Note 6: Boeing Service Bulletin 767-57A0070, Revision 1, refers 
to Boeing Service Bulletin 767-57-0053 as an additional source of 
service information for accomplishment of the replacement of the 
outboard pitch load fitting on Model 767-200 series airplanes.

Optional Terminating Action

    (i) For Model 767-200 series airplanes, as listed in Boeing 
Service Bulletin 767-57A0070, Revision 1, dated November 16, 2000: 
Replacement of the outboard pitch load fitting of the wing front 
spar with a new, improved fitting, according to Boeing Service 
Bulletin 767-57A0070, Revision 1, dated November 16, 2000; Revision 
2, dated August 2, 2001; or Revision 3, dated November 8, 2001; 
terminates the repetitive inspections required by paragraph (g) of 
this AD for the replaced fitting.

Spares

    (j) For Model 767-200 series airplanes, as listed in Boeing 
Service Bulletin 767-57A0070, Revision 1, dated November 16, 2000: 
As of May 14, 2001, no one may install on any airplane an outboard 
pitch load fitting that has a part number listed in the ``Existing 
Part Number'' column of Paragraph 2.E. of Boeing Service Bulletin 
767-57A0070, Revision 1, dated November 16, 2000.

New Requirements of This AD

Boeing Service Bulletin 767-54-0080, Revision 1, Groups 4 Through 
10: Inspection and Additional Work, if Necessary

    (k) For airplanes listed in Groups 4 through 10 of Boeing 
Service Bulletin 767-54-0080, Revision 1, dated May 9, 2002, on 
which the modification required by paragraph (a) of this AD has been 
accomplished prior to the effective date of this AD: Within 18 
months after the effective date of this AD, perform an inspection of 
the aft pitch load fitting of the wing front spar to determine the 
part number (P/N) of the fitting.
    (1) If the aft pitch load fitting on the left-hand side of the 
airplane has P/N 112T7005-57 and the aft pitch load fitting on the 
right-hand side of the airplane has P/N 112T7005-58: No further 
action is required by this paragraph.
    (2) If the aft pitch load fitting on the left-hand side of the 
airplane has P/N 112T7005-53 or the aft pitch load fitting on the 
right-hand side of the airplane has P/N 112T7005-54: Within 18 
months after the effective date of this AD, rework the affected aft 
pitch load fitting and install the diagonal brace with a new fuse 
pin, in accordance with Steps E. and F. under the heading 
``Additional Work Required--Group 4 through 10 Airplanes'' in the 
Accomplishment Instructions of the service bulletin.

    Note 7: This AD does not require the installation of new markers 
that is specified under the heading ``Additional Work Required--
Group 4 through 10 Airplanes'' in the Accomplishment Instructions of 
Boeing Service Bulletin 767-54-0080, Revision 1, dated May 9, 2002.

Boeing Service Bulletin 767-54-0081, Revision 1, Groups 3 Through 
12: Inspection and Additional Work, if Necessary

    (l) For airplanes listed in Groups 3 through 12 of Boeing 
Service Bulletin 767-54-0081,

[[Page 51006]]

Revision 1, dated February 7, 2002, on which the modification 
required by paragraph (d) of this AD has been accomplished per the 
original issue of Boeing Service Bulletin 767-54-0081, dated July 
29, 1999: Within 18 months after the effective date of this AD, 
perform an inspection of the aft pitch load fitting of the wing 
front spar to determine the P/N of the fitting.
    (1) If the aft pitch load fitting on the left-hand side of the 
airplane has P/N 112T7005-57 and the aft pitch load fitting on the 
right-hand side of the airplane has P/N 112T7005-58: No further 
action is required by this paragraph.
    (2) If the aft pitch load fitting on the left-hand side of the 
airplane has P/N 112T7005-53 or the aft pitch load fitting on the 
right-hand side of the airplane has P/N 112T7005-54: Within 18 
months after the effective date of this AD, rework the affected aft 
pitch load fitting and install the diagonal brace with a new fuse 
pin, in accordance with Steps CB. and CC. under the heading 
``Additional Work Required--Group 3 through 12 Airplanes'' in the 
Accomplishment Instructions of the service bulletin.

    Note 8: This AD does not require the installation of new markers 
that is specified under the heading ``Additional Work Required--
Group 3 through 12 Airplanes'' in the Accomplishment Instructions of 
Boeing Service Bulletin 767-54-0081, Revision 1, dated February 7, 
2002.

L/Ns 1-101 Inclusive: Replacement of Outboard Pitch Load Fitting

    (m) For Model 767-200 series airplanes having L/Ns 1 through 101 
inclusive: At the applicable time specified in paragraph (m)(1) or 
(m)(2) of this AD, replace the outboard pitch load fitting of the 
wing front spar, on the left- and right-hand sides of the airplane, 
with a new, improved fitting, in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin 767-57A0070, Revision 1, 
dated November 16, 2000; Revision 2, dated August 2, 2001; or 
Revision 3, dated November 8, 2001. Accomplishment of this 
replacement constitutes terminating action for the repetitive 
inspections required by paragraph (g) of this AD.
    (1) For airplanes on which the modification required by 
paragraph (a) or (d) of this AD, as applicable, has not been 
accomplished before the effective date of this AD: Do the 
replacement prior to or concurrently with the accomplishment of the 
modification of the nacelle strut and wing structure required by 
paragraph (a) of this AD, as specified in paragraph 1.D., Table 2, 
of Boeing Service Bulletin 767-54-0080, Revision 1, dated May 9, 
2002.
    (2) For airplanes on which the modification required by 
paragraph (a) or (d) of this AD, as applicable, has been 
accomplished before the effective date of this AD: Do the 
replacement within 48 months after the effective date of this AD.

Alternative Methods of Compliance

    (n)(1) In accordance with 14 CFR 39.19, the Manager, Seattle 
ACO, is authorized to approve alternative methods of compliance 
(AMOCs) for this AD.
    (2) An AMOC that provides an acceptable level of safety may be 
used for a repair required by this AD, if it is approved by a Boeing 
Company DER who has been authorized by the Manager, Seattle ACO, to 
make such findings.
    (3) AMOCs approved previously per AD 2001-02-07, amendment 39-
12091, are approved as alternative methods of compliance with the 
applicable actions in paragraphs (a), (b), and (c) of this AD.
    (4) AMOCs approved previously per AD 2001-06-12, amendment 39-
12159, are approved as alternative methods of compliance with the 
applicable actions in paragraphs (d), (e), and (f) of this AD.
    (5) AMOCs approved previously in accordance with AD 2000-12-17, 
amendment 39-11795; AD 2000-07-05, amendment 39-11659; AD 2001-02-
07, amendment 39-12091; and AD 94-11-02, amendment 39-8918; are 
approved as alternative methods of compliance with the applicable 
actions in paragraph (e) of this AD.
    (6) AMOCs approved previously per AD 2001-08-23, amendment 39-
12200, are approved as alternative methods of compliance with the 
applicable actions in paragraphs (g), (h), and (i) of this AD.

Incorporation by Reference

    (o) Unless otherwise specified in this AD, the actions shall be 
done in accordance with the Boeing Service Bulletins listed in Table 
1 of this AD, as applicable.

      Table 1.--Boeing Service Bulletins Incorporated by Reference
------------------------------------------------------------------------
      Service bulletin            Revision                Date
------------------------------------------------------------------------
767-29-0057.................  Original.......  December 16, 1993.
767-29-0057 NSC 1...........  Original.......  November 23, 1994.
767-29-0057.................  1..............  August 14, 2003.
767-54-0069.................  1..............  January 29, 1998.
767-54-0069.................  2..............  August 31, 2000.
767-54-0080.................  Original.......  October 7, 1999.
767-54-0080, Including        1..............  May 9, 2002.
 Appendices A, B, and C.
767-54-0081.................  Original.......  July 29, 1999.
767-54-0081, Including        1..............  February 7, 2002.
 Appendices A, B, C, and D.
767-54-0083.................  Original.......  September 17, 1998.
767-54-0088.................  1..............  July 29, 1999.
767-54A0094.................  1..............  September 16, 1999.
767-54A0094.................  2..............  February 7, 2002.
767-57-0053.................  2..............  September 23, 1999.
767-57A0070.................  1..............  November 16, 2000.
767-57A0070.................  2..............  August 2, 2001.
767-57A0070.................  3..............  November 8, 2001.
------------------------------------------------------------------------

    (1) The incorporation by reference of the Boeing Service 
Bulletins in Table 2 of this AD is approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51:

    Table 2.--New Boeing Service Bulletins Incorporated by Reference
------------------------------------------------------------------------
      Service bulletin            Revision                Date
------------------------------------------------------------------------
767-29-0057.................  1..............  August 14, 2003.
767-54-0080, Including        1..............  May 9, 2002.
 Appendices A, B, and C.
767-54-0081, Including        1..............  February 7, 2002.
 Appendices A, B, C, and D.
767-54A0094.................  2..............  February 7, 2002.
767-57A0070.................  2..............  August 2, 2001.

[[Page 51007]]

 
767-57A0070.................  3..............  November 8, 2001.
------------------------------------------------------------------------

    (2) The incorporation by reference of Boeing Service Bulletin 
767-57A0070, Revision 1, dated November 16, 2000, was approved 
previously by the Director of the Federal Register as of May 14, 
2001 (66 FR 21069), April 27, 2001).
    (3) The incorporation by reference of Boeing Service Bulletin 
767-54-0081, dated July 29, 1999, was approved previously by the 
Director of the Federal Register as of May 7, 2001 (66 FR 17492, 
April 2, 2001).
    (4) The incorporation by reference of the Boeing Service 
Bulletins in Table 3 of this AD was approved previously by the 
Director of the Federal Register as of March 5, 2001 (66 FR 8085, 
January 29, 2001).

 Table 3.--Boeing Service Bulletins Previously Incorporated by Reference
------------------------------------------------------------------------
      Service bulletin            Revision                Date
------------------------------------------------------------------------
767-29-0057 NSC 1...........  Original.......  November 23, 1994.
767-54-0080.................  Original.......  October 7, 1999.
767-54-0069.................  2..............  August 31, 2000.
767-54A0094.................  1..............  September 16, 1999.
------------------------------------------------------------------------

    (5) The incorporation by reference of the Boeing Service 
Bulletins in Table 4 of this AD was approved previously by the 
Director of the Federal Register as of October 17, 2000 (65 FR 
58641, October 2, 2000).

 Table 4.--Boeing Service Bulletins Previously Incorporated by Reference
------------------------------------------------------------------------
      Service bulletin            Revision                Date
------------------------------------------------------------------------
767-29-0057.................  Original.......  December 16, 1993.
767-54-0069.................  1..............  January 29, 1998.
767-54-0083.................  Original.......  September 17, 1998.
767-54-0088.................  1..............  July 29, 1999.
------------------------------------------------------------------------

    (6) The incorporation by reference of Boeing Service Bulletin 
767-57-0053, Revision 2, dated September 23, 1999, was approved 
previously by the Director of the Federal Register as of July 24, 
2000 (65 FR 37843, June 19, 2000).
    (7) Copies may be obtained from Boeing Commercial Airplanes, 
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 National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

Effective Date

    (p) This amendment becomes effective on September 21, 2004.

    Issued in Renton, Washington, on July 29, 2004.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-17984 Filed 8-16-04; 8:45 am]
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