[Federal Register Volume 70, Number 183 (Thursday, September 22, 2005)]
[Rules and Regulations]
[Pages 55519-55524]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-18785]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21355; Directorate Identifier 2005-NM-037-AD; 
Amendment 39-14288; AD 2005-19-23]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 767-200, -300, and -300F 
Series Airplanes Powered by General Electric or Pratt & Whitney Engines

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

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to certain Boeing Model 767 series airplanes. That 
AD currently requires repetitive inspections to detect discrepancies of 
the eight aft-most fastener holes in the horizontal tangs of the 
midspar fitting of the strut, and corrective actions if necessary. That 
AD also provides an optional terminating action for the repetitive 
inspections.

[[Page 55520]]

This new AD adds repetitive inspections for cracks of the closeout 
angle that covers the two aft-most fasteners in the lower tang of the 
midspar fitting, and related investigative and corrective actions if 
necessary. This AD also reduces the inspection interval of the upper 
tang of the outboard midspar fitting; and provides an optional 
terminating action for the repetitive inspections. This AD results from 
a report of a crack in a closeout angle that covers the two aft-most 
fasteners in the lower tang of the midspar fitting; and the discovery 
of a crack in the lower tang of the midspar fitting under the cracked 
closeout angle. We are issuing this AD to prevent fatigue cracking in 
the primary strut structure and reduced structural integrity of the 
strut, which could result in separation of the strut and engine.

EFFECTIVE DATE: This AD becomes effective October 27, 2005.
    The Director of the Federal Register approved the incorporation by 
reference of Boeing Alert Service Bulletin 767-54A0101, Revision 4, 
dated February 10, 2005, listed in the AD as of October 27, 2005.
    On June 9, 2004 (69 FR 24947, May 5, 2004), the Director of the 
Federal Register approved the incorporation by reference of Boeing 
Service Bulletin 767-54A0101, Revision 3, dated September 5, 2002.
    On May 15, 2001 (66 FR 18523, April 10, 2001), the Director of the 
Federal Register approved the incorporation by reference of Boeing 
Service Bulletin 767-54A0101, Revision 1, dated February 3, 2000.

ADDRESSES: You may examine the AD docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif Building, 
room PL-401, Washington, DC.
    Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Candice Gerretsen, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6428; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION: 

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at http://dms.dot.gov or 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 street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 2004-09-14, amendment 
39-13603 (69 FR 24947, May 5, 2004). The existing AD applies to certain 
Model 767 series airplanes. That NPRM was published in the Federal 
Register on June 3, 2005 (70 FR 32527). That NPRM proposed to continue 
to require repetitive inspections to detect discrepancies of the eight 
aft-most fastener holes in the horizontal tangs of the midspar fitting 
of the strut, and corrective actions if necessary. That NPRM also 
proposed to require repetitive inspections for cracks of the closeout 
angle that covers the two aft-most fasteners in the lower tang of the 
midspar fitting, and related investigative and corrective actions if 
necessary. That NPRM also proposed to reduce the inspection interval of 
the upper tang of the outboard midspar fitting; and to provide an 
optional terminating action for the repetitive inspections.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments received.

Request To Remove Airplane Reference From Applicability

    The airplane manufacturer requests that we remove the reference to 
Boeing Model 767-400ER series airplanes from the applicability of the 
NPRM. The commenter points out that these airplanes have improved 
corrosion resistant steel (CRES) mid-spar fittings.
    We agree with the commenter. The Model 767-400ER series airplanes 
are not included in the effectivity of the Boeing Alert Service 
Bulletin 767-54A0101, Revision 4, dated February 10, 2005 (which was 
cited as the appropriate source of service information for doing the 
actions in the NPRM), but were inadvertently included in the 
applicability of the NPRM. We have changed the final rule to remove 
this model designation from the applicability.

Request To Include Inspection Requirements for Airplanes With CRES 
Repair Strap

    The same commenter points out that some airplanes have had the 
closeout angle previously repaired by the addition of a CRES repair 
strap. This repair strap covers two aft-most bolts of the closeout 
angle at the midspar fitting. The commenter states that the repair 
strap prevents high-frequency eddy current inspections of the closeout 
angle. The commenter requests that the final rule include inspection 
requirements for these airplanes.
    We partially agree with the commenter. We agree that additional 
inspections may be required for these airplanes. We disagree with 
including inspection requirements for these airplanes in the final 
rule. In accordance with 14 CFR 39.17, if the original airplane 
configuration is altered, modified, or repaired in any way that may 
affect the ability to accomplish the actions of an AD, the operator 
should apply for an alternative method of compliance (AMOC) through the 
FAA. Information about AMOCs is included in paragraph (q) of the final 
rule. We have not changed the final rule in this regard.

Explanation of Change Made to Paragraph (i)

    We have simplified paragraph (i) of the final rule by referring to 
the ``Alternative Methods of Compliance (AMOCs)'' paragraph of this AD 
for repair methods.

Clarification of Alternative Method of Compliance (AMOC) Paragraph

    We have revised this action to clarify the appropriate procedure 
for notifying the principal inspector before using any approved AMOC on 
any airplane to which the AMOC applies.

Conclusion

    We have carefully reviewed the available data, including the 
comments received, and determined that air safety and the public 
interest require adopting the AD with the changes described previously. 
We have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this AD.

[[Page 55521]]



                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                              Average                                           Number of
                                     Work      labor                                              U.S.-
             Action                 hours     rate per       Parts        Cost per airplane    registered                    Fleet cost
                                                hour                                            airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Option 1: Detailed inspection             1        $65  None...........  $65, per inspection           263  N/A (depends on chosen option).
 (required by AD 2004-09-14).                                             cycle.
Option 2: HFEC inspection                 3        $65  None...........  $195, per                     263  N/A (depends on chosen option).
 (required by AD 2004-09-14).                                             inspection cycle.
HFEC inspection (new proposed             4        $65  None...........  $260, per                     263  $68,380, per inspection cycle.
 action).                                                                 inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD 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.
    For the reasons discussed above, I certify that this AD:
    (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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket. 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 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. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-13603 (69 FR 24947, May 5, 2004) and by adding 
the following new airworthiness directive (AD):

2005-19-23 Boeing: Amendment 39-14288. Docket No. FAA-2005-21355; 
Directorate Identifier 2005-NM-037-AD.

Effective Date

    (a) This AD becomes effective October 27, 2005.

Affected ADs

    (b) This AD supersedes AD 2004-09-14.

Applicability

    (c) This AD applies to Boeing Model 767-200, -300, and -300F 
series airplanes, certificated in any category, as identified in 
Boeing Alert Service Bulletin 767-54A0101, Revision 4, dated 
February 10, 2005.

Unsafe Condition

    (d) This AD was prompted by a report of a crack in a closeout 
angle that covers the two aft-most fasteners in the lower tang of 
the midspar fitting; and the discovery of a crack in the lower tang 
of the midspar fitting under the cracked closeout angle. We are 
issuing this AD to prevent fatigue cracking in the primary strut 
structure and reduced structural integrity of the strut, which could 
result in separation of the strut and engine.

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.

Restatement of Requirements of AD 2004-09-14

Repetitive Inspections

    (f) Except as provided by paragraph (g) of this AD, before the 
accumulation of 10,000 total flight cycles, or within 600 flight 
cycles after May 15, 2001 (the effective date of AD 2001-07-05, 
amendment 39-12170), whichever occurs later: Accomplish the 
inspections required by paragraph (f)(1) or (f)(2) of this AD, as 
applicable.
    (1) Perform a detailed inspection of the four aft-most fastener 
holes in the horizontal tangs of the midspar fitting of the strut to 
detect cracking, in accordance with Part 1, ``Detailed Inspection,'' 
of the Accomplishment Instructions of Boeing Service Bulletin 767-
54A0101, Revision 1, dated February 3, 2000. If no cracking is 
detected, repeat the inspection thereafter at the applicable 
intervals specified in Table 1, ``Reinspection Intervals for Part 
1--Detailed Inspection'' included in Figure 1 of the service 
bulletin.

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

    (2) Perform a high frequency eddy current (HFEC) inspection of 
the four aft-most fastener holes in the horizontal tangs of the 
midspar fitting of the strut to detect discrepancies (cracking, 
incorrect fastener hole diameter), in accordance with Part 2, ``High 
Frequency Eddy Current (HFEC) Inspection,'' of the Accomplishment 
Instructions of the service bulletin. Accomplish the requirements 
specified in paragraph (f)(2)(i) or (f)(2)(ii) of this AD, as 
applicable; and repeat the inspection thereafter at the applicable 
intervals specified in Table 2, ``Reinspection Intervals for Part 
2--HFEC Inspection'' included in Figure 1 of the service bulletin.
    (i) If no cracking is detected and the fastener hole diameter is 
less than or equal to 0.5322 inch, before further flight, rework the 
hole in accordance with Part 3 of the Accomplishment Instructions of 
the service bulletin.

[[Page 55522]]

    (ii) If no cracking is detected and the fastener hole diameter 
is greater than 0.5322 inch, before further flight, accomplish the 
requirements specified in either paragraph (h)(1) or (h)(2) of this 
AD.
    (g) For airplanes on which the two aft-most fasteners have been 
inspected in accordance with Boeing Service Bulletin 767-54A0101, 
Revision 1, dated February 3, 2000, prior to May 15, 2001: Perform 
the initial inspection of the four aft-most fasteners in accordance 
with paragraph (f) of this AD before the accumulation of 10,000 
total flight cycles, or within 1,500 flight cycles after May 15, 
2001, whichever occurs later.

Corrective Actions

    (h) If any cracking is detected after accomplishment of any 
inspection required by paragraph (f) of this AD, before further 
flight, accomplish the requirements specified in either paragraph 
(h)(1) or (h)(2) of this AD.
    (1) Accomplish the terminating action specified in Part 4 of the 
Accomplishment Instructions of Boeing Service Bulletin 767-54A0101, 
Revision 1, dated February 3, 2000; Boeing Service Bulletin 767-
54A0101, Revision 3, dated September 5, 2002; or Boeing Alert 
Service Bulletin 767-54A0101, Revision 4, dated February 10, 2005. 
Accomplishment of this paragraph terminates the requirements of this 
AD. After the effective date of this AD, only Boeing Alert Service 
Bulletin 767-54A0101, Revision 4, may be used.
    (2) Replace the midspar fitting of the strut with a serviceable 
part, or repair in accordance with a method approved by the Manager, 
Seattle Aircraft Certification Office (ACO), FAA. Repeat the 
applicable inspection thereafter at the applicable time specified in 
paragraph (f)(1) or (f)(2) of this AD.
    (i) If any discrepancies (cracking, incorrect fastener hole 
diameter) are detected during any inspection required by paragraph 
(f) or (p) of this AD, for which the service bulletin specifies that 
the manufacturer may be contacted for disposition of those repair 
conditions: Before further flight, accomplish the applicable related 
investigative and corrective actions (including fastener hole rework 
and/or midspar fitting replacement) using a method approved in 
accordance with the procedures specified in paragraph (q) of this 
AD.

Additional Inspections

    (j) Prior to the accumulation of 10,000 total flight cycles, or 
within 600 flight cycles after June 9, 2004 (the effective date of 
AD 2004-09-14), whichever occurs later: Perform the inspections 
specified in paragraph (f)(1) or (f)(2) of this AD, as applicable, 
on all eight aft-most fastener holes or the four forward fastener 
holes in the group of eight aft-most fastener holes not inspected 
per paragraph (f)(1), (f)(2), or (g) of this AD. The inspection must 
be done per the Accomplishment Instructions in Boeing Service 
Bulletin 767-54A0101, Revision 3, dated September 5, 2002; or Boeing 
Alert Service Bulletin 767-54A0101, Revision 4, dated February 10, 
2005. Accomplishment of the applicable inspection on all eight aft-
most fastener holes constitutes terminating action for the 
repetitive inspection requirements of paragraphs (f)(1), (f)(2), and 
(g) of this AD.
    (k) If no cracking or discrepancy is detected during any 
detailed inspection required by paragraph (j) of this AD, repeat the 
inspections of all eight aft-most fastener holes thereafter at the 
applicable intervals specified in Table 1 of this AD.
    (l) If no cracking or discrepancy is detected during any HFEC 
inspection required by paragraph (j) of this AD or by this paragraph 
of this AD: Perform the follow-on actions specified in paragraph 
(f)(2)(i) or (f)(2)(ii) of this AD, as applicable, per the 
Accomplishment Instructions in Boeing Service Bulletin 767-54A0101, 
Revision 3, dated September 5, 2002; or Boeing Alert Service 
Bulletin 767-54A0101, Revision 4, dated February 10, 2005; and 
repeat the inspections of all eight aft-most fastener holes 
thereafter at the applicable intervals specified in Table 1 of this 
AD.

    Table 1.--Repetitive Inspection Intervals for All Eight Aft-Most
                             Fastener Holes
------------------------------------------------------------------------
             If--                        Repetitive intervals--
------------------------------------------------------------------------
(1) All eight aft-most         At the applicable intervals specified in
 fastener holes were            Table 1, ``Reinspection Intervals for
 inspected per paragraph (j)    Part 1,'' or Table 2, ``Reinspection
 of this AD:.                   Intervals for Part 2,'' as applicable.
                                Both tables are included in Figure 1 of
                                the applicable service bulletin.
                               Within 1,500 flight cycles after the
                                effective date of this AD, only the
                                repetitive intervals in Boeing Alert
                                Service Bulletin 767-54A0101, Revision
                                4, dated February 10, 2005, may be used.
(2) Only the four forward      At the next scheduled repetitive
 fastener holes in the group    inspection required by paragraph (f)(1)
 of eight aft-most fastener     of (f)(2) of this AD, as applicable.
 holes were inspected per       Thereafter at the applicable intervals
 paragraph (j) of this AD:.     specified in Table 1, ``Reinspection
                                Intervals for Part 1,'' or Table 2,
                                ``Reinspection Intervals for Part 2,''
                                as applicable. Both tables are included
                                in Figure 1 of the applicable service
                                bulletin.
                               Within 1,500 flight cycles after the
                                effective date of this AD, only the
                                repetitive intervals in Boeing Alert
                                Service Bulletin 767-54A0101, Revision
                                4, dated February 10, 2005, may be used.
------------------------------------------------------------------------

Corrective Actions for Discrepancies

    (m) If any cracking or discrepancy is detected during any 
inspection required by paragraphs (j), (k), or (l) of this AD, 
before further flight: Accomplish the corrective actions described 
in paragraph (h) of this AD, except as provided in paragraph (i) of 
this AD.

Service Bulletin Revisions

    (n) Accomplishing the terminating action in paragraph (h)(1) of 
this AD before June 9, 2004, in accordance with the service bulletin 
revisions in Table 2 of this AD, is acceptable for compliance with 
the requirements of this AD. After the effective date of this AD, 
only Boeing Alert Service Bulletin 767-54A0101, Revision 4, dated 
February 10, 2005, may be used for accomplishing the terminating 
action in paragraph (h)(1) of this AD.

                               Table 2.--Service Bulletins for Terminating Action
----------------------------------------------------------------------------------------------------------------
            Service bulletin                        Revision                              Date
----------------------------------------------------------------------------------------------------------------
Boeing Alert Service Bulletin 767-        Original...................  September 23, 1999.
 54A0101.
Boeing Service Bulletin 767-54A0101.....  2..........................  January 10, 2002.
----------------------------------------------------------------------------------------------------------------

Inspections Accomplished per Previous Issues of Service Bulletin

    (o) Inspections required by paragraphs (f) and (g) of this AD 
that are accomplished before June 9, 2004, in accordance with the 
service bulletin revisions in Table 3 of this AD are considered 
acceptable for compliance with the corresponding action specified in 
this AD.

[[Page 55523]]



                       Table 3.--Service Bulletins for Previously Accomplished Inspections
----------------------------------------------------------------------------------------------------------------
             Boeing service bulletin                Revision                          Date
----------------------------------------------------------------------------------------------------------------
Boeing Service Bulletin 767-54A0101.............            2  January 10, 2002.
Boeing Service Bulletin 767-54A0101.............            3  September 5, 2002.
Boeing Alert Service Bulletin 767-54A0101.......            4  February 10, 2005.
----------------------------------------------------------------------------------------------------------------

New Requirements of This AD

Inspections of Closeout Angle and Corrective Action

    (p) For airplanes for which the ``Reinspection Intervals for 
Part 1,'' referenced in Table 1 of paragraph (l) of this AD apply: 
At the next applicable inspection, do an HFEC inspection for cracks 
of the closeout angle that covers the two aft-most fasteners in the 
lower tang of the midspar fitting and any related investigative and 
corrective actions, by doing all the applicable actions specified in 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
767-54A0101, Revision 4, dated February 10, 2005. Repeat the 
inspection at the applicable interval in Table 1, ``Reinspection 
Intervals for Part 1,'' in Figure 1 of the alert service bulletin.

    Note 2: Boeing Alert Service Bulletin 767-54A0101, Revision 4, 
dated February 10, 2005, refers to the Boeing service bulletins in 
the Table 4 of this AD as additional sources of service information 
for doing the terminating action in paragraph (h)(1) of this AD.


                               Table 4.--Additional Sources of Service Information
----------------------------------------------------------------------------------------------------------------
      Boeing service bulletin            Revision level               Date                      Title
----------------------------------------------------------------------------------------------------------------
767-54-0052.......................  Original...............  June 11, 1992.........  Nacelles/Pylons--Strut--Aft
                                                                                      Lower Spar--Fastener
                                                                                      Corrosion--Inspection and
                                                                                      Replacement.
767-54-0061.......................  2......................  November 23, 1999.....  Nacelles/Pylons--Wing-to-
                                                                                      Strut Attach Fittings--
                                                                                      Lower Spar Bushing
                                                                                      Inspection and
                                                                                      Replacement.
767-54-0069.......................  2......................  August 31, 2000.......  Nacelles/Pylons--Midspar
                                                                                      Fitting--Underwing
                                                                                      Sideload Fitting--Fuse Pin
                                                                                      Replacement and Wing
                                                                                      Rework.
767-54-0072.......................  Original...............  March 13, 1997........  Nacelles/Pylons--Strut
                                                                                      Attach Upper Link--Upper
                                                                                      Link Inspection, Rework or
                                                                                      Replacement.
767-54-0074.......................  Original...............  March 27, 1997........  Nacelles/Pylons--Strut
                                                                                      Attach Fuse Pins--Upper
                                                                                      link Fuse Pin Inspection/
                                                                                      Replacement. Where this
                                                                                      service bulletin refers to
                                                                                      a cotter pin with part
                                                                                      number (P/N) MS25665-374,
                                                                                      the P/N should be MS24665-
                                                                                      374. Where this service
                                                                                      bulletin says, ``If no
                                                                                      crack indication is found,
                                                                                      reinstall the fuse pin,''
                                                                                      the correct statement is
                                                                                      ``If no crack indication
                                                                                      is found, continue to Step
                                                                                      F.''
767-54-0080.......................  1......................  May 9, 2002...........  Nacelles/Pylons--Pratt and
                                                                                      Whitney Powered Airplanes--
                                                                                      Nacelle Strut and Wing
                                                                                      Structure Modification.
767-54-0081.......................  1......................  February 7, 2002......  Nacelles/Pylons--General
                                                                                      Electric Powered
                                                                                      Airplanes--Nacelle Strut
                                                                                      and Wing Structure
                                                                                      Modification.
767-54A0062.......................  5......................  November 11, 2002.....  Nacelles/Pylons--Strut
                                                                                      Attach Fuse Pins--Midspar
                                                                                      Fuse Pin Inspection and
                                                                                      Replacement.
767-54A0094.......................  2......................  February 7, 2002......  Nacelles/Pylons--Strut-to-
                                                                                      Wing Attachment--Diagonal
                                                                                      Brace Inspection/Rework/
                                                                                      Replacement.
767-57-0063.......................  1......................  November 30, 2000.....  Wings--Side Load Underwing
                                                                                      Fitting--Inspection/
                                                                                      Rework.
----------------------------------------------------------------------------------------------------------------


    Note 3: Certain service bulletins referenced in Table 4 of this 
AD are related to the ADs listed in Table 5 of this AD.


                                       Table 5.--Other Relevant Rulemaking
----------------------------------------------------------------------------------------------------------------
                                                                 Related Boeing service
                  AD                        Applicability               bulletin              AD requirement
----------------------------------------------------------------------------------------------------------------
AD 94-11-02, amendment 39-8918, (59    All Boeing Model 767     767-54A0062............  Repetitive detailed
 FR 27229, May 26, 1994).               series airplanes.                                 visual and eddy
                                                                                          current inspections to
                                                                                          detect cracks of
                                                                                          certain midspar fuse
                                                                                          pins, and replacement
                                                                                          of any cracked midspar
                                                                                          fuse pin with a new
                                                                                          fuse pin.
AD 99-07-06, amendment 39-11091 (64    Certain Boeing Model     767-54A0094............  Repetitive inspections
 FR 14578, March 26, 1999).             767 series airplanes.                             to detect cracking or
                                                                                          damage of the forward
                                                                                          and aft lugs of the
                                                                                          diagonal brace of the
                                                                                          nacelle strut; follow-
                                                                                          on actions, if
                                                                                          necessary; and an
                                                                                          optional terminating
                                                                                          action for the
                                                                                          repetitive
                                                                                          inspections.
                                                                                          Superseded by AD 2000-
                                                                                          07-05.
AD 2000-07-05, amendment 39-11659 (65  Certain Boeing Model     767-54A0094............  Requires the previously
 FR 18883, April 10, 2000).             767 series airplanes.                             optional terminating
                                                                                          action of AD 99-07-06.

[[Page 55524]]

 
AD 2000-10-51, amendment 39-11770 (65  Certain Boeing Model     767-54-0074............  One-time inspection to
 FR 37011, June 13, 2000).              767 series airplances.                            determine whether
                                                                                          certain bolts are
                                                                                          installed in the side
                                                                                          load underwing
                                                                                          fittings on both
                                                                                          struts, and various
                                                                                          follow-on actions, if
                                                                                          necessary.
AD 2001-02-07, amendment 39-12091 (66  Certain Boeing Model     767-54-0069, 767-54-     Modification of the
 FR 8085, January 29, 2001).            767 series airplanes     0080, and 767-54-0094.   nacelle strut and wing
                                        powered by Pratt &                                structure. Terminates
                                        Whitney engines.                                  certain requirements
                                                                                          of AD 94-11-02.
AD 2001-06-12, amendment 39-12159 (66  Certain Boeing Model     767-54-0069, 767-54-     Modification of the
 FR 17492, April 2, 2001).              767 series airplanes     0081, and 767-54-0094.   nacelle strut and wing
                                        powered by General                                structure. Terminates
                                        Electric engines.                                 certain requirements
                                                                                          of AD 94-11-02.
AD 2003-03-02, amendment 39-13026 (68  All Boeing Model 767     767-54A0062............  Supersedes AD 94-11-02;
 FR 4374, January 29, 2003).            series airplanes.                                 Retains all
                                                                                          requirements but
                                                                                          reduces certain
                                                                                          compliance times for
                                                                                          certain inspections,
                                                                                          expands the detailed
                                                                                          and eddy current
                                                                                          inspections, and
                                                                                          limits the
                                                                                          applicability.
----------------------------------------------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

    (q)(1) The Manager, Seattle ACO, FAA, has the authority to 
approve AMOCs for this AD, if requested in accordance with the 
procedures found in 14 CFR 39.19.
    (2) AMOCs approved previously according to AD 2004-09-14, 
amendment 39-13603, are approved as AMOCs for the corresponding 
requirements of this AD.
    (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 an 
Authorized Representative for the Boeing Commercial Airplanes 
Delegation Option Authorization Organization who has been authorized 
by the Manager, Seattle ACO, to make those findings. For a repair 
method to be approved, the repair must meet the certification basis 
of the airplane, and the approval must specifically refer to this 
AD.
    (4) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Material Incorporated by Reference

    (r) You must use the service information identified in Table 6 
of this AD to perform the actions that are required by this AD, 
unless the AD specifies otherwise.

                                  Table 6.--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
                                                    Revision
                Service bulletin                     level                            Date
----------------------------------------------------------------------------------------------------------------
Boeing Service Bulletin 767-54A0101.............            1  February 3, 2000.
Boeing Service Bulletin 767-54A0101.............            3  September 5, 2002.
Boeing Alert Service Bulletin 767-54A0101.......            4  February 10, 2005.
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    (1) The Director of the Federal Register approved the 
incorporation by reference of Boeing Alert Service Bulletin 767-
54A0101, Revision 4, dated February 10, 2005, in accordance with 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) On June 9, 2004 (69 FR 24947, May 5, 2004), the Director of 
the Federal Register approved the incorporation by of Boeing Service 
Bulletin 767-54A0101, Revision 3, dated September 5, 2002.
    (3) On May 15, 2001 (66 FR 18523, April 10, 2001), the Director 
of the Federal Register approved the incorporation by reference of 
Boeing Service Bulletin 767-54A0101, Revision 1, dated February 3, 
2000.
    (4) Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for a copy of this service information. You 
may review copies at the Docket Management Facility, U.S. Department 
of Transportation, 400 Seventh Street, SW., room PL-401, Nassif 
Building, Washington, DC; on the Internet at http://dms.dot.gov; or 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at the NARA, call 
(202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on September 13, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-18785 Filed 9-21-05; 8:45 am]
BILLING CODE 4910-13-P