```

[Federal Register Volume 75, Number 140 (Thursday, July 22, 2010)]
[Rules and Regulations]
[Pages 42592-42597]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-17611]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0671; Directorate Identifier 2010-NM-142-AD; 
Amendment 39-16363; AD 2010-14-18]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company 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; request for comments.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) that applies to certain Model 767-200, -300, and -300F series 
airplanes. The

[[Page 42593]]

existing AD currently requires repetitive inspections to detect 
discrepancies of the 8 aft-most fastener holes in the horizontal tangs 
of the midspar fitting of the strut, and corrective actions if 
necessary. The existing AD also requires repetitive inspections for 
cracks of the closeout angle that covers the 2 aft-most fasteners in 
the lower tang of the midspar fitting, and related investigative and 
corrective actions if necessary. The existing AD also provides an 
optional terminating action for the repetitive inspections. This new AD 
reduces the compliance times for doing the inspections. This AD results 
from reports of cracks in the midspar fitting tangs. We are issuing 
this AD to detect and correct fatigue cracking in the primary strut 
structure and reduced structural integrity of the strut, which could 
result in separation of the strut and engine.

DATES: This AD becomes effective August 6, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of August 6, 
2010.
    We must receive any comments on this AD by September 7, 2010.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Boeing 
Commercial Airplanes, Attention: Data & Services Management, P.O. Box 
3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-544-5000, 
extension 1; fax 206-766-5680; e-mail me.boecom@boeing.com; Internet 
https://www.myboeingfleet.com.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Berhane Alazar, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone 
(425) 917-6577; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Discussion

    On September 13, 2005, we issued AD 2005-19-23, amendment 39-14288 
(70 FR 55519, September 22, 2005). That AD applies to certain Boeing 
Model 767-200, -300, and -300F series airplanes. That AD 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 requires 
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 AD also 
provides an optional terminating action for the repetitive inspections. 
That AD resulted 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. The actions specified in that 
AD are intended 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.

Actions Since AD Was Issued

    Since we issued that AD, we received two reports of cracks in the 
midspar fitting tangs. The first report indicated severed upper and 
lower tangs at the aft two fastener locations in the Number 1 pylon 
inboard midspar fitting. The cracks were found during a routine check 
of a Model 767-300 airplane at approximately 92,205 total flight hours 
and 14,969 total flight cycles. This airplane had incurred 408 flight 
cycles from the previous inspection. The second report indicated cracks 
in the Number 1 pylon inboard midspar fitting lower tang, between the 
aft two fastener holes, on a Model 767-300 airplane at approximately 
94,176 total flight hours and 15,405 total flight cycles. This airplane 
had incurred 830 cycles from the previous inspection.
    AD 2005-19-23 specified repetitive inspection intervals between 
1,500 flight cycles and 16,000 flight cycles, depending on the 
inspection type and location. We have determined that the affected 
airplanes must be inspected within 400 flight cycles since the previous 
inspection and, for those airplanes that have not yet been inspected, 
the compliance time threshold of 10,000 total flight cycles specified 
in AD 2005-19-23 must be reduced to 8,000 total flight cycles. We have 
also determined that repetitive inspection intervals must be reduced to 
400 flight cycles and 6,000 flight cycles, depending on the inspection 
type.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 767-54A0101, 
Revision 5, dated June 29, 2010. We referred to Boeing Alert Service 
Bulletin 767-54A0101, Revision 4, dated February 10, 2005, for doing 
certain actions required by AD 2005-19-23. The procedures in Revision 5 
are similar to the procedures in Revision 4. Revision 5 reduces the 
compliance times for doing the procedures.
    We have also reviewed Boeing Alert Service Bulletin 767-54A0062, 
Revision 6, dated November 5, 2009; and Boeing Alert Service Bulletin 
767-54A0074, Revision 1, dated April 24, 2008; which are the latest 
versions of certain service bulletins referred to in AD 2005-19-23 as 
additional sources of guidance for doing the terminating action. Boeing 
Alert Service Bulletin 767-54A0101, Revision 5, dated June 29, 2010, 
refers to Boeing Alert Service Bulletin 767-54A0062, Revision 6, dated 
November 5, 2009; and Boeing Alert Service Bulletin 767-54A0074, 
Revision 1, dated April 24, 2008; as additional sources of guidance for 
doing the terminating action in Part 4 of the alert service bulletin.

Other Relevant Rulemaking

    The FAA has issued the following ADs that are related to the 
additional sources of guidance specified in this AD.

[[Page 42594]]

                                        Table--Other Relevant Rulemaking
----------------------------------------------------------------------------------------------------------------
                                                                 Related Boeing Service
                  AD                        Applicability               Bulletin              AD requirement
----------------------------------------------------------------------------------------------------------------
AD 2000-07-05, amendment 39-11659 (65  Certain Boeing Model     767-54A0094............  Repetitive inspections
 FR 18883, April 10, 2000).             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
                                                                                          terminating action for
                                                                                          the repetitive
                                                                                          inspections.
AD 2004-16-12, amendment 39-13768 (69  Certain Boeing Model     767-54-0069, 767-54-     Modification of the
 FR 51002, August 17, 2004).            767-200, -300, and -     0080, 767-54-0081, and   nacelle strut and wing
                                        300F series airplanes    767-54A0094.             structure. (AD 2004-16-
                                        powered by Pratt &                                12 superseded AD 2001-
                                        Whitney engines or                                02-07, Amendment 39-
                                        General Electric                                  12091 and AD 2001-06-
                                        engines.                                          12, Amendment 39-
                                                                                          12159.)
AD 2009-20-09, amendment 39-16032 (74  Certain Boeing Model     767-54A0074............  Repetitive inspections
 FR 50692, October 1, 2009).            767-200, -300, and -                              for fatigue cracking
                                        300F series airplanes.                            and corrosion of the
                                                                                          upper link fuse pin of
                                                                                          the nacelle struts,
                                                                                          and related
                                                                                          investigative and
                                                                                          corrective actions if
                                                                                          necessary.
AD 2010-03-08, amendment 39-16192 (75  Certain Boeing Model     767-54A0062,...........  Repetitive detailed and
 FR 5677, February 4, 2010).            767-200, -300, and -    767-54-0069............   eddy current
                                        300F series airplanes.                            inspections to detect
                                                                                          cracks of certain
                                                                                          midspar fuse pins, and
                                                                                          corrective action if
                                                                                          necessary. (AD 2010-03-
                                                                                          08 superseded AD 2003-
                                                                                          03-02, Amendment 39-
                                                                                          13026.)
----------------------------------------------------------------------------------------------------------------

FAA's Determination and Requirements of This AD

    The unsafe condition described previously is likely to exist or 
develop on other airplanes of the same type design. For this reason, we 
are issuing this AD to supersede AD 2005-19-23. This AD requires 
accomplishing the actions specified in Boeing Alert Service Bulletin 
767-54A0101, Revision 5, dated June 29, 2010, described previously, 
except as discussed under ``Differences Between the AD and the Service 
Bulletin.''

Differences Between the AD and the Service Bulletin

    The service bulletin specifies to contact the manufacturer for 
instructions on how to repair certain conditions, but this AD requires 
repairing those conditions in one of the following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.
    Steps 4.a. and 4.b. of Part 2 of the Work Instructions of Boeing 
Alert Service Bulletin 767-54A0101, Revision 5, dated June 29, 2010, 
specify actions if cracking is found and the hole size is either 
greater than 0.5322 inch or less than 0.5322 inch but not if the hole 
size equals 0.5322 inch. This AD specifies that if cracking is found 
and the hole size equals 0.5322 inch, then the terminating action 
specified in step 4.a. of Part 2 of the Work Instructions of Boeing 
Alert Service Bulletin 767-54A0101, Revision 5, dated June 29, 2010, 
must be accomplished.

Interim Action

    We consider this AD interim action. We are currently considering 
additional rulemaking to expand the inspection area.

FAA's Justification and Determination of the Effective Date

    Fatigue cracking in the primary strut structure could result in 
reduced structural integrity of the strut and consequent separation of 
the strut and engine. Because of our requirement to promote safe flight 
of civil aircraft and thus, the critical need to ensure the structural 
integrity of the pylon structure and midspar fittings and the short 
compliance time involved with this action, this AD must be issued 
immediately.
    Because an unsafe condition exists that requires the immediate 
adoption of this AD, we find that notice and opportunity for prior 
public comment hereon are impracticable and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments before it becomes effective. However, we invite 
you to send any written data, views, or arguments about this AD. Send 
your comments to an address listed under the ADDRESSES section. Include 
``Docket No. FAA-2010-0671; Directorate Identifier 2010-NM-142-AD'' at 
the beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of this 
AD. We will consider all comments received by the closing date and may 
amend this AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

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,

[[Page 42595]]

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 the regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this 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 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. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-14288 (70 FR 55519, September 22, 2005) and by 
adding the following new airworthiness directive (AD):

2010-14-18 The Boeing Company: Amendment 39-16363. Docket No. FAA-
2010-0671; Directorate Identifier 2010-NM-142-AD.

Effective Date

    (a) This AD becomes effective August 6, 2010.

Affected ADs

    (b) This AD supersedes AD 2005-19-23, Amendment 39-14288.

Applicability

    (c) This AD applies to The Boeing Company Model 767-200, -300, 
and -300F series airplanes, certificated in any category; as 
identified in Boeing Alert Service Bulletin 767-54A0101, Revision 5, 
dated June 29, 2010.

Subject

    (d) Air Transport Association (ATA) of America Code 54: 
Nacelles/Pylons.

Unsafe Condition

    (e) This AD results from reports of cracks in the midspar 
fitting tangs. The Federal Aviation Administration is issuing this 
AD to detect and correct 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

    (f) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

    Note 1: Notwithstanding any inspection done in accordance with 
AD 2005-19-23, inspect within the compliance times specified in this 
AD.

Initial Inspection

    (g) At the applicable time specified in paragraph (h) of this 
AD: Do the actions specified in either paragraph (g)(1) or (g)(2) of 
this AD.
    (1) Do a detailed inspection for cracking of the 8 aft-most 
fastener holes in the horizontal tangs of the midspar fitting of the 
strut, and a surface high frequency eddy current (HFEC) inspection 
for cracking of the closeout angle that covers the 2 aft-most 
fasteners in the lower tang of the midspar fitting, in accordance 
with Part 1, ``Detailed Inspection of Midspar Fitting and Surface 
High Frequency Eddy Current (HFEC) Inspection of Closeout Angle,'' 
of the Work Instructions of Boeing Alert Service Bulletin 767-
54A0101, Revision 5, dated June 29, 2010.
    (2) Do an open-hole HFEC inspection for cracking of each 
fastener hole, inspect to determine the size of each fastener hole, 
and do all applicable related investigative and corrective actions, 
in accordance with Part 2, ``Open Hole HFEC Inspection,'' of the 
Work Instructions of Boeing Alert Service Bulletin 767-54A0101, 
Revision 5, dated June 29, 2010, except as required by paragraphs 
(m) and (n) of this AD, and except as provided by paragraph (p) of 
this AD. Do all applicable related investigative and corrective 
actions before further flight.
    (h) At the applicable time specified in paragraph (h)(1) or 
(h)(2) of this AD, do the actions specified in paragraph (g) of this 
AD.
    (1) For airplanes on which an inspection (any Part 1 or Part 2 
inspection) has not been done in accordance with any service 
bulletin listed in Table 1 of this AD as of the effective date of 
this AD: Prior to the accumulation of 8,000 total flight cycles, or 
within 90 days after the effective date of this AD, whichever occurs 
later, do the actions specified in paragraph (g) of this AD.

                       Table 1--Service Bulletins
------------------------------------------------------------------------
       Service Bulletin            Revision               Date
------------------------------------------------------------------------
Boeing Alert Service Bulletin  4..............  February 10, 2005.
 767-54A0101.
Boeing Alert Service Bulletin  5..............  June 29, 2010.
 767-54A0101.
Boeing Service Bulletin 767-   2..............  January 10, 2002.
 54A0101.
Boeing Service Bulletin 767-   3..............  September 5, 2002.
 54A0101.
------------------------------------------------------------------------

     (2) For airplanes on which any inspection (any Part 1 or Part 2 
inspection) has been done in accordance with any service bulletin 
listed in Table 1 of this AD as of the effective date of this AD: 
Within 400 flight cycles after doing the most recent inspection or 
within 90 days after the effective date of this AD, whichever occurs 
later, do the actions specified in paragraph (g) of this AD.

Repetitive Inspections

    (i) If, during any detailed and surface HFEC inspection 
specified by paragraph (g)(1) of this AD, no cracking is found, do 
the actions specified in either paragraph (i)(1) or (i)(2) of this 
AD.
    (1) Repeat the inspections specified in paragraph (g)(1) of this 
AD thereafter at intervals not to exceed 400 flight cycles.
    (2) Within 400 flight cycles after doing the most recent 
inspections specified in paragraph (g)(1) of this AD, do the actions 
specified in paragraph (g)(2) of this AD and repeat thereafter at 
intervals not to exceed 6,000 flight cycles.
    (j) If, during the actions specified by paragraph (g)(2) of this 
AD, the terminating action specified in Part 4 of the Work 
Instructions of Boeing Alert Service Bulletin

[[Page 42596]]

767-54A0101, Revision 5, dated June 29, 2010, is not done, do the 
actions specified in either paragraph (j)(1) or (j)(2) of this AD.
    (1) Within 6,000 flight cycles after doing the actions specified 
in paragraph (g)(2) of this AD, do the inspections specified in 
paragraph (g)(1) of this AD and repeat the inspections thereafter at 
intervals not to exceed 400 flight cycles.
    (2) Repeat the actions specified in paragraph (g)(2) of this AD 
thereafter at intervals not to exceed 6,000 flight cycles.

Corrective Actions for Inspections Done per Paragraph (g)(1) of This AD

    (k) If, during any inspection specified by paragraph (g)(1) of 
this AD, any crack is found in the midspar fitting tangs, before 
further flight, do the actions specified in paragraph (k)(1) or 
(k)(2) of this AD.
    (1) Do the terminating action specified in Part 4 of the Work 
Instructions of Boeing Alert Service Bulletin 767-54A0101, Revision 
5, dated June 29, 2010, except as required by paragraph (m) of this 
AD. Accomplishment of this paragraph terminates the requirements of 
this AD.
    (2) Replace the midspar fitting of the strut with a new part, or 
repair in accordance with a method approved by the Manager, Seattle 
Aircraft Certification Office (ACO), FAA. Within 8,000 flight cycles 
after doing the replacement, do the actions specified in either 
paragraph (k)(2)(i) or (k)(2)(ii) of this AD.
    (i) Do the inspections specified in paragraph (g)(1) of this AD 
and repeat the inspections thereafter at intervals not to exceed 400 
flight cycles.
    (ii) Do the actions specified in paragraph (g)(2) of this AD and 
repeat the actions thereafter at intervals not to exceed 6,000 
flight cycles.
    (l) If, during any surface HFEC inspection specified by 
paragraph (g)(1) of this AD, any crack is found in the closeout 
angle, before further flight, do the open-hole HFEC inspection for 
cracking and all applicable related investigative and corrective 
actions, in accordance with Part 2, ``Open Hole HFEC Inspection,'' 
and step 4.b.(2) of Part 1, ``Detailed Inspection of Midspar Fitting 
and Surface High Frequency Eddy Current (HFEC) Inspection of 
Closeout Angle,'' of the Work Instructions of Boeing Alert Service 
Bulletin 767-54A0101, Revision 5, dated June 29, 2010, except as 
required by paragraphs (m) and (n) of this AD, and except as 
provided by paragraph (p) of this AD. If the terminating action 
specified in Part 4 of the Work Instructions of Boeing Alert Service 
Bulletin 767-54A0101, Revision 5, dated June 29, 2010, is not done, 
do the actions specified in either paragraph (l)(1) or (l)(2) of 
this AD.
    (1) Within 6,000 flight cycles after doing the actions specified 
in paragraph (l) of this AD, do the inspections specified in 
paragraph (g)(1) of this AD and repeat the inspections thereafter at 
intervals not to exceed 400 flight cycles.
    (2) Within 6,000 flight cycles after doing the actions specified 
in paragraph (l) of this AD, do the actions specified in paragraph 
(g)(2) of this AD, and repeat the actions thereafter at intervals 
not to exceed 6,000 flight cycles.

Service Bulletin Exceptions

    (m) Where Boeing Alert Service Bulletin 767-54A0101, Revision 5, 
dated June 29, 2010, specifies that the manufacturer may be 
contacted for disposition of repair conditions: Before further 
flight, accomplish the repair using a method approved in accordance 
with the procedures specified in paragraph (r) of this AD.
    (n) If, during any open-hole HFEC inspection required by 
paragraph (g)(2) or (l) of this AD, any crack is found in the 
midspar fitting and the hole size is 0.5322 inch, before further 
flight, do the terminating action specified in paragraph (k)(1) of 
this AD.

Optional Terminating Action

    (o) Doing the terminating action specified in Part 4 of the Work 
Instructions of Boeing Alert Service Bulletin 767-54A0101, Revision 
5, dated June 29, 2010, terminates the requirements of this AD.

    Note 2:  Boeing Alert Service Bulletin 767-54A0101, Revision 5, 
dated June 29, 2010, refers to the Boeing service bulletins in Table 
2 of this AD as additional sources of guidance for doing the 
terminating action in paragraphs (k) and (o) of this AD.

                                     Table 2--Additional Sources of Guidance
----------------------------------------------------------------------------------------------------------------
    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.
767-54-0080...................  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...................  6................  November 5, 2009.  Nacelles/Pylons--Strut Attach Fuse Pins--
                                                                       Midspar Fuse Pin Inspection and
                                                                       Replacement.
767-54A0074...................  1................  April 24, 2008...  Nacelles/Pylons--Strut Attach Fuse Pins--
                                                                       Upper link Fuse Pin Inspection/
                                                                       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 2 of this 
AD are related to the ADs listed in Table 3 of this AD.

                                       Table 3--Other Relevant Rulemaking
----------------------------------------------------------------------------------------------------------------
                                                     Related Boeing
              AD                  Applicability     Service Bulletin                AD requirement
----------------------------------------------------------------------------------------------------------------
AD 2000-07-05, amendment 39-    Certain Boeing     767-54A0094......  Repetitive inspections to detect cracking
 11659.                          Model 767 series                      or damage of the forward and aft lugs of
                                 airplanes.                            the diagonal brace of the nacelle strut;
                                                                       follow-on actions, if necessary; and
                                                                       terminating action for the repetitive
                                                                       inspections.

[[Page 42597]]

 
AD 2004-16-12, amendment 39-    Certain Boeing     767-54-0069, 767-  Modification of the nacelle strut and wing
 13768.                          Model 767-200, -   54-0080, 767-54-   structure.
                                 300, and -300F     0081, and 767-
                                 series airplanes   54A0094.
                                 powered by Pratt
                                 & Whitney
                                 engines or
                                 General Electric
                                 engines.
AD 2009-20-09, amendment 39-    Certain Boeing     767-54A0074......  Repetitive inspections for fatigue
 16032.                          Model 767-200, -                      cracking and corrosion of the upper link
                                 300, and -300F                        fuse pin of the nacelle struts, and
                                 series airplanes.                     related investigative and corrective
                                                                       actions if necessary.
AD 2010-03-08, amendment 39-    Certain Boeing     767-54A0062, 767-  Repetitive detailed and eddy current
 16192.                          Model 767-200, -   54-0069.           inspections to detect cracks of certain
                                 300, and -300F                        midspar fuse pins, and corrective action
                                 series airplanes.                     if necessary.
----------------------------------------------------------------------------------------------------------------

Optional Corrective Action for Paragraph (g)(2) or (l) of This AD

    (p) In lieu of doing the related investigative and corrective 
actions required by paragraph (g)(2) or (l) of this AD, before 
further flight, replace the midspar fitting of the strut with a new 
part, or repair in accordance with a method approved by the Manager, 
Seattle Aircraft Certification Office (ACO), FAA. Within 8,000 
flight cycles after doing any replacement, do the actions specified 
in either paragraph (p)(1) or (p)(2) of this AD.
    (1) Do the inspections specified in paragraph (g)(1) of this AD 
and repeat the inspections thereafter at intervals not to exceed 400 
flight cycles.
    (2) Do the actions specified in paragraph (g)(2) of this AD and 
repeat the actions thereafter at intervals not to exceed 6,000 
flight cycles.

Terminating Action Accomplished per Previous Issues of Service Bulletin

    (q) Doing the terminating action specified in Part 4 of the Work 
Instructions of any service bulletin listed in Table 4 of this AD 
before the effective date of this AD is acceptable for compliance 
with the requirements of this AD.

        Table 4--Credit Service Bulletins for Terminating Action
------------------------------------------------------------------------
      Service Bulletin            Revision                Date
------------------------------------------------------------------------
Boeing Alert Service          Original.......  September 23, 1999.
 Bulletin 767-54A0101.
Boeing Alert Service          4..............  February 10, 2005.
 Bulletin 767-54A0101.
Boeing Service Bulletin 767-  1..............  February 3, 2000.
 54A0101.
Boeing Service Bulletin 767-  2..............  January 10, 2002.
 54A0101.
Boeing Service Bulletin 767-  3..............  September 5, 2002.
 54A0101.
------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

    (r)(1) The Manager, Seattle Aircraft Certification Office, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. Send information to Attn: 
Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, 
Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue, SW., 
Renton, Washington 98057-3356; telephone (425) 917-6577; fax (425) 
917-6590. Information may be e-mailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office. 
The AMOC approval letter must specifically reference 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 the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that 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.

Material Incorporated by Reference

    (s) You must use Boeing Alert Service Bulletin 767-54A0101, 
Revision 5, dated June 29, 2010, to do the actions required by this 
AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 
206-544-5000, extension 1; fax 206-766-5680; e-mail 
me.boecom@boeing.com; Internet https://www.myboeingfleet.com.
    (3) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221.
    (4) You may also review copies of the service information that 
is incorporated by reference 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.

    Issued in Renton, Washington, on July 9, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-17611 Filed 7-21-10; 8:45 am]
BILLING CODE 4910-13-P
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