AD 2010-14-18 - Airworthiness Directives; The Boeing Company Model 767-200, -300, and -300F S...

Type	Manufacturer	Model	Details
aircraft	The Boeing Company	767-200 Series	Airworthiness Directives; The Boeing Company Model 767-200, -300, and -300F Series Airplanes Powered by General Electric or Pratt & Whitney Engines
aircraft	The Boeing Company	767-300 Series	Airworthiness Directives; The Boeing Company Model 767-200, -300, and -300F Series Airplanes Powered by General Electric or Pratt & Whitney Engines
aircraft	The Boeing Company	767-300F Series	Airworthiness Directives; The Boeing Company Model 767-200, -300, and -300F Series Airplanes Powered by General Electric or Pratt & Whitney Engines

Unsafe Condition

Fatigue cracking in the primary strut structure and reduced structural integrity of the strut, which could result in separation of the strut and engine.

AI-generated summary from the source AD text. Verify against the official source before acting.

Required Actions

Inspect the eight aft-most fastener holes in the horizontal tangs of the midspar fitting of the strut for discrepancies. Inspect for cracks in the closeout angle that covers the two aft-most fasteners in the lower tang of the midspar fitting. Perform investigative and corrective actions if necessary. Reduce repetitive inspection intervals to 400 flight cycles and 6,000 flight cycles, depending on the inspection type.

AI-generated summary from the source AD text. Verify against the official source before acting.

Compliance Time

Within 400 flight cycles since the previous inspection, or within 8,000 total flight cycles for airplanes that have not yet been inspected.

AI-generated summary from the source AD text. Verify against the official source before acting.

Affected Aircraft

The Boeing Company Model 767-200, -300, and -300F series airplanes powered by General Electric or Pratt & Whitney engines.

AI-generated summary from the source AD text. Verify against the official source before acting.

Federal Register Abstract

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

Document Text

Show stored source text (verify against official source)

[Federal Register Volume 75, Number 140 (Thursday, July 22, 2010)]
[Rules and Regulations]
[Pages 42592-42597]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2010-17611]

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

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:
<bullet> Federal eRulemaking Portal: Go to <a href="http://www.regulations.gov">http://www.regulations.gov</a>. Follow the instructions for submitting comments.
<bullet> Fax: 202-493-2251.
<bullet> 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.
<bullet> 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 <a href="/cdn-cgi/l/email-protection#bbd6de95d9d4ded8d4d6fbd9d4ded2d5dc95d8d4d6">[email&#160;protected]</a>; Internet
<a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.

Examining the AD Docket

You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a>; 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:
<bullet> In accordance with a method that we approve; or
<bullet> 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a>, 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: <a href="/cdn-cgi/l/email-protection#4b72660a050666182e2a3f3f272e660a0804660a06040866192e3a3e2e383f380b2d2a2a652c243d">[email&#160;protected]</a>.
(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
<a href="/cdn-cgi/l/email-protection#f49991da969b91979b99b4969b919d9a93da979b99">[email&#160;protected]</a>; Internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.
(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: <a href="http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html">http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html</a>.

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

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

Applicability

Unsafe Condition

Required Actions

Compliance Time

Affected Aircraft

Federal Register Abstract

Document Text

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