Airworthiness Directives; The Boeing Company Model 767-200, -300, and -300F Series Airplanes Powered by General Electric or Pratt & Whitney Engines, 42592-42597 [2010-17611]
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Federal Register / Vol. 75, No. 140 / Thursday, July 22, 2010 / Rules and Regulations
TABLE 2—CREDIT SERVICE INFORMATION—Continued
Airbus mandatory service bulletin—
Revision—
Dated—
A330–27–3152
A330–27–3152
A340–27–4151
A340–27–4152
A340–27–4152
A340–27–5040
A340–27–5040
01 .......................................................................................
02 .......................................................................................
Original ...............................................................................
Original ...............................................................................
01 .......................................................................................
Original ...............................................................................
01 .......................................................................................
March 19, 2008.
September 23, 2008.
August 9, 2007.
August 9, 2007.
March 19, 2008.
August 9, 2007.
March 19, 2008.
...................................................................
...................................................................
...................................................................
...................................................................
...................................................................
...................................................................
...................................................................
Note 1: Airbus should be contacted in
order to get appropriate information for
airplanes on which the original delivery date
of the airplane is unknown to the operator.
FAA AD Differences
Note 2: This AD differs from the MCAI
and/or service information as follows: No
differences.
Other FAA AD Provisions
(h) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Send information to ATTN: Vladimir
Ulyanov, Aerospace Engineer, International
Branch, ANM–116, FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–1138; fax (425) 227–1149. 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.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(i) Refer to MCAI EASA Airworthiness
Directive 2008–0026, dated February 12,
2008, and the service information specified
in Table 1 of this AD, for related information.
Material Incorporated by Reference
(j) You must use the service information
contained in Table 3 of this AD to do the
actions required by this AD, unless the AD
specifies otherwise.
TABLE 3—MATERIAL INCORPORATED BY REFERENCE
Airbus mandatory service bulletin—
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A330–27–3151,
A330–27–3152,
A340–27–4151,
A340–27–4152,
A340–27–5040,
including
including
including
including
including
Appendix 1
Appendices
Appendix 1
Appendices
Appendix 1
Revision—
....................................................................................................
1 and 2 ......................................................................................
....................................................................................................
1 and 2 ......................................................................................
....................................................................................................
(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 Airbus SAS—Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80, e-mail
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.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: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
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Dated—
01
03
01
02
02
March 19, 2008
February 22, 2010
March 19, 2008
September 23, 2008
September 23, 2008
Issued in Renton, Washington, on June 30,
2010.
Todd G. Dixon,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
DEPARTMENT OF TRANSPORTATION
[FR Doc. 2010–17064 Filed 7–21–10; 8:45 am]
[Docket No. FAA–2010–0671; Directorate
Identifier 2010–NM–142–AD; Amendment
39–16363; AD 2010–14–18]
BILLING CODE 4910–13–P
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Federal Aviation Administration
14 CFR Part 39
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 767–200, –300, and
–300F Series Airplanes Powered by
General Electric or Pratt & Whitney
Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
The FAA is superseding an
existing airworthiness directive (AD)
that applies to certain Model 767–200,
–300, and –300F series airplanes. The
SUMMARY:
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Federal Register / Vol. 75, No. 140 / Thursday, July 22, 2010 / Rules and Regulations
emcdonald on DSK2BSOYB1PROD with RULES
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
https://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 https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
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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 aftmost 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
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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.
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Federal Register / Vol. 75, No. 140 / Thursday, July 22, 2010 / Rules and Regulations
TABLE—OTHER RELEVANT RULEMAKING
AD
Applicability
Related Boeing Service Bulletin
AD requirement
AD 2000–07–05, amendment 39–
11659 (65 FR 18883, April 10,
2000).
Certain Boeing Model 767 series
airplanes.
767–54A0094 ...............................
AD 2004–16–12, amendment 39–
13768 (69 FR 51002, August 17,
2004).
Certain Boeing Model 767–200,
–300, and –300F series airplanes powered by Pratt &
Whitney engines or General
Electric engines.
767–54–0069,
767–54–0081,
54A0094.
AD 2009–20–09, amendment 39–
16032 (74 FR 50692, October 1,
2009).
Certain Boeing Model 767–200,
–300, and –300F series airplanes.
767–54A0074 ...............................
AD 2010–03–08, amendment 39–
16192 (75 FR 5677, February 4,
2010).
Certain Boeing Model 767–200,
–300, and –300F series airplanes.
767–54A0062, ..............................
767–54–0069 ................................
Repetitive inspections 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.
Modification of the nacelle strut
and wing structure. (AD 2004–
16–12 superseded AD 2001–
02–07, Amendment 39–12091
and AD 2001–06–12, Amendment 39–12159.)
Repetitive inspections for fatigue
cracking and corrosion of the
upper link fuse pin of the nacelle struts, and related investigative and corrective actions if
necessary.
Repetitive detailed and eddy current 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.)
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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
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and
767–
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.
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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 https://
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,
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Federal Register / Vol. 75, No. 140 / Thursday, July 22, 2010 / Rules and Regulations
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
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 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.
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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
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Boeing
Boeing
Boeing
Boeing
Revision
Alert Service Bulletin 767–54A0101 ..........................................................
Alert Service Bulletin 767–54A0101 ..........................................................
Service Bulletin 767–54A0101 ...................................................................
Service Bulletin 767–54A0101 ...................................................................
(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.
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3
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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.
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Date
February 10, 2005.
June 29, 2010.
January 10, 2002.
September 5, 2002.
(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
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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 .......
767–54–0061 ..........
2 ............................
767–54–0069 ..........
2 ............................
November 23,
1999.
August 31, 2000 ...
767–54–0072 ..........
Original ..................
March 13, 1997 .....
767–54–0080 ..........
1 ............................
May 9, 2002 ..........
767–54–0081 ..........
1 ............................
February 7, 2002 ..
767–54A0062 ..........
6 ............................
November 5, 2009
767–54A0074 ..........
1 ............................
April 24, 2008 .......
767–54A0094 ..........
2 ............................
February 7, 2002 ..
767–57–0063 ..........
1 ............................
November 30,
2000.
Nacelles/Pylons—Strut—Aft Lower Spar—Fastener Corrosion—Inspection
and Replacement.
Nacelles/Pylons—Wing–to–Strut Attach Fittings—Lower Spar Bushing Inspection and Replacement.
Nacelles/Pylons—Midspar Fitting—Underwing Sideload Fitting—Fuse Pin Replacement and Wing Rework.
Nacelles/Pylons—Strut Attach Upper Link—Upper Link Inspection, Rework or
Replacement.
Nacelles/Pylons—Pratt and Whitney Powered Airplanes—Nacelle Strut and
Wing Structure Modification.
Nacelles/Pylons—General Electric Powered Airplanes—Nacelle Strut and
Wing Structure Modification.
Nacelles/Pylons—Strut Attach Fuse Pins—Midspar Fuse Pin Inspection and
Replacement.
Nacelles/Pylons—Strut Attach Fuse Pins—Upper link Fuse Pin Inspection/Replacement.
Nacelles/Pylons—Strut—to—Wing Attachment—Diagonal Brace Inspection/
Rework/Replacement.
Wings—Side Load Underwing Fitting —Inspection/Rework.
emcdonald on DSK2BSOYB1PROD with RULES
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
Applicability
AD
AD 2000–07–05,
amendment 39–
11659.
VerDate Mar<15>2010
Related Boeing
Service Bulletin
AD requirement
Certain Boeing
Model 767 series
airplanes.
767–54A0094 ........
Repetitive inspections 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.
16:12 Jul 21, 2010
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42597
TABLE 3—OTHER RELEVANT RULEMAKING—Continued
AD
Related Boeing
Service Bulletin
Applicability
AD 2004–16–12,
amendment 39–
13768.
AD 2009–20–09,
amendment 39–
16032.
AD 2010–03–08,
amendment 39–
16192.
Certain Boeing
Model 767–200,
–300, and –300F
series airplanes
powered by Pratt
& Whitney engines or General
Electric engines.
Certain Boeing
Model 767–200,
–300, and –300F
series airplanes.
Certain Boeing
Model 767–200,
–300, and –300F
series airplanes.
AD requirement
767–54–0069,
767–54–0080,
767–54–0081,
and 767–
54A0094.
Modification of the nacelle strut and wing structure.
767–54A0074 ........
Repetitive inspections for fatigue cracking and corrosion of the upper link fuse
pin of the nacelle struts, and related investigative and corrective actions if
necessary.
767–54A0062,
767–54–0069.
Repetitive detailed and eddy current inspections to detect cracks of certain
midspar fuse pins, and corrective action 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
Boeing
Boeing
Boeing
Boeing
Boeing
Alert Service Bulletin 767–54A0101 .........................................................
Alert Service Bulletin 767–54A0101 .........................................................
Service Bulletin 767–54A0101 ..................................................................
Service Bulletin 767–54A0101 ..................................................................
Service Bulletin 767–54A0101 ..................................................................
Alternative Methods of Compliance
(AMOCs)
emcdonald on DSK2BSOYB1PROD with RULES
Revision
(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-ANMSeattle-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
VerDate Mar<15>2010
16:12 Jul 21, 2010
Jkt 220001
Date
Original ..................................................
4 ............................................................
1 ............................................................
2 ............................................................
3 ............................................................
September 23, 1999.
February 10, 2005.
February 3, 2000.
January 10, 2002.
September 5, 2002.
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.
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(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: https://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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]]>Agencies
[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]
-----------------------------------------------------------------------
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 https://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 https://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 https://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: https://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
