AD 2010-22-01
Recurring
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | The Boeing Company | 767-200 Series | Airworthiness Directives; The Boeing Company Model 767-200, -300, and -300F Series Airplanes |
| aircraft | The Boeing Company | 767-300 Series | Airworthiness Directives; The Boeing Company Model 767-200, -300, and -300F Series Airplanes |
| aircraft | The Boeing Company | 767-300F Series | Airworthiness Directives; The Boeing Company Model 767-200, -300, and -300F Series Airplanes |
Unsafe Condition
Fatigue cracking or corrosion of the upper link fuse pin of the nacelle struts, which could result in failure of the fuse pin and consequent reduced structural integrity of the nacelle strut and possible separation of the strut and engine from the airplane during flight.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
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. Replacement of the fuse pins terminates the repetitive inspection requirements, but the strut modification is still required.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 50 flight hours after the effective date of this AD.
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.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
We are superseding an existing airworthiness directive (AD) for the products listed above. That AD currently requires 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. The existing AD also provides terminating action for the repetitive inspections. This AD revises certain criteria for the terminating action. This AD was prompted by two reports of cracked upper link fuse pins. We are issuing this AD to prevent fatigue cracking or corrosion of the upper link fuse pin, which could result in failure of the fuse pin and consequent reduced structural integrity of the nacelle strut and possible separation of the strut and engine from the airplane during flight.
Document Text
Show stored source text (verify against official source)
[Federal Register Volume 75, Number 202 (Wednesday, October 20, 2010)]
[Rules and Regulations]
[Pages 64633-64636]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2010-26224]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-1036; Directorate Identifier 2009-NM-247-AD;
Amendment 39-16480; AD 2010-22-01]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 767-200, -300,
and -300F Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for the products listed above. That AD currently requires 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. The existing AD also provides terminating action
for the repetitive inspections. This AD revises certain criteria for
the terminating action. This AD was prompted by two reports of cracked
upper link fuse pins. We are issuing this AD to prevent fatigue
cracking or corrosion of the upper link fuse pin, which could result in
failure of the fuse pin and consequent reduced structural integrity of
the nacelle strut and possible separation of the strut and engine from
the airplane during flight.
DATES: This AD is effective November 4, 2010.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of November 4,
2010.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
November 5, 2009 (74 FR 50692, October 1, 2009).
We must receive comments on this AD by December 6, 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#f79a92d995989294989ab79598929e9990d994989a"><span class="__cf_email__" data-cfemail="6c0109420e03090f03012c0e030905020b420f0301">[email protected]</span></a>; Internet
<a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>. You may review copies of the referenced
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.
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 (phone: 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 18, 2009, we issued AD 2009-20-09, Amendment 39-16032
(74 FR 50692, October 1, 2009), for certain Model 767-200, -300, and -
300F series airplanes. That AD requires 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. That AD also provides terminating action for the repetitive
inspections. That AD resulted from two reports of cracked upper link
fuse pins. We issued that AD to prevent fatigue cracking or corrosion
of the upper link fuse pin, which could result in failure of the fuse
pin and consequent reduced structural integrity of the nacelle strut
and possible separation of the strut and engine from the airplane
during flight.
Actions Since Existing AD Was Issued
We have learned that paragraph (h) of AD 2009-20-09 incorrectly
identifies the pin replacement as acceptable for compliance with the
optional strut modification specified in paragraph (g) of that AD.
Rather, replacing the pin terminates only the repetitive inspections of
the pins as required by paragraph (g) of this AD; replacing the pin
does not terminate the requirement for the strut modification. We have
removed credit for replacement of the fuse pins with new fuse pins from
paragraph (h) of the existing AD (specified as paragraph (i) in this
AD) because it is not a terminating action. We have added new paragraph
(j) in this AD to specify that replacement of the fuse pins terminates
the repetitive inspection requirements of paragraph (g) of this AD, and
the strut modification is still required.
We have also revised paragraph (b) of this AD to clarify that
certain requirements of this AD terminate certain requirements of AD
2000-19-09, Amendment 39-11910 (65 FR 58641, October 2, 2000), and AD
2004-16-12, Amendment 39-13768 (69 FR 51002, August 17, 2004).
Explanation of Additional Paragraph in the AD
We have added a new paragraph (d) to this AD to provide the Air
Transport Association (ATA) of America subject code 54: Nacelles/
Pylons. This code is added to make this AD parallel with other new AD
actions. We have reidentified subsequent paragraphs accordingly.
FAA's Determination
We are issuing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of these same type
designs.
[[Page 64634]]
AD Requirements
This AD requires 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. This AD also
provides terminating action for the repetitive inspections.
FAA's Justification and Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because this
AD shortens the time for the repetitive intervals. Therefore, we find
that notice and opportunity for prior public comment 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 was not preceded by notice and an opportunity for public
comment. 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-2010-1036; Directorate
Identifier 2009-NM-247-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.
Costs of Compliance
We estimate that this AD affects 354 airplanes of U.S. registry.
This new AD adds no new costs to affected operators. The current costs
for this AD are repeated for the convenience of affected operators, as
follows:
Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection of fuse pins (requirement 4 work-hours x $85 per $0 $340 per inspection $120,360 per inspection cycle.
of AD 2009-20-09). hour = $340 per cycle.
inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation Programs''
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2009-20-09, Amendment 39-16032 (74 FR 50692, October 1, 2009), and
adding the following new AD:
2010-22-01 The Boeing Company: Amendment 39-16480; Docket No. FAA-
2010-1036; Directorate Identifier 2009-NM-247-AD.
Effective Date
(a) This AD is effective November 4, 2010.
Affected ADs
(b) This AD supersedes AD 2009-20-09, Amendment 39-16032.
Certain requirements of this AD terminate certain requirements of AD
2000-19-09, Amendment 39-11910, and AD 2004-16-12, Amendment 39-
13768.
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 767-54A0074, Revision 1,
dated April 24, 2008.
Subject
(d) Joint Aircraft System Component (JASC)/Air Transport
Association (ATA) of America Code 54: Nacelles/Pylons.
Unsafe Condition
(e) This AD was prompted by two reports of cracked upper link
fuse pins. We are issuing this AD to prevent fatigue cracking or
corrosion of the upper link fuse pin, which could result in failure
of the fuse pin and consequent reduced structural integrity of the
nacelle strut and possible separation of the strut and engine from
the airplane during flight.
Compliance
(f) Comply with this AD within the compliance times specified,
unless already done.
[[Page 64635]]
Restatement of Requirements of AD 2009-20-09, With Revised Credit
Provisions in Paragraph (I) of This AD
Initial and Repetitive Inspections/Investigative and Corrective
Actions
(g) Inspect the upper link fuse pin of the nacelle struts for
fatigue cracking and corrosion at the applicable time specified in
Table 1 of this AD. Do the applicable inspection by doing all the
applicable actions specified in the Accomplishment Instructions of
Boeing Alert Service Bulletin 767-54A0074, Revision 1, dated April
24, 2008; and do all applicable related investigative and corrective
actions before further flight. Repeat the applicable inspection at
intervals not to exceed 3,000 flight cycles or 24 months, whichever
is first, until the requirements of paragraph (h) of this AD have
been done.
Table 1--Compliance Times
------------------------------------------------------------------------
At the later of:
----------------------------------------------
Engine type Initial inspection
threshold Grace period
------------------------------------------------------------------------
JT9D..................... 14,000 total flight Within 3,000 flight
cycles. cycles or 18 months
after November 5, 2009
(the effective date of
AD 2009[dash]20-09),
whichever is first.
CF6-80A.................. 24,000 total flight Within 3,000 flight
cycles. cycles or 18 months
after November 5, 2009,
whichever is first.
PW4000................... 8,000 total flight Within 3,000 flight
cycles. cycles or 18 months
after November 5, 2009,
whichever is first.
CF6-80C2................. 10,000 total flight Within 3,000 flight
cycles. cycles or 18 months
after November 5, 2009,
whichever is first.
RB211.................... 24,000 total flight Within 3,000 flight
cycles. cycles or 18 months
after November 5, 2009,
whichever is first.
------------------------------------------------------------------------
Note 1: The upper link inspections can be done with the pylon
and/or engine in any position.
Note 2: In paragraph 3.B, Steps 4.b.(1)(a) and
4.b.(2)(b)(2){a{time} of the Accomplishment Instructions of Boeing
Alert Service Bulletin 767-54A0074, Revision 1, dated April 24,
2008, the procedures specify to apply two layers of Boeing Material
Specification (BMS) 10-11 primer to the inside surface of the fuse
pin if no crack indication is found. However, two layers of primer
are only necessary to touch up bare areas on the fuse pin if no
crack indication is found.
Terminating Action in AD 2000-19-09, Amendment 39-11910, and AD 2004-
16-12, Amendment 39-13768
(h) Accomplishment of the modification specified in paragraph
(h)(1) or (h)(2) of this AD, as applicable, terminates the
inspections required by paragraph (g) of this AD.
(1) For Model 767 series airplanes powered by Rolls-Royce RB211
series engines, as identified in AD 2000-19-09: Modification of the
nacelle strut and wing structure, as required by paragraphs (a) and
(b) of AD 2000-19-09.
(2) For Model 767-200, -300, and -300F series airplanes powered
by Pratt & Whitney and General Electric engines, as identified in AD
2004-16-12: Modification of the nacelle strut and wing structure, as
required by paragraphs (a), (b), (d), and (e) of AD 2004-16-12.
Credit for Inspection Done Using Previous Service Information
(i) Inspection of the fuse pins before November 5, 2009, in
accordance with Boeing Service Bulletin 767-54-0074, dated March 27,
1997, is acceptable for compliance with the inspections required by
paragraph (g) of this AD, except that operator's equivalent
procedures are not allowed.
New Requirements of This AD
Optional Terminating Action for Inspections
(j) Replacement of the fuse pins with new fuse pins (not
serviceable fuse pins), in accordance with Boeing Service Bulletin
767-54-0074, dated March 27, 1997; or Boeing Alert Service Bulletin
767-54A0074, Revision 1, dated April 24, 2008; terminates the
repetitive inspections of the fuse pins required by paragraph (g) of
this AD.
Alternative Methods of Compliance (AMOCs)
(k)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in the Related Information
section of this AD. Information may be e-mailed to: <a href="/cdn-cgi/l/email-protection#c3faee828d8eee90a6a2b7b7afa6ee82808cee828e8c80ee91a6b2b6a6b0b7b083a5a2a2eda4acb5"><span class="__cf_email__" data-cfemail="cdf4e08c8380e09ea8acb9b9a1a8e08c8e82e08c80828ee09fa8bcb8a8beb9be8dabacace3aaa2bb">[email protected]</span></a>.
(2) Before using any approved AMOC, notify your Principal
Maintenance Inspector or Principal Avionics Inspector, as
appropriate, or lacking a principal inspector, your local Flight
Standards District Office.
(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. AMOCs that specified using new pins
(not serviceable pins) approved previously in accordance with AD
2009-20-09, Amendment 39-16032, are approved as AMOCs for the
corresponding provisions of paragraph (h) of this AD.
Related Information
(l) For more information about this AD, 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.
Material Incorporated by Reference
(m) You must use Boeing Alert Service Bulletin 767-54A0074,
Revision 1, dated April 24, 2008, to do the actions required by this
AD, unless the AD specifies otherwise. If you accomplish the
optional terminating actions specified in this AD, you must use
Boeing Alert Service Bulletin 767-54A0074, Revision 1, dated April
24, 2008; or Boeing Service Bulletin 767-54-0074, dated March 27,
1997; to perform those actions, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of Boeing Service Bulletin 767-54-0074,
dated March 27, 1997, under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) The Director of the Federal Register previously approved the
incorporation by reference of Boeing Alert Service Bulletin 767-
54A0074, Revision 1, dated April 24, 2008, on November 5, 2009 (74
FR 50692, October 1, 2009).
(3) 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#4528206b272a20262a2805272a202c2b226b262a28"><span class="__cf_email__" data-cfemail="89e4eca7ebe6eceae6e4c9ebe6ece0e7eea7eae6e4">[email protected]</span></a>; Internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.
(4) 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.
(5) 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 an NARA facility, 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>.
[[Page 64636]]
Issued in Renton, Washington, on October 6, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-26224 Filed 10-19-10; 8:45 am]
BILLING CODE 4910-13-P
Source: Official FAA Source ↗
Retrieved: Apr 6, 2026
Rights: U.S. Government Public Domain
This site is not affiliated with or endorsed by the FAA. Always verify with official sources.
Related Airworthiness Directives
2026-05-07
final ruleAirworthiness Directives; The Boeing Company Airplanes
Unsafe Condition: Discovery of a crack at one of the forward lower fastener holes following replacement of a cracked underwing longeron (UWL) fitting. Such cracking could result in loss in the primary load path betw...
2026-05-03 Recurring
final ruleAirworthiness Directives; The Boeing Company Airplanes
Unsafe Condition: scribe lines found at skin lap joints and butt joints, around external repairs and antennas, and at locations where external decals had been cut, which could develop into fatigue cracks in the skin...
2026-04-10 Recurring
final ruleAirworthiness Directives; The Boeing Company Airplanes
Unsafe Condition: Corrosion damage on the Model 767 satellite communications (SATCOM) high gain antenna adapter plate, which could result in parts departing the airplane (PDA). A PDA event of the SATCOM high gain an...
2025-15-08 Recurring
final ruleAirworthiness Directives; The Boeing Company Airplanes
Unsafe Condition: uncommanded fore and aft movement of the Captain's and First Officer's seats, which could cause a flight control obstruction or unintended flight control input, resulting in the loss of the ability...