AD 2012-22-17
Recurring
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | The Boeing Company | 767-200 Series | Airworthiness Directives; The Boeing Company Airplanes |
| aircraft | The Boeing Company | 767-300 Series | Airworthiness Directives; The Boeing Company Airplanes |
Unsafe Condition
Reports of cracks in the inner chords at both left-side and right-side stations 859.5, 883.5, and 903.5, which can lead to large cracks in the frames and adjacent structure, adversely affecting the structural integrity of the airplane.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Repetitive inspections of the frame inner chord transition radius for cracks, and related investigative and corrective actions if necessary.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within the compliance times specified in the referenced service information.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
The Boeing Company Model 767-200 and -300 series airplanes.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200 and -300 series airplanes. This AD was prompted by reports of cracks in the inner chords at both left-side and right-side stations 859.5, 883.5, and 903.5. This AD requires repetitive inspections of the frame inner chord transition radius for cracks, and related investigative and corrective actions if necessary. We are issuing this AD to prevent large cracks in the frames and adjacent structure that can adversely affect the structural integrity of the airplane.
Applicability Source Text
Show captured applicability text from the source AD
(c) Applicability
(1) This AD applies to The Boeing Company Model 767-200 and -300
series airplanes, certificated in any category, as identified in
Boeing Service Bulletin 767-53A0209, Revision 1, dated July 27,
2011.
(2) Supplemental Type Certificate (STC) ST01920SE (http://
rgl.faa.gov/Regulatory--and--Guidance--Library/rgstc.nsf/0/
082838ee177dbf62862576a4005cdfc0/$FILE/ST01920SE.pdf) does not
affect the ability to accomplish the actions required by this AD.
Therefore, for airplanes on which STC ST01920SE is installed, a
``change in product'' alternative method of compliance (AMOC)
approval request is not necessary to comply with the requirements of
14 CFR 39.17. For all other AMOC requests, the operator must request
approval for an AMOC in accordance with the procedures specified in
paragraph (j) of this AD.
Document Text
Show stored source text (verify against official source)
[Federal Register Volume 77, Number 225 (Wednesday, November 21, 2012)]
[Rules and Regulations]
[Pages 69744-69747]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2012-27344]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-1168; Directorate Identifier 2010-NM-239-AD;
Amendment 39-17255; AD 2012-22-17]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
The Boeing Company Model 767-200 and -300 series airplanes. This AD was
prompted by reports of cracks in the inner chords at both left-side and
right-side stations 859.5, 883.5, and 903.5. This AD requires
repetitive inspections of the frame inner chord transition radius for
cracks, and related investigative and corrective actions if necessary.
We are issuing this AD to prevent large cracks in the frames and
adjacent structure that can adversely affect the structural integrity
of the airplane.
DATES: This AD is effective December 26, 2012.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of December 26,
2012.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; 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, WA. 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 address for the
Docket Office (phone: 800-647-5527) is Document Management Facility,
U.S. Department of Transportation, Docket Operations, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Berhane Alazar, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6577; fax: 425-917-6590; email: <a href="/cdn-cgi/l/email-protection#521037203a333c377c133e33283320123433337c353d24"><span class="__cf_email__" data-cfemail="9cdef9eef4fdf2f9b2ddf0fde6fdeedcfafdfdb2fbf3ea">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM published in the Federal Register on November 9, 2011 (76 FR
69685). That NPRM proposed to require repetitive inspections of the
frame inner chord transition radius for cracks, and related
investigative and corrective actions if necessary.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the proposal
(76 FR 69685, November 9, 2011) and the FAA's response to each comment.
Statement of Intent To Comply With the NPRM (76 FR 69685, November 9,
2011)
American Airlines stated that it will incorporate the NPRM (76 FR
69685, November 9, 2011) requirements into its maintenance program and
that any corrective actions will be performed at a time that is
appropriate based on the compliance thresholds in the NPRM.
Request To Revise Note 1 to Paragraph (g) of the NPRM (76 FR 69685,
November 9, 2011)
Boeing requested that we revise the wording of Note 1 to paragraph
(g) of the NPRM (76 FR 69685, November 9, 2011) to clarify that
structural inspections of fuselage structure are mandated by AD 2003-
18-10, Amendment 39-13301 (68 FR 53503, September 11, 2003). (AD 2003-
18-10 requires revising the airworthiness limitations section of the
maintenance planning data document to incorporate certain inspections
and compliance times to detect fatigue cracking of principal structural
elements.) Boeing stated that an alteration of these structural
inspections will be required for repair(s) done in accordance with
Boeing Service Bulletin 767-53A0209, Revision 1, dated July 27, 2011.
That service bulletin contains post-repair inspections that already
provide alternative method of compliance (AMOC) coverage for the
requirements of AD 2003-18-10.
We disagree with the commenter's request. Paragraph F.,
``Approval,'' of Boeing Service Bulletin 767-53A0209, Revision 1, dated
July 27, 2011, already contains approval of the inspections as an AMOC
for the requirements of the pertinent paragraphs of AD 2003-18-10,
Amendment 39-13301 (68 FR 53503, September 11, 2003). We have not
changed the final rule in this regard.
[[Page 69745]]
Request To Exclude Certain Inspections
All Nippon Airways (ANA) requested that we include a statement in
the proposed requirements of the NPRM (76 FR 69685, November 9, 2011)
to give credit for the inspection at the locations where FAA-approved
repairs have been accomplished for the subject cracking of the inner
chords prior to the release of Boeing Service Bulletin 767-53A0209,
Revision 1, dated July 27, 2011. ANA stated that Boeing Service
Bulletin 767-53A0209, Revision 1, dated July 27, 2011, does not
describe how operators treat the previously FAA-approved repairs and
that a credit statement was included in the service information
referenced in AD 2011-02-06, Amendment 39-16579 (76 FR 4224, January
25, 2011). ANA stated that it would have to obtain approvals for all
previously FAA-approved repairs as AMOCs to the new AD; and considered
this a huge burden that increases costs and work-hours.
We disagree with the commenter's request. The structural issues in
the identified unsafe condition for this AD are significantly different
and more complex than those addressed by AD 2011-02-06, Amendment 39-
16579 (76 FR 4224, January 25, 2011). We are unable to approve AMOCs
for repairs that may have had previous FAA approvals without
information as to how they mitigate the unsafe condition addressed in
this AD. Under the provisions of paragraph (j) of this AD, we will
consider requests for approval of an AMOC for previous repairs if
sufficient data are submitted to substantiate that the repairs would
provide an acceptable level of safety for the unsafe condition
addressed in this AD. We have not changed the final rule in this
regard.
Request for Global Terminating Action and Delay of AD
Delta Airlines (Delta) requested that we revise the NPRM (76 FR
69685, November 9, 2011) to add the statement ``FAA approved repairs
for cracking at the subject locations prior to the release of this
service bulletin (Boeing Service Bulletin 767-53A0209, Revision 1,
dated July 27, 2011), constitute terminating action for the inspections
defined in this AD.'' Delta stated that, if previously installed FAA-
approved repairs are not approved as terminating action, then it would
request that the AD effective date be three months after the release of
the AD, rather than two or three weeks after the release of the AD.
Delta asserted that this would allow additional time for Boeing and
Aviation Partners Boeing to review and provide AMOC information for the
large volume of previous repairs associated with this area.
We disagree to add approval of a global terminating action for
previously approved repairs. We are unable to approve a global
terminating action for repairs that might have had previous FAA
approvals without information as to how each repair mitigates the
identified unsafe condition addressed in this AD. In addition,
requirements that must be met for approvals of AMOC requests exceed
those for repair approvals. We also disagree to delay the effective
date of this AD. We considered that delaying issuance of this AD is
inappropriate in light of the identified unsafe condition. We have not
changed the final rule in this regard.
Clarification of Effect of Winglet Installation
We have added new paragraph (c)(2) to this AD, which states that
Supplemental Type Certificate (STC) ST01920SE (http://rgl.faa.gov/
Regulatory--and--Guidance--Library/rgstc.nsf/0/
082838ee177dbf62862576a4005cdfc0/$FILE/ST01920SE.pdf) does not affect
the ability to accomplish the actions required by this AD. Therefore,
for airplanes on which STC ST01920SE is installed, a ``change in
product'' AMOC approval request is not necessary to comply with the
requirements of 14 CFR 39.17. For all other AMOC requests, the operator
must request approval for an AMOC in accordance with the procedures
specified in paragraph (j) of this AD.
Change to Paragraph (j)(3) of This AD
We have removed the reference to Federal Aviation Regulations 14
CFR 25.571, Amendment 45 from this AD that was specified in paragraph
(j)(3) of the NPRM (76 FR 69685, November 9, 2011). Removing this
reference will neither increase the economic burden on any operator nor
increase the scope of this AD.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD with the changes described previously--and minor editorial
changes. We have determined that these changes:
<bullet> Are consistent with the intent that was proposed in the
NPRM (76 FR 69685, November 9, 2011), for correcting the unsafe
condition; and
<bullet> Do not add any additional burden upon the public than was
already proposed in the NPRM (76 FR 69685, November 9, 2011).
Costs of Compliance
We estimate that this AD will affect 325 airplanes of U.S.
registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Detailed or HFEC inspection...... 23 or 26 work-hours $0 $1,955 or $2,210 Up to $718,250 per
x $85 per hour = per inspection inspection cycle.
$1,955 or 2,210 cycle.
per inspection
cycle.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs that
would be required based on the results of the inspection. We have no
way of determining the number of aircraft that might need these
repairs.
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Repair............................... 24 work-hours x $85 per $383 to $8,327 per $2,423 to $10,367 per
hour = $2,040. frame. frame.
[[Page 69746]]
On-condition detailed and HFEC 7 work-hours x $85 per $0..................... $595
inspections and measurement. hour = $595 per frame.
----------------------------------------------------------------------------------------------------------------
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
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2012-22-17 The Boeing Company: Amendment 39-17255; Docket No. FAA-
2011-1168; Directorate Identifier 2010-NM-239-AD.
(a) Effective Date
This AD is effective December 26, 2012.
(b) Affected ADs
None.
(c) Applicability
(1) This AD applies to The Boeing Company Model 767-200 and -300
series airplanes, certificated in any category, as identified in
Boeing Service Bulletin 767-53A0209, Revision 1, dated July 27,
2011.
(2) Supplemental Type Certificate (STC) ST01920SE (http://
rgl.faa.gov/Regulatory--and--Guidance--Library/rgstc.nsf/0/
082838ee177dbf62862576a4005cdfc0/$FILE/ST01920SE.pdf) does not
affect the ability to accomplish the actions required by this AD.
Therefore, for airplanes on which STC ST01920SE is installed, a
``change in product'' alternative method of compliance (AMOC)
approval request is not necessary to comply with the requirements of
14 CFR 39.17. For all other AMOC requests, the operator must request
approval for an AMOC in accordance with the procedures specified in
paragraph (j) of this AD.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of cracks in the inner chords at
both left-side and right-side stations 859.5, 883.5, and 903.5. We
are issuing this AD to prevent large cracks in the frames and
adjacent structure that can adversely affect the structural
integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections, Related Investigative Actions, and
Corrective Actions
Except as required by paragraph (h)(2) of this AD, at the times
specified in paragraph 1.E., ``Compliance,'' of Boeing Service
Bulletin 767-53A0209, Revision 1, dated July 27, 2011: Perform a
detailed inspection or a surface high frequency eddy current (HFEC)
inspection for cracking in the frame inner chord transition radius
at stations 859.5, 883.5, and 903.5, as applicable, left buttock
line and right buttock line 89, below water line 200; and do all
applicable related investigative and corrective actions; in
accordance with the Accomplishment Instructions of Boeing Service
Bulletin 767-53A0209, Revision 1, dated July 27, 2011; except as
required by paragraph (h)(1) of this AD. Do all applicable related
investigative and corrective actions before further flight. If no
cracking is found, repeat the inspections thereafter at the
applicable interval specified in paragraph 1.E., ``Compliance,'' of
Boeing Service Bulletin 767-53A0209, Revision 1, dated July 27,
2011.
Note 1 to paragraph (g) of this AD: The post-repair inspections
specified in Tables 2, 4, 6, and 8 of paragraph 1.E.,
``Compliance,'' of Boeing Service Bulletin 767-53A0209, Revision 1,
dated July 27, 2011, may be used in support of compliance with
paragraph (c)(2) of Section 121.1109 or 129.109 of the Federal
Aviation Regulations (14 CFR 121.1109(c)(2) or 14 CFR
129.109(c)(2)).
(h) Exceptions to the Service Information
(1) If any cracking is found during any inspection required by
this AD, and Boeing Service Bulletin 767-53A0209, Revision 1, dated
July 27, 2011, specifies to contact Boeing for appropriate action:
Before further flight, repair the cracking using a method approved
in accordance with the procedures specified in paragraph (j) of this
AD.
(2) Where Boeing Service Bulletin 767-53A0209, Revision 1, dated
July 27, 2011, specifies a compliance time after the date on that
service bulletin, this AD requires compliance within the specified
compliance time after the effective date of this AD.
(i) No Reporting Required
Although Boeing Service Bulletin 767-53A0209, Revision 1, dated
July 27, 2011, specifies to submit certain information to the
manufacturer, this AD does not include that requirement.
(j) Alternative Methods of Compliance (AMOCs)
(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
[[Page 69747]]
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 emailed to: <a href="/cdn-cgi/l/email-protection#4b72660a050666182e2a3f3f272e660a0804660a06040866192e3a3e2e383f380b2d2a2a652c243d"><span class="__cf_email__" data-cfemail="61584c202f2c4c32040015150d044c20222e4c202c2e224c3304101404121512210700004f060e17">[email protected]</span></a>.
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
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.
(k) Related Information
For more information about this AD, contact Berhane Alazar,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, ACO, 1601 Lind
Avenue SW., Renton, WA 98057-3356; phone: 425-917-6577; fax: 425-
917-6590; email: <a href="/cdn-cgi/l/email-protection#591b3c2b3138373c7718353823382b193f3838773e362f"><span class="__cf_email__" data-cfemail="a7e5c2d5cfc6c9c289e6cbc6ddc6d5e7c1c6c689c0c8d1">[email protected]</span></a>.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Boeing Service Bulletin 767-53A0209, Revision 1, dated July
27, 2011.
(ii) Reserved.
(3) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.
(4) You may review copies of the referenced service information
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. 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 NARA, call 202-741-6030, or go to: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.
Issued in Renton, Washington, on October 31, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-27344 Filed 11-20-12; 8:45 am]
BILLING CODE 4910-13-P
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