[Federal Register Volume 76, Number 229 (Tuesday, November 29, 2011)]
[Rules and Regulations]
[Pages 73491-73494]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-29801]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-1206; Directorate Identifier 2009-NM-216-AD;
Amendment 39-16868; AD 2011-24-04]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Corporation Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Model DC-10-10, DC-10-10F, and MD-10-10F airplanes. This AD was
prompted by reports of three instances of fuel leaks in the lower cap
splice of the wing rear spar at station Xors=409. Investigation
revealed the fuel leak was due to a crack in the lower cap. If not
corrected, this condition could result in fuel leaks or cracking of the
lower wing skin and structure, causing possible inability of the
structure to sustain the limit load and adversely affecting the
structural integrity of the airplane. This AD requires repetitive
inspections for cracking on the lower cap of the rear spar of the left
and right wings between stations Xors=417 and the outboard edge of the
lower cap splice of the wing rear spar at station Xors=400; temporary
and permanent repairs if necessary; and repetitive inspections of
repaired areas, and corrective actions if necessary. We are issuing
this AD to correct the unsafe condition on these products.
DATES: This AD is effective January 3, 2012.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of January 3,
2012.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
3855 Lakewood Boulevard, MC D800-0019, Long Beach, California 90846-
0001; telephone (206) 544-5000, extension 2; fax (206) 766-5683; email
[email protected]; Internet https://www.myboeingfleet.com. 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 http://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The 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: Nenita Odesa, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137;
phone: (562) 627-5234; fax: (562) 627-5210; email:
[email protected].
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 was published in the Federal Register on December 30, 2010
(75 FR 82333). That NPRM proposed to require repetitive inspections for
cracking on the lower cap of the rear spar of the left and right wings
between stations Xors=417 and the outboard edge of the lower cap splice
of the wing rear spar at station Xors=400; temporary and permanent
repairs if necessary; and repetitive inspections of repaired areas, and
corrective actions if necessary.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM (75 FR 82333, December 30,
2010) or on the determination of the cost to the public.
New Service Information
Since publication of the NPRM (75 FR 82333, December 30, 2010),
Boeing has
[[Page 73492]]
issued Alert Service Bulletin DC10-57A156, Revision 2, dated August 23,
2011. We have updated the references in paragraphs (c) and (g) of this
AD to include Boeing Alert Service Bulletin DC10-57A156, Revision 2,
dated August 23, 2011. The changes in this revised service bulletin are
for clarification only. However, certain inspections called eddy
current test high frequency (ETHF) inspections in Boeing Alert Service
Bulletin DC10-57A156, Revision 1, dated March 10, 2010 (which was
referenced in the NPRM (75 FR 82333, December 30, 2010) as the
appropriate source of service information for certain actions), are
called high frequency eddy current inspections in Boeing Alert Service
Bulletin DC10-57A156, Revision 2, dated August 23, 2011. This is
different terminology for the same inspection method. We have followed
the terminology in Boeing Alert Service Bulletin DC10-57A156, Revision
2, dated August 23, 2011, and used both terminologies as specified in
Boeing Alert Service Bulletin DC10-57A156, Revision 2, dated August 23,
2011. We are also allowing credit for actions done before the effective
date of this AD, in accordance with Boeing Alert Service Bulletin DC10-
57A156, Revision 1, dated March 10, 2010, and have added that reference
to paragraph (h) of this AD.
Since publication of the NPRM (75 FR 82333, December 30, 2010),
Boeing has also issued revised service rework drawings to clarify the
repair instructions. These service rework drawings do not provide
repairs for all conditions specified in the NPRM (75 FR 82333, December
30, 2010). We have updated the references in paragraph (g) of this AD
to include Boeing DC-10-10 Service Rework Drawing SR10570019, Revision
K, dated April 17, 2009, including Parts List PL SR10570019, Revision
K, dated April 23, 2009, including Boeing Engineering Order, Revision
L, dated April 14, 2010; and Boeing DC-10-10 Service Rework Drawing
SR10570048, Revision K, dated October 7, 2010, including Parts List PL
SR10570048, Revision K, dated October 14, 2010. We have also revised
the actions in paragraph (g) of this AD to specify which conditions are
addressed by these service rework drawings, and which conditions need a
repair method approved by the FAA.
Conclusion
We reviewed the relevant data and determined that air safety and
the public interest require adopting the AD as proposed with the
changes described previously--except for minor editorial changes. We
have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (75 FR 82333, December 30, 2010), for correcting the unsafe
condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Costs of Compliance
We estimate that this AD affects 68 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Parts
Action Labor cost cost Cost per product Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Inspection................... 2 work-hours x $85 $0 $170 per $11,560 per inspection cycle.
per hour = $170 per inspection
inspection cycle. cycle.
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We have received no definitive data that would enable us to provide
a cost estimate for the on-condition actions specified in 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, 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):
2011-24-04 McDonnell Douglas Corporation: Amendment 39-16868; Docket
No. FAA-2010-1206; Directorate Identifier 2009-NM-216-AD.
(a) Effective Date
This AD is effective January 3, 2012.
(b) Affected ADs
None.
(c) Applicability
This AD applies to McDonnell Douglas Corporation Model DC-10-10,
DC-10-10F, and MD-10-10F airplanes; certificated in any category; as
identified in Boeing Alert
[[Page 73493]]
Service Bulletin DC10-57A156, Revision 2, dated August 23, 2011.
(d) Subject
Air Transport Association (ATA) of America Code 57: Wings.
(e) Unsafe Condition
This AD results from reports of three instances of fuel leaks in
the lower cap splice of the wing rear spar at station Xors=409. The
Federal Aviation Administration is issuing this AD to detect and
correct cracking on the lower cap of the rear spar of the left and
right wings between stations Xors=417 and the outboard edge of the
lower cap splice of the wing rear spar at station Xors=400, which
could result in fuel leaks or cracking of the lower wing skin and
structure, causing possible inability of the structure to sustain
the limit load and adversely affecting the structural integrity of
the airplane.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Inspection
Within 1,750 flight cycles after the effective date of this AD,
do an eddy current test high frequency (ETHF) inspection for
cracking on the lower cap of the rear spar of the left and right
wings between stations Xors=417 and the outboard edge of the lower
cap splice of the wing rear spar at station Xors=400, in accordance
with the Accomplishment Instructions of Boeing Alert Service
Bulletin DC10-57A156, Revision 2, dated August 23, 2011.
(1) If no cracking is found, repeat the inspection required by
paragraph (g) of this AD thereafter at intervals not to exceed 1,750
flight cycles.
(2) If any cracking is found in the spar cap aft leg at the
fastener holes, and that cracking can be removed by hole
enlargement, before further flight, do a permanent repair, in
accordance with Boeing DC-10-10 Service Rework Drawing SR10570048,
Revision K, dated October 7, 2010, including Parts List PL
SR10570048, Revision K, dated October 14, 2010. Within 1,750 flight
cycles after doing the applicable permanent repair, and thereafter
at intervals not to exceed 1,750 flight cycles, do ETHF and high
frequency eddy current inspections for cracking in accordance with
Boeing DC-10-10 Service Rework Drawing SR10570048, Revision K, dated
October 7, 2010, including Parts List PL SR10570048, Revision K,
dated October 14, 2010. If any cracking is found during any
inspection required by this paragraph, before further flight, repair
the cracking, in accordance with the procedures specified in
paragraph (i) of this AD.
(3) If any cracking is found in the spar cap aft leg at the
fastener holes, and that cracking cannot be removed by hole
enlargement but it does not extend into the vertical leg, before
further flight, do the applicable actions specified in paragraph
(g)(3)(i) or (g)(3)(ii) of this AD:
(i) If cracking is found between Station Xors=400 and inboard of
Station Xors=408, repair the cracking, in accordance with the
procedures specified in paragraph (i) of this AD (Alternative Method
of Compliance (AMOCs) paragraph).
(ii) If cracking is found between Stations Xors=408 and
Xors=417, do a permanent repair, in accordance with Boeing DC-10-10
Service Rework Drawing SR10570048, Revision K, dated October 7,
2010, including Parts List PL SR10570048, Revision K, dated October
14, 2010. Within 4,550 flight cycles after doing a permanent repair,
and thereafter at intervals not to exceed 4,550 flight cycles, do
ETHF and ultrasonic inspections for cracking, in accordance with
Boeing DC-10-10 Service Rework Drawing SR10570048, Revision K, dated
October 7, 2010, including Parts List PL SR10570048, Revision K,
dated October 14, 2010. If any cracking is found during any
inspection required by this paragraph, before further flight, repair
the cracking, in accordance with the procedures specified in
paragraph (i) of this AD.
(4) If any cracking is found in the spar cap aft leg at fastener
holes and that cracking extends into the vertical leg of the spar
cap, do the actions specified in paragraph (g)(4)(i) or (g)(4)(ii)
of this AD.
(i) If any cracking is found between Station Xors=400 and
inboard of Station Xors=408, before further flight, do the
applicable permanent repair, in accordance with Boeing DC-10-10
Service Rework Drawing SR10570019, Revision K, dated April 17, 2009,
including Parts List PL SR10570019, Revision K, dated April 23,
2009, including Boeing Engineering Order, Revision L, dated April
14, 2010. Within 4,550 flight cycles after doing the permanent
repair, and thereafter at intervals not to exceed 4,550 flight
cycles, do ETHF and ultrasonic inspections for cracking of the
repaired area, in accordance with Boeing DC-10-10 Service Rework
Drawing SR10570019, Revision K, dated April 17, 2009, including
Parts List PL SR10570019, Revision K, dated April 23, 2009,
including Boeing Engineering Order, Revision L, dated April 14,
2010. If any cracking is found during any inspection required by
this paragraph, before further flight, repair the cracking, in
accordance with the procedures specified in paragraph (i) of this
AD.
(ii) If any cracking is found between Stations Xors=408 and
Xors=417, do the actions in paragraphs (g)(4)(ii)(A) or
(g)(4)(ii)(B) of this AD.
(A) Do the actions in paragraphs (g)(4)(ii)(A)(1) and
(g)(4)(ii)(A)(2) of this AD.
(1) Before further flight, do a temporary repair, in accordance
with Boeing DC-10-10 Service Rework Drawing SR10570048, Revision K,
dated October 7, 2010, including Parts List PL SR10570048, Revision
K, dated October 14, 2010. Within 1,650 flight cycles after doing
the temporary repair; and thereafter at intervals not to exceed
1,650 flight cycles, do ETHF and ultrasonic inspections for cracking
of the repaired area, in accordance with Boeing DC-10-10 Service
Rework Drawing SR10570048, Revision K, dated October 7, 2010,
including Parts List PL SR10570048, Revision K, dated October 14,
2010, until the permanent repair required by paragraph
(g)(4)(ii)(A)(2) of this AD is done. If any cracking is found during
any inspection required by this paragraph, before further flight,
repair the cracking, in accordance with the procedures specified in
paragraph (i) of this AD.
(2) Within 7,000 flight cycles after the temporary repair has
been done, do the applicable permanent repair, in accordance with
Boeing DC-10-10 Service Rework Drawing SR10570019, Revision K, dated
April 17, 2009, including Parts List PL SR10570019, Revision K,
dated April 23, 2009, including Boeing Engineering Order, Revision
L, dated April 14, 2010. Within 4,550 flight cycles after doing the
permanent repair, and thereafter at intervals not to exceed 4,550
flight cycles, do ETHF and ultrasonic inspections for cracking of
the repaired area, in accordance with Boeing DC-10-10 Service Rework
Drawing SR10570019, Revision K, dated April 17, 2009, including
Parts List PL SR10570019, Revision K, dated April 23, 2009,
including Boeing Engineering Order, Revision L, dated April 14,
2010. If any cracking is found during any inspection required by
this paragraph, before further flight, repair the cracking, in
accordance with the procedures specified in paragraph (i) of this
AD.
(B) Before further flight do the applicable permanent repair, in
accordance with Boeing DC-10-10 Service Rework Drawing SR10570019,
Revision K, dated April 17, 2009, including Parts List PL
SR10570019, Revision K, dated April 23, 2009, including Boeing
Engineering Order, Revision L, dated April 14, 2010. Within 4,550
flight cycles after doing the permanent repair, and thereafter at
intervals not to exceed 4,550 flight cycles, do ETHF and ultrasonic
inspections for cracking of the repaired area, in accordance with
Boeing DC-10-10 Service Rework Drawing SR10570019, Revision K, dated
April 17, 2009, including Parts List PL SR10570019, Revision K,
dated April 23, 2009, including Boeing Engineering Order, Revision
L, dated April 14, 2010. If any cracking is found during any
inspection required by this paragraph, before further flight, repair
the cracking, in accordance with the procedures specified in
paragraph (i) of this AD.
(h) Credit for Actions Accomplished in Accordance With Previous Service
Information
Actions accomplished before the effective date of this AD
according to Boeing Alert Service Bulletin DC10-57A156, dated
September 16, 2009; and Revision 1, dated March 10, 2010; are
considered acceptable for compliance with the corresponding actions
specified in this AD.
(i) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles 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. Send
information to ATTN: Nenita Odesa, Aerospace Engineer, Airframe
Branch, ANM-120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard,
Lakewood, California 90712-4137; phone: (562) 627-5234; fax: (562)
627-5210; email: [email protected].
(2) To request a different method of compliance or a different
compliance time
[[Page 73494]]
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, Los Angeles ACO to
make those findings. For a repair method to be approved, the repair
must meet the certification basis of the airplane and 14 CFR 25.571,
Amendment 45, and the approval must specifically refer to this AD.
(j) Related Information
For more information about this AD, contact Nenita Odesa,
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO,
3960 Paramount Boulevard, Lakewood, California 90712-4137; phone:
(562) 627-5234; fax: (562) 627-5210; email: [email protected].
(k) Material Incorporated by Reference
You must use the following service information to do the actions
required by this AD, unless the AD specifies otherwise. The Director
of the Federal Register approved the incorporation by reference
(IBR) under 5 U.S.C. 552(a) and 1 CFR part 51 of the following
service information on the date specified:
(1) Boeing Alert Service Bulletin DC10-57A156, Revision 2, dated
August 23, 2011; IBR approved January 3, 2012.
(2) Boeing DC-10-10 Service Rework Drawing SR10570019, Revision
K, dated April 17, 2009, including Parts List PL SR10570019,
Revision K, dated April 23, 2009, including Boeing Engineering
Order, Revision L, dated April 14, 2010; IBR approved January 3,
2012. Only Sheet 1 of this drawing indicates the revision date of
this document.
(3) Boeing DC-10-10 Service Rework Drawing SR10570048, Revision
K, dated October 7, 2010, including Parts List PL SR10570048,
Revision K, dated October 14, 2010; IBR approved January 3, 2012.
Only Sheet 1 of this drawing indicates the revision date for this
document.
(4) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
3855 Lakewood Boulevard, MC D800-0019, Long Beach, California 90846-
0001; telephone (206) 544-5000, extension 2; fax (206) 766-5683;
email [email protected]; Internet https://www.myboeingfleet.com.
(5) 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.
(6) 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 http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on November 7, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-29801 Filed 11-28-11; 8:45 am]
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