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[Federal Register Volume 76, Number 229 (Tuesday, November 29, 2011)]
[Rules and Regulations]
[Pages 73491-73494]
From the Federal Register Online via the Government Printing 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 
dse.boecom@boeing.com; 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: 
nenita.odesa@faa.gov.

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.
----------------------------------------------------------------------------------------------------------------

    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: nenita.odessa@faa.gov.
    (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: nenita.odessa@faa.gov.

(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 dse.boecom@boeing.com; 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]
BILLING CODE 4910-13-P
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