Airworthiness Directives; McDonnell Douglas Corporation Model DC-9-14, DC-9-15, and DC-9-15F Airplanes; and Model DC-9-20, DC-9-30, DC-9-40, and DC-9-50 Series Airplanes

[Federal Register Volume 75, Number 216 (Tuesday, November 9, 2010)]
[Rules and Regulations]
[Pages 68686-68688]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-28084]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0705; Directorate Identifier 2009-NM-206-AD; 
Amendment 39-16499; AD 2010-23-10]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Corporation Model DC-
9-14, DC-9-15, and DC-9-15F Airplanes; and Model DC-9-20, DC-9-30, DC-
9-40, and DC-9-50 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding an existing airworthiness directive (AD) 
for the products listed above. That AD currently requires repetitive 
high frequency eddy current inspections to detect cracking in the 
vertical radius (also known as the ``vertical leg'') of the upper cap 
of the center wing rear spar, and repair if necessary. This new AD 
expands the area to be inspected by including inspections to detect 
cracking of the horizontal flange of the upper cap of the left and 
right center wing rear spar, and repair if necessary. This new AD also 
adds certain airplanes to the applicability. This AD was prompted by 
reports of cracking in the vertical radius of the upper cap of the 
center wing rear spar, and the horizontal flange on the inboard side of 
the of the rear spar upper cap, which resulted from stress corrosion. 
We are issuing this AD to detect and correct cracking in the vertical 
leg or the horizontal flange of the upper cap of the left or right 
center wing rear spar, which could cause a possible fuel leak, damage 
to the wing skin, and structural failure of the upper cap, and result 
in reduced structural integrity of the airplane.

DATES: This AD is effective December 14, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of December 14, 
2010.

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; e-mail 
[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: Wahib Mina, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5324; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede airworthiness

[[Page 68687]]

directive (AD) 2004-23-11, Amendment 39-13866 (69 FR 65522, November 
15, 2004). That AD applies to the specified products. The NPRM was 
published in the Federal Register on August 5, 2010 (75 FR 47242). That 
NPRM proposed to continue to require repetitive high frequency eddy 
current inspections to detect cracks in the vertical radius (also known 
as the ``vertical leg'') of the upper cap of the center wing rear spar, 
and repair if necessary. That NPRM also proposed to expand the area to 
be inspected by including inspections to detect cracking of the 
horizontal flange of the upper cap of the left and right center wing 
rear spar, and repair if necessary. In addition, that NPRM proposed to 
add certain airplanes to the applicability.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting the AD as proposed, except for 
minor editorial changes. We have determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Costs of Compliance

    There are approximately 510 airplanes of the affected design in the 
worldwide fleet. We estimate that 322 airplanes of U.S. registry will 
be affected by this AD. The following table provides the estimated 
costs for U.S. operators to comply with this AD.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                            Number of U.S.-
         Action            Work hours     Average labor       Parts      Cost per airplane     registered                    Fleet cost
                                          rate per hour                                        airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection.............              3             $85              $0   $255 per                     322   $82,110 per inspection 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

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that 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
2. The FAA amends Sec.  39.13 by removing airworthiness directive (AD) 
2004-23-11, Amendment 39-13866 (69 FR 65522, November 15, 2004), and 
adding the following new AD:

2010-23-10 McDonnell Douglas Corporation: Amendment 39-16499; Docket 
No. FAA-2010-0705; Directorate Identifier 2009-NM-206-AD.

Effective Date

    (a) This airworthiness directive (AD) is effective December 14, 
2010.

Affected ADs

    (b) This AD supersedes AD 2004-23-11, Amendment 39-13866.

Applicability

    (c) This AD applies to McDonnell Douglas Corporation Model DC-9-
14, DC-9-15, DC-9-15F, DC-9-21, DC-9-31, DC-9-32, DC-9-32 (VC-9C), 
DC-9-32F, DC-9-33F, DC-9-34, DC-9-34F, DC-9-32F (C-9A, C-9B), DC-9-
41, and DC-9-51 airplanes; certificated in any category; as 
identified in Boeing Service Bulletin DC9-57-223, Revision 1, dated 
August 13, 2009.

Subject

    (d) Air Transport Association (ATA) of America Code 57: Wings.

Unsafe Condition

    (e) This AD results from reports of cracking in the vertical 
radius (also known as the ``vertical leg'') of the upper cap of the 
center wing rear spar, and the horizontal flange on the inboard side 
of the rear spar upper cap, which resulted from stress corrosion. 
The Federal Aviation Administration is issuing this AD to detect and 
correct cracking in the vertical leg or the horizontal flange of the 
upper cap of the left or right center wing rear spar, which could 
cause a possible fuel leak, damage to the wing skin, and structural 
failure of the upper cap, and result in reduced structural integrity 
of the airplane.

Compliance

    (f) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

[[Page 68688]]

Restatement of Requirements of AD 2004-23-11, With Revised Service 
Information

Inspection

    (g) For all airplanes except Model DC-9-15F airplanes, at the 
later of the times specified in paragraphs (g)(1) and (g)(2) of this 
AD: Do a high frequency eddy current inspection to detect cracks in 
the vertical radius of the upper cap of the center wing rear spar, 
in accordance with the Accomplishment Instructions of Boeing Service 
Bulletin DC9-57-223, dated July 21, 2003; or Revision 1, dated 
August 13, 2009. After the effective date of this AD, only Revision 
1 may be used.
    (1) Before the accumulation of 25,000 total flight cycles.
    (2) Within 15,000 flight cycles or 5 years after December 20, 
2004 (the effective date of AD 2004-23-11), whichever occurs first.

Corrective Action

    (h)(1) If no crack is found during any inspection required by 
paragraph (g) of this AD, then repeat the inspection thereafter at 
intervals not to exceed 15,000 flight cycles or 5 years, whichever 
occurs first, until the initial inspection required by paragraph (i) 
of this AD is done.
    (2) If any crack is found during the inspection required by 
paragraph (g) of this AD, before further flight, repair per a method 
approved by the Manager, Los Angeles Aircraft Certification Office 
(ACO), FAA. For a repair method to be approved by the Manager, Los 
Angeles ACO, as required by this paragraph, the Manager's approval 
letter must specifically refer to this AD.

New Requirements of This AD

Inspection

    (i) At the later of the times specified in paragraphs (i)(1) and 
(i)(2) of this AD: Do a high frequency eddy current inspection to 
detect cracking in the vertical leg (also known as the ``vertical 
radius'') and horizontal flange of the left and right rear spar 
upper cap, inboard and outboard sides, at the bulkhead at wing 
station Xcw=58.500, in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin DC9-57-223, Revision 1, 
dated August 13, 2009. If no cracking is found, repeat the 
inspection thereafter at intervals not to exceed 15,000 flight 
cycles or 5 years, whichever occurs first. Accomplishment of the 
initial inspection required by paragraph (i) of this AD terminates 
the requirements of paragraphs (g) and (h)(1) of this AD.
    (1) Before the accumulation of 25,000 total flight cycles.
    (2) Within 15,000 flight cycles or 5 years after accomplishing 
the most recent high frequency eddy current inspection required by 
paragraph (g) of this AD, whichever occurs first.

Corrective Action

    (j) If any cracking is found during any inspection required by 
paragraph (i) of this AD, before further flight, repair the cracking 
using a method approved in accordance with the procedures specified 
in paragraph (k) of this AD.

Alternative Methods of Compliance (AMOCs)

    (k)(1) The Manager, Los Angeles 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: Wahib Mina, Aerospace 
Engineer, Airframe Branch, ANM-120L, Los Angeles ACO, FAA, 3960 
Paramount Boulevard, Lakewood, California 90712-4137; telephone 
(562) 627-5324; fax (562) 627-5210.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office. 
The AMOC approval letter must specifically refer to 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 the approval 
must specifically refer to this AD.
    (4) AMOCs approved previously in accordance with AD 2004-23-11, 
Amendment 39-13866, are approved as AMOCs for the corresponding 
provisions of paragraph (h)(2) of this AD.

Material Incorporated by Reference

    (l) You must use Boeing Service Bulletin DC9-57-223, Revision 1, 
dated August 13, 2009, to do the actions required by this AD, unless 
the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
3855 Lakewood Boulevard, MC D800-0019, Long Beach, California 90846-
0001; telephone 206-544-5000, extension 2; fax 206-766-5683; e-mail 
[email protected]; Internet https://www.myboeingfleet.com.
    (3) You may review copies of the service information at the FAA, 
1601 Lind Avenue, SW., Renton, Washington. For information on the 
availability of this material at the FAA, call 425-227-1221.
    (4) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at 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 October 21, 2010.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-28084 Filed 11-8-10; 8:45 am]
BILLING CODE 4910-13-P

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