[Federal Register Volume 75, Number 55 (Tuesday, March 23, 2010)]
[Proposed Rules]
[Pages 13695-13697]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-6307]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0233; Directorate Identifier 2009-NM-014-AD]
RIN 2120-AA64


Airworthiness Directives; Lockheed Martin Corporation/Lockheed 
Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Model 382, 382B, 382E, 382F, and 382G airplanes. This proposed AD would 
require repetitive eddy current inspections to detect cracks in the 
center wing upper and lower rainbow fittings, and corrective actions if 
necessary; and repetitive replacements of rainbow fittings, which would 
extend the repetitive interval for the next inspection. This proposed 
AD results from a report of fatigue cracking of the wing upper and 
lower rainbow fittings during durability testing and on in-service 
airplanes. Analysis of in-service cracking has shown that these rainbow 
fittings are susceptible to multiple site fatigue damage. We are 
proposing this AD to detect and correct such fatigue cracks, which 
could grow large and lead to the failure of the fitting and a 
catastrophic failure of the center wing.

DATES: We must receive comments on this proposed AD by May 7, 2010.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     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.
     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 proposed AD, contact 
Lockheed Martin Corporation/Lockheed Martin Aeronautics Company, 
Airworthiness Office, Dept. 6A0M, Zone 0252, Column P-58, 86 S. Cobb 
Drive, Marietta, Georgia 30063; telephone 770-494-5444; fax 770-494-
5445; e-mail [email protected]; Internet http://www.lockheedmartin.com/ams/tools/TechPubs.htmlx. 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 proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (telephone 800-647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

FOR FURTHER INFORMATION CONTACT: Carl Gray, Aerospace Engineer, 
Airframe Branch, ACE-117A, FAA, Atlanta Aircraft Certification Office 
(ACO), 1701 Columbia Avenue, College Park, Georgia 30337; telephone 
(404) 474-5554; fax (404) 474-5606.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2010-0233; 
Directorate Identifier 2009-NM-014-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    Fatigue cracking of the wing upper and lower rainbow fittings 
during the durability test and on in-service airplanes indicates a 
requirement to perform inspections prior to the current published 
Hercules Airfreighter Series Progressive Inspection Procedures and 
Hercules Airfreighter Progressive Inspection Procedures intervals. 
Analysis of in-service cracking has shown that these rainbow fittings 
are susceptible to multiple site fatigue damage. This condition, if not 
corrected, could lead to the failure of the rainbow fittings and a 
catastrophic failure of the center wing.

Relevant Service Information

    We have reviewed Lockheed Service Bulletin 382-57-82, Revision 3, 
including Appendixes A, B, and C, dated April 25, 2008. The service 
bulletin describes procedures for repetitive eddy current inspections 
to detect cracks in the center wing upper and lower rainbow fittings. 
The service bulletin specifies marking and reporting suspected cracks 
but does not provide corrective actions.
    The service bulletin also describes procedures for repetitively 
replacing the upper and lower rainbow fittings, which would extend the 
interval for the next eddy current inspection. The replacement includes 
related investigative and corrective actions. The related investigative 
actions consist of two types of inspections: (1) A general visual 
inspection for damage and defects (including corrosion and cracking) of 
the wing faying structure; and (2) a primary automated bolt hole eddy 
current (ABHEC) inspection to detect cracks of all opened fitting 
attachment fastener holes in the upper and lower surface skin panel, 
stringers, splice straps, and splice angles that are common to the 
rainbow fittings prior to installing the new rainbow fitting. The 
service bulletin describes procedures for a ``redundant'' (backup) 
ABHEC inspection of any suspected damage.
    The corrective actions consist of repairing confirmed damage within 
certain limits, and contacting the manufacturer for damage that exceeds 
those limits. The service bulletin provides no corrective actions for 
damage or defects found during the visual inspection.

[[Page 13696]]

FAA's Determination and Requirements of This Proposed AD

    We are proposing this AD because we evaluated all relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design. 
This proposed AD would require accomplishing the actions specified in 
the service information described previously, except as discussed under 
``Differences Between the Proposed AD and Service Bulletin.'' The 
proposed AD would also require sending the inspection results to 
Lockheed.

Differences Between the Proposed AD and Service Bulletin

    In Lockheed Service Bulletin 382-57-82, Revision 3, dated April 25, 
2008, the NOTE in paragraph 1.B.(1) states that operators who have 
completed a Lockheed Martin usage evaluation analysis may adjust the 
intervals provided in the service bulletin by severity factors 
developed for their inspection programs. The proposed AD would require 
approval of an alternative method of compliance (AMOC) for such an 
adjustment.
    Although the service bulletin specifies that operators may contact 
the manufacturer for disposition of certain repair conditions and the 
service bulletin does not specify corrective actions for damage or 
cracking found during the visual inspection, this proposed AD would 
require operators to repair those conditions using a method approved by 
the FAA.
    Although the service bulletin does not specify corrective actions 
for airplanes on which cracking is found during the eddy current 
inspections, this proposed AD would require operators to replace the 
rainbow fittings if any cracking is found.
    Lockheed Service Bulletin 382-57-82, Revision 3, dated April 25, 
2008, also recommends grounding airplanes that have accumulated 20,000 
or more flight hours until inspections are done. We have provided a 
grace period of 365 days or 600 flight hours after the effective date 
of this AD in paragraph (g)(2) of this AD to prevent grounding the 
fleet. This time period does not present a safety concern since this 
area is already being inspected at a repetitive interval and the 
inspection to this point would have found cracks as intended. We find 
that the short initial inspection period provided in the proposed AD 
provides an adequate level of safety.

Interim Action

    We consider this proposed AD interim action. If final action is 
later identified, we might consider further rulemaking then.

Costs of Compliance

    We estimate that this proposed AD would affect 14 airplanes of U.S. 
registry. The following table provides the estimated costs for U.S. 
operators to comply with this proposed AD.

                                                                 Table--Estimated Costs
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                                                                                                                Number of
                                                         Average                                                  U.S.-
                 Action                    Work hours  labor  rate    Parts         Cost per  airplane         registered             Fleet cost
                                                         per hour                                               airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection..............................           20          $85       None  $1,700 per inspection cycle.              14  $23,800 per inspection
                                                                                                                              cycle.
Fitting replacement.....................        2,438          $85    $40,000  $247,230....................              14  $3,461,220
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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 determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866,
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979), and
    3. 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.
    You can find our regulatory evaluation and the estimated costs of 
compliance in the AD Docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    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]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Lockheed Martin Corporation/Lockheed Martin Aeronautics Company: 
Docket No. FAA-2010-0233; Directorate Identifier 2009-NM-014-AD.

Comments Due Date

    (a) We must receive comments by May 7, 2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Lockheed Martin Corporation/Lockheed 
Martin Aeronautics Company Model 382, 382B, 382E, 382F, and 382G 
airplanes, certificated in any category.

Subject

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

[[Page 13697]]

Unsafe Condition

    (e) This AD results from a report of fatigue cracking of the 
wing upper and lower rainbow fittings during durability testing and 
on in-service airplanes. Analysis of in-service cracking has shown 
that these rainbow fittings are susceptible to multiple site fatigue 
damage. The Federal Aviation Administration is issuing this AD to 
detect and correct such fatigue cracks, which could grow large and 
lead to the failure of the fitting and a catastrophic failure of the 
center wing.

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.

Initial Inspections

    (g) At the later of the times specified in paragraphs (g)(1) and 
(g)(2) of this AD: Do eddy current inspections to detect cracking of 
the center wing upper and lower rainbow fittings on the left and 
right side of the airplane. Do the actions in accordance with the 
Accomplishment Instructions of Lockheed Service Bulletin 382-57-82, 
Revision 3, including Appendixes A and B, dated April 25, 2008. Any 
cracks found during the inspections required by paragraph (g) of 
this AD must be repaired before further flight in accordance with 
the actions required by paragraph (l) of this AD.
    (1) Before the accumulation of 15,000 total flight hours on the 
rainbow fitting.
    (2) Within 365 days or 600 flight hours on the rainbow fitting 
after the effective date of this AD, whichever occurs first.

Repetitive Inspection Schedule

    (h) Repeat the inspection required by paragraph (g) of this AD 
at intervals not to exceed 3,600 flight hours on the center wing, 
until the rainbow fitting has accumulated 30,000 total flight hours. 
Any cracks found during the inspections required by paragraph (h) of 
this AD must be repaired before further flight in accordance with 
the actions required by paragraph (l) of this AD.

Rainbow Fitting Replacements

    (i) Before the accumulation of 30,000 flight hours on the 
rainbow fitting or within 600 flight hours after the effective date 
of this AD, whichever occurs later: Replace the rainbow fitting, do 
all related investigative actions, and do all applicable corrective 
actions, in accordance with paragraph 2.C. of the Accomplishment 
Instructions of Lockheed Service Bulletin 382-57-82, Revision 3, 
including Appendix C, dated April 25, 2008. Replace the rainbow 
fitting thereafter at intervals not to exceed 30,000 flight hours.

Post-Replacement Repetitive Inspections

    (j) For upper and lower rainbow fittings replaced in accordance 
with paragraph (i) or (k) of this AD: Do the eddy current 
inspections specified in paragraph (g) of this AD within 15,000 
flight hours after doing the replacement and repeat the eddy current 
inspections specified in paragraph (h) of this AD thereafter at 
intervals not to exceed 3,600 flight hours until the rainbow 
fittings are replaced in accordance with paragraph (i) or (k) of 
this AD.

Repair of Damaged Rainbow Fittings and Associated Areas

    (k) If, during any inspection required by paragraph (g) or (h) 
of this AD, any crack is detected, before further flight, replace 
the rainbow fitting, do all related investigative actions and do all 
applicable corrective actions, in accordance with Paragraph 2.C. of 
the Accomplishment Instructions of Lockheed Service Bulletin 382-57-
82, Revision 3, including Appendix C, dated April 25, 2008, except 
as provided by paragraph (l) of this AD.

Exceptions to Service Bulletin

    (l) Where Lockheed Service Bulletin 382-57-82, Revision 3, 
including Appendixes A, B, and C, dated April 25, 2008, specifies to 
contact the manufacturer for disposition of certain repair 
conditions, and where the service bulletin does not specify 
corrective actions if certain conditions are found, this AD requires 
repairing those conditions using a method approved by the Manager, 
Atlanta Aircraft Certification Office (ACO), FAA. For a repair 
method to be approved by the Manager, Atlanta ACO, as required by 
this paragraph, the Manager's approval letter must specifically 
refer to this AD.

Alternative Methods of Compliance (AMOCs)

    (m)(1) The Manager, Atlanta 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: Carl Gray, Aerospace 
Engineer, Airframe Branch, ACE-117A, FAA, Atlanta Aircraft 
Certification Office, 1701 Columbia Avenue, College Park, Georgia 
30337; telephone (404) 474-5554; fax (404) 474-5606.
    (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 reference this AD.

    Issued in Renton, Washington, on March 17, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-6307 Filed 3-22-10; 8:45 am]
BILLING CODE 4910-13-P