[Federal Register Volume 72, Number 219 (Wednesday, November 14, 2007)]
[Proposed Rules]
[Pages 64005-64008]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 07-5595]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0109; Directorate Identifier 2007-NM-235-AD]
RIN 2120-AA64


Airworthiness Directive; Lockheed Model 382, 382B, 382E, 382F, 
and 382G Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for all Lockheed Model 382, 382B, 382E, 382F, and 382G series 
airplanes. This proposed AD would require revising the FAA-approved 
maintenance inspection program to include inspections that will give no 
less than the required damage to tolerance rating for each structural 
significant item (SSI), doing repetitive inspections to detect cracks 
of all SSIs, and repairing cracked structure. This proposed AD results 
from a report of incidents involving fatigue cracking and corrosion in 
transport category airplanes that are approaching or have exceeded 
their design service objective. We are proposing this AD to maintain 
the continued structural integrity of the entire fleet of Model 382, 
382B, 382E, 382F, and 382G series airplanes.

DATES: We must receive comments on this proposed AD by December 31, 
2007.

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 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.

[[Page 64006]]

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, 
One Crown Center, 1895 Phoenix Boulevard, Suite 450, Atlanta, Georgia 
30349; telephone (770) 703-6131; fax (770) 703-6097.

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 ADDRESSES section. Include ``Docket No. FAA-2007-0109; 
Directorate Identifier 2007-NM-235-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 data and may amend 
this proposed AD because of those comments.
    We will post all comments we received, 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

    In the early 1980s, as part of its continuing work to maintain the 
structural integrity of older transport category airplanes, the FAA 
concluded that the incidence of fatigue cracking may increase as these 
airplanes reach or exceed their design service objective (DSO). In 
light of this, and as a result of increased utilization and longer 
operational lives, we determined that a supplemental structural 
inspection program (SSIP) was necessary to maintain the continued 
structural integrity for all airplanes in the transport fleet.

Issuance of Advisory Circular (AC)

    As a follow-on from that determination, we issued AC No. 91-56 
``Supplemental Structural Inspection Program for Large Transport 
Category Airplanes,'' dated May 6, 1981. That AC provides guidance 
material to manufacturers and operators for use in developing a 
continuing structural integrity program to ensure safe operation of 
older airplanes throughout their operational lives. This guidance 
material applies to transport airplanes that were certified under the 
fail-safe requirements of part 4b (``Airplane Airworthiness, Transport 
Categories'') of the Civil Air Regulations or damage tolerance 
structural requirements of part 25 (``Airworthiness Standards: 
Transport Category Airplanes'') of the Federal Aviation Regulations 
(FAR) (14 CFR part 25), and that have a maximum gross weight greater 
than 75,000 pounds. The procedures set forth in that AC are applicable 
to transport category airplanes operated under subpart D (``Special 
Flight Operations'') of part 91 of the FAR (14 CFR part 91); part 121 
(``Operating Requirements: Domestic, Flag, and Supplemental 
Operations''); part 125 (``Certification and Operations: Airplanes 
having a Seating Capacity of 20 or More Passengers or a Maximum Payload 
of 6,000 Pounds or More''); and part 135 (``Operating Requirements: 
Commuter and On-Demand Operations'') of the FAR (14 CFR parts 121, 125, 
and 135). The objective of the SSIP was to establish inspection 
programs to ensure timely detection of fatigue cracking.

Development of the SSIP

    In order to evaluate the effect of increased fatigue cracking with 
respect to maintaining fail-safe design and damage tolerance of the 
structure of Lockheed Model 382, 382B, 382E, 382F,and 382G series 
airplanes, Lockheed conducted a structural easement of those airplanes, 
using damage tolerance evaluation techniques. Lockheed accomplished 
this reassessment using the criteria contained in AC No. 91-56, as well 
as Amendment 25-45 of section 25.571 (``Damage-tolerance and fatigue 
evaluation of structure'') of the FAR (14 CFR 25.571). During the 
reassessment, members of the airline industry participated with 
Lockheed in working group sessions and developed the SSIP for Lockheed 
Model 382, 382B 382E, 382F, and 382G series airplanes. Engineers and 
maintenance specialist from the FAA also supported these sessions. 
Subsequently, based on the working groups's recommendations, Lockheed 
developed the Supplemental Structural Inspection Document (SSID).

Revelant Service Information

    We have reviewed Lockheed Martin Model 382, 382B, 382E, 382F, and 
382G Series Aircraft Service Manual Publication (SMP), Supplemental 
Structural Inspection Document, SMP 515-C-SSID, Change 1, dated 
September 10, 2007 (hereafter ``the SSID''). The SSID describes 
procedures for revising the FAA-approved maintenance inspection program 
to include inspections that will give no less than the required damage 
tolerance assessment/analysis (DTA) for each supplemental significant 
item (SSI), and doing repetitive inspections to detect cracks of all 
SSIs. Accomplishing the actions specified in the SSID is intended to 
adequately address the unsafe condition.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other airplanes 
of the same type design. For this reason, we are proposing this AD, 
which would require the following actions:
    Paragraph (g) of the proposed AD would require incorporation of a 
revision into the FAA-approved maintenance inspection program that 
provides no less than the required damage tolerance rating (DTR) for 
each SSI listed in the SSID.
    Paragraph (h) of the proposed AD would require repetitive 
inspections to detect cracks of all SSIs.
    Paragraph (n) of the proposed AD would require repairing any 
cracked structure in accordance with the method approved by the FAA.
    Paragraph (o) of the proposed AD specifies the requirements of the 
inspection program for transferred airplanes. Before any airplane that 
is subject to this proposal AD can be added to an air carrier's 
operations specifications, a program for doing the inspections required 
by this proposed AD must be established.

Differences Between the Proposed AD and Service Information

    Section 6.0, ``Structural Inspection Requirements'' of the SSID 
specifies a threshold for accomplishing the initial inspections; 
however, it does not specify a grace period for airplanes that are near 
or have passed that threshold. This proposed AD would allow a grace 
period of 36 months after the effective date of the AD to initiate the 
applicable inspections to detect cracks of all SSIs. In addition, this 
proposed AD would require incorporation of the SSID into

[[Page 64007]]

the FAA-approved maintenance inspection program within 12 months after 
the effective date of the AD.
    The SSID does not specify instructions on how to repair certain 
conditions. This proposed AD would require operators to repair those 
conditions using a method approved by the FAA.
    These differences have been coordinated with Lockheed.

Cost of Compliance

    There are about 91 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this proposed AD.

                                                 Estimated Costs
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                                                                                 Number of U.S.-
            Action               Work hours     Average labor        Cost          registered       Fleet cost
                                                rate per hour                       airplanes
----------------------------------------------------------------------------------------------------------------
Revision of maintenance                   600             $80  $48,000 per                   14  $672,000.
 inspection program.                                            airplane.
Inspections..................           2,724              80  $217,920, per                 14  $3,050,880, per
                                                                airplane, per                     inspection
                                                                inspection                        cycle.
                                                                cycle.
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    The number of inspection work hours, as indicated above, is 
presented as if the accomplishment of the actions in this proposed AD 
are to be conducted as ``stand alone'' actions. However, in actual 
practice, these actions for the most part will be done coincidentally 
or in combination with normally scheduled airplane inspections and 
other maintenance program tasks. Therefore, the actual number of 
necessary additional inspection work hours will be minimal in many 
instances. Additionally, any costs associated with special airplane 
scheduling will be minimal.
    Further, compliance with this proposed AD would be a means of 
compliance with the aging airplane safety final rule (AASFR) for the 
baseline structure of Model 382, 382B, 382E, 382F, and 382G series 
airplanes. The AASFR final rule requires certain operators to 
incorporate damage tolerance inspections into their maintenance 
inspection programs. These requirements are described in 14 CFR 
121.370(a) and 129.16. Accomplishment of the actions required by this 
proposed AD will meet the requirements of these CFR sections for the 
baseline structure. The costs for accomplishing the inspection portion 
of this proposed AD were accounted for in the regulatory evaluation of 
the AASFR final rule.

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 determine 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 that the 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket. See the 
ADDRESSES section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

Lockheed: Docket No. FAA-2007-0109; Directorate Identifier 2007-NM-
235-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by December 
31, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Lockheed Model 382, 382B, 382E, 382F, 
and 382G series airplanes, certificated in any category.

Unsafe Condition

    (d) This AD results from a report of incidents involving fatigue 
cracking and corrosion in transport category airplanes that are 
approaching or have exceeded their design service objective. We are 
issuing this AD to maintain the continued structural integrity of 
the entire fleet of Lockheed Model 382, 382B, 382E, 382F, and 382G 
series airplanes.

Compliance

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

Service Information

    (f) The term ``the SSID,'' as used in this AD, means Lockheed 
Martin Model 382, 382B, 382E, 382F, and 382G Series Aircraft Service 
Manual Publication (SMP), Supplemental Structural Inspection 
Document, SMP 515-C-SSID, Change 1, dated September 10, 2007.

[[Page 64008]]

Revision of the FAA-Approved Maintenance Inspection Program

    (g) Within 12 months after the effective date of this AD, 
incorporte a revision into the FAA-approved maintenance inspection 
program that provides no less than the required damage tolerance 
assessment/analysis (DTA) for each structural significant item (SSI) 
listed in the SSID. (The required DTA value for each SSI is listed 
in the SSID.) The revision to the maintenance inspection program 
must include and must be implemented in accordance with the 
procedures in Section 5.0, ``Damage Tolerance Analysis 
Methodology,'' and Section 7.0, ``Discrepancy Reporting,'' of the 
SSID. Under the provisions of the Paperwork Reduction Act of 1980 
(44 U.S.C. 3501, et seq.), the Office of Management and Budget (OMB) 
has approved the information collection requirements contained in 
this AD and has assigned OMB Control Number 2120-0056.

Initial and Repetitive Inspections

    (h) At the later of the times specified in paragraphs (h)(1) and 
(h)(2) of this AD, except as provided by paragraphs (i) through (m) 
of this AD: Do the applicable initial inspections to detect cracks 
of all SSIs, in accordance with the SSID. Repeat the applicable 
inspections thereafter at intervals not to exceed the ``Recurring'' 
intervals specified in Section 6.0.0 of the SSID, except as provided 
by paragraphs (k) through (m) of this AD.
    (1) Before the applicable ``Initial'' threshold specified in 
Section 6.0.0, ``Structural Inspection Requirements'' of the SSID.
    (2) Within 36 months after the effective date of this AD, or 
within one ``Recurring'' interval measured from 12 months after the 
effective date of the AD, whichever comes first.

Exceptions to the SSID

    (i) Where Section 6.0.0 of the SSID specifies the ``Initial'' 
threshold in years (since new), this AD requires compliance within 
the specified year since the date of issuance of the original 
standard airworthiness certificate or the date of issuance of the 
original export certificate of airworthiness.
    (j) Where Section 6.0 of the SSID specifies the ``Initial'' 
threshold as ``Special Condition,'' this AD requires compliance 
within 24 months after the effective date of this AD.
    (k) Where Section 6.0 of the SSID specifies the ``Initial'' 
threshold and ``Recurring'' interval as ``FS 1041 Fitting 
Replacement,'' this AD requires compliance within 24 months after 
the effective date of this AD and thereafter at intervals not to 
exceed 12 months.
    (l) Where Section 6.0 of the SSID specifies the ``Initial'' 
threshold and ``Recurring'' interval as ``Engine Change,'' this AD 
requires compliance within 24 months after the effective date of 
this AD and thereafter at intervals not to exceed 36 months.
    (m) Where Section 6.0 of the SSID specifies the ``Initial'' 
threshold and ``Recurring'' interval as ``Aft Lord Mount Change,'' 
this AD requires compliance within 24 months after the effective 
date of this AD and thereafter at intervals not to exceed 24 months.

Repair

    (n) If any cracked structure is found during any inspection 
required by paragraph (h) of this AD, before further flight, repair 
the cracked structure 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.

Inspection Program for Transferred Airplanes

    (o) Before any airplane that is subject to this AD and that has 
exceeded the applicable compliance times specified in paragraph (h) 
of this AD can be added to an air carrier's operations 
specifications, a program for the accomplishment of the inspections 
required by this AD must be established in accordance with paragraph 
(o)(1) or (o)(2) of this AD, as applicable.
    (1) For airplanes that have been inspected in accordance with 
this AD: The inspection of each SSI must be done by the new operator 
in accordance with the previous operator's schedule and inspection 
method, or the new operator's schedule and inspection method, at 
whichever time would result in the earlier accomplishment for that 
SSI inspection. The compliance time for accomplishment of this 
inspection must be measured from the last inspection accomplished by 
the previous operator. After each inspection has been done once, 
each subsequent inspection must be performed in accordance with the 
new operator's schedule and inspection method.
    (2) For airplanes that have not been inspected in accordance 
with this AD: The inspection of each SSI required by this AD must be 
done either before adding the airplane to the air carrier's 
operations specification, or in accordance with a schedule and an 
inspection method approved by the Manager, Atlanta Aircraft 
Certification Office (ACO), FAA. After each inspection has been done 
once, each subsequent inspection must be done in accordance with the 
new operator's schedule.

Alternative Methods of Compliance (AMOCs)

    (p)(1) The Manager, Atlanta ACO, has the authority to approve 
AMOCs for this AD, if required in accordance with the procedures 
found in 14 CFR 39.19.
    (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 appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.

    Issued in Renton, Washington, on October 23, 2007.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft 
Certification Service.
[FR Doc. 07-5595 Filed 11-13-07; 8:45 am]
BILLING CODE 4910-13-M