[Federal Register Volume 60, Number 237 (Monday, December 11, 1995)]
[Rules and Regulations]
[Pages 63414-63415]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-30132]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 93-NM-219-AD; Amendment 39-9454; AD 95-20-04 R1]


Airworthiness Directives; Lockheed Model L-1011-385-1 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; correction.

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SUMMARY: This amendment revises an existing airworthiness directive 
(AD), applicable to all Lockheed Model L-1011-385-1 series airplanes, 
that currently requires implementation of a Supplemental Inspection 
Document (SID) program of structural inspections to detect fatigue 
cracking, and repair, if necessary, to ensure continued airworthiness 
of these airplanes as they approach the manufacturer's original fatigue 
design life goal. That AD originally was prompted by a structural re-
evaluation by the manufacturer that identified certain structural 
details where fatigue damage is likely to occur. The actions specified 
in that AD are intended to prevent fatigue cracking that could 
compromise the structural integrity of these airplanes. This amendment 
corrects the compliance time for the initial inspection of each 
structurally significant detail (SSD).

DATES: Effective November 2, 1995.
    The incorporation by reference of certain publications listed in 
the regulations was approved previously by the Director of the Federal 
Register as of November 2, 1995 (60 FR 51713, October 3, 1995).

ADDRESSES: The service information referenced in this AD may be 
obtained from Lockheed Aeronautical Systems Support Company, Field 
Support Department, Dept. 693, Zone 0755, 2251 Lake Park Drive, Smyrna, 
Georgia 30080. This information may be examined at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at 
the FAA, Small Airplane Directorate, Atlanta Aircraft Certification 
Office, Campus Building, 1701 Columbia Avenue, Suite 2-160, College 
Park, Georgia; or at the Office of the Federal Register, 800 North 
Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Thomas Peters, Aerospace Engineer, 
Flight Test Branch, ACE-116A, FAA, Small Airplane Directorate, Atlanta 
Aircraft Certification Office, Campus Building, 1701 Columbia Avenue, 
Suite 2-160, College Park, Georgia 30337-2748; telephone (404) 305-
7367; fax (404) 305-7348.

SUPPLEMENTARY INFORMATION: On September 20, 1995, the FAA issued AD 95-
20-04, amendment 39-9382 (60 FR 51713, October 3, 1995), applicable to 
all Lockheed Model L-1011-385-1 series airplanes. That AD requires 
implementation of a Supplemental Inspection Document (SID) program of 
structural inspections to detect fatigue cracking, and repair, if 
necessary, to ensure continued airworthiness of these airplanes as they 
approach the manufacturer's original fatigue design life goal. That 
action was prompted by a structural re-evaluation by the manufacturer 
that identified certain structural details where fatigue damage is 
likely to occur. The actions required by that AD are intended to 
prevent fatigue cracking that could compromise the structural integrity 
of these airplanes.
    Since the issuance of that AD, the FAA has received communications 
from an affected operator indicating confusion about the compliance 
time for accomplishing the inspections of each structurally significant 
detail (SSD). This operator points out that the AD specifies, first, 
that the inspections contained in the SID must be incorporated into the 
FAA-approved maintenance program within 12 months after the effective 
date of the AD. Second, the AD requires that the initial inspection of 
each SSD must be accomplished within one repeat interval after the 
effective date of the AD. The operator points out that this presents a 
problem in complying with the AD, since, in some cases, the initial 
inspection of an SSD may be required to be accomplished prior to the 
incorporation of the SID program into an operator's maintenance 
program.
    The FAA has reviewed the compliance time specified in AD 95-20-04, 
and finds that it is indeed erroneous. It was the FAA's intent that the 
SID program be incorporated into the FAA-approved maintenance 
inspection program prior to the performance of any inspection contained 
in the SID. Therefore, the FAA has determined that it is appropriate to 
take action to correct paragraph (a)(1) of that AD to specify that the 
compliance time for performing the initial inspection of each SSD is 
within one repeat interval measured from a date 12 months after 
November 2, 1995 (the effective date of the AD). The FAA finds that 
this change will not compromise safety and is consistent with what the 
FAA had originally intended.
    Action is taken herein to correct the error and to correctly add 
the AD as an amendment to section 39.13 of the Federal Aviation 
Regulations (14 CFR 39.13). The effective date of the rule remains 
November 2, 1995.
    The final rule is being reprinted in its entirety for the 
convenience of affected operators.
    Since this AD merely corrects the compliance time for a previously-
required action, it requires no additional work to be performed by 
affected operators. In light of this, the FAA has determined that it 
has no adverse economic impact and imposes no additional burden on any 
person. Therefore, notice and public procedures hereon are unnecessary.

List of Subjects in 14 CFR Part 39

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

Adoption of the Correction

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 USC 106(g), 40101, 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-9382 (60 FR 
51713, October 3, 1995), and by adding 

[[Page 63415]]
a new airworthiness directive (AD), amendment 39-    , to read as 
follows:

95-20-04 R1  Lockheed: Amendment 39-9454. Docket 93-NM-219-AD. 
Revises AD 95-20-04, Amendment 39-9382.

    Applicability: Model L-1011-385-1, L-1011-385-1-14, and L-1011-
385-1-15 series airplanes, certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must use the authority 
provided in paragraph (d) of this AD to request approval from the 
FAA. This approval may address either no action, if the current 
configuration eliminates the unsafe condition; or different actions 
necessary to address the unsafe condition described in this AD. Such 
a request should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any airplane from the applicability of this AD.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent fatigue cracking that could compromise the structural 
integrity of these airplanes, accomplish the following:
    (a) Within 12 months the effective date of this AD, incorporate 
a revision into the FAA-approved maintenance inspection program 
which provides for inspection(s) of the structurally significant 
details (SSD) defined in Lockheed Document Number LG92ER0060, ``L-
1011-385 Series Supplemental Inspection Document,'' revised January 
1994.
    (1) The initial inspection for each SSD must be performed at the 
later of the times specified in paragraph (a)(1)(i) or (a)(1)(ii) of 
this AD:
    (i) Within one repeat interval measured from a date 12 months 
after the effective date of this AD; or
    (ii) Prior to the threshold specified in the Lockheed Document 
for that SSD.
    (2) A 10 percent deviation from the repetitive interval 
specified in the Lockheed Document for that SSD is acceptable to 
allow for planning and scheduling time.
    (3) If the Lockheed Document specifies that inspection of any 
SSD be performed at every ``C'' check, those inspections must be 
performed at intervals not to exceed 5,000 hours time-in-service or 
2,500 flight cycles, whichever occurs earlier.
    (4) If the Lockheed Document specifies either the initial 
inspection or the repetitive inspection intervals for any SSD in 
terms of flight hours or flight cycles, the inspection shall be 
performed prior to the earlier of the terms (whichever occurs first 
on the airplane: either accumulated number of flight hours, or 
accumulated number of flight cycles).
    (5) The non-destructive inspection techniques referenced in 
Appendix VI of the Lockheed Document provide acceptable methods for 
accomplishing the inspections required by this AD.
    (b) If any cracking is found in any SSD, prior to further 
flight, repair in accordance with paragraph (b)(1), (b)(2), or 
(b)(3) of this AD.
    (1) In accordance with the applicable service bulletin 
referenced in Lockheed Document Number LG92ER0060, ``L-1011-385 
Series Supplemental Inspection Document,'' revised January 1994; or
    (2) In accordance with the Structural Repair Manual; or
    (3) In accordance with a method approved by the Manager, Atlanta 
Aircraft Certification Office (ACO), FAA, Small Airplane 
Directorate.
    (c) Within 30 days after returning the airplane to service, 
subsequent to accomplishment of the inspection(s) specified in 
Lockheed Document Number LG92ER0060, ``L-1011-385 Series 
Supplemental Inspection Document,'' revised January 1994, submit a 
report of the results (positive or negative) of the inspection(s) to 
Lockheed in accordance with Section V., Data Reporting System (DRS), 
of the Lockheed Document. Information collection requirements 
contained in this regulation have been approved by the Office of 
Management and Budget (OMB) under the provisions of the Paperwork 
Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been 
assigned OMB Control Number 2120-0056.
    (d) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Atlanta ACO, FAA, Small Airplane 
Directorate. Operators shall submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Atlanta ACO.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Atlanta ACO.
    (e) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.
    (f) The incorporation of the revision and reporting requirements 
shall be done in accordance with Lockheed Document Number 
LG92ER0060, ``L-1011-385 Series Supplemental Inspection Document,'' 
revised January 1994. This incorporation by reference was approved 
previously by the Director of the Federal Register in accordance 
with 5 U.S.C. 552(a) and 1 CFR part 51 as of November 2, 1995 (60 FR 
51713, October 3, 1995). Copies may be obtained from Lockheed 
Aeronautical Systems Support Company, Field Support Department, 
Dept. 693, Zone 0755, 2251 Lake Park Drive, Smyrna, Georgia 30080. 
Copies may be inspected at the FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Atlanta 
Aircraft Certification Office, Small Airplane Directorate, Campus 
Building, 1701 Columbia Avenue, Suite 2-160, College Park, Georgia; 
or at the Office of the Federal Register, 800 North Capitol Street, 
NW., suite 700, Washington, DC.
    (g) This amendment is effective on November 2, 1995.

    Issued in Renton, Washington, on December 5, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-30132 Filed 12-8-95; 8:45 am]
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