[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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