[Federal Register Volume 60, Number 116 (Friday, June 16, 1995)]
[Rules and Regulations]
[Pages 31624-31626]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-14633]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-NM-103-AD; Amendment 39-9277; AD 95-12-24]
Airworthiness Directives; Lockheed Model L-1011-385 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to all Lockheed Model L-1011-385 series airplanes. This
action requires an inspection to detect cracking of the bulkhead at
fuselage station (FS) 1363 at butt line (BL) 42.5, and repair or
additional inspections, if necessary. This amendment is prompted by
reports indicating that fatigue cracking was found in the rear bulkhead
at FS 1363. The actions specified in this AD are intended to prevent
reduced structural integrity of the fuselage due to fatigue cracking of
the pressure bulkhead.
DATES: Effective July 3, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of July 3, 1995.
Comments for inclusion in the Rules Docket must be received on or
before August 15, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-103-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056.
The service information referenced in this AD may be obtained from
Lockheed Aeronautical Systems Support Company (LASSC), 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,
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.
FOR FURTHER INFORMATION CONTACT: Thomas Peters, Aerospace Engineer,
Flight Test Branch, ACE-116A, FAA, Atlanta Aircraft Certification
Office, Small Airplane Directorate, Campus Building, 1701 Columbia
Avenue, Suite 2-160, College Park, Georgia 30337-2748; telephone (404)
305-7367; fax (404) 305-7348.
SUPPLEMENTARY INFORMATION: The FAA has received reports indicating that
cracking was found in the rear bulkhead of the center section pressure
deck at fuselage station (FS) 1363 on a Lockheed Model L-1011-385
series airplane. The cracking extended approximately 30 inches downward
along butt line (BL) 42.5 and through the frame at the lower edge of
the bulkhead. At that point, the cracking extended aft an additional 26
inches through a skin panel on the lower fuselage. The cause of this
cracking appears to be fatigue. Such fatigue cracking, if not detected
and corrected in a timely manner, could result in reduced structural
integrity of the fuselage.
Lockheed has issued L-1011 Service Bulletin 093-53-268, dated April
15, 1993, which describes procedures for certain inspections to detect
cracking of the bulkhead at FS 1363 in the area of the stiffeners at
left and right BL 42.5, and repair, if necessary. The repair involves
installing web doublers and a splice.
The Lockheed service bulletin specifies that repair of cracking may
be delayed if the cracking falls within certain parameters described in
the service bulletin. For these cases, the service bulletin specifies
procedures for accomplishing repetitive visual and eddy current
inspections until the repair is accomplished. The FAA has reviewed and
approved the procedures specified in this Lockheed service bulletin.
The FAA also has reviewed and approved a second document issued by
Lockheed: LCC-7622-373, dated May 9, 1995. This document describes
procedures for additional inspections to detect cracking of the frame
cap for airplanes on which cracking of the bulkhead is found below
waterline (WL) 117. Those inspections include the following:
--A bolt hole eddy current inspection to detect cracking of the eight
fastener holes at the intersection of the vertical stiffener at BL 42.5
and the frame cap vertical flange;
[[Page 31625]]
--A bolt hole eddy current inspection to detect cracking at eight
fastener locations in the frame cap lower flange that connect the lower
fuselage skin panel to the frame at the BL 42.5 vertical stiffener; and
--A visual inspection to detect stress corrosion cracking of the
accessible portions of the fillet radius of the frame cap.
A third document issued by Lockheed, LCC-7622-374, dated May 9,
1995, is referenced in LCC-7622-373. LCC-7622-374 describes procedures
for repair of any cracking of the frame cap that is found during the
inspections described previously. The repair involves a bolt hole eddy
current inspection to detect cracking of the fastener holes (where the
fastener holes are removed to perform the repair), and removal of
cracks. The FAA has reviewed and approved Lockheed documents LCC-7622-
373 and LCC-7622-374.
Since an unsafe condition has been identified that is likely to
exist or develop on other Lockheed Model L-1011-385 series airplanes of
the same type design, this AD is being issued to prevent reduced
structural integrity of the fuselage due to fatigue cracking of the
pressure bulkhead. This AD requires a visual inspection to detect
cracking of the bulkhead at FS 1363 in the area of the stiffeners at
left and right BL 42.5, and repair, if necessary. For airplanes on
which cracking of the bulkhead is found below WL 117, this AD requires
additional inspections to detect cracking at certain fastener locations
and fastener holes and to detect stress corrosion of the frame cap, and
repair, if necessary. The actions are required to be accomplished in
accordance with the procedures specified in the service bulletin and in
the Lockheed documents described previously.
This AD contains provisions specifying that flight with cracking in
the bulkhead, within certain parameters, is allowed provided that
repetitive visual and eddy current inspections are performed until a
repair is accomplished.
This is considered to be interim action until final action is
identified, at which time the FAA may consider further rulemaking.
As a result of recent communications with the Air Transport
Association (ATA) of America, the FAA has learned that, in general,
some operators may misunderstand the legal effect of AD's on airplanes
that are identified in the applicability provision of the AD, but that
have been altered or repaired in the area addressed by the AD. The FAA
points out that all airplanes identified in the applicability provision
of an AD are legally subject to the AD. If an airplane has been altered
or repaired in the affected area in such a way as to affect compliance
with the AD, the owner or operator is required to obtain FAA approval
for an alternative method of compliance with the AD, in accordance with
the paragraph of each AD that provides for such approvals. A note has
been included in this rule to clarify this long-standing requirement.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this rule by
submitting such written data, views, or arguments as they may desire.
Communications shall identify the Rules Docket number and be submitted
in triplicate to the address specified under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the rule. All comments submitted will be
available, both before and after the closing date for comments, in the
Rules Docket for examination by interested persons. A report that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 95-NM-103-AD.'' The postcard will be date stamped and
returned to the commenter.
The regulations adopted herein will not have substantial direct
effects 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. Therefore, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and that it is not a ``significant regulatory
action'' under Executive Order 12866. It has been determined further
that this action involves an emergency regulation under DOT Regulatory
Policies and Procedures (44 FR 11034, February 26, 1979). If it is
determined that this emergency regulation otherwise would be
significant under DOT Regulatory Policies and Procedures, a final
regulatory evaluation will be prepared and placed in the Rules Docket.
A copy of it, if filed, may be obtained from the Rules Docket at the
location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
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 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
95-12-24 Lockheed Aeronautical Systems Company: Amendment 39-9277.
Docket 95-NM-103-AD.
Applicability: All Model L-1011-385 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
[[Page 31626]]
owner/operator must use the authority provided in paragraph (f) 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 reduced structural integrity of the fuselage due to
fatigue cracking of the pressure bulkhead, accomplish the following:
(a) Prior to the accumulation of 18,000 total landings, or
within 30 days after the effective date of this AD, whichever occurs
later, perform a visual inspection to detect cracking of the
bulkhead at fuselage station (FS) 1363 in the area of the stiffeners
at left and right butt line (BL) 42.5, in accordance with the
procedures specified in paragraphs 2.A. and 2.B. of the
Accomplishment Instructions of Lockheed L-1011 Service Bulletin 093-
53-268, dated April 15, 1993.
Note 2: This AD does not require that the eddy current
inspection referenced in paragraph 2.B. of the Accomplishment
Instructions of Lockheed L-1011 Service Bulletin 093-53-268, dated
April 15, 1993, be accomplished as a requirement of paragraph (a) of
this AD.
(b) If no cracking of the bulkhead is detected, no further
action is required by this AD.
(c) Except as provided by paragraph (e) of this AD, if any
cracking of the bulkhead is detected below waterline (WL) 117: Prior
to further flight, perform the inspections required by paragraphs
(c)(1), (c)(2), and (c)(3) of this AD, in accordance with LCC-7622-
373, dated May 9, 1995. Prior to further flight, repair any cracking
of the frame cap found during these inspections, in accordance with
Lockheed document LCC-7622-374, dated May 9, 1995.
(1) Perform a bolt hole eddy current inspection to detect
cracking of the eight fastener holes at the intersection of the
vertical stiffener at BL 42.5 and the frame cap vertical flange; and
(2) Perform a bolt hole eddy current inspection to detect
cracking at eight fastener locations in the frame cap lower flange
that connect the lower fuselage skin panel to the frame at the BL
42.5 vertical stiffener; and
(3) Perform a visual inspection to detect stress corrosion
cracking of the accessible portions of the fillet radius of the
frame cap.
(d) Except as provided by paragraph (e) of this AD, if any
cracking of the bulkhead is detected at or above WL 117: Prior to
further flight, repair the bulkhead cracking in accordance with the
procedures specified in Part II of the Accomplishment Instructions
of Lockheed L-1011 Service Bulletin 093-53-268, dated April 15,
1993.
(e) Continued flight with cracking of the bulkhead is permitted,
provided that the conditions specified in paragraph 1.C. of the
Planning Information of Lockheed L-1011 Service Bulletin 093-53-268,
dated April 15, 1993, are met. For flight with cracking, both the
visual and eddy current inspections specified in paragraphs 2.B. and
2.C. of the Accomplishment Instructions of the service bulletin must
be accomplished prior to returning the aircraft to service. These
visual and eddy current inspections must be repeated within 900
landings. Prior to the accumulation of 1,800 total landings, these
inspections must be terminated by the installation of the repair
specified in Part II of the Accomplishment Instructions of the
service bulletin.
(f) 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 Aircraft Certification
Office (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 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Atlanta ACO.
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.
(h) The inspections and repair shall be done in accordance with
Lockheed L-1011 Service Bulletin 093-53-268, dated April 15, 1993;
Lockheed document LCC-7622-373, dated May 9, 1995; and Lockheed
document LCC-7622-374, dated May 9, 1995. This incorporation by
reference was approved by the Director of the Federal Register in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be
obtained from Lockheed Aeronautical Systems Support Company (LASSC),
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.
(i) This amendment becomes effective on July 3, 1995.
Issued in Renton, Washington, on June 9, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-14633 Filed 6-15-95; 8:45 am]
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