[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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