[Federal Register Volume 64, Number 71 (Wednesday, April 14, 1999)]
[Rules and Regulations]
[Pages 18324-18327]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-9130]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-315-AD; Amendment 39-11128; AD 99-08-20]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to all Lockheed Model L-1011-385 series airplanes, 
that currently requires a one-time inspection to detect cracking of the 
bulkhead at fuselage

[[Page 18325]]

station (FS) 1363 at butt line 42.5, and repair or additional 
inspections, if necessary. This amendment adds repetitive inspections 
to detect cracking of the bulkhead web and bulkhead cap (frame cap) at 
FS 1363, and repair, if necessary. This amendment is prompted by 
reports that additional, more extensive, fatigue cracking was found in 
the bulkhead web and cap. The actions specified by this AD are intended 
to detect and correct cracking of the bulkhead web and cap, which could 
result in reduced structural integrity of the fuselage.

DATES: Effective May 19, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of May 19, 1999.
    The incorporation by reference of certain other publications, as 
listed in the regulations, was approved previously by the Director of 
the Federal Register as of July 3, 1995 (60 FR 31624, June 16, 1995).

ADDRESSES: The service information referenced in this AD may be 
obtained from Lockheed Martin Aircraft & Logistics Center, 120 Orion 
Street, Greenville, South Carolina 29605. This information may be 
examined at the Federal Aviation Administration (FAA), Transport 
Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, 
Washington; or at the FAA, Small Airplane Directorate, Atlanta Aircraft 
Certification Office, One Crown Center, 1895 Phoenix Boulevard, suite 
450, Atlanta, 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, 
Systems and Flight Test Branch, ACE-116A, FAA, Small Airplane 
Directorate, Atlanta Aircraft Certification Office, One Crown Center, 
1895 Phoenix Boulevard, suite 450, Atlanta, Georgia 30349; telephone 
(770) 703-6063; fax (770) 703-6097.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 95-12-24, 39-
9277 (60 FR 31624, June 16, 1995), applicable to all Lockheed Model L-
1011-385 series airplanes, was published in the Federal Register on 
September 11, 1998 (63 FR 48655). The action proposed to continue to 
require a one-time visual inspection to detect cracking of the bulkhead 
at fuselage station (FS) 1363 at butt line 42.5, and repair or 
additional inspections, if necessary. The action also proposed to add 
repetitive visual and eddy current surface scan inspections to detect 
cracking of the bulkhead web at FS 1363; repetitive visual, eddy 
current bolt hole, eddy current surface scan, and X-ray inspections to 
detect cracking of the bulkhead cap at FS 1363; and repair, if 
necessary. The inspections would be required to be accomplished in 
accordance with the service bulletins described previously. The action 
also proposed to provide for modification of the bulkhead web or 
bulkhead cap, which, if accomplished, introduces a new threshold of 
18,000 flight cycles for the repetitive inspections of the modified 
area.
    In addition, the action also proposed that flight with a crack in 
the bulkhead web is allowed, provided that (1) the crack does not 
extend beyond a certain area, (2) the crack does not exceed a certain 
maximum length, (3) the horizontal stiffeners above and below the web 
crack have no detectable cracks, and (4) inspections of the bulkhead 
are repeated on a more frequent basis until repair is accomplished.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Support for the Proposal

    Two commenters support the proposed rule.

Request To Add Approval for Previously Approved Alternative Methods 
of Compliance

    One commenter requests that approval be granted to use previously 
issued alternative methods of compliance (AMOC) that were issued for AD 
95-12-24.
    The FAA concurs with the commenter's request. The FAA inadvertently 
omitted reference to the fact that AMOC's issued for AD 95-12-24 are 
approved for this AD. Accordingly, the final rule has been revised to 
add new paragraph (i)(2) to specify that AMOC's approved previously in 
accordance with AD 95-12-24 are approved as AMOC's for this AD.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the change previously 
described. The FAA has determined that this change will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    There are approximately 236 Model L-1011 series airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 118 
airplanes of U.S. registry will be affected by this AD.
    The actions that are currently required by AD 95-12-24 take 
approximately 16 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Based on these figures, the cost 
impact of the currently required actions on U.S. operators is estimated 
to be $113,280, or $960 per airplane.
    The new inspections of the bulkhead web that are required by this 
new AD action will take approximately 16 work hours per airplane to 
accomplish, at an average labor rate of $60 per work hour. Based on 
these figures, the cost impact of the inspections of the bulkhead web 
required by this AD on U.S. operators is estimated to be $113,280, or 
$960 per airplane, per inspection cycle.
    The new inspections of the bulkhead cap that are required by this 
AD action will take approximately 40 work hours per airplane to 
accomplish, at an average labor rate of $60 per work hour. Based on 
these figures, the cost impact of the inspections of the bulkhead cap 
required by this AD on U.S. operators is estimated to be $283,200, or 
$2,400 per airplane, per inspection cycle.
    Should an operator be required to accomplish the repair of cracking 
in the bulkhead web, it will take between 8 to 32 work hours per 
airplane (8 work hours for each cracked area) to accomplish the repair, 
at an average labor rate of $60 per work hour. Based on these figures, 
the cost impact of any necessary repair of the bulkhead web is 
estimated to be between $480 to $1,920 per airplane.
    Should an operator be required to accomplish the repair of cracking 
in the bulkhead cap, it will take approximately 200 work hours per 
airplane to accomplish the repair, at an average labor rate of $60 per 
work hour. Based on these figures, the cost impact of any necessary 
repair of the bulkhead cap is estimated to be $12,000 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the current or proposed 
requirements of this AD action, and that no operator would accomplish 
those actions in the future if this AD were not adopted.
    Should an operator elect to accomplish the optional modification of 
the bulkhead web that will be provided by this AD action, it would take 
approximately 48 work hours to accomplish, at an average labor rate of

[[Page 18326]]

$60 per work hour. Based on these figures, the cost impact of the 
optional modification of the bulkhead web will be $2,880 per airplane.
    Should an operator elect to accomplish the optional modification of 
the bulkhead cap that will be provided by this AD action, it would take 
approximately 200 work hours to accomplish, at an average labor rate of 
$60 per work hour. Based on these figures, the cost impact of the 
optional modification of the bulkhead cap would be $12,000 per 
airplane.

Regulatory Impact

    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.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under 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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-9277 (60 FR 
31624, June 16, 1995), and by adding a new airworthiness directive 
(AD), amendment 39-11128, to read as follows:

99-08-20  Lockheed: Amendment 39-11128. Docket 97-NM-315-AD. 
Supersedes AD 95-12-24, Amendment 39-9277.

    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 owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (i)(1) 
of this AD. The request should include an assessment of the effect 
of the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct cracking of the bulkhead web and cap, 
which could result in reduced structural integrity of the fuselage, 
accomplish the following:

Restatement of the Requirements of AD 95-12-24, Amendment 39-9277

    (a) Prior to the accumulation of 18,000 total landings, or 
within 30 days after July 3, 1995 (the effective date of AD 95-12-
24, amendment 39-9277), 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 Part I of the Accomplishment Instructions of 
Lockheed L-1011 Service Bulletin 093-53-268, dated April 15, 1993; 
or in accordance with the procedures specified in paragraphs 2.A. 
and 2.B. of Part II of the Accomplishment Instructions of Lockheed 
L-1011 Service Bulletin 093-53-268, Revision 1, dated July 2, 1996.

    Note 2: This AD does not require that the eddy current 
inspection referenced in paragraph 2.B. of Part I of the 
Accomplishment Instructions of Lockheed L-1011 Service Bulletin 093-
53-268, dated April 15, 1993; and referenced in paragraph 2.B. of 
Part II of the Accomplishment Instructions of Lockheed L-1011 
Service Bulletin 093-53-268, Revision 1, dated July 2, 1996; be 
accomplished as a requirement of paragraph (a) of this AD.

    (b) Except as provided by paragraph (d) of this AD, if any 
cracking of the bulkhead is detected below waterline (WL) 117 during 
any inspection performed in accordance with paragraph (a) of this 
AD: Prior to further flight, perform the inspections required by 
paragraphs (b)(1), (b)(2), and (b)(3) of this AD, in accordance with 
Lockheed Document LCC-7622-373, dated May 9, 1995. Prior to further 
flight, repair any cracking of the bulkhead 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 bulkhead cap vertical flange; 
and
    (2) Perform a bolt hole eddy current inspection to detect 
cracking at eight fastener locations in the bulkhead 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 
bulkhead cap.
    (c) Except as provided by paragraph (d) of this AD, if any 
cracking of the bulkhead is detected at or above WL 117 during any 
inspection performed in accordance with paragraph (a) of this AD: 
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; or in accordance with the procedures specified in 
Part III of the Accomplishment Instructions of Lockheed L-1011 
Service Bulletin 093-53-268, Revision 1, dated July 2, 1996.
    (d) 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; or Revision 1, dated July 2, 1996; are met. 
For flight with cracking, both the visual and eddy current 
inspections specified in paragraphs 2.B. and 2.C. of Part I of the 
Accomplishment Instructions of Lockheed L-1011 Service Bulletin 093-
53-268, dated April 15, 1993; or specified in paragraphs 2.B. and 
2.C. of Part II of the Accomplishment Instructions of Lockheed L-
1011 Service Bulletin 093-53-268, Revision 1, dated July 2, 1996; 
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 
Lockheed L-1011 Service Bulletin 093-53-268, dated April 15, 1993; 
or by installation of the repair specified in Part III of the 
Accomplishment Instructions of Lockheed L-1011 Service Bulletin 093-
53-268, Revision 1, dated July 2, 1996.

New Requirements of This AD

    (e) Prior to the accumulation of 18,000 total landings, or 
within 6 months after the effective date of the AD, whichever occurs 
later, perform a visual and eddy current surface scan inspection for 
cracking of the bulkhead web at FS 1363, in accordance with Lockheed 
L-1011 Service Bulletin 093-53-268, Revision 1, dated July 2, 1996.
    (1) If no cracking of the bulkhead web is detected, except as 
provided by paragraph (f) of this AD, repeat the visual and eddy 
current surface scan inspections thereafter at intervals not to 
exceed 2,000 landings.
    (2) If cracking of the bulkhead web is detected, and that 
cracking is within the

[[Page 18327]]

limits specified in Part I of the Accomplishment Instructions of the 
service bulletin: Accomplish the requirements of either paragraph 
(e)(2)(i) or (e)(2)(ii) of this AD, in accordance with the service 
bulletin. Except as provided by paragraph (f) of this AD, repeat the 
inspections thereafter at intervals not to exceed 2,000 landings 
after repair of the cracking.
    (i) Prior to further flight, repair the cracking. Or
    (ii) Repeat the inspections specified in Part I of the 
Accomplishment Instructions of the service bulletin at intervals not 
to exceed 900 landings, and repair the cracking within 1,800 
landings after the cracking was detected.
    (3) If cracking of the bulkhead web is detected, and that 
cracking is outside the limits specified in Part I of the 
Accomplishment Instructions of the service bulletin: Prior to 
further flight, repair in accordance with Part III of the 
Accomplishment Instructions of the service bulletin. Except as 
provided by paragraph (f) of this AD, repeat the inspections 
thereafter at intervals not to exceed 2,000 landings.
    (f) For airplanes on which modification of the bulkhead web is 
accomplished in accordance with Part IV of the Accomplishment 
Instructions of Lockheed L-1011 Service Bulletin 093-53-268, 
Revision 1, dated July 2, 1996: Repeat the inspections specified in 
paragraph (e) of this AD within 18,000 landings after accomplishment 
of the modification, in accordance with the service bulletin.
    (g) Prior to the accumulation of 18,000 total landings, or 
within 6 months after the effective date of this AD, whichever 
occurs later, perform visual, bolt hole eddy current, eddy current 
surface scan, and X-ray inspections for cracking of the bulkhead cap 
at FS 1363, in accordance with Lockheed L-1011 Service Bulletin 093-
53-272, dated November 12, 1996.
    (1) If no cracking of the bulkhead cap is detected, except as 
provided by paragraph (h) of this AD, repeat the inspections 
thereafter at intervals not to exceed 2,000 landings, in accordance 
with the service bulletin.
    (2) If any cracking of the bulkhead cap is detected, accomplish 
the requirements of either paragraph (g)(2)(i) or (g)(2)(ii) of this 
AD, in accordance with the service bulletin.
    (i) Prior to further flight, repair in accordance with Part I of 
the Accomplishment Instructions of the service bulletin. Thereafter, 
repeat the inspections at intervals not to exceed 2,000 landings. Or
    (ii) Prior to further flight, replace the bulkhead cap, in 
accordance with Part II of the Accomplishment Instructions of the 
service bulletin. Following such replacement, repeat the inspection 
within 18,000 landings, in accordance with the service bulletin.
    (h) For airplanes on which replacement of the bulkhead cap is 
accomplished in accordance with Part II of the Accomplishment 
Instructions of Lockheed L-1011 Service Bulletin 093-53-272, dated 
November 12, 1996: Repeat the inspections specified in paragraph (g) 
of this AD within 18,000 landings after accomplishment of the 
replacement, in accordance with the service bulletin.
    (i)(1) 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.

    (i)(2) Alternative methods of compliance approved previously in 
accordance with AD 95-12-24, amendment 39-9277, are approved as 
alternative methods of compliance for this AD.
    (j) Special flight permits may be issued in accordance with 
Secs. 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.

Incorporation by Reference

    (k) The actions shall be done in accordance with Lockheed L-1011 
Service Bulletin 093-53-268, Revision 1, dated July 2, 1996; 
Lockheed L-1011 Service Bulletin 093-53-268, dated April 15, 1993; 
Lockheed Document LCC-7622-373, dated May 9, 1995; Lockheed Document 
LCC-7622-374, dated May 9, 1995; and Lockheed L-1011 Service 
Bulletin 093-53-272, dated November 12, 1996; as applicable.
    (1) The incorporation by reference of Lockheed L-1011 Service 
Bulletin 093-53-268, Revision 1, dated July 2, 1996, and Lockheed L-
1011 Service Bulletin 093-53-272, dated November 12, 1996, is 
approved by the Director of the Federal Register in accordance with 
5 U.S.C. 552(a) and 1 CFR part 51.
    (2) The incorporation by reference of 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, was approved previously by the Director of the 
Federal Register as of July 3, 1995 (60 FR 31624, June 16, 1995).
    (3) Copies may be obtained from Lockheed Martin Aircraft & 
Logistics Center, 120 Orion Street, Greenville, South Carolina 
29605. This information may be examined at the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, Rules Docket, 
1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Small 
Airplane Directorate, Atlanta Aircraft Certification Office, One 
Crown Center, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia; 
or at the Office of the Federal Register, 800 North Capitol Street, 
NW., suite 700, Washington, DC.
    (l) This amendment becomes effective on May 19, 1999.

    Issued in Renton, Washington, on April 6, 1999.
John J. Hickey,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-9130 Filed 4-13-99; 8:45 am]
BILLING CODE 4910-13-U