AD 2000-10-20

[Federal Register Volume 65, Number 110 (Wednesday, June 7, 2000)]
[Rules and Regulations]
[Pages 36053-36055]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 00-14018]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-311-AD; Amendment 39-11744; AD 2000-10-20]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to all Lockheed Model L-1011-385 series airplanes, that 
requires repetitive inspections to detect cracking of the fuselage skin 
in the areas of the left- and right-hand stringerless sidewall window 
belts, and repair, if necessary. This amendment is prompted by reports 
of fatigue cracks found in the fuselage skin where the skin thickness 
steps from 0.40 to 0.23 inch. The actions specified by this AD are 
intended to detect and correct cracking of the fuselage skin, which 
could result in reduced structural integrity of the airplane.

DATES: Effective July 12, 2000. The incorporation by reference of 
certain publications listed in the regulations is approved by the 
Director of the Federal Register as of July 12, 2000.

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) to include an airworthiness 
directive (AD) that is applicable to all Lockheed Model L-1011-385 
series airplanes was published in the Federal Register on February 16, 
2000 (65 FR 7801). That action proposed to require require repetitive 
inspections to detect cracking of the fuselage skin in the areas of the 
left- and right-hand stringerless sidewall window belts, and repair, if 
necessary.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

Conclusion

    The FAA has determined that air safety and the public interest 
require the adoption of the rule as proposed.

Cost Impact

    There are approximately 235 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 117 airplanes of U.S. registry 
will be

[[Page 36054]]

affected by this AD, that it will take approximately 48 work hours per 
airplane to accomplish the required inspection, and that the average 
labor rate is $60 per work hour. Based on these figures, the cost 
impact of the AD on U.S. operators is estimated to be $336,960, or 
$2,880 per airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the requirements of this AD 
action, and that no operator would accomplish those actions in the 
future if this AD were not adopted.

Regulatory Impact

    The regulations adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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 adding the following new 
airworthiness directive:

2000-10-20 Lockheed: Amendment 39-11744. Docket 98-NM-311-AD.

    Applicability: All Model L-1011-385 series airplanes, as listed 
in Lockheed Service Bulletin 093-53-279, dated May 6, 1998; 
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 (f) 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 fuselage skin, which could 
result in reduced structural integrity of the airplane, accomplish 
the following:
    (a) Perform an ultrasonic inspection on the fuselage skin in the 
area of the stringerless sidewall window belts, at the radii on both 
the forward and aft sides of the machined cutout where the fuselage 
skin steps from 0.40 to 0.23 inch, to detect cracking in the base of 
the radii. Accomplish the inspection in accordance with Lockheed 
Service Bulletin 093-53-279, dated May 6, 1998, at each of the 6 
specific inspection zones identified in the service bulletin at the 
later of the times specified in paragraphs (a)(1) and (a)(2) of this 
AD.
    (1) Prior to the accumulation of 20,000 total flight cycles; or
    (2) Within 600 flight cycles or 6 months after the effective 
date of this AD, whichever occurs first.
    (b) For readings of less than 20 percent obtained at all 6 
inspection zones during the ultrasonic inspection required by 
paragraph (a) of this AD: Repeat the ultrasonic inspection 
thereafter at intervals not to exceed 1,500 flight cycles.
    (c) Except as provided by paragraph (e) of this AD: For any 
reading of 20 percent or greater and less than or equal to 50 
percent obtained at any inspection zone during the ultrasonic 
inspection required by paragraph (a) of this AD, prior to further 
flight, perform a low frequency eddy current (LFEC) inspection to 
measure the depth of the cracking, in accordance with Lockheed 
Service Bulletin 093-53-279, dated May 6, 1998.
    (1) If the results of the LFEC inspection are outside the reject 
zone, as defined in the service bulletin: Within 1,500 flight 
cycles, repeat both the ultrasonic and LFEC inspections specified by 
paragraphs (a) and (c), respectively, of this AD.
    (i) If the results of the LFEC inspection specified by paragraph 
(c)(1) of this AD are outside the reject zone: Within 1,800 flight 
cycles after the initial crack finding, as detected during the 
ultrasonic inspection specified in paragraph (a) of this AD, repair 
any affected inspection zone in accordance with Part II of the 
Accomplishment Instructions of the service bulletin. Such repair 
constitutes terminating action for the repetitive inspection 
requirements of this AD for the repaired inspection zone only.
    (ii) If the results of the LFEC inspection specified by 
paragraph (c)(1) of this AD are within the reject zone: Prior to 
further flight, repair any affected inspection zone in accordance 
with Part II of the Accomplishment Instructions of the service 
bulletin. Such repair constitutes terminating action for the 
repetitive inspection requirements of this AD for the repaired 
inspection zone only.
    (2) If the results of the LFEC inspection are within the reject 
zone, as defined in the service bulletin: Prior to further flight, 
repair any affected inspection zone in accordance with Part II of 
the Accomplishment Instructions of the service bulletin. Such repair 
constitutes terminating action for the repetitive inspection 
requirements of this AD for the repaired inspection zone only.
    (d) Except as provided by paragraph (e) of this AD: For any 
reading of 50 percent or greater obtained at any inspection zone 
during the ultrasonic inspection required by paragraph (a) of this 
AD, prior to further flight, perform a LFEC inspection to measure 
the depth of the cracking, in accordance with Lockheed Service 
Bulletin 093-53-279, dated May 6, 1998.
    (1) If the results of the LFEC inspection are outside the reject 
zone, as defined in the service bulletin: Within 300 flight cycles, 
repeat both the ultrasonic and LFEC inspections specified in 
paragraphs (a) and (c), respectively, of this AD.
    (i) If the results of the LFEC inspection specified by paragraph 
(d)(1) of this AD are outside the reject zone: Within 600 flight 
cycles after the initial crack finding, as detected during the 
ultrasonic inspection specified in paragraph (a) of this AD, repair 
any affected inspection zone in accordance with Part II of the 
Accomplishment Instructions of the service bulletin. Such repair 
constitutes terminating action for the repetitive inspection 
requirements of this AD for the repaired inspection zone only.
    (ii) If the results of the LFEC inspection specified by 
paragraph (d)(1) of this AD are within the reject zone: Prior to 
further flight, repair any affected inspection zone in accordance 
with Part II of the Accomplishment Instructions of the service 
bulletin. Such repair constitutes terminating action for the 
repetitive inspection requirements of this AD for the repaired 
inspection zone only.
    (2) If the results from the LFEC inspection are within the 
reject zone, as defined in the service bulletin: Prior to further 
flight, repair any affected inspection zone in accordance with Part 
II of the Accomplishment Instructions of the service bulletin. Such 
repair constitutes terminating action for the repetitive inspection 
requirements of this AD for the repaired inspection zone only.
    (e) For any inspection results that require repair in two 
adjacent zones: Prior to further flight, repair in accordance with a 
method approved by the Manager, Atlanta Aircraft Certification 
Office (ACO), FAA, Small Airplane Directorate.

[[Page 36055]]

Alternative Methods of Compliance

    (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 ACO. 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.

Special Flight Permits

    (g) 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.

Incorporation by Reference

    (h) Except as provided by paragraph (e) of this AD, the actions 
shall be done in accordance with Lockheed Service Bulletin 093-53-
279, dated May 6, 1998. 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 
Martin Aircraft & Logistics Center, 120 Orion Street, Greenville, 
South Carolina 29605. Copies may be inspected at the FAA, Transport 
Airplane Directorate, 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.
    (i) This amendment becomes effective on July 12, 2000.

    Issued in Renton, Washington, on May 17, 2000.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 00-14018 Filed 6-6-00; 8:45 am]
BILLING CODE 4910-13-U