[Federal Register Volume 64, Number 161 (Friday, August 20, 1999)]
[Rules and Regulations]
[Pages 45423-45425]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-21363]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-315-AD; Amendment 39-11261; AD 99-17-13]
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 adopts a new airworthiness directive (AD), 
applicable to certain Lockheed Model L-1011-385 series airplanes, that 
requires repetitive inspections to detect discrepancies of the lower 
actuator pins and/or bushings of the horizontal stabilizer, and 
replacement of any discrepant component with a new component. 
Replacement of all four actuator pins and bushings terminates the 
repetitive inspections. This amendment is prompted by a report 
indicating that a fractured lower actuator pin of the horizontal 
stabilizer was detected. The actions specified by this AD are intended 
to detect and correct discrepancies of the lower actuator pins and 
bushings of the horizontal stabilizer, which could result in reduced 
structural integrity of the horizontal stabilizer control system, and 
consequent reduced controllability of the airplane.

DATES: Effective September 24, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 24, 1999.

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, Program Manager, 
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 30337-2748; 
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 certain Lockheed Model L-1011-385 
series airplanes was published in the Federal Register on April 16, 
1999 (64 FR 18842). That action proposed to require repetitive 
inspections to detect discrepancies of the lower actuator pins and/or 
bushings of the horizontal stabilizer, and replacement of any 
discrepant component with a new component. Replacement of all four 
actuator pins and bushings terminates the repetitive inspections.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the single comment received.
    The commenter supports the proposed rule.

Explanation of Change Made to Proposal

    The FAA has added ``Note 2'' to the final rule to clarify that the 
12,000 flight cycle life limit imposed on the lower actuator pins of 
the stabilizer by AD 92-16-19, amendment 39-8329 (57 FR 36892, August 
17, 1992), is not affected by this rulemaking.

Conclusion

    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the change described 
previously. 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 235 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 117 airplanes of U.S. registry 
will be affected by this AD.
    It will take approximately 4 work hours per airplane to accomplish 
the required inspection, at an average labor rate of $60 per work hour. 
Based on these figures, the cost impact of the inspection required by 
this AD on U.S. operators is estimated to be $28,080, or $240 per 
airplane, per inspection cycle.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the 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 terminating 
action that is provided by this AD action, it would take approximately 
2 work hours to accomplish it, at an average labor rate of $60 per work 
hour. Required parts would cost approximately $4,550 per set of four 
pins and bushings, per airplane. Based

[[Page 45424]]

on these figures, the cost impact of the accomplishment of the optional 
terminating action would be $4,670 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 adding the following new 
airworthiness directive:

99-17-13  Lockheed: Amendment 39-11261. Docket 98-NM-315-AD.

    Applicability: Model L-1011-385-1, -1-14, -1-15, and -3 series 
airplanes, as listed in Lockheed Service Bulletin 093-27-306, dated 
January 14, 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 (e) 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 discrepancies of the lower actuator pins 
and bushings of the horizontal stabilizer, which could result in 
reduced structural integrity of the horizontal stabilizer control 
system, and consequent reduced controllability of the airplane, 
accomplish the following:

Initial Inspection

    (a) Except as provided by paragraph (a)(3) of this AD: Perform 
an inspection to detect discrepancies (e.g., damage, cracking), of 
the lower actuator pins and/or bushings of the horizontal stabilizer 
using one of the three inspection methods (borescope, eddy current, 
or magnetic particle) listed in Lockheed Service Bulletin 093-27-
306, dated January 14, 1998, in accordance with that service 
bulletin, at the time specified in paragraph (a)(1), (a)(2), or 
(a)(3) of this AD, as applicable.
    (1) For airplanes that have accumulated fewer than 3,500 flight 
cycles since replacement of the actuator pins or bushings as of the 
effective date of this AD: Inspect within 3,500 flight cycles since 
replacement, or within 6 months after the effective date of this AD, 
whichever occurs later.
    (2) For airplanes that have accumulated 3,500 or more flight 
cycles, but fewer than 5,000 flight cycles, since replacement of the 
actuator pins or bushings as of the effective date of this AD: 
Inspect within 60 days after the accumulation of 5,000 flight cycles 
since replacement, or within 6 months after the effective date of 
this AD, whichever occurs first.
    (3) For airplanes that have accumulated 5,000 or more flight 
cycles since replacement of the actuator pins or bushings as of the 
effective date of this AD: Perform a magnetic particle inspection 
within 60 days after the effective date of this AD.

    Note 2: The 12,000 flight cycle life limit imposed on the lower 
actuator pins of the stabilizer by AD 92-16-19, amendment 39-8329 
(57 FR 36892, August 17, 1992), is not affected by this rulemaking.

Repetitive Inspections

    (b) Thereafter, repeat the inspection required by paragraph (a) 
of this AD in accordance with Lockheed Service Bulletin 093-27-306, 
dated January 14, 1998, at the interval specified in paragraph 
(b)(1), (b)(2), (b)(3), or (b)(4) of this AD; as applicable; until 
the actions specified in paragraph (d) of this AD have been 
accomplished.
    (1) If the immediately preceding inspection was performed using 
borescope or eddy current procedures, and fewer than 5,000 flight 
cycles have accumulated since the most recent replacement of the 
actuator pins or bushings: Within 350 flight cycles after 
accomplishment of the initial inspection, perform a borescope, eddy 
current, or magnetic particle inspection. Repeat the inspection 
using a borescope or eddy current technique, as applicable, 
thereafter at intervals not to exceed 350 flight cycles.
    (2) If the immediately preceding inspection was performed using 
borescope or eddy current procedures, and 5,000 or more flight 
cycles have accumulated since the most recent replacement of the 
actuator pins or bushings: Within 350 flight cycles after 
accomplishment of the initial inspection, perform a magnetic 
particle inspection. Repeat the magnetic particle inspection 
thereafter at intervals not to exceed 1,000 flight cycles.
    (3) If the immediately preceding inspection was performed using 
magnetic particle procedures, and fewer than 5,000 flight cycles 
have accumulated since the most recent replacement of the actuator 
pins or bushings: Perform a borescope, eddy current, or magnetic 
particle inspection within 1,000 flight cycles.
    (4) If the immediately preceding inspection was performed using 
magnetic particle procedures, and 5,000 or more flight cycles have 
accumulated since the most recent replacement of the actuator pins 
or bushings: Perform a magnetic particle inspection with 1,000 
flight cycles. Repeat the magnetic particle inspection thereafter at 
intervals not to exceed 1,000 flight cycles.

Corrective Action

    (c) If any discrepancy (e.g., damage, cracking) is detected 
during any inspection required by this AD, prior to further flight, 
accomplish paragraph (c)(1) or (c)(2) of this AD, as applicable, in 
accordance with Lockheed Service Bulletin 093-27-306, dated January 
14, 1998.
    (1) If any discrepancy is detected after performing a borescope 
or eddy current inspection, perform a magnetic particle inspection.
    (2) If any discrepancy is detected after performing a magnetic 
particle inspection, replace the discrepant component with a new 
component. Accomplishment of this replacement terminates the 
repetitive inspections for that component.

Terminating Action

    (d) Replacement of all four actuator pins and bushings with new 
actuator pins and bushings, in accordance with Lockheed Service 
Bulletin 093-27-306, dated January 14, 1998, constitutes terminating 
action for the repetitive inspections required by this AD.

Alternative Methods of Compliance

    (e) 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

[[Page 45425]]

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

    (f) Special flight permits may be issued in accordance with 
Sec. Sec. 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

    (g) The actions shall be done in accordance with Lockheed 
Service Bulletin 093-27-306, dated January 14, 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.
    (h) This amendment becomes effective on September 24, 1999.

    Issued in Renton, Washington, on August 10, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-21363 Filed 8-19-99; 8:45 am]
BILLING CODE 4910-13-U