[Federal Register Volume 64, Number 73 (Friday, April 16, 1999)]
[Proposed Rules]
[Pages 18842-18845]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-9511]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-NM-315-AD]
RIN 2120-AA64
Airworthiness Directives; Lockheed Model L-1011-385 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to certain Lockheed Model L-1011-385
series airplanes. This proposal would 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
would
[[Page 18843]]
terminate the repetitive inspections. This proposal is prompted by a
report indicating that a fractured lower actuator pin of the horizontal
stabilizer was detected. The actions specified by the proposed 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: Comments must be received by June 1, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 98-NM-315-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056. Comments may be inspected at this
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except
Federal holidays.
The service information referenced in the proposed rule may be
obtained from Lockheed Martin Aircraft & Logistics Center, 120 Orion
Street, Greenville, South Carolina 29605. This information may be
examined 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.
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:
Comments Invited
Interested persons are invited to participate in the making of the
proposed 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 above. All
communications received on or before the closing date for comments,
specified above, will be considered before taking action on the
proposed rule. The proposals contained in this notice may be changed in
light of the comments received.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the proposed 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 summarizing each FAA-public contact concerned with
the substance of this proposal will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 98-NM-315-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules
Docket No. 98-NM-315-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The FAA has received a report indicating that a fractured lower
actuator pin of the horizontal stabilizer was detected on a Lockheed
Model L-1011-385 series airplane. Subsequently, cracking of another pin
and galling of two adjacent pins were detected. Such cracking and
galling have been attributed to extensive pitting corrosion damage to
the bushings of the horizontal stabilizer actuator assembly. Further
investigation revealed that certain actuator pins could have been
replaced without the installation of new bushings; the old bushings do
not have the required interference fit with the new pins. This lack of
adequate interference fit can result in the pin surface rubbing against
the bushing, which, when combined with corrosion damage on the bushing,
can lead to galling damage on the pin surface. The galling damage may
lead to crack initiation and early failure of the pin. Such
discrepancies, if not corrected, could result in reduced structural
integrity of the horizontal stabilizer control system, and consequent
reduced controllability of the airplane.
Other Relevant Rulemaking
In 1992, the FAA issued AD 92-16-19, amendment 39-8329 (57 FR
36892, August 17, 1992), which requires a one-time inspection to detect
missing, sheared, or deformed horizontal stabilizer lower actuator
pins, and replacement of the pins, if necessary. That AD also requires
either a one-time magnetic particle inspection to detect cracks on the
horizontal stabilizer actuator pins and replacement of any cracked pins
found, or replacement of each of the four actuator pins. That AD also
specifies a life limit of 12,000 flight cycles on certain actuator
pins.
Explanation of Relevant Service Information
The FAA has reviewed and approved Lockheed Service Bulletin 093-27-
306, dated January 14, 1998, which describes procedures for repetitive
inspections (borescope, eddy current, magnetic particle) of the lower
actuator pins and/or bushings of the horizontal stabilizer to detect
discrepancies, and replacement of certain actuator pins and bushings
with new components. Replacement of all four actuator pins and bushings
would terminate the repetitive inspections. Accomplishment of the
actions specified in the service bulletin is intended to adequately
address the identified unsafe condition.
Explanation of Requirements of Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other products of this same type design, the
proposed AD would require accomplishment of the actions specified in
the service bulletin described previously.
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
would be affected by this proposed AD.
It would take approximately 4 work hours per airplane to accomplish
the proposed inspection, at an average labor rate of $60 per work hour.
Based on these figures, the cost impact of the inspection proposed 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 would be 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 on these
figures, the cost impact of the optional terminating action would be
$4,670 per airplane.
[[Page 18844]]
Regulatory Impact
The regulations proposed herein would 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 proposal would not have sufficient federalism
implications to warrant the preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this proposed
regulation (1) is not a ``significant regulatory action'' under
Executive Order 12866; (2) is not a ``significant rule'' under the DOT
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);
and (3) if promulgated, 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 copy of the draft
regulatory evaluation prepared for this action is contained in the
Rules Docket. A copy of it may be obtained by contacting the Rules
Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
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:
Lockheed: 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.
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 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
(f) Special flight permits may be issued in accordance with
Secs. 21.197 and 21.199 of the
[[Page 18845]]
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.
Issued in Renton, Washington, on April 9, 1999.
John J. Hickey,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-9511 Filed 4-15-99; 8:45 am]
BILLING CODE 4910-13-U
