[Federal Register Volume 60, Number 81 (Thursday, April 27, 1995)]
[Proposed Rules]
[Pages 20659-20663]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-10320]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 60, No. 81 / Thursday, April 27, 1995 /
Proposed Rules
[[Page 20659]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-NM-30-AD]
Airworthiness Directives; Lockheed Model L-1011-385 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to all Lockheed Model L-1011-385
series airplanes. This proposal would require an inspection to detect
evidence of sealant around the lug bushing flanges of certain actuator
attach pin assemblies of the main landing gear (MLG), and replacement
of the pin assembly with a serviceable unit if no sealant is present.
This proposal is prompted by reports of cracks emanating from corrosion
pits of the lug bores on the actuator attach pin assemblies of two
MLG's. The actions specified by the proposed AD are intended to prevent
failure of the actuator attach pins as a result of corrosion and
subsequent cracking of the lug bores. Such failure could result in the
MLG failing to extend completely or rapidly free-falling during
extension and causing additional damage to the landing gear.
DATES: Comments must be received by May 26, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-30-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 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.
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:
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 95-NM-30-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-103, Attention: Rules
Docket No. 95-NM-30-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The FAA received reports indicating that cracked lugs were found on
the actuator attach pin assemblies of two main landing gears (MLG)
installed on Lockheed Model L-1011-385 series airplanes. The actuator
attach pins connect the piston end of the retract actuator of the MLG
to the gear strut. Results of an examination of one pin assembly
revealed that cracks emanated from corrosion pits beneath the bushing
surface on the lug bores. The corrosion may have been caused by the
intrusion of moisture between the lug surface and the bushing flange.
The lug bores on the pin assemblies lacked a proper protective finish.
In addition, the bushings were sealed insufficiently to prevent the
intrusion of moisture and resultant corrosion. Corrosion and subsequent
cracking of the lug bores, if not corrected, could result in failure of
the attach pins. This condition, if not corrected, could result in the
MLG failing to extend completely or rapidly free-falling during
extension and causing additional damage to the landing gear.
The FAA has reviewed and approved Lockheed Service Bulletin 093-32-
256, dated November 11, 1994, which describes procedures for a one-time
inspection to detect evidence of sealant around the lug bushing flanges
of certain actuator attach pin assemblies of the MLG. If sealant is not
present, the service bulletin recommends replacement of the pin
assembly with a serviceable unit.
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 a one-time inspection to detect evidence of
sealant around the lug bushing flanges of certain actuator attach pin
assemblies of the MLG and, if no sealant is present, replacement of the
pin assembly. The actions would be required to be accomplished in
accordance with the service bulletin described previously.
Operators should note that, although the service bulletin
recommends that the inspection be performed within 6 months, the FAA is
proposing a compliance time of 90 days for accomplishment of the
inspection. In developing this proposed compliance [[Page 20660]] time,
the FAA considered the safety implications, availability of required
replacement parts, and normal maintenance schedules for timely
accomplishment of the proposed actions. The FAA has determined that
accomplishment of the proposed inspection requires no special access.
Further, the proposed inspection requires only one work hour to
perform, which is sufficiently short to easily allow the inspection to
be accomplished outside normal maintenance facilities. In consideration
of these factors, the FAA has determined that a compliance time of 90
days represents an appropriate interval in which the inspection of the
pin assemblies can be accomplished in a timely manner within the fleet
and still maintain an adequate level of safety.
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 notice to clarify this long-standing requirement.
There are approximately 236 Model L-1011-385 series 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, that
it would take approximately 1 work hour per airplane to accomplish the
proposed actions, and that the average labor rate is $60 per work hour.
Based on these figures, the total cost impact of the proposed AD on
U.S. operators is estimated to be $7,020, or $60 per airplane.
The total 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.
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. 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:
Lockheed Aeronautical Systems Company: Docket 95-NM-30-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 owner/operator must use the authority
provided in paragraph (c) 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 failure of the actuator attach pins as a result of
corrosion and subsequent cracking of the lug bores, which could
result in the main landing gear (MLG) failing to extend completely
or rapidly free-falling during extension and causing additional
damage to the landing gear, accomplish the following:
(a) Within 90 days after the effective date of this AD, perform
a one-time inspection to detect evidence of sealant around the lug
bushing flanges of the actuator attach pin assembly, part number
1642699-101, of the MLG, in accordance with Lockheed Service
Bulletin 093-32-256, dated November 11, 1994.
(1) If the inspection reveals that sealant is present, no
further action is required by this AD.
(2) If the inspection reveals that no evidence of sealant is
present, within 6 months after accomplishing the inspection, replace
the actuator attach pin assembly with a serviceable unit in
accordance with Lockheed Service Bulletin 093-32-256, dated November
11, 1994.
(b) As of the effective date of this AD, no actuator attach pin
assembly, part number 1642699-101, shall be installed on the MLG of
any airplane unless that assembly has been inspected in accordance
with the requirements of paragraph (a) of this AD and evidence of
sealant has been found; or unless that assembly has been reworked
and reidentified with the letter ``A'' etched at the end of the
serial number, in accordance with Lockheed Service Bulletin 093-32-
256, dated November 11, 1994.
(c) 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.
(d) 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.
Issued in Renton, Washington, on April 21, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-10318 Filed 4-26-95; 8:45 am]
BILLING CODE 4910-13-U
[[Page 20661]]
14 CFR Part 39
[Docket No. 94-NM-186-AD]
Airworthiness Directives; British Aerospace Model BAC 1-11 200
and 400 Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: This document proposes the supersedure of an existing
airworthiness directive (AD), applicable to certain British Aerospace
Model BAC 1-11 200 and 400 airplanes, that currently requires
incorporation of certain structural modifications. That AD was prompted
by reports of fatigue cracking and corrosion in transport category
airplanes that are approaching or have exceeded their economic design
goal. The actions specified by that AD are intended to prevent reduced
structural integrity of the airplane. This action would require
incorporation of additional structural modifications.
DATES: Comments must be received by May 6, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 94-NM-186-D, 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 British Aerospace, Airbus Limited, P.O. Box 77, Bristol
BS99 7AR, England. This information may be examined at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton,
Washington.
FOR FURTHER INFORMATION CONTACT: William Schroeder, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, Washington 98055-4056; telephone (206)
227-1148; fax (206) 227-1320.
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 94-NM-186-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-103, Attention: Rules
Docket No. 94-NM-186-AD, 1601 Lind Avenue SW., Renton, Washington
98055-4056.
Discussion
On October 24, 1990, the FAA issued AD 90-23-09, amendment 39-6795
(55 FR 46502, November 5, 1990), applicable to certain British
Aerospace Model BAC 1-11 200 and 400 airplanes, to require
incorporation of certain structural modifications. That action was
prompted by reports of fatigue cracking and corrosion in transport
category airplanes that are approaching or have exceeded their economic
design goal. The requirements of that AD are intended to prevent
reduced structural integrity of the airplane.
Since the issuance of that AD, British Aerospace has issued Alert
Service Bulletin 5-A-PM5995, Issue 3, dated March 19, 1993, which
references terminating modifications described in 16 service bulletins,
and recommends that they be installed in the applicable British
Aerospace Model BAC 1-11 airplanes. The modifications described in the
service bulletins consist of:
--1 modification of the landing gear,
--5 modifications of the doors,
--5 modifications of the fuselage structure,
--3 modifications of the stabilizer, and
--2 modifications of the wings.
Additionally, Issue 3 of this alert service bulletin adds one new
modification (fuselage structure) and revises the item numbers in Table
1 of several modifications that were previously addressed by AD 90-23-
09.
Accomplishment of these modifications would terminate the
repetitive inspections required by the following AD's:
----------------------------------------------------------------------------------------------------------------
AD No. Amendment No.- Federal Register citation Date of publication
----------------------------------------------------------------------------------------------------------------
67-30-02-........................ 39-0507- 32 FR 15421-..................... November 4, 1967.
87-21-06-........................ 39-5744- 52 FR 38396-..................... October 16, 1987.
82-01-02 R1-..................... 39-4824- 49 FR 9412-...................... March 13, 1984.
83-20-02-........................ 39-4735- 48 FR 44462-..................... September 29, 1983.
88-11-09-........................ 39-5891- 53 FR 17918-..................... May 19, 1988.
72-06-01-........................ 39-1406- 37 FR 4900-...................... March 7, 1972.
71-25-02-........................ 39-1349- 36 FR 22363-..................... November 25, 1971.
----------------------------------------------------------------------------------------------------------------
Implementation of these modifications will positively address the
unsafe condition identified as reduced structural integrity of the
airplane. The Civil Aviation Authority (CAA), which is the
airworthiness authority for the United Kingdom, classified this alert
service bulletin as mandatory.
This airplane model is manufactured in the United Kingdom and is
type certificated for operation in the United States under the
provisions of section 21.29 of the Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral airworthiness agreement. Pursuant
to this bilateral airworthiness agreement, the CAA has kept the FAA
informed of the situation described above. The FAA has examined the
findings of the CAA, [[Page 20662]] reviewed all available information,
and determined that AD action is necessary for products of this type
design that are certificated for operation in the United States.
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design registered
in the United States, the proposed AD would supersede AD 90-23-09 to
require incorporation of additional structural modifications. The
actions would be required to be accomplished in accordance with the
alert service bulletin described previously.
Operators should note that the actions specified as Items 6, 11,
13, and 14 in Table 1 of British Aerospace Alert Service Bulletin 5-A-
PM5995, Issue 3, are not included in the proposed requirements of this
AD due to the following reasons:
------------------------------------------------------------------------
Item--- Reason
------------------------------------------------------------------------
6-..... Currently required by AD 91-06-16, amendment 39-6935.
11-.... Will be addressed in a separate rulemaking action.
13 -... Currently required by AD 67-15-01, amendment 39-401.
14-.... Currently required by AD 67-14-04, amendment 39-397.
------------------------------------------------------------------------
The FAA estimates that 31 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 387 work
hours per airplane to accomplish the proposed actions, and that the
average labor rate is $60 per work hour.
Required parts would cost approximately $10,315 per airplane. Based
on these figures, the total cost impact of the proposed AD on U.S.
operators is estimated to be $1,039,585, or $33,535 per airplane.
The total 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.
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. 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 removing amendment 39-6795 (55 FR
46502, November 5, 1990), and by adding a new airworthiness directive
(AD), to read as follows:
British Aerospace Airbus Limited (Formerly British Aerospace
Commercial Aircraft Limited, British Aerospace Aircraft Group):
Docket 94-NM-186-AD. Supersedes AD 90-23-09, Amendment 39-6795.
Applicability: Model BAC 1-11 200 and 400 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 use the authority
provided in paragraph (c) 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 airplane,
accomplish the following:
(a) Prior to reaching the ``Not Exceed Time'' interval specified
in Table 1 of British Aerospace Alert Service Bulletin 5-A-PM5995,
Issue 3, dated March 19, 1993; or within 15 months after the
effective date of this AD; whichever occurs later: Install the
structural modification listed in each Item in Table 1 of the alert
service bulletin, except for Items 6, 11, 13, and 14. The
modifications shall be done in accordance with the appropriate
service bulletin specified for each Item in Table 1, listed under
``Service Bulletin No.''
-Note 2: Items 6, 11, 13, and 14 in Table 1 of British Aerospace
Alert Service Bulletin 5-A-PM5995, Issue 3, are not included in the
requirements of this AD since those items are addressed by separate
rulemaking actions.
(b) Accomplishment of the modifications required by paragraph
(a) of this AD constitutes terminating action for the repetitive
inspections required by the following AD's:
----------------------------------------------------------------------------------------------------------------
AD No.- Amendment No. Federal Register citation Date of publication
----------------------------------------------------------------------------------------------------------------
67-30-02-........................ 39-0507- 32 FR 15421-..................... November 4, 1967.
87-21-06-........................ 39-5744- 52 FR 38396-..................... October 16, 1987.
82-01-02 R1-..................... 39-4824- 49 FR 9412-...................... March 13, 1984.
83-20-02-........................ 39-4735- 48 FR 44462-..................... September 29, 1983.
88-11-09-........................ 39-5891- 53 FR 17918-..................... May 19, 1988.
72-06-01-........................ 39-1406- 37 FR 4900-...................... March 7, 1972.
71-25-02-........................ 39-1349- 36 FR 22363-..................... November 25, 1971.
----------------------------------------------------------------------------------------------------------------
[[Page 20663]] (c) 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, Standardization
Branch, ANM-13, FAA, Transport 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, Standardization Branch, ANM-113.
-Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(d) 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.
Issued in Renton, Washington, on April 21, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-10320 Filed 4-26-95; 8:45 am]
BILLING CODE 4910-13-U
