[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]



 ========================================================================
 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