[Federal Register Volume 61, Number 82 (Friday, April 26, 1996)]
[Proposed Rules]
[Pages 18524-18528]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-10308]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-CE-22-AD]
RIN 2120-AA64


Airworthiness Directives; Fairchild Aircraft SA26, SA226, and 
SA227 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Supplemental notice of proposed rulemaking (NPRM); Reopening of 
the comment period.

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SUMMARY: This document proposes to revise an earlier proposed 
airworthiness directive (AD), which would have superseded AD 93-19-06. 
That AD currently requires repetitively inspecting acrylic cabin and 
cockpit side windows for cracks on certain Fairchild Aircraft SA26, 
SA226, and SA227 series airplanes, and, if cracks are found that exceed 
certain limitations, replacing that window. The previous document 
included the following: the proposed requirement of modifying certain 
cockpit side windows; more fully-defined crack limitations; and more 
clear repetitive inspection intervals for the affected airplanes over 
those included in AD 93-19-06. Comments received regarding the NPRM 
have prompted the Federal Aviation Administration to change the 
proposal and allow the public a further opportunity to participate in 
the rulemaking process. The actions specified by the proposed AD are 
intended to prevent acrylic cabin or cockpit side window failures, 
which, if not detected and corrected, could result in airframe damage 
and decompression injuries.

DATES: Comments must be received on or before June 24, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Central Region, Office of the Assistant Chief 
Counsel, Attention: Rules Docket No. 94-CE-22-AD, Room 1558, 601 E. 
12th Street, Kansas City, Missouri 64106. Comments may be inspected at 
this location between 8 a.m. and 4 p.m., Monday through Friday, 
holidays excepted.
    Service information that applies to the proposed AD may be obtained 
from Fairchild Aircraft, P.O. Box 790490, San Antonio, Texas 78279-
0490; telephone (210) 824-9421. This information also may be examined 
at the Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT:
Mr. Hung Viet Nguyen, Aerospace Engineer, FAA, Airplane Certification 
Office, 2601 Meacham Boulevard, Fort Worth, Texas 76193-0150; telephone 
(817) 222-5155; facsimile (817) 222-5960.

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 should 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 that summarizes 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 No. 94-CE-22-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of Supplemental NPRM

    Any person may obtain a copy of this supplemental NPRM by 
submitting a request to the FAA, Central Region, Office of the 
Assistant Chief Counsel, Attention: Rules Docket No. 94-CE-22-AD, Room 
1558, 601 E. 12th Street, Kansas City, Missouri 64106.

Discussion

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to include an AD that would apply to certain Fairchild 
Aircraft SA26, SA226, and SA227 series airplanes was published in the 
Federal Register on February 21, 1995 (60 FR 9649). The action proposed 
to supersede AD 93-19-06 with a new AD that would maintain the 
requirement of repetitively inspecting acrylic cabin and cockpit side 
windows for cracks, and replacing any window where cracks are found 
that exceed certain limitations. That NPRM proposed to require 
modifying windows that do not have inner window panes installed. 
Accomplishment of the modification proposed in the NPRM would be in 
accordance with the following service bulletins (SB), as applicable:

----------------------------------------------------------------------------------------------------------------
                        Page No.                                                   Date                         
----------------------------------------------------------------------------------------------------------------
  Fairchild SB 26-56-10-045, which incorporates the following pages and revision levels:                        
                                                                                                                
3, 4, 5, and 9.........................................  Revised: December 1, 1994.                             

[[Page 18525]]

                                                                                                                
1, 2, 6, 7, 8, and 10 through 14.......................  Issued: August 11, 1994.                               
                                                                                                                
   Fairchild SB 226-56-005, which incorporates the following pages and revision levels:                         
                                                                                                                
3 through 7, and 9.....................................  Revised: December 1, 1994.                             
1, 2, and 8............................................  Revised: August 11, 1994.                              
10 through 16..........................................  Issued: July 31, 1991.                                 
                                                                                                                
   and Fairchild SB 227-56-005, which incorporates the following pages and revision levels:                     
                                                                                                                
3 through 7, and 9.....................................  Revised: December 1, 1994.                             
1, 2, and 8............................................  Revised: August 11, 1994.                              
10 through 16..........................................  Issued: July 31, 1991.                                 
----------------------------------------------------------------------------------------------------------------



    Accomplishment of the repetitive inspections proposed in the NPRM 
would be in accordance with the following SB's, as applicable:

Fairchild SB 26-56-20-042, Issued: November 28, 1988; Revised: February 
7, 1991.
Fairchild SB 226-56-001, Issued: February 2, 1983; Revised: November 
26, 1991.
Fairchild SB 227-56-001, Issued: February 2, 1983; Revised: November 
26, 1991.
Fairchild SB 226-56-002, Issued: March 3, 1983; Revised: May 29, 1992.
Fairchild SB 227-56-002, Issued: January 5, 1984; Revised: May 29, 
1992, and April 1, 1993.
Fairchild SB 226-56-003, Issued: September 13, 1984; Revised: November 
2, 1989.
Fairchild SB 227-56-003, Issued: September 13, 1984; Revised: November 
2, 1989.
Fairchild SB 26-56-10-038, Issued: October 8, 1984; Revised: February 
7, 1991.

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. After reviewing all the comments 
received on the NPRM, the FAA is revising the proposal to eliminate the 
proposed dual-pane cockpit side window modification, and is proposing 
repetitive single-pane cockpit side window replacements (every 5,000 
hours time-in-service). The repetitive inspections would remain as 
originally proposed. Due consideration has been given to the comments 
that follow.
    Fifteen comments were received in reference to the dual-pane 
cockpit side window modification. These comments present the view that 
the compliance times for the modification are unrealistic, that there 
is no justification for the FAA to mandate the dual-pane modification, 
and that a new improved cockpit side window defogging system should be 
developed instead of the modification. Since the FAA has revised the 
NPRM to include repetitive single-pane cockpit side window replacements 
instead of the dual-pane cockpit side window modification, these 
comments no longer apply to the rule as now proposed.
    Seven commenters state that the FAA miscalculated the economic 
impact of the AD upon the operators, specifically that the 14 hours 
proposed to accomplish the modification is closer to 50 workhours for 
each side or 100 workhours per airplane. The FAA concurs that it 
miscalculated the economic impact and agrees that the proposed 
modification would take approximately 100 workhours per airplane (50 
workhours each side). However, since the proposal is being revised to 
incorporate a life limit on the single-pane windows and since mandatory 
dual-pane modification is no longer proposed, the economic portion to 
the preamble of this proposal has been adjusted to reflect the single-
pane installation costs instead of the double pane modification costs.
    After examining the circumstances and reviewing all available 
information related to the subject described above including the 
comments received, the FAA has determined that the NPRM should be 
revised and that AD action should still be taken to prevent acrylic 
cabin or cockpit side window failures, which, if not detected and 
corrected, could result in airframe damage and decompression injuries.
    Since this revision of the NPRM to add a life limit for the single-
pane cockpit side windows proposes actions that go beyond the scope of 
what was already proposed, the FAA is reopening the comment period to 
allow the public additional time to comment on this proposed action.
    Since an unsafe condition has been identified that is likely to 
exist or develop in other Fairchild Aircraft SA26, SA226, and SA227 
series airplanes of the same type design, the proposed AD would 
supersede AD 93-19-06 with a new AD that would maintain the requirement 
of repetitively inspecting the cabin and cockpit side windows, and 
would add a life limit for the single-pane cockpit side windows. 
Accomplishment of the single-pane window installation would be in 
accordance with the applicable maintenance manual. The proposed 
inspections would continue to be accomplished in accordance with the 
service bulletins previously referenced.
    The compliance time for the proposed AD is presented in both hours 
time-in-service (TIS) and calendar time. The referenced acrylic cabin 
and cockpit side windows are affected whether the airplane is in flight 
or on the ground. In addition, the utilization rates of the affected 
airplanes vary among operators. For example, operators in unscheduled 
service utilize their airplanes an average of approximately 200 to 300 
hours TIS annually, while those in commuter service (scheduled) utilize 
their airplanes an average of approximately 2,000 hours TIS annually. 
Based on this wide utilization rate variance and the fact that these 
windows are affected when the airplane is in flight and on the ground, 
the FAA has determined that the compliance time for the proposed rule 
should be in hours TIS and calendar time.
    The FAA estimates that 633 airplanes in the U.S. registry would be 
affected by the proposed AD, that it would take approximately 28 
workhours per airplane (14 workhours per window) to accomplish the 
proposed life limit installation and that the average labor rate is 
approximately $60 an hour. Parts cost approximately $2,200 per airplane 
($1,100 per window). Based on these figures, the total cost impact of 
the proposed AD on U.S. operators is estimated to be $2,456,040. AD 93-
19-06 currently requires the same inspections as the proposed AD for 
all of the affected airplanes. Therefore, the cost impact of the 
proposed inspections (3 workhours  x  $60  x  633 airplanes = $113,940) 
for operators of all affected airplanes is the same as AD 93-19-06. The 
figure does not take into account the cost of repetitive inspections. 
The FAA has no way of determining how many repetitive inspections each 
owner/operator may incur over the life of the airplane.

[[Page 18526]]

    In addition, Fairchild Aircraft has informed the FAA that 
approximately 250 of the 633 affected airplanes are equipped with 
cockpit side windows with inner window panes, and therefore are not 
subject to the single-pane window replacements (dual-pane windows would 
still be subject to repetitive inspections). With this in mind, the 
proposed cost impact upon U.S. operators would be reduced approximately 
$970,000 from $2,456,040 to $1,486,040.
    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 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) 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 has been placed 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 removing Airworthiness Directive 
(AD) 93-19-06, Amendment 39-8705 (58 FR 51771, October 5, 1993), and by 
adding a new AD to read as follows:

Fairchild Aircraft: Docket No. 94-CE-22-AD. Supersedes AD 93-19-06, 
Amendment 39-8705.

    Applicability: Models SA26-T, SA26-AT, SA226-T, SA226-T(B), 
SA226-AT, SA226-TC, SA227-AT, SA227-AC, SA227-BC, and SA227-TT 
airplanes (all serial numbers for all models), 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.
    Note 2: The applicability of this AD takes precedence over that 
specified in the service information.

    Compliance: Required as indicated in the body of the AD, unless 
already accomplished.
    To prevent acrylic cabin or cockpit side window failures, which, 
if not detected and corrected, could result in airframe damage and 
decompression injuries, accomplish the following:

    Note 3: The paragraph structure of this AD is as follows:

Level 1: (a), (b), (c), etc.
Level 2: (1), (2), (3), etc.
Level 3: (i), (ii), (iii), etc.
Level 4: (A), (B), (C), etc.

Level 2, Level 3, and Level 4 structures are designations of the 
Level 1 paragraph they immediately follow.
    (a) Upon the accumulation of 5,000 hours time-in-service (TIS) 
or within the next 1,000 hours TIS after the effective date of this 
AD, whichever occurs later, and thereafter at intervals not to 
exceed 5,000 hours TIS, replace each single-pane cockpit side window 
with a new window of like design in accordance with the applicable 
maintenance manual.
    (1) Accomplish the inspection specified in paragraph (b) of this 
AD between 10 to 20 hours TIS after replacing each window to ensure 
that no damage has occurred after installation; and
    (2) If cracks are found, utilize the chart in paragraph (b) of 
this AD to determine the applicable action necessary.
    (b) Visually inspect all acrylic single-pane cockpit side 
windows for cracks in accordance with the service information 
presented in paragraph (d)(2) of this AD, as applicable. Accomplish 
the initial inspection, and applicable reinspection or replacement 
as specified in the following chart:

----------------------------------------------------------------------------------------------------------------
             Condition                      Initial action                       Repetitive action              
----------------------------------------------------------------------------------------------------------------
Upon the effectiveness of this AD..  Inspect at 150 hours TIS     Reinspect at intervals not to exceed 1,000    
                                      after the effective date     hours TIS or 12 calender months, whichever   
                                      of the AD.                   occurs first, provided no cracks are found.  
                                                                   Use applicable condition column entry to     
                                                                   determine compliance times if cracks are     
                                                                   found.                                       
If cracks are found where the sum    Accomplish one of the        Accomplish the corresponding repetitive       
 total of all cracks is less than     following:.                  action:                                      
 4.3 inches in combined length, but                                                                             
 where a crack meets or exceeds .30                                                                             
 inches as specified in the Crack                                                                               
 Limitations section of the service                                                                             
 information referenced in                                                                                      
 paragraph (d)(2) of this AD.                                                                                   
                                     1. Prior to further flight,  1. Reinspect initially between 10 and 20 hours
                                      replace the window with a    TIS after replacing the window to ensure that
                                      new window of like design    no damage has occurred after installation,   
                                      in accordance with the       and thereafter at intervals not to exceed    
                                      applicable maintenance       1,000 hours TIS or 12 calendar months,       
                                      manual or.                   whichever occurs first, provided no cracks   
                                                                   are found. Use applicable condition column   
                                                                   entry to determine compliance times if cracks
                                                                   are found or                                 

[[Page 18527]]

                                                                                                                
                                     2. Prior to further flight,  2. Repeat the inspection specified in         
                                      fabricate a placard with     paragraph (b) of this AD at intervals not to 
                                      the following words in       exceed 25 hours TIS or 30 calendar days, and 
                                      letters at least 0.10-inch   whichever occurs first, provided the sum     
                                      in height and install this   total of all cracks does the not exceed 4.3  
                                      placard within the pilot's   inches in combined length. Replace the window
                                      clear view close to the      and continue the actions necessary under the 
                                      pressurization controls:     ``With cracks found where the sum total of   
                                      ``AIRPLANE MUST BE           all cracks meets or exceeds 4.3 inches in    
                                      OPERATED UNPRESSURIZED'',    combined length'' condition column.          
                                      and prior to further                                                      
                                      flight, insert a copy of                                                  
                                      this AD into Limitations                                                  
                                      Section of the FAA-                                                       
                                      approved Airplane Flight                                                  
                                      Manual (AFM).                                                             
If cracks are ound where the sum     Prior to further flight,     Reinspect initially between 10 and 20 hours   
 total of all cracks meets or         replace the window with a    TIS after replacing the window to ensure that
 exceeds 4.3 inches in combined       new window of like design    no damage has occurred after installation,   
 length.                              in accordance with           and thereafter at intervals not to exceed    
                                      applicable maintenance       1,000 hours TIS or 12 calendar months,       
                                      manual.                      whichever occurs first, provided no cracks   
                                                                   are found. Use applicable condition column   
                                                                   entry to determine compliance times if cracks
                                                                   are found.                                   
With cracks found that are less      Reinspect within 25 hours    Continue this reinspection at intervals not to
 than .30 inches (as specified in     TIS or 30 calendar days,     exceed 25 hours TIS or 30 calendar days,     
 the applicable service information   whichever occurs first.      whichever occurs first, provided no crack is 
 referenced in paragraph (d)(2) of                                 found that is .30 inches or greater or the   
 this AD) provided the sum total of                                combined length of all cracks exceeds 4.3    
 all cracks does not exceed 4.3                                    inches in combined length. Use applicable    
 inches in combined length.                                        condition column entry to determine          
                                                                   compliance times if any of these crack limits
                                                                   are met.                                     
With no cracks found after one of    Reinspect within 1,000       Reinspect at intervals not to exceed 1,000    
 the inspections required by this     hours TIS and 12 calendar    hours TIS or 12 calendar months, whichever   
 AD.                                  months after the last        occurs first, provided no cracks are found.  
                                      inspection, whichever        Use applicable condition column entry to     
                                      occurs first.                determine compliance times if cracks are     
                                                                   found.                                       
----------------------------------------------------------------------------------------------------------------


    (c) Visually inspect all acrylic cabin and dual-pane cockpit 
side windows for cracks in accordance with the service information 
specified in paragraphs (d)(1) and (d)(2) of this AD. Accomplish the 
initial inspection and applicable reinspection or replacement as 
specified in the following chart:

----------------------------------------------------------------------------------------------------------------
             Condition                      Initial action                       Repetitive action              
----------------------------------------------------------------------------------------------------------------
Upon the effectiveness of this AD..  Inspect at 150 hours TIS     Reinspect at intervals not to exceed 1,000    
                                      after the effective date     hours TIS or 12 calender months, whichever   
                                      of the AD, unless already    occurs first, provided no cracks are found.  
                                      accomplished within the      Use applicable condition column entry to     
                                      last 1,000 hours TIS or 12   determine compliance times if cracks are     
                                      calendar months, which       found.                                       
                                      would put airplane in                                                     
                                      compliance with superseded                                                
                                      AD 93-19-06. Use the                                                      
                                      results of the previous                                                   
                                      inspection under AD 93-19-                                                
                                      06 to determine repetitive                                                
                                      interval.                                                                 
                                                                  For airplanes taking ``unless already         
                                                                   accomplished'' credit for the initial        
                                                                   inspection, use the results of the previous  
                                                                   inspection under AD 93-19-06 to determine the
                                                                   repetitive action.                           
If cracks are found where the sum    Accomplish one of the        Accomplish the corresponding repetitive       
 total of all cracks is less than     following:.                  action:                                      
 4.3 inches in combined length, but                                                                             
 where a crack meets or exceeds .30                                                                             
 inches as specified in the Crack                                                                               
 Limitations section of the service                                                                             
 information referenced in                                                                                      
 paragraph (d)(2) of this AD.                                                                                   
                                     1. Prior to further flight,  1. Reinspect initially between 10 and 20 hours
                                      replace the window with a    TIS after replacing the window to ensure that
                                      new window of like design    no damage has occurred after installation,   
                                      in accordance with the       and thereafter at intervals not to exceed    
                                      applicable maintenance       1,000 hours TIS or 12 calendar months,       
                                      manual or.                   whichever occurs first, provided no cracks   
                                                                   are found. Use applicable condition column   
                                                                   entry to determine compliance times if cracks
                                                                   are found or                                 

[[Page 18528]]

                                                                                                                
                                     2. Prior to further flight,  2. Repeat the inspection specified in         
                                      fabricate a placard with     paragraph (b) of this AD at intervals not to 
                                      the following words in       exceed 25 hours TIS or 30 calendar days,     
                                      letters at least 0.10-inch   whichever occurs first, provided the sum     
                                      in height and install this   total of all cracks does not exceed 4.3      
                                      placard within the pilot's   inches in combined length. Replace the window
                                      clear view close to the      and continue the actions necessary under the 
                                      pressurization controls:     ``With cracks found where the sum total of   
                                      ``AIRPLANE MUST BE           all cracks meets or exceeds 4.3 inches in    
                                      OPERATED UNPRESSURIZED'',    combined length'' condition column.          
                                      and prior to further                                                      
                                      flight, insert a copy of                                                  
                                      this AD into the                                                          
                                      Limitations Section of the                                                
                                      FAA-approved Airplane                                                     
                                      Flight Manual (AFM).                                                      
If cracks are found where the sum    Prior to further flight,     Reinspect initially between 10 and 20 hours   
 total of all cracks meets or         replace the window with a    TIS after replacing the window to ensure that
 exceeds 4.3 inches in combined       new window of like design    no damage has occurred after installation,   
 length.                              in accordance with the       and thereafter at intervals not to exceed    
                                      applicable maintenance       1,000 hours TIS or 12 calendar months,       
                                      manual.                      whichever occurs first, provided no cracks   
                                                                   are found. Use applicable condition column   
                                                                   entry to determine compliance times if cracks
                                                                   are found.                                   
With cracks found that are less      Reinspect within 25 hours    Continue this reinspection at intervals not to
 than .30 inches (as specified in     TIS or 30 calendar days,     exceed 25 hours TIS or 30 calendar days,     
 the applicable service information   whichever occurs first.      whichever occurs first, provided no crack is 
 referenced in paragraph (d)(2) of                                 found that is .30 inches or greater or the   
 this AD) provided the sum total of                                combined length of all cracks exceeds 4.3    
 all cracks does not exceed 4.3                                    inches in combined length. Use applicable    
 inches in combined length.                                        condition column entry to determine          
                                                                   compliance times if any of these crack limits
                                                                   are met.                                     
With no cracks found after one of    Reinspect within 1,000       Reinspect at intervals not to exceed 1,000    
 the inspections required by this     hours TIS and 12 calendar    hours TIS or 12 calendar months, whichever   
 AD.                                  months after the last        occurs first, provided no cracks are found.  
                                      inspection, whichever        Use applicable condition column entry to     
                                      occurs first.                determine compliance times if cracks are     
                                                                   found.                                       
----------------------------------------------------------------------------------------------------------------


    (d) The following specifies the service bulletins that contain 
the procedures to accomplish the required inspections:

--------------------------------------------------------------------------------------------------------------------------------------------------------
               Models                                                                  Service bulletins                                                
--------------------------------------------------------------------------------------------------------------------------------------------------------
(1) For acrylic cabin windows:                                                                                                                          
    SA26-T and SA26-AT..............  26-56-20-042, Issued: November 28, 1988, Revised: February 7, 1991.                                               
    SA226-T and SA226-T(B)..........  226-56-001, Issued: February 2, 1983, Revised: November 26, 1991.                                                 
    SA226-AT and SA226-TC...........  226-56-002, Issued: March 3, 1983, Revised: May 29, 1992.                                                         
    SA227-AT, SA227-AC, and SA227-BC  227-56-002, Issued: January 5, 1984, Revised: May 29, 1992, and April 1, 1993.                                    
    SA227-TT........................  227-56-001, Issued: February 2, 1983, Revised: November 26, 1991.                                                 
(2) For acrylic cockpit side                                                                                                                            
 windows:                                                                                                                                               
    SA26-T and SA26-AT..............  26-56-10-038, Issued: October 8, 1984, Revised: February 7, 1991.                                                 
    SA226-T, SA226-T(B), SA226-AT,    226-56-003, Issued: September 13, 1984, Revised: November 2, 1989.                                                
     and SA226-TC.                                                                                                                                      
    SA227-AT, SA227-AC, SA227-BC,     227-56-003, Issued: September 13, 1984, Revised: November 2, 1989.                                                
     and SA227-TT.                                                                                                                                      
--------------------------------------------------------------------------------------------------------------------------------------------------------

    Note 4: The repetitive inspections required by this AD are also 
referenced in the FAA-approved Fairchild Airframe Airworthiness 
Limitations Manual, ST-UN-M001.

    (e) 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.
    (f) An alternative method of compliance or adjustment of the 
initial or repetitive compliance times that provides an equivalent 
level of safety may be approved by the Manager, Airplane 
Certification Office (ACO), FAA, 2601 Meacham Boulevard, Fort Worth, 
Texas 76193-0150. The request shall be forwarded through an 
appropriate FAA Maintenance Inspector, who may add comments and then 
send it to the Manager, Fort Worth ACO.

    Note 5: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Fort Worth ACO.
    Note 6: Alternative methods of compliance approved in accordance 
with AD 93-19-06 (superseded by this action) are not considered 
approved as alternative methods of compliance with this AD.

    (g) All persons affected by this directive may obtain copies of 
the document referred to herein upon request to Fairchild Aircraft, 
P.O. Box 790490, San Antonio, Texas 78279-0490; or may examine this 
document at the FAA, Central Region, Office of the Assistant Chief 
Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.
    (h) This amendment supersedes AD 93-19-06, Amendment 39-8705.

    Issued in Kansas City, Missouri, on April 19, 1996.
Henry A. Armstrong,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-10308 Filed 4-25-96; 8:45 am]
BILLING CODE 4910-13-P