[Federal Register Volume 61, Number 190 (Monday, September 30, 1996)]
[Rules and Regulations]
[Pages 50999-51003]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-24886]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-CE-22-AD; Amendment 39-9774; AD 96-20-08]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes AD 93-19-06, which currrently 
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. This action maintains the requirement of 
repetitively inspecting the cabin and cockpit side windows, and adds a 
life limit for the single-pane cockpit side windows. Acrylic window 
failures on the affected airplanes prompted this action. The actions 
specified by this AD are intended to prevent acrylic cabin or cockpit 
side window failures, which could result in airframe damage and 
decompression injuries.

DATES: Effective November 14, 1996.
    The incorporation by reference of certain publications listed in 
the regulations was previously approved by the Director of the Federal 
Register as of November 19, 1993 (58 FR 51771, October 5, 1993).

ADDRESSES: Service information that applies to this AD may be obtained 
from Fairchild Aircraft, P.O. Box 790490, San Antonio, Texas 78279-
0490; telephone (210) 824-9421. This information may also be examined 
at the Federal Aviation Administration (FAA), Central Region, Office of 
the Assistant Chief Counsel, Attention: Rules Docket 94-CE-22-AD, Room 
1558, 601 E. 12th Street, Kansas City, Missouri 64106; or at the Office 
of the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

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:

Events Leading to This Action

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to include an AD that would apply to Fairchild Aircraft 
SA26, SA226, and SA227 series airplanes was published in the Federal 
Register on April 26, 1996 (61 FR 18524). The action proposed to 
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 as specified in 
the supplemental notice of proposed rulemaking (NPRM) would be in 
accordance with the applicable maintenance manual. The proposed 
inspections as specified in the supplemental NPRM would be accomplished 
in accordance with the following service bulletins (SB), 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. Due consideration has been given to 
the comment received.

Disposition of the Comment

    The commenter supports the proposal as written, and would like the 
FAA to treat this as interim action until a new improved cockpit side 
window defogging system is developed. The FAA basically concurs. A new 
window design is now going through analysis and testing. Based on the 
results of this analysis and testing, the FAA will determine if 
additional improvements are needed to assure that an acceptable level 
of safety (to the actions specified in this AD) can be maintained. The 
FAA then may initiate additional rulemaking activity to require 
installation of the new design window. In the meantime, the FAA has 
determined that the actions required by this AD will maintain the 
required level of safety (as it relates to cabin and cockpit side 
windows) until the improved design windows are approved and available. 
No changes have been made to the AD as a result of this comment.
    No comments were received regarding the FAA's determination of the 
cost impact on the public.

The FAA's Determination

    After careful review of all available information related to the 
subject presented above, including the referenced service information, 
the FAA has determined that air safety and the public interest require 
the adoption of the rule as proposed except for minor editorial 
corrections. The FAA has determined that these minor corrections will 
not change the meaning of the AD and will not add any additional burden 
upon the public than was already proposed.

Compliance Time Criteria

    The compliance time for this 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

[[Page 51000]]

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 this rule should be in hours 
TIS and calendar time.

Cost Impact

    The FAA estimates that 633 airplanes in the U.S. registry will be 
affected by this AD, that it will take approximately 28 workhours per 
airplane (14 workhours per window) to accomplish the 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 this AD on U.S. 
operators is estimated to be $2,456,040. AD 93-19-06 currently requires 
the same inspections as this AD for all of the affected airplanes. 
Therefore, the cost impact of the required 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.
    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 will 
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.

Regulatory Impact

    The regulations adopted herein will not have substantial direct 
effects on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government. Therefore, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a 
significant economic impact, positive or negative, on a substantial 
number of small entities under the criteria of the Regulatory 
Flexibility Act. A copy of the final 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by 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:

96-20-08  Fairchild Aircraft: Amendment 39-9774; 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 
could result in airframe damage and decompression injuries, accomplish 
the following:

    (a) Upon accumulating 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     Inspect at 150 hours  Reinspect at        
 this Ad.                      TIS after the         intervals not to   
                               effective date of     exceed 1,000 hours 
                               this AD.              TIS or 12 calendar 
                                                     months, whichever  
                                                     occurs first,      
                                                     provided no cracks 
                                                     are found. Use     
                                                     applicable         
                                                     condition column   
                                                     entry to determine 
                                                     compliance times if
                                                     cracks are found.  

[[Page 51001]]

                                                                        
If cracks are found where     Accomplish one of     Accomplish the      
 the sum total of all cracks   the following:        corresponding      
 is less than 4.3 inches in   1. Prior to further    repetitive action: 
 combined length, but where    flight, replace the  1. Reinspect        
 a crack meets or exceeds      window with a new     initially between  
 .30 inches as specified in    window of like        10 and 20 hours TIS
 the Crack Limitations         design in             after replacing the
 section of the service        accordance with the   window to ensure   
 information referenced in     applicable            that no damage has 
 paragraph (d)(2) of this AD.  maintenance manual.   occurred after     
                                                     installation, and  
                                                     thereafter at      
                                                     intervals not to   
                                                     exceed 1,000 hours 
                                                     TIS or 12 calendar 
                                                     months, whichever  
                                                     occurs first,      
                                                     provided no cracks 
                                                     are found. Use     
                                                     applicable         
                                                     condition column   
                                                     entry to determine 
                                                     compliance times if
                                                     cracks are found.  
                                       or                    or         
                              2. Prior to further   2. Repeat the       
                               flight, fabricate a   inspection         
                               placard with the      specified in       
                               following words in    paragraph (b) of   
                               letters at least      this AD at         
                               0.10-inch in height   intervals not to   
                               and install this      exceed 25 hours TIS
                               placard within the    or 30 calendar     
                               pilot's clear view    days, whichever    
                               close to the          occurs first,      
                               pressurization        provided the sum   
                               controls:             total of all cracks
                               ``AIRPLANE MUST BE    does not exceed 4.3
                               OPERATED              inches in combined 
                               UNPRESSURIZED'',      length. Use the    
                               and prior to          ``If cracks are    
                               further flight,       found where the sum
                               insert a copy of      total of all cracks
                               this AD into the      meets or exceeds   
                               Limitations Section   4.3 inches in      
                               of the FAA-approved   combined length''  
                               Airplane Flight       condition column   
                               Manual (AFM).         for replacement and
                                                     inspection times if
                                                     the cracks found   
                                                     are at that level. 
If cracks are found where     Prior to further      Reinspect initially 
 the sum total of all cracks   flight, replace the   between 10 and 20  
 meets or exceeds 4.3 inches   window with a new     hours TIS after    
 in combined length.           window of like        replacing the      
                               design in             window to ensure   
                               accordance with the   that no damage has 
                               applicable            occurred after     
                               maintenance manual.   installation, and  
                                                     thereafter at      
                                                     intervals not to   
                                                     exceed 1,000 hours 
                                                     TIS or 12 calendar 
                                                     months, 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    Reinspect within 25   Continue this       
 less than .30 inches (as      hours TIS or 30       reinspection at    
 specified in the applicable   calendar days,        intervals not to   
 service information           whichever occurs      exceed 25 hours TIS
 referenced in paragraph       first.                or 30 calendar     
 (d)(2) of the AD) provided                          days, whichever    
 the sum total of all cracks                         occurs first,      
 does not exceed 4.3 inches                          provided no crack  
 in combined length.                                 is found that is   
                                                     .30 inches or      
                                                     greater or the     
                                                     combined length of 
                                                     all cracks exceeds 
                                                     4.3 inches in      
                                                     combined length.   
                                                     Use applicable     
                                                     condition column   
                                                     entry to determine 
                                                     compliance times if
                                                     any of these crack 
                                                     limits are met.    
With no cracks found after    Reinspect within      Reinspect at        
 one of the inspections        1,000 hours TIS and   intervals not to   
 required by this AD.          12 calendar months    exceed 1,000 hours 
                               after the last        TIS or 12 calendar 
                               inspection,           months, whichever  
                               whichever occurs      occurs first,      
                               first.                provided no cracks 
                                                     are found. Use     
                                                     applicable         
                                                     condition column   
                                                     entry to 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     Inspect at 150 hours  Reinspect at        
 this AD                       TIS after the         intervals not to   
                               effective date of     exceed 1,000 hours 
                               this AD, unless       TIS or 12 calendar 
                               already               months, whichever  
                               accomplished within   occurs first,      
                               the last 1,000        provided no cracks 
                               hours TIS or 12       are found. Use     
                               calendar months,      applicable         
                               which would put       condition column   
                               airplane in           entry to determine 
                               compliance with       compliance times if
                               superseded AD 93-19-  cracks are found.  
                               06. Use the results  For airplane owners/
                               of the previous       operators taking   
                               inspection under AD   ``unless already   
                               93-19-06 to           accomplished''     
                               determine             credit for the     
                               repetitive action     initial inspection,
                                                     use the results of 
                                                     the previous       
                                                     inspection under AD
                                                     93-19-06 to        
                                                     determine the      
                                                     repetitive action. 

[[Page 51002]]

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

    (d) The following specifies the service bulletins that contain 
the procedures to accomplish the required inspections:
    (1) For acrylic cabin windows:

------------------------------------------------------------------------
            Models                         Service bulletins            
------------------------------------------------------------------------
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- 227-56-002, Issued: January 5, 1984,     
 BC.                            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:

------------------------------------------------------------------------
            Models                          Service bulletin            
------------------------------------------------------------------------
SA26-T and SA26-AT...........  26-56-10-038, Issued: October 8, 1984,   
                                Revised: February 7, 1991.              
SA226-T, SA226-T(B)..........                                           
SA226-AT, and SA226-TC.......  226-56-003, Issued: September 13, 1984,  
                                Revised: November 2, 1989.              
SA227-AT, SA227-AC, SA227-BC,  227-56-003, Issued: September 13, 1984,  
 and SA227-TT.                  Revised: November 2, 1989.              
------------------------------------------------------------------------

    Note 3: 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

[[Page 51003]]

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. 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.

    Note 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Fort Worth ACO.

    (g) The inspections required by this AD shall be done in 
accordance with Fairchild Service Bulletin 26-56-20-042, Issued: 
November 28, 1988; Revised: February 7, 1991, Fairchild Service 
Bulletin 226-56-001, Issued: February 2, 1983; Revised: November 26, 
1991, Fairchild Service Bulletin 227-56-001, Issued: February 2, 
1983; Revised: November 26, 1991, Fairchild Service Bulletin 226-56-
002, Issued: March 3, 1983; Revised: May 29, 1992, Fairchild Service 
Bulletin 227-56-002, Issued: January 5, 1984; Revised: May 29, 1992, 
and April 1, 1993, Fairchild Service Bulletin 226-56-003, Issued: 
September 13, 1984; Revised: November 2, 1989, Fairchild Service 
Bulletin 227-56-003, Issued: September 13, 1984; Revised: November 
2, 1989, and Fairchild Service Bulletin 26-56-10-038, Issued: 
October 8, 1984; Revised: February 7, 1991, as applicable. This 
incorporation by reference was previously approved by the Director 
of the Federal Register in accordance with 5 U.S.C. 552 (a) and 1 
CFR part 51. Copies may be obtained from Fairchild Aircraft, P.O. 
Box 790490, San Antonio, Texas 78279-0490. Copies may be inspected 
at the FAA, Central Region, Office of the Assistant Chief Counsel, 
Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the 
Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.
    (h) This amendment (39-9774) supersedes AD 93-19-06, Amendment 
39-8705.
    (i) This amendment (39-9774) becomes effective on November 14, 
1996.

    Issued in Kansas City, Missouri, on September 19, 1996.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 96-24886 Filed 9-27-96; 8:45 am]
BILLING CODE 4910-13-U