[Federal Register Volume 60, Number 34 (Tuesday, February 21, 1995)]
[Proposed Rules]
[Pages 9649-9652]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-4132]



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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 94-CE-22-AD]


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes to supersede AD 93-19-06, which 
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 proposed action would require 
modifying certain cockpit side windows, and would more fully define the 
crack limitations and establish clearer repetitive inspection intervals 
for the affected airplanes. The actions specified by the proposed AD 
are intended to prevent acrylic cockpit or cabin 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 April 28, 1995.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
[[Page 9650]] 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) 
222-5959.

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 NPRMs

    Any person may obtain a copy of this 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

    AD 93-19-06, Amendment 39-8705 (58 FR 51771, October 5, 1993), 
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.
    Since issuance of AD 93-19-06, the FAA has received several 
incident reports of cockpit side window failures on the affected 
airplanes in compliance with that AD.
    After examining the circumstances and reviewing all available 
information related to the action referenced above including the 
referenced incident reports, the FAA has determined that (1) A 
modification should be incorporated on cockpit side windows that do not 
have inner window panes; (2) the crack limitations specified in AD 93-
19-06 should coincide with the applicable service information; and (3) 
AD action should be taken to prevent acrylic cockpit or cabin side 
window failures, which, if not detected and corrected, could result in 
airframe damage and decompression injuries.
    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 repetitive 
inspection requirements of AD 93-19-06, and add the modification 
referenced above. The proposed modification would be accomplished in 
accordance with the following service bulletins (SB), as applicable:
    Fairchild SB 26-56-10-045, which incorporates the following table 
of effective pages:

------------------------------------------------------------------------
                  Page Nos.                              Date           
------------------------------------------------------------------------
3, 4, 5, and 9..............................  Revised: December 1, 1994.
1, 2, 6, 7, 8, and 10 through 14............  Issued: August 11, 1994.  
------------------------------------------------------------------------

    Fairchild SB 226-56-005, which incorporates the following table of 
effective pages:

------------------------------------------------------------------------
                  Page Nos.                              Date           
------------------------------------------------------------------------
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 table 
of effective pages:

------------------------------------------------------------------------
                  Page Nos.                              Date           
------------------------------------------------------------------------
3 through 7, and 9..........................  Revised: December 1, 1994.
1, 2, and 8.................................  Revised: August 11, 1994. 
10 through 16...............................  Issued: July 31, 1991.    
------------------------------------------------------------------------

    The proposed repetitive inspections would be accomplished in 
accordance with the following SB's, as applicable:

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.
Fairchild SB 26-56-20-042, Issued: November 28, 1988; Revised: 
February 7, 1991.

    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 by those conditions present while 
the airplane is in flight and while the airplane is 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 14 
workhours per airplane to accomplish the proposed modification, and 
that the average labor rate is approximately $60 an hour. Parts cost 
approximately $5,000 per airplane. Based on these figures, the total 
cost impact of the proposed AD on U.S. operators is estimated to be 
$3,696,720. 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 [[Page 9651]] 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, and is based on the 
assumption that no owner/operator has incorporated the proposed 
modification. The FAA has no way of determining how many repetitive 
inspections each owner/operator may incur.
    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 do not need 
the proposed modification. With this in mind, the proposed cost impact 
upon U.S. operators would be reduced about 40-percent from $3,696,720 
to $2,218,032.
    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. 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 AD 93-19- 06, Amendment 39-
8705 (58 FR 51771, October 5, 1993), and by adding a new airworthiness 
directive 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: 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 cockpit or cabin side window failures, which, 
if not detected and corrected, could result in airframe damage and 
decompression injuries, accomplish the following:

    Note 2: 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 2 and Level 3 structures are designations of the Level 1 
paragraph they immediately follow.
    (a) Within the next 200 hours time-in-service (TIS) after the 
effective date of this AD or six calendar months after the effective 
date of this AD, whichever occurs first, modify all single pane 
cockpit side windows to dual panes (two acrylic cockpit side 
windows) in accordance with the ACCOMPLISHMENT INSTRUCTIONS section 
of the following service bulletins (SB), as applicable:
    Fairchild SB 26-56-10-045, which incorporates the following 
table of effective pages:

------------------------------------------------------------------------
                  Page Nos.                              Date           
------------------------------------------------------------------------
3, 4, 5, and 9..............................  Revised: December 1, 1994.
1, 2, 6, 7, 8, and 10 through 14............  Issued: August 11, 1994.  
------------------------------------------------------------------------

Fairchild SB 226-56-005, which incorporates the following table of 
effective pages:

------------------------------------------------------------------------
                  Page Nos.                              Date           
------------------------------------------------------------------------
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 table 
of effective pages:

------------------------------------------------------------------------
                  Page Nos.                              Date           
------------------------------------------------------------------------
3 through 7, and 9..........................  Revised: December 1, 1994.
1, 2, and 8.................................  Revised: August 11, 1994. 
10 through 16...............................  Issued: July 31, 1991.    
------------------------------------------------------------------------

    Note 3: The above modification only applies to airplanes without 
existing inner window panes. The installation requires replacing the 
existing left and right hand outer window panes, except those panes 
with part number 26-21383-009/-010 that are installed and are in 
serviceable condition.
    (b) Within the next 50 hours time-in-service (TIS) after the 
effective date of this AD, unless already accomplished within the 
last 1,000 hours TIS or 12 calendar months (compliance with AD 89-
06-02 or AD 93-19-06), visually inspect all acrylic cabin and 
cockpit side windows for cracks in accordance with the following 
SB's, as applicable:
    (1) For acrylic cabin side windows:

------------------------------------------------------------------------
        Model                          Service bulletin                 
------------------------------------------------------------------------
SA26-T..............  26-56-20-042, Issued: November 28, 1988, Revised: 
                       February 7, 1991.                                
SA26-AT.............  26-56-20-042, Issued: November 28, 1988, Revised: 
                       February 7, 1991.                                
SA226-T.............  226-56-001, Issued: February 2, 1983, Revised:    
                       November 26, 1991.                               
SA226-T(B)..........  226-56-001, Issued: February 2, 1983, Revised:    
                       November 26, 1991.                               
SA226-AT............  226-56-002, Issued: March 3, 1983, Revised: May   
                       29, 1992.                                        
SA226-TC............  226-56-002, Issued: March 3, 1983, Revised: May   
                       29, 1992.                                        
SA227-AT............  227-56-002, Issued: January 5, 1984, Revised: May 
                       29, 1992, and April 1, 1993.                     
SA227-AC............  227-56-002, Issued January 5, 1984, Revised: May  
                       29, 1992, and April 1, 1993.                     
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:

------------------------------------------------------------------------
        Model                          Service bulletin                 
------------------------------------------------------------------------
SA26-T..............  26-56-10-038, Issued: October 8, 1984, Revised:   
                       February 7, 1991.                                
SA26-AT.............  26-56-10-038, Issued: October 8, 1984, Revised:   
                       February 7, 1991.                                
SA226-T.............  226-56-003, Issued: September 13, 1984, Revised:  
                       November 2, 1989.                                
[[Page 9652]]
                                                                        
SA226-T(B)..........  226-56-003, Issued: September 13, 1984, Revised:  
                       November 2, 1989.                                
SA226-AT............  226-56-003, Issued: September 13, 1984, Revised:  
                       November 2, 1989.                                
SA226-TC............  226-56-003, Issued: September 13, 1984, Revised:  
                       November 2, 1989.                                
SA227-AT............  227-56-003, Issued: September 13, 1984, Revised:  
                       November 2, 1989.                                
SA227-AC............  227-56-003, Issued: September 13, 1984, Revised:  
                       November 2, 1989.                                
SA227-BC............  227-56-003, Issued: September 13, 1984, Revised:  
                       November 2, 1989.                                
SA227-TT............  227-56-003, Issued: September 13, 1984, Revised   
                       November 2, 1989.                                
------------------------------------------------------------------------

  (c) If cracks are found that meet or exceed 4.3 inches in 
combined length, prior to further flight, replace the window with a 
new or serviceable window, and reinspect thereafter at intervals not 
to exceed 1,000 hours TIS or 12 calendar months, whichever occurs 
first.
    (d) If cracks are found that are less than 4.3 inches in 
combined length but that meet or exceed .30 inches as specified in 
the Crack Limitations section of the service information referenced 
in paragraphs (b)(1) and (b)(2) of this AD, prior to further flight, 
accomplish one of the following:
    (1) Replace the window with a new or serviceable window and 
reinspect thereafter at intervals not to exceed 1,000 hours TIS or 
12 calendar months, whichever occurs first; or
    (2) Fabricate a placard with the following words in letters at 
least 0.10-inch in height and install this placard within the 
pilot's clear view close to the pressurization controls: ``AIRPLANE 
MUST BE OPERATED UNPRESSURIZED'', and accomplish both of the 
following:
    (i) Insert a copy of this AD into the Limitations Section of the 
FAA-approved Airplane Flight Manual (AFM); and
    (ii) Within the next 25 hours TIS or 30 calendar days, whichever 
occurs first, reinspect the cracked window for crack progression in 
accordance with the inspections specified in paragraphs (b)(1) and 
(b)(2) of this AD, as applicable, and accomplish either paragraph 
(c), (d) or (e) of this AD, as applicable.
    (e) If cracks are found that are less than .30 inches as 
specified in the Crack Limitations section of the applicable service 
information referenced in paragraphs (b)(1) and (b)(2) of this AD, 
within the next 25 hours TIS or 30 calendar days, whichever occurs 
first, reinspect the cracked window for crack progression in 
accordance with the applicable service information specified in 
paragraphs (b)(1) and (b)(2) of this AD, and accomplish either 
paragraph (c), (d), or (e) of this AD, as applicable.

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

    (f) 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.
    (g) 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.

    (h) 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.
    (i) This amendment supersedes AD 93-19-06, Amendment 39-8705.

    Issued in Kansas City, Missouri, on February 14, 1995.
Barry D. Clements,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 95-4132 Filed 2-17-95; 8:45 am]
BILLING CODE 4910-13-U