[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]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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airworthiness directive (AD), which would have superseded AD 93-19-06.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
