[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
