Airworthiness Directives; Fairchild Aircraft, Inc. SA226 and SA227 Series Airplanes, 13359-13362 [05-5383]
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Federal Register / Vol. 70, No. 53 / Monday, March 21, 2005 / Rules and Regulations
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99–CE–12–AD; Amendment 39–
14023; AD 2005–06–13]
RIN 2120–AA64
Airworthiness Directives; Fairchild
Aircraft, Inc. SA226 and SA227 Series
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
Airworthiness Directive (AD) to
supersede AD 99–06–02, which
currently applies to certain Fairchild
Aircraft (Fairchild) SA226 and SA227
series airplanes. AD 99–06–02 requires
you to repetitively inspect the wing spar
center web cutout on both wings for
cracks between Wing Station (WS) 8 and
WS 17.5. That AD also requires you to
repair any area found cracked before
further flight. The repair will eliminate
the need for the repetitive inspections
on that particular wing spar. Since that
AD became effective, we have
determined that we inadvertently
omitted certain Model SA227–CC/DC
airplane serial numbers from the
applicability. This AD retains the
actions of AD 99–06–02 and adds
additional Model SA227–CC/DC
airplanes to the Applicability section.
The actions specified in this AD are
intended to detect and correct fatigue
cracking of the wing spar center web
cutout area, which could result in
structural failure of the wing spar. This
could lead to loss of control of the
airplane.
This AD becomes effective on
May 2, 2005.
On April 16, 1999 (64 FR 11761,
March 10, 1999), the Director of the
Federal Register approved the
incorporation by reference of Fairchild
Airframe Airworthiness Limitations
Manual ST–UN–M001, Rev. No. C–6,
dated April 7, 1998; Fairchild Airframe
Inspection Manual ST–UN–M002, Rev.
No. A–6, dated December 8, 1997;
Fairchild Airframe Airworthiness
Limitations Manual ST–UN–M003, Rev.
No. 5, dated April 7, 1998; Fairchild
SA226/227 Series Structural Repair
Manual, part number (P/N) 27–10054–
079, pages 57 through 90; Initial Issue:
March 1, 1983; Revision 28, dated June
24, 1998; and Fairchild SA227 Series
Structural Repair Manual, P/N 27–
10054–127, pages 47 through 60; Initial
DATES:
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Issue: December 1, 1991; Revision 7,
dated June 24, 1998.
As of May 2, 2005, the Director of the
Federal Register approved the
incorporation by reference of Fairchild
Airframe Airworthiness Limitations
Manual ST–UN–M001, SA227 Series,
Reissue C, dated January 18, 1991;
Fairchild Airframe Inspection Manual
ST–UN–M002, SA226 Series, Reissue A,
dated December 9, 1986; and Fairchild
Airframe Airworthiness Limitations
Manual ST–UN–M003, SA227
Commuter Category, Initial issue dated
December 6, 1991.
ADDRESSES: You may get the service
information identified in this AD from
Field Support Engineering, Fairchild
Aircraft, Inc., P.O. Box 790490, San
Antonio, Texas 78279–0490; telephone:
(210) 824–9421; facsimile: (210) 820–
8609.
You may view the AD docket at FAA,
Central Region, Office of the Regional
Counsel, Attention: Rules Docket No.
99–CE–12–AD, 901 Locust, Room 506,
Kansas City, Missouri 64106. Office
hours are 8 a.m. to 4 p.m., Monday
through Friday, except Federal holidays.
FOR FURTHER INFORMATION CONTACT: Mr.
Hung Viet Nguyen, FAA, Forth Worth
Airplane Certification Office (ACO),
2601 Meacham Boulevard, Fort Worth,
Texas 76193–0150; telephone: (817)
222–5155; facsimile: (817) 222–5960.
SUPPLEMENTARY INFORMATION:
Discussion
What events have caused this AD? AD
99–06–02, Amendment 39–11066 (64
FR 11761, March 10, 1999), currently
requires you to do the following on
certain Fairchild SA226 and SA227
series airplanes:
—Repetitively inspecting the wing spar
center web cutout on both wings for
cracks between Wing Station (WS) 8
and WS 17.5; and
—Immediately repairing any area found
cracked. This repair will eliminate the
need for the repetitive inspections on
that particular wing spar.
Doing the actions as specified in AD
99–06–02 is required per the following
documents:
—Fairchild Airframe Airworthiness
Limitations Manual ST–UN–M001,
Rev. No. C–6, dated April 7, 1998;
—Fairchild Airframe Inspection Manual
ST–UN–M002, Rev. No. A–6, dated
December 8, 1997;
—Fairchild Airframe Airworthiness
Limitations Manual ST–UN–M003,
Rev. No. 5, dated April 7, 1998;
—Fairchild SA226/227 Series Structural
Repair Manual, part number (P/N) 27–
10054–079, pages 57 through 90;
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13359
Initial Issue: March 1, 1983; Revision
28, dated June 24, 1998; and
—Fairchild SA227 Series Structural
Repair Manual, P/N 27–10054–127,
pages 47 through 60; Initial Issue:
December 1, 1991; Revision 7, dated
June 24, 1998.
AD 99–06–02 was the result of reports
of cracks in the wing spar center web
cutout caused by fatigue due to airplane
maneuvering and wind gusts.
What has happened since AD 99–06–
02 to initiate this action? The FAA
inadvertently omitted certain Fairchild
Model SA227–CC/DC airplane serial
numbers from the applicability of AD
99–06–02. In particular, we restricted
the applicability of these airplanes to
serial numbers CC/DC784 and CC/
DC790 through CC/DC878. Any
Fairchild Model SA227–CC/DC airplane
incorporating a serial number from CC/
DC879 through CC/DC896 should also
be affected by the actions of AD 99–06–
02.
What is the potential impact if FAA
took no action? If not detected and
corrected, fatigue cracking of the wing
spar center web cutout area could result
in structural failure of the wing spar to
the point of failure with consequent loss
of control of the airplane.
Has FAA taken any action to this
point? We issued 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 SA226 and SA227 series
airplanes. This proposal was published
in the Federal Register as a notice of
proposed rulemaking (NPRM) on April
23, 1999 (64 FR 19934). The NPRM
proposed to retain the actions of AD 99–
06–02 and add additional Model
SA227–CC/DC airplanes to the
applicability section.
Was the public invited to comment?
We provided the public the opportunity
to participate in developing this AD.
The following presents the comment
received on the proposal and FAA’s
response to the comment:
Comment Issue: Incorporate Revised
Service Information
What is the commenter’s concern?
The manufacturer has revised the
applicable service information to
incorporate minor changes.
These revisions do not change the
procedures contained in the service
information referenced in AD 99–06–02;
however, the manufacturer suggests
incorporating the revised service
information into the final rule AD
action.
What is FAA’s response to the
concern? We concur with the
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commenter and will make this change
in the final rule AD action.
Conclusion
What is FAA’s final determination on
this issue? We have carefully reviewed
the available data and determined that
air safety and the public interest require
adopting the AD as proposed except for
the changes discussed above and minor
editorial corrections. We have
determined that these changes and
minor corrections:
—Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
—Do not add any additional burden
upon the public than was already
proposed in the NPRM.
flight permits, and alternative methods
of compliance. This material previously
was included in each individual AD.
Since this material is included in 14
CFR part 39, we will not include it in
future AD actions.
Changes to 14 CFR Part 39—Effect on
the AD
How does the revision to 14 CFR part
39 affect this AD? On July 10, 2002, the
FAA published a new version of 14 CFR
part 39 (67 FR 47997, July 22, 2002),
which governs the FAA’s AD system.
This regulation now includes material
that relates to altered products, special
Costs of Compliance
How many airplanes does this AD
impact? We estimate that this AD affects
508 airplanes in the U.S. registry.
What is the cost impact of this AD on
owners/operators of the affected
airplanes? We estimate the following
costs to do the inspection:
Labor cost
Parts cost
Total cost per
airplane
5 work hours × $65 = $325 ...............................................
Not Applicable ....................................
$325
These figures only take into account
the costs of the initial inspection and do
not take into account the costs of
repetitive inspections and the costs
associated with any repair that would be
necessary if cracks are found. We have
no way of determining the number of
repetitive inspections an owner/
operator will incur over the life of the
airplane, or the number of airplanes that
will need repairs.
Total cost on
U.S. operators
$325 × 508 = $165,100
We estimate the following costs to do
any necessary repairs in both wing spar
center webs that will be required based
on the results of the inspection. We
have no way of determining the number
of airplanes that may need this repair:
Labor cost to repair cracked wing spar center webs on both sides of the airplane
Parts cost
Total cost per airplane
to repair cracked wing
spar center webs on both
sides of the airplane
400 work hours × $65 = $26,000 .......................................................................................................
$400
$26,000 + $400 = $26,400
What is the difference between the
cost impact of this AD and the cost
impact of AD 99–06–02? The only
difference between AD 99–06–02 and
this AD is the addition of 18 Fairchild
Model SA227–CC/DC airplanes that we
inadvertently omitted from the
Applicability section of AD 99–06–02.
Therefore, the only impact this AD has
over that already required by AD 99–06–
02 is the cost of the actions on the 18
additional airplanes.
Regulatory Findings
Will this AD impact various entities?
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect 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.
Will this AD involve a significant rule
or regulatory action? For the reasons
discussed above, I certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
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2. Is not a ‘‘significant rule’’ under the
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.
We prepared a summary of the costs
to comply with this AD and placed it in
the AD Docket. You may get a copy of
this summary by sending a request to us
at the address listed under ADDRESSES.
Include ‘‘AD Docket No. 99–CE–12–AD’’
in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under 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:
I
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PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. FAA amends § 39.13 by removing
Airworthiness Directive (AD) 99–06–02,
Amendment 39–11066 (64 FR 11761,
March 10, 1999), and by adding a new
AD to read as follows:
I
2005–06–13 Fairchild Aircraft, Inc.:
Amendment 39–14023; Docket No. 99–
CE–12–AD; Supersedes AD 99–06–02,
Amendment 39–11066.
When Does This AD Become Effective?
(a) This AD becomes effective on May 2,
2005.
What Other ADs Are Affected by This
Action?
(b) This AD supersedes AD 99–06–02,
Amendment 39–11066.
What Airplanes Are Affected by This AD?
(c) This AD affects the following airplane
models and serial numbers that are
certificated in any category:
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Model
(1)
(2)
(3)
(4)
(5)
(6)
13361
Serial Nos.
SA226–AT ...........................................................................................
SA226–TC ...........................................................................................
SA226–T .............................................................................................
SA226–T(B) ........................................................................................
SA227–TT ...........................................................................................
SA227–TT(300) ...................................................................................
(7) SA227–AC ..........................................................................................
(8) SA227–AT ...........................................................................................
(9) SA227–BC ..........................................................................................
(10) SA227–CC/DC ..................................................................................
What Is the Unsafe Condition Presented in
This AD?
(d) This AD is the result of reports of
cracks in the wing spar center web cutout
caused by fatigue due to airplane
AT001 through AT074.
TC201 through TC419.
T201 through T291.
T(B)276 and T(B)292 through T(B)417.
TT421 through TT541.
TT(300)447, TT(300)465, TT(300)471, TT(300)483, TT(300)512,
TT(300)518, TT(300)521, TT(300)527, TT(300)529, and TT(300)536.
AC406, AC415, AC416, and AC420 through AC785.
AT423 through AT631 and AT695.
BC762, BC764, BC766, and BC770 through BC789.
CC/DC784, and CC/DC790 through CC/DC896.
maneuvering and wind gusts. The actions
specified in this AD are intended to detect
and correct fatigue cracking of the wing spar
center web cutout area, which could result in
structural failure of the wing spar. This could
lead to loss of control of the airplane.
What Must I Do To Address This Problem?
(e) To address this problem, you must do
the following:
Actions
Compliance
Procedures
(1) Inspect each wing spar center web cutout
for cracks between Wing Station (WS) 8 and
WS 17.5.
Initially inspect upon accumulating 6,500
hours time-in-service (TIS) on each wing
spar; within the next 2,000 hours TIS after
the last inspection done following the applicable Airworthiness Limitations Manual (the
last inspection done following AD 99–06–
02); or within the next 500 hours TIS after
May 2, 2005 the effective date of this AD,
whichever occurs later. Repetitively inspect
thereafter at intervals not to exceed 2,000
hours TIS.
(2) If any crack(s) is/are found during any inspection required by paragraph (e)(1) of this
AD, repair the crack(s). This repair eliminates
the repetitive inspections required in paragraph (e)(1) of this AD for that particular
wing spar.
Before further flight ..........................................
For Models SA227–TT, SA227–AT, SAA227–
AC, and SA227–BC airplanes: Follow Fairchild Airframe Airworthiness Limitations
Manual ST–UN–M001, Rev. No. C–6, dated
April 7, 1998; or Fairchild Airframe Airworthiness Limitations Manual ST–UN–
M001, SA227 Series, Reissue C dated January 18, 1991, at the revision levels stated
on page iii and page iv (page iii dated August 16, 1995, and page iv dated March 8,
2004); For Models SA226–T, SA226–T(B),
SA226–AT, and SA226–TC airplanes; Follow Fairchild Airframe Inspection Manual
ST–UN–M002, Rev. No. A–6, dated December 8, 1997; or Fairchild Airframe Inspection Manual ST–Un–M002, Reissue A,
SA226 Series, dated December 9, 1986, at
the revision levels stated on page iii and
page iv (page iii dated April 7, 1998 and
page iv dated March 8, 2004); and For
Models SA227–CC and SA227–DC airplanes: Follow Fairchild Airframe Airworthiness Limitations Manual ST–UN–M003,
Rev. No. 5, dated April 7, 1998; or Fairchild
Airframe Airworthiness Limitations Manual
ST–UN–M003, SA227 Commuter Category,
Initial issue dated December 6, 1991, at the
revision levels stated on page iii and page
iv (page iii dated July 29, 2003, and page iv
dated March 8, 2004).
For Models SA226–T, SA226–T(B), SA226–
AT, SA226–TC, SA227–TT, SA227–AT,
SA227–AC, and SA227–BC airplanes: Follow Fairchild SA226/227 Series Structural
Repair Manual, part number (P/N) 27–
10054–079, pages 57 through 90; Initial
Issue: March 1, 1983; Revision 28, dated
June 24, 1998; and For Models SA227–CC
and SA227–DC airplanes: Follow Fairchild
SA227 Series Structural Repair Manual, P/
N 27–10054–127, pages 47 through 60; Initial Issue: December 1, 1991; Revision 7,
dated June 24, 1998.
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Actions
Compliance
(3) The repetitive inspections required in paragraph (e)(1) of this AD may be terminated if
the wing spar center web repair specified in
paragraph (e)(2) of this AD has been done
on both the left and right wing spar. If one
wing spar center web has been repaired,
then repetitive inspections are still required
on the other one until the repair is done.
Not applicable ..................................................
Not applicable.
May I Request an Alternative Method of
Compliance?
(f) You may request a different method of
compliance or a different compliance time
for this AD by following the procedures in 14
CFR 39.19:
(1) Unless FAA authorizes otherwise, send
your request to your principal inspector. The
principal inspector may add comments and
will send your request to the Manager, Fort
Worth Aircraft Certification Office (ACO),
FAA. For information on any already
approved alternative methods of compliance,
contact Mr. Hung Viet Nguyen, Forth Worth
ACO, FAA, 2601 Meacham Boulevard, Fort
Worth, Texas 76193–0150; telephone: (817)
222–5155; facsimile: (817) 222–5960.
(2) Alternative methods of compliance
approved for AD 99–06–02 are considered
approved as alternative methods of
compliance for this AD.
Series Structural Repair Manual, part number
(P/N) 27–10054–079, pages 57 through 90;
Initial Issue: March 1, 1983; Revision 28,
dated June 24, 1998; and Fairchild SA227
Series Structural Repair Manual, P/N 27–
10054–127, pages 47 through 60; Initial Issue:
December 1, 1991; Revision 7, dated June 24,
1998.
(2) As of May 2, 2005, and in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51, the
Director of the Federal Register approved the
incorporation by reference of Fairchild
Airframe Airworthiness Limitations Manual
ST–UN–M001, SA227 Series, Reissue C
dated January 18, 1991, at the revision levels
stated on page iii and page iv (page iii dated
August 16, 1995, and page iv dated March 8,
2004); Fairchild Airframe Inspection Manual
ST–UN–M002, Reissue A, SA226 Series,
dated December 9, 1986, at the revision
levels stated on page iii and page iv (page iii
dated April 7, 1998, and page iv dated March
8, 2004); and Fairchild Airframe
Airworthiness Limitations Manual ST–UN–
M003, SA227 Commuter Category, Initial
issue dated December 6, 1991, at the revision
levels stated on page iii and page iv (page iii
dated July 29, 2003, and page iv dated March
8, 2004).
(3) You may get a copy from Field Support
Engineering, Fairchild Aircraft, Inc., P.O. Box
790490, San Antonio, Texas 78279–0490.
You may review copies at FAA, Central
Region, Office of the Regional Counsel, 901
Locust, Room 506, Kansas City, Missouri
64106; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call (202) 741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
DEPARTMENT OF TRANSPORTATION
Does This AD Incorporate Any Material by
Reference?
(g) You must do the inspections required
by this AD following the instructions in
Fairchild Airframe Airworthiness Limitations
Manual ST–UN–M001, Rev. No. C–6, dated
April 7, 1998; Fairchild Airframe
Airworthiness Limitations Manual ST–UN–
M001, Rev. No. C–8, dated March 8, 2004;
Fairchild Airframe Inspection Manual ST–
UN–M002, Rev. No. A–6, dated December 8,
1997; Fairchild Airframe Inspection Manual
ST–UN–M002, Rev. No. A–9, dated March 8,
2004; Fairchild Airframe Airworthiness
Limitations Manual ST–UN–M003, Rev. No.
5, dated April 7, 1998; or Fairchild Airframe
Airworthiness Limitations Manual ST–UN–
M003, Rev. No. 7, dated March 8, 2004, as
applicable. You must do the repairs required
by this AD following the instructions in
Fairchild SA226/227 Series Structural Repair
Manual, part number (P/N) 27–10054–079,
pages 57 through 90; Initial Issue: March 1,
1983; Revision 28, dated June 24, 1998; or
Fairchild SA227 Series Structural Repair
Manual, P/N 27–10054–127, pages 47
through 60; Initial Issue: December 1, 1991;
Revision 7, dated June 24, 1998, as
applicable.
(1) On April 16, 1999 (64 FR 11761, March
10, 1999), and in accordance with 5 U.S.C.
552(a) and 1 CFR part 51, the Director of the
Federal Register approved the incorporation
by reference of Fairchild Airframe
Airworthiness Limitations Manual ST–UN–
M001, Rev. No. C–6, dated April 7, 1998;
Fairchild Airframe Inspection Manual ST–
UN–M002, Rev. No. A–6, dated December 8,
1997; Fairchild Airframe Airworthiness
Limitations Manual ST–UN–M003, Rev. No.
5, dated April 7, 1998; Fairchild SA226/227
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Procedures
Issued in Kansas City, Missouri, on March
14, 2005.
David R. Showers,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–5383 Filed 3–18–05; 8:45 am]
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20513; Directorate
Identifier 2005–CE–07–AD; Amendment 39–
14022; AD 2005–05–52]
RIN 2120–AA64
Airworthiness Directives; the Cessna
Aircraft Company Models 402C and
414A Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) to
supersede emergency AD 2005–05–51
and AD 2000–23–01 for The Cessna
Aircraft Company (Cessna) Models 402C
and 414A airplanes. This AD contains
the same information as emergency AD
2005–05–52 and publishes the action in
the Federal Register. It requires you to
eddy current inspect the forward wing
spars and visually inspect the aft and
auxiliary spars. This AD is the result of
extensive cracks found on three wing
spars of the affected airplanes. We are
issuing this AD to detect and correct
cracking in the wing spars before the
cracks grow to failure. Such a wing
failure could result in the wing
separating from the airplane with
consequent loss of control of the
airplane.
This AD becomes effective on
March 21, 2005, to all affected persons
who did not receive emergency AD
2005–05–52, issued March 2, 2005.
Emergency AD 2005–05–52 contained
the requirements of this amendment and
became effective immediately upon
receipt. As of March 21, 2005, the
Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the
regulations.
We must receive any comments on
this AD by April 30, 2005.
ADDRESSES: Use one of the following to
submit comments on this AD:
DATES:
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]]>Agencies
[Federal Register Volume 70, Number 53 (Monday, March 21, 2005)]
[Rules and Regulations]
[Pages 13359-13362]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-5383]
[[Page 13359]]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-CE-12-AD; Amendment 39-14023; AD 2005-06-13]
RIN 2120-AA64
Airworthiness Directives; Fairchild Aircraft, Inc. SA226 and
SA227 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new Airworthiness Directive (AD) to
supersede AD 99-06-02, which currently applies to certain Fairchild
Aircraft (Fairchild) SA226 and SA227 series airplanes. AD 99-06-02
requires you to repetitively inspect the wing spar center web cutout on
both wings for cracks between Wing Station (WS) 8 and WS 17.5. That AD
also requires you to repair any area found cracked before further
flight. The repair will eliminate the need for the repetitive
inspections on that particular wing spar. Since that AD became
effective, we have determined that we inadvertently omitted certain
Model SA227-CC/DC airplane serial numbers from the applicability. This
AD retains the actions of AD 99-06-02 and adds additional Model SA227-
CC/DC airplanes to the Applicability section. The actions specified in
this AD are intended to detect and correct fatigue cracking of the wing
spar center web cutout area, which could result in structural failure
of the wing spar. This could lead to loss of control of the airplane.
DATES: This AD becomes effective on May 2, 2005.
On April 16, 1999 (64 FR 11761, March 10, 1999), the Director of
the Federal Register approved the incorporation by reference of
Fairchild Airframe Airworthiness Limitations Manual ST-UN-M001, Rev.
No. C-6, dated April 7, 1998; Fairchild Airframe Inspection Manual ST-
UN-M002, Rev. No. A-6, dated December 8, 1997; Fairchild Airframe
Airworthiness Limitations Manual ST-UN-M003, Rev. No. 5, dated April 7,
1998; Fairchild SA226/227 Series Structural Repair Manual, part number
(P/N) 27-10054-079, pages 57 through 90; Initial Issue: March 1, 1983;
Revision 28, dated June 24, 1998; and Fairchild SA227 Series Structural
Repair Manual, P/N 27-10054-127, pages 47 through 60; Initial Issue:
December 1, 1991; Revision 7, dated June 24, 1998.
As of May 2, 2005, the Director of the Federal Register approved
the incorporation by reference of Fairchild Airframe Airworthiness
Limitations Manual ST-UN-M001, SA227 Series, Reissue C, dated January
18, 1991; Fairchild Airframe Inspection Manual ST-UN-M002, SA226
Series, Reissue A, dated December 9, 1986; and Fairchild Airframe
Airworthiness Limitations Manual ST-UN-M003, SA227 Commuter Category,
Initial issue dated December 6, 1991.
ADDRESSES: You may get the service information identified in this AD
from Field Support Engineering, Fairchild Aircraft, Inc., P.O. Box
790490, San Antonio, Texas 78279-0490; telephone: (210) 824-9421;
facsimile: (210) 820-8609.
You may view the AD docket at FAA, Central Region, Office of the
Regional Counsel, Attention: Rules Docket No. 99-CE-12-AD, 901 Locust,
Room 506, Kansas City, Missouri 64106. Office hours are 8 a.m. to 4
p.m., Monday through Friday, except Federal holidays.
FOR FURTHER INFORMATION CONTACT: Mr. Hung Viet Nguyen, FAA, Forth Worth
Airplane Certification Office (ACO), 2601 Meacham Boulevard, Fort
Worth, Texas 76193-0150; telephone: (817) 222-5155; facsimile: (817)
222-5960.
SUPPLEMENTARY INFORMATION:
Discussion
What events have caused this AD? AD 99-06-02, Amendment 39-11066
(64 FR 11761, March 10, 1999), currently requires you to do the
following on certain Fairchild SA226 and SA227 series airplanes:
--Repetitively inspecting the wing spar center web cutout on both wings
for cracks between Wing Station (WS) 8 and WS 17.5; and
--Immediately repairing any area found cracked. This repair will
eliminate the need for the repetitive inspections on that particular
wing spar.
Doing the actions as specified in AD 99-06-02 is required per the
following documents:
--Fairchild Airframe Airworthiness Limitations Manual ST-UN-M001, Rev.
No. C-6, dated April 7, 1998;
--Fairchild Airframe Inspection Manual ST-UN-M002, Rev. No. A-6, dated
December 8, 1997;
--Fairchild Airframe Airworthiness Limitations Manual ST-UN-M003, Rev.
No. 5, dated April 7, 1998;
--Fairchild SA226/227 Series Structural Repair Manual, part number (P/
N) 27-10054-079, pages 57 through 90; Initial Issue: March 1, 1983;
Revision 28, dated June 24, 1998; and
--Fairchild SA227 Series Structural Repair Manual, P/N 27-10054-127,
pages 47 through 60; Initial Issue: December 1, 1991; Revision 7, dated
June 24, 1998.
AD 99-06-02 was the result of reports of cracks in the wing spar
center web cutout caused by fatigue due to airplane maneuvering and
wind gusts.
What has happened since AD 99-06-02 to initiate this action? The
FAA inadvertently omitted certain Fairchild Model SA227-CC/DC airplane
serial numbers from the applicability of AD 99-06-02. In particular, we
restricted the applicability of these airplanes to serial numbers CC/
DC784 and CC/DC790 through CC/DC878. Any Fairchild Model SA227-CC/DC
airplane incorporating a serial number from CC/DC879 through CC/DC896
should also be affected by the actions of AD 99-06-02.
What is the potential impact if FAA took no action? If not detected
and corrected, fatigue cracking of the wing spar center web cutout area
could result in structural failure of the wing spar to the point of
failure with consequent loss of control of the airplane.
Has FAA taken any action to this point? We issued 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 SA226 and SA227
series airplanes. This proposal was published in the Federal Register
as a notice of proposed rulemaking (NPRM) on April 23, 1999 (64 FR
19934). The NPRM proposed to retain the actions of AD 99-06-02 and add
additional Model SA227-CC/DC airplanes to the applicability section.
Was the public invited to comment? We provided the public the
opportunity to participate in developing this AD. The following
presents the comment received on the proposal and FAA's response to the
comment:
Comment Issue: Incorporate Revised Service Information
What is the commenter's concern? The manufacturer has revised the
applicable service information to incorporate minor changes.
These revisions do not change the procedures contained in the
service information referenced in AD 99-06-02; however, the
manufacturer suggests incorporating the revised service information
into the final rule AD action.
What is FAA's response to the concern? We concur with the
[[Page 13360]]
commenter and will make this change in the final rule AD action.
Conclusion
What is FAA's final determination on this issue? We have carefully
reviewed the available data and determined that air safety and the
public interest require adopting the AD as proposed except for the
changes discussed above and minor editorial corrections. We have
determined that these changes and minor corrections:
--Are consistent with the intent that was proposed in the NPRM for
correcting the unsafe condition; and
--Do not add any additional burden upon the public than was already
proposed in the NPRM.
Changes to 14 CFR Part 39--Effect on the AD
How does the revision to 14 CFR part 39 affect this AD? On July 10,
2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997,
July 22, 2002), which governs the FAA's AD system. This regulation now
includes material that relates to altered products, special flight
permits, and alternative methods of compliance. This material
previously was included in each individual AD. Since this material is
included in 14 CFR part 39, we will not include it in future AD
actions.
Costs of Compliance
How many airplanes does this AD impact? We estimate that this AD
affects 508 airplanes in the U.S. registry.
What is the cost impact of this AD on owners/operators of the
affected airplanes? We estimate the following costs to do the
inspection:
----------------------------------------------------------------------------------------------------------------
Total cost per
Labor cost Parts cost airplane Total cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
5 work hours x $65 = $325........ Not Applicable...... $325 $325 x 508 = $165,100
----------------------------------------------------------------------------------------------------------------
These figures only take into account the costs of the initial
inspection and do not take into account the costs of repetitive
inspections and the costs associated with any repair that would be
necessary if cracks are found. We have no way of determining the number
of repetitive inspections an owner/operator will incur over the life of
the airplane, or the number of airplanes that will need repairs.
We estimate the following costs to do any necessary repairs in both
wing spar center webs that will be required based on the results of the
inspection. We have no way of determining the number of airplanes that
may need this repair:
----------------------------------------------------------------------------------------------------------------
Labor cost to repair cracked wing spar Total cost per airplane to repair cracked wing
center webs on both sides of the airplane Parts cost spar center webs on both sides of the airplane
----------------------------------------------------------------------------------------------------------------
400 work hours x $65 = $26,000.............. $400 $26,000 + $400 = $26,400
----------------------------------------------------------------------------------------------------------------
What is the difference between the cost impact of this AD and the
cost impact of AD 99-06-02? The only difference between AD 99-06-02 and
this AD is the addition of 18 Fairchild Model SA227-CC/DC airplanes
that we inadvertently omitted from the Applicability section of AD 99-
06-02. Therefore, the only impact this AD has over that already
required by AD 99-06-02 is the cost of the actions on the 18 additional
airplanes.
Regulatory Findings
Will this AD impact various entities? We have determined that this
AD will not have federalism implications under Executive Order 13132.
This AD will not have a substantial direct effect 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.
Will this AD involve a significant rule or regulatory action? For
the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the 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.
We prepared a summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary by
sending a request to us at the address listed under ADDRESSES. Include
``AD Docket No. 99-CE-12-AD'' in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under 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
0
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]
0
2. FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 99-
06-02, Amendment 39-11066 (64 FR 11761, March 10, 1999), and by adding
a new AD to read as follows:
2005-06-13 Fairchild Aircraft, Inc.: Amendment 39-14023; Docket No.
99-CE-12-AD; Supersedes AD 99-06-02, Amendment 39-11066.
When Does This AD Become Effective?
(a) This AD becomes effective on May 2, 2005.
What Other ADs Are Affected by This Action?
(b) This AD supersedes AD 99-06-02, Amendment 39-11066.
What Airplanes Are Affected by This AD?
(c) This AD affects the following airplane models and serial
numbers that are certificated in any category:
[[Page 13361]]
------------------------------------------------------------------------
Model Serial Nos.
------------------------------------------------------------------------
(1) SA226-AT........................... AT001 through AT074.
(2) SA226-TC........................... TC201 through TC419.
(3) SA226-T............................ T201 through T291.
(4) SA226-T(B)......................... T(B)276 and T(B)292 through
T(B)417.
(5) SA227-TT........................... TT421 through TT541.
(6) SA227-TT(300)...................... TT(300)447, TT(300)465,
TT(300)471, TT(300)483,
TT(300)512, TT(300)518,
TT(300)521, TT(300)527,
TT(300)529, and TT(300)536.
(7) SA227-AC........................... AC406, AC415, AC416, and AC420
through AC785.
(8) SA227-AT........................... AT423 through AT631 and AT695.
(9) SA227-BC........................... BC762, BC764, BC766, and BC770
through BC789.
(10) SA227-CC/DC....................... CC/DC784, and CC/DC790 through
CC/DC896.
------------------------------------------------------------------------
What Is the Unsafe Condition Presented in This AD?
(d) This AD is the result of reports of cracks in the wing spar
center web cutout caused by fatigue due to airplane maneuvering and
wind gusts. The actions specified in this AD are intended to detect
and correct fatigue cracking of the wing spar center web cutout
area, which could result in structural failure of the wing spar.
This could lead to loss of control of the airplane.
What Must I Do To Address This Problem?
(e) To address this problem, you must do the following:
------------------------------------------------------------------------
Actions Compliance Procedures
------------------------------------------------------------------------
(1) Inspect each wing spar Initially inspect For Models SA227-
center web cutout for cracks upon accumulating TT, SA227-AT,
between Wing Station (WS) 8 and 6,500 hours time- SAA227-AC, and
WS 17.5. in-service (TIS) SA227-BC
on each wing airplanes: Follow
spar; within the Fairchild
next 2,000 hours Airframe
TIS after the Airworthiness
last inspection Limitations
done following Manual ST-UN-
the applicable M001, Rev. No. C-
Airworthiness 6, dated April 7,
Limitations 1998; or
Manual (the last Fairchild
inspection done Airframe
following AD 99- Airworthiness
06-02); or within Limitations
the next 500 Manual ST-UN-
hours TIS after M001, SA227
May 2, 2005 the Series, Reissue C
effective date of dated January 18,
this AD, 1991, at the
whichever occurs revision levels
later. stated on page
Repetitively iii and page iv
inspect (page iii dated
thereafter at August 16, 1995,
intervals not to and page iv dated
exceed 2,000 March 8, 2004);
hours TIS. For Models SA226-
T, SA226-T(B),
SA226-AT, and
SA226-TC
airplanes; Follow
Fairchild
Airframe
Inspection Manual
ST-UN-M002, Rev.
No. A-6, dated
December 8, 1997;
or Fairchild
Airframe
Inspection Manual
ST-Un-M002,
Reissue A, SA226
Series, dated
December 9, 1986,
at the revision
levels stated on
page iii and page
iv (page iii
dated April 7,
1998 and page iv
dated March 8,
2004); and For
Models SA227-CC
and SA227-DC
airplanes: Follow
Fairchild
Airframe
Airworthiness
Limitations
Manual ST-UN-
M003, Rev. No. 5,
dated April 7,
1998; or
Fairchild
Airframe
Airworthiness
Limitations
Manual ST-UN-
M003, SA227
Commuter
Category, Initial
issue dated
December 6, 1991,
at the revision
levels stated on
page iii and page
iv (page iii
dated July 29,
2003, and page iv
dated March 8,
2004).
(2) If any crack(s) is/are found Before further For Models SA226-
during any inspection required flight. T, SA226-T(B),
by paragraph (e)(1) of this AD, SA226-AT, SA226-
repair the crack(s). This TC, SA227-TT,
repair eliminates the SA227-AT, SA227-
repetitive inspections required AC, and SA227-BC
in paragraph (e)(1) of this AD airplanes: Follow
for that particular wing spar. Fairchild SA226/
227 Series
Structural Repair
Manual, part
number (P/N) 27-
10054-079, pages
57 through 90;
Initial Issue:
March 1, 1983;
Revision 28,
dated June 24,
1998; and For
Models SA227-CC
and SA227-DC
airplanes: Follow
Fairchild SA227
Series Structural
Repair Manual, P/
N 27-10054-127,
pages 47 through
60; Initial
Issue: December
1, 1991; Revision
7, dated June 24,
1998.
[[Page 13362]]
(3) The repetitive inspections Not applicable.... Not applicable.
required in paragraph (e)(1) of
this AD may be terminated if
the wing spar center web repair
specified in paragraph (e)(2)
of this AD has been done on
both the left and right wing
spar. If one wing spar center
web has been repaired, then
repetitive inspections are
still required on the other one
until the repair is done.
------------------------------------------------------------------------
May I Request an Alternative Method of Compliance?
(f) You may request a different method of compliance or a
different compliance time for this AD by following the procedures in
14 CFR 39.19:
(1) Unless FAA authorizes otherwise, send your request to your
principal inspector. The principal inspector may add comments and
will send your request to the Manager, Fort Worth Aircraft
Certification Office (ACO), FAA. For information on any already
approved alternative methods of compliance, contact Mr. Hung Viet
Nguyen, Forth Worth ACO, FAA, 2601 Meacham Boulevard, Fort Worth,
Texas 76193-0150; telephone: (817) 222-5155; facsimile: (817) 222-
5960.
(2) Alternative methods of compliance approved for AD 99-06-02
are considered approved as alternative methods of compliance for
this AD.
Does This AD Incorporate Any Material by Reference?
(g) You must do the inspections required by this AD following
the instructions in Fairchild Airframe Airworthiness Limitations
Manual ST-UN-M001, Rev. No. C-6, dated April 7, 1998; Fairchild
Airframe Airworthiness Limitations Manual ST-UN-M001, Rev. No. C-8,
dated March 8, 2004; Fairchild Airframe Inspection Manual ST-UN-
M002, Rev. No. A-6, dated December 8, 1997; Fairchild Airframe
Inspection Manual ST-UN-M002, Rev. No. A-9, dated March 8, 2004;
Fairchild Airframe Airworthiness Limitations Manual ST-UN-M003, Rev.
No. 5, dated April 7, 1998; or Fairchild Airframe Airworthiness
Limitations Manual ST-UN-M003, Rev. No. 7, dated March 8, 2004, as
applicable. You must do the repairs required by this AD following
the instructions in Fairchild SA226/227 Series Structural Repair
Manual, part number (P/N) 27-10054-079, pages 57 through 90; Initial
Issue: March 1, 1983; Revision 28, dated June 24, 1998; or Fairchild
SA227 Series Structural Repair Manual, P/N 27-10054-127, pages 47
through 60; Initial Issue: December 1, 1991; Revision 7, dated June
24, 1998, as applicable.
(1) On April 16, 1999 (64 FR 11761, March 10, 1999), and in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51, the Director of
the Federal Register approved the incorporation by reference of
Fairchild Airframe Airworthiness Limitations Manual ST-UN-M001, Rev.
No. C-6, dated April 7, 1998; Fairchild Airframe Inspection Manual
ST-UN-M002, Rev. No. A-6, dated December 8, 1997; Fairchild Airframe
Airworthiness Limitations Manual ST-UN-M003, Rev. No. 5, dated April
7, 1998; Fairchild SA226/227 Series Structural Repair Manual, part
number (P/N) 27-10054-079, pages 57 through 90; Initial Issue: March
1, 1983; Revision 28, dated June 24, 1998; and Fairchild SA227
Series Structural Repair Manual, P/N 27-10054-127, pages 47 through
60; Initial Issue: December 1, 1991; Revision 7, dated June 24,
1998.
(2) As of May 2, 2005, and in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51, the Director of the Federal Register approved the
incorporation by reference of Fairchild Airframe Airworthiness
Limitations Manual ST-UN-M001, SA227 Series, Reissue C dated January
18, 1991, at the revision levels stated on page iii and page iv
(page iii dated August 16, 1995, and page iv dated March 8, 2004);
Fairchild Airframe Inspection Manual ST-UN-M002, Reissue A, SA226
Series, dated December 9, 1986, at the revision levels stated on
page iii and page iv (page iii dated April 7, 1998, and page iv
dated March 8, 2004); and Fairchild Airframe Airworthiness
Limitations Manual ST-UN-M003, SA227 Commuter Category, Initial
issue dated December 6, 1991, at the revision levels stated on page
iii and page iv (page iii dated July 29, 2003, and page iv dated
March 8, 2004).
(3) You may get a copy from Field Support Engineering, Fairchild
Aircraft, Inc., P.O. Box 790490, San Antonio, Texas 78279-0490. You
may review copies at FAA, Central Region, Office of the Regional
Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; or at
the National Archives and Records Administration (NARA). For
information on the availability of this material at NARA, call (202)
741-6030, or go to: https://www.archives.gov/federal_register/code_
of_federal_regulations/ibr_locations.html.
Issued in Kansas City, Missouri, on March 14, 2005.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-5383 Filed 3-18-05; 8:45 am]
BILLING CODE 4910-13-P
