[Federal Register Volume 64, Number 78 (Friday, April 23, 1999)]
[Proposed Rules]
[Pages 19934-19936]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-10170]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-CE-12-AD]
RIN 2120-AA64
Airworthiness Directives; Fairchild Aircraft, Inc. SA226 and
SA227 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to supersede Airworthiness Directive
(AD) 99-06-02, which currently requires repetitively inspecting the
wing spar center web cutout on both wings for cracks between Wing
Station (WS) 8 and WS 17.5 on certain Fairchild Aircraft (Fairchild)
SA226 and SA227 series airplanes, and immediately repairing any area
found cracked. The repair will eliminate the need for the repetitive
inspections on that particular wing spar. Since that AD became
effective, the FAA has determined that it inadvertently omitted certain
serial numbers of the Model SA227-CC/DC airplanes. The proposed AD
would retain the actions of AD 99-06-02, and would add these Model
SA227-CC/DC airplanes to the Applicability section of the AD. The
actions specified by the proposed AD are intended to continue to detect
and correct fatigue cracking of the wing spar center web cutout area,
which could result in structural failure of the wing spar to the point
of failure with consequent loss of control of the airplane.
DATES: Comments must be received on or before June 21, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Regional Counsel,
Attention: Rules Docket No. 99-CE-12-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 Field Support Engineering, Fairchild Aircraft, Inc., P.O. Box
790490, San Antonio, Texas 78279-0490; telephone: (210) 824-9421;
facsimile: (210) 820-8609. This information also may be examined at the
Rules Docket at the address above.
FOR FURTHER INFORMATION CONTACT: Mr. Hung Viet Nguyen, 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. 99-CE-12-AD.'' The postcard will be date stamped and
returned to the commenter.
Availability of NPRMs
Any person may obtain a copy of this NPRM by submitting a request
to the FAA, Central Region, Office of the Regional Counsel, Attention:
Rules Docket No. 99-CE-12-AD, Room 1558, 601 E. 12th Street, Kansas
City, Missouri 64106.
Discussion
AD 99-06-02, Amendment 39-11066 (64 FR 11761, March 10, 1999),
currently requires 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.
Accomplishment of the actions as specified in AD 96-06-02 is
required in
[[Page 19935]]
accordance with 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;
--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
--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.
The actions specified in AD 99-06-02 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 to the point of
failure with consequent loss of control of the airplane.
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.
Actions Since Issuance of Previous Rule
Since AD 99-06-02 became effective, the FAA has determined that it
inadvertently omitted certain serial numbers of the Fairchild Model
SA227-CC/DC airplanes. In particular, the FAA 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.
The FAA's Determination
After examining the circumstances and reviewing all available
information related to the incidents described above, the FAA has
determined that:
--The actions of AD 99-06-02 should also apply to the serial numbered
Fairchild Model SA227-CC/DC airplanes referenced above; and
--AD action should be taken to continue to detect and correct fatigue
cracking of the wing spar center web cutout area, which could result in
structural failure of the wing spar to the point of failure with
consequent loss of control of the airplane.
Explanation of the Provisions of the Proposed AD
Since an unsafe condition has been identified that is likely to
exist or develop in other Fairchild SA226 and SA227 series airplanes of
the same type design, the FAA is proposing AD action to supersede AD
99-06-02. The proposed AD would retain the actions of AD 99-06-02, and
would add these Model SA227-CC/DC airplanes to the Applicability
section of the AD.
Cost Impact
The FAA estimates that 508 airplanes in the U.S. registry would be
affected by the proposed AD, that it would take approximately 5
workhours per airplane to accomplish the proposed initial inspection,
and that the average labor rate is approximately $60 an hour. Based on
these figures, the total cost impact of the proposed initial inspection
specified in this AD on U.S. operators is estimated to be $152,400, or
$300 per airplane.
These figures only take into account the costs of the proposed
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. The FAA has 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.
If an affected airplane would have cracks in both wing spar center
webs, the repair would take 400 workhours to accomplish at an average
labor rate of $60 per hour. Parts to accomplish this repair cost
approximately $400 per airplane. Based on these figures, the cost to
repair cracked wing spar center webs on both sides of the airplane
would be approximately $24,400 per airplane.
The only difference between AD 99-06-02 and the proposed AD is the
addition of 18 Fairchild Model SA227-CC/DC airplanes that the FAA
inadvertently omitted from the ``Applicability'' section of AD 99-06-
02. Therefore, the only impact the proposed AD would have over that
already required by AD 99-06-02 is the cost of the proposed actions on
these 18 additional airplanes.
Regulatory Impact
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 14
CFR part 39 of the Federal Aviation Regulations 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) 99-06-02, Amendment 39-11066, and by adding a new AD to read as
follows:
Fairchild Aircraft, Inc.: Docket No. 99-CE-12-AD; Supersedes AD 99-
06-02, Amendment 39-11066.
Applicability: The following model airplanes and serial numbers,
certificated in any category:
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Model Serial Nos.
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SA226-AT........................ AT001 through AT074.
SA226-TC........................ TC201 through TC419.
SA226-T......................... T201 through T291.
SA226-T(B)...................... T(B)276 and T(B)292 through T(B)417.
[[Page 19936]]
SA227-TT........................ TT421 through TT541.
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.
SA227-AC........................ AC406, AC415, AC416, and AC420 through
AC785.
SA227-AT........................ AT423 through AT631 and AT695.
SA227-BC........................ BC762, BC764, BC766, and BC770 through
BC789.
SA227-CC/DC..................... CC/DC784 and CC/DC790 through CC/
DC896.
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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 (e) 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.
Compliance: Required as indicated in the body of this AD, unless
already accomplished.
To detect and correct fatigue cracking of the wing spar center
web cutout area, which could result in structural failure of the
wing spar to the point of failure with consequent loss of control of
the airplane, accomplish the following:
(a) Upon accumulating 6,500 hours time-in-service (TIS) on each
wing spar; within the next 2,000 hours TIS after the last inspection
accomplished per the applicable Airworthiness Limitations Manual
(referenced in the paragraphs below); or within the next 500 hours
TIS after the effective date of this AD, whichever occurs later,
unless already accomplished (accomplishment of AD 99-06-02,
including any FAA-approved alternative methods of compliance with AD
99-06-02); and thereafter at intervals not to exceed 2,000 hours
TIS, inspect each wing spar center web cutout for cracks between
Wing Station (WS) 8 and WS 17.5. Accomplish this inspection in
accordance with one of the following, as applicable:
(1) For Models SA227-TT, SA227-AT, SAA227-AC, and SA227-BC
airplanes: In accordance with Fairchild Airframe Airworthiness
Limitations Manual ST-UN-M001, Rev. No. C-6, dated April 7, 1998;
(2) For Models SA226-T, SA226-T(B), SA226-AT, and SA226-TC
airplanes: In accordance with Fairchild Airframe Inspection Manual
ST-UN-M002, Rev. No. A-6, dated December 8, 1997; or
(3) For Models SA227-CC and SA227-DC airplanes: In accordance
with Fairchild Airframe Airworthiness Limitations Manual ST-UN-M003,
Rev. No. 5, dated April 7, 1998.
(b) If any crack(s) is/are found during any inspection required
by paragraph (a) of this AD, prior to further flight, repair the
crack(s) in accordance with one of the following, as applicable.
This repair eliminates the repetitive inspections (2,000 hours TIS
intervals) required in paragraph (a) of this AD for that particular
wing spar.
(1) For Models SA226-T, SA226-T(B), SA226-AT, SA226-TC, SA227-
TT, SA227-AT, SA227-AC, and SA227-BC airplanes: In accordance with
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
(2) For Models SA227-CC and SA227-DC airplanes: In accordance
with 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.
(c) The repetitive inspections required by paragraph (a) of this
AD may be terminated if the wing spar center web repair specified in
paragraph (b) of this AD has been accomplished 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 if the
repair has not been incorporated.
(d) Special flight permits may be issued in accordance with
Secs. 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.
(e) 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, FAA, Airplane
Certification Office (ACO), 2601 Meacham Boulevard, Fort Worth,
Texas 76193-0150.
(1) The request shall be forwarded through an appropriate FAA
Maintenance Inspector, who may add comments and then send it to the
Manager, Forth Worth ACO.
(2) Alternative methods of compliance approved in accordance
with AD 99-06-02 are considered approved as alternative methods of
compliance for this AD.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Fort Worth ACO.
(f) All persons affected by this directive may obtain copies of
the documents referred to herein upon request to Field Support
Engineering, Fairchild Aircraft, Inc., P.O. Box 790490, San Antonio,
Texas 78279-0490; or may examine these documents at the FAA, Central
Region, Office of the Regional Counsel, Room 1558, 601 E. 12th
Street, Kansas City, Missouri 64106.
(g) This amendment supersedes AD 99-06-02, Amendment 39-11066.
Issued in Kansas City, Missouri, on April 15, 1999.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 99-10170 Filed 4-22-99; 8:45 am]
BILLING CODE 4910-13-P
