[Federal Register Volume 70, Number 53 (Monday, March 21, 2005)]
[Rules and Regulations]
[Pages 13359-13362]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-5383]



[[Page 13359]]

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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: http://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]
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