Airworthiness Directives; Short Brothers Model SD3-60 Series Airplanes

[Federal Register Volume 69, Number 124 (Tuesday, June 29, 2004)]
[Rules and Regulations]
[Pages 38813-38815]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-14321]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-236-AD; Amendment 39-13690; AD 2004-13-08]
RIN 2120-AA64


Airworthiness Directives; Short Brothers Model SD3-60 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to all Short Brothers Model SD3-60 series airplanes. This AD 
requires inspection of the welded joints of the balance weight brackets 
for the left and right elevator trim tabs for cracking; repetitive 
inspections, as applicable; and corrective actions including the 
eventual replacement of all brackets, which constitutes terminating 
action for the repetitive inspections. This action is necessary to 
prevent the loss of the balance weight for the elevator trim tab, which 
could result in incorrect trim during takeoff and landing, and reduced 
controllability of the airplane. This action is intended to address the 
identified unsafe condition.

DATES: Effective August 3, 2004.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 3, 2004.

ADDRESSES: The service information referenced in this AD may be 
obtained from Short Brothers, Airworthiness & Engineering Quality, P.O. 
Box 241, Airport Road, Belfast BT3 9DZ, Northern Ireland. This 
information may be examined at the Federal Aviation Administration 
(FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, 
SW., Renton, Washington; 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 html.

FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-1175; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to all Short Brothers Model SD3-60 
series airplanes was published in the Federal Register on April 22, 
2004 (69 FR 21766). That action proposed to require inspection of the 
welded joints of the balance weight brackets for the left and right 
elevator trim tabs for cracking; repetitive inspections, as applicable; 
and corrective actions including the eventual replacement of all 
brackets, which would constitute terminating action for the repetitive 
inspections.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were submitted in response 
to the proposal or the FAA's determination of the cost to the public.

[[Page 38814]]

Conclusion

    We have determined that air safety and the public interest require 
the adoption of the rule as proposed.

Cost Impact

    We estimate that 42 airplanes of U.S. registry will be affected by 
this AD, that it will take approximately 12 work hours per airplane to 
accomplish the required inspections, and that the average labor rate is 
$65 per work hour. Based on these figures, the cost impact of this 
action on U.S. operators is estimated to be $32,760, or $780 per 
airplane.
    It will take approximately 8 work hours per airplane to accomplish 
the replacement of the brackets. Required parts will cost approximately 
$632 per airplane. Based on these figures, the cost impact of this 
action on U.S. operators is estimated to be $48,384, or $1,152 per 
airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the requirements of this 
AD action, and that no operator would accomplish those actions in the 
future if this AD were not adopted. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

Regulatory Impact

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from 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

0
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

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. Section 39.13 is amended by adding the following new airworthiness 
directive:

2004-13-08 Short Brothers PLC: Amendment 39-13690. Docket 2003-NM-
236-AD.

    Applicability: All Model SD3-60 series airplanes, certificated 
in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent the loss of the balance weight for the elevator trim 
tab, which could result in incorrect trim during takeoff and 
landing, and reduced controllability of the airplane, accomplish the 
following:

Service Bulletin Reference

    (a) The term ``service bulletin,'' as used in this AD, means the 
Accomplishment Instructions of Short Brothers Service Bulletin 
SD360-55-20, dated June 26, 2003.

Initial Inspection

    (b) Within 2 months after the effective date of this AD: Do a 
dye penetrant inspection for cracking in the welded joints of the 
balance weight brackets for the left and right elevator trim tabs, 
in accordance with the service bulletin.

Investigative and Corrective Actions if No Cracking Is Found

    (c) If no cracking is found during the inspection required by 
paragraph (b) of this AD, do the actions required by paragraphs 
(c)(1) and (c)(2) of this AD at the applicable compliance times.
    (1) Repeat the inspection required by paragraph (b) of this AD 
at intervals not to exceed 4,800 flight hours until the bracket is 
replaced per paragraph (c)(2) or (d) of this AD.
    (2) Prior to the accumulation of 28,800 total flight hours, or 
within 6 months after the effective date of this AD, whichever 
occurs later: Replace any bracket that has not been replaced per 
paragraph (d) of this AD with a new bracket or with a serviceable 
bracket that has been inspected in accordance with paragraph (b) of 
this AD. Replace in accordance with the service bulletin. 
Replacement of the brackets constitutes terminating action for the 
repetitive inspections required by paragraph (c)(1) of this AD.

Corrective Actions if Any Cracking Is Found

    (d) If any cracking is found during any inspection required by 
paragraph (b) or (c) of this AD: Before further flight, accomplish 
the applicable action in paragraph (d)(1) or (d)(2) of this AD in 
accordance with the service bulletin.
    (1) For airplanes that have accumulated less than 28,800 flight 
hours and on which all cracking on brackets is less than 0.25 inch 
in length: Repair the affected bracket in accordance with Part B of 
the service bulletin (including the additional dye penetrant 
inspection of the repaired welded joint) and repeat the inspection 
required by paragraph (b) of this AD at intervals not to exceed 
4,800 flight hours; or replace the bracket in accordance with 
paragraph (d)(2) of this AD. Replacement of the bracket constitutes 
terminating action for the repetitive inspections.
    (2) For any airplane on which any cracking on a bracket is 0.25 
inch in length or greater, and for any airplane that has accumulated 
28,800 flight hours or more on which any cracking of any length is 
found on a bracket: Replace the affected bracket with a new bracket 
or with a serviceable bracket that has been inspected in accordance 
with paragraph (b) of this AD. Replacement of the bracket 
constitutes terminating action for the repetitive inspections 
required by paragraph (d)(1) of this AD.

Refitting

    (e) Before further flight following any inspection per 
paragraphs (b) or (c) of this AD; or before further flight following 
repair or replacement of a bracket per paragraphs (c)(2) or (d) of 
this AD: Refit the balance weights, covers, and trim tabs, in 
accordance with the service bulletin. Where the service bulletin 
specifies to contact the manufacturer for disposition of certain 
conditions while refitting, obtain further disposition instructions 
from the Manager, International Branch, ANM-116, FAA, Transport 
Airplane Directorate; or the Civil Aviation Authority (CAA) (or its 
delegated agent).

Parts Installation

    (f) As of the effective date of this AD, no person may install 
on any airplane a balance weight bracket unless the welded joint has 
been inspected in accordance with paragraph (b) of this AD.

Alternative Methods of Compliance

    (g) In accordance with 14 CFR 39.19, the Manager, International 
Branch, ANM-116, is authorized to approve alternative methods of 
compliance for this AD.

Incorporation by Reference

    (h) Unless otherwise specified in this AD the actions shall be 
done in accordance with Short Brothers Service Bulletin SD360-55-20, 
dated June 26, 2003. This incorporation by reference was 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 Short 
Brothers, Airworthiness & Engineering Quality, P.O.

[[Page 38815]]

Box 241, Airport Road, Belfast BT3 9DZ, Northern Ireland. Copies may 
be inspected at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington; 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.

    Note 1: The subject of this AD is addressed in British 
airworthiness directive 009-06-2003.

Effective Date

    (i) This amendment becomes effective on August 3, 2004.

    Issued in Renton, Washington, on June 16, 2004.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 04-14321 Filed 6-28-04; 8:45 am]
BILLING CODE 4910-13-P

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