2008-16-09 R1 Short Brothers PLC: Amendment 39-15992. Docket No. FAA-2009-0464; Directorate Identifier 2008-NM-189-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective September 16, 2009.
Affected ADs
(b) This AD revises AD 2008-16-09.
Applicability
(c) This AD applies to all Shorts Model SD3-60 airplanes, certificated in any category.
Subject
(d) Air Transport Association (ATA) of America Code 55: Stabilizers.
Reason
(e) The mandatory continuing airworthiness information (MCAI) (i.e., European Aviation Safety Agency Airworthiness Directive 2007- 0107-E, dated April 18, 2007) states:
There have been several occurrences of cracked elevator trim tab balance weight attachment brackets, on one occasion, the elevator trim tab mass balance weight bracket separated from the aircraft. The loss of an elevator trim tab mass balance weight bracket has the potential to cause damage to an aircraft, or cause serious injury topersonnel.
* * * * *
Compliance
(f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Restatement of Requirements of AD 2004-13-08, Amendment 39-13690, With Revised Service Information
Initial Inspection
(g) Within 2 months after August 3, 2004 (the effective date of AD 2004-13-08, amendment 39-13690): 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 Accomplishment Instructions of Short Brothers Service Bulletin SD360-55-20, dated June 26, 2003; Shorts Service Bulletin SD360-55- 20, Revision 1, dated June 20, 2005; or Shorts Service Bulletin SD360-55-20, Revision 2, dated March 29, 2007.
Investigative and Corrective Actions if No Cracking Is Found
(h) If no cracking is found during the inspection required by paragraph (g) of this AD, do theactions required by paragraphs (h)(1) and (h)(2) of this AD at the applicable compliance times.
(1) Repeat the inspection required by paragraph (g) of this AD at intervals not to exceed 4,800 flight hours until the bracket is replaced per paragraph (h)(2) or (i) of this AD.
(2) Prior to the accumulation of 28,800 total flight hours, or within 6 months after August 3, 2004, whichever occurs later: Replace any bracket that has not been replaced per paragraph (i) of this AD with a new bracket or with a serviceable bracket that has been inspected in accordance with paragraph (g) of this AD. Replace in accordance with the Accomplishment Instructions of Short Brothers Service Bulletin SD360-55-20, dated June 26, 2003; Shorts Service Bulletin SD360-55-20, Revision 1, dated June 20, 2005; or Shorts Service Bulletin SD360-55-20, Revision 2, dated March 29, 2007. Replacement of the brackets constitutes terminating action for the repetitive inspections required by paragraph (h)(1) of this AD.
Corrective Actions if Any Cracking Is Found
(i) If any cracking is found during any inspection required by paragraph (g) or (h) of this AD: Before further flight, accomplish the applicable action in paragraph (i)(1) or (i)(2) of this AD in accordance with the Accomplishment Instructions of Short Brothers Service Bulletin SD360-55-20, dated June 26, 2003; Shorts Service Bulletin SD360-55-20, Revision 1, dated June 20, 2005; or Shorts Service Bulletin SD360-55-20, Revision 2, dated March 29, 2007.
(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 Accomplishment Instructions of Short Brothers Service Bulletin SD360-55-20, dated June 26, 2003; Shorts Service Bulletin SD360-55- 20, Revision 1, dated June 20, 2005; or Shorts Service Bulletin SD360-55-20, Revision 2, dated March 29, 2007 (including the additional dye penetrantinspection of the repaired welded joint); and repeat the inspection required by paragraph (g) of this AD at intervals not to exceed 4,800 flight hours; or replace the bracket in accordance with paragraph (h)(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 (g) of this AD. Replacement of the bracket constitutes terminating action for the repetitive inspections required by paragraph (i)(1) of this AD.
Refitting
(j) Before further flight, following any inspection per paragraph (g) or (h) of this AD; or before further flight following repair or replacement of a bracket per paragraph (h)(2) or (i) of this AD: Refit the balance weights, covers, and trim tabs, in accordance with the Accomplishment Instructions of Short Brothers Service Bulletin SD360-55-20, dated June 26, 2003; Shorts Service Bulletin SD360-55-20, Revision 1, dated June 20, 2005; or Shorts Service Bulletin SD360-55-20, Revision 2, dated March 29, 2007. Where the Accomplishment Instructions of Short Brothers Service Bulletin SD360-55-20, dated June 26, 2003; Shorts Service Bulletin SD360-55-20, Revision 1, dated June 20, 2005; or Shorts Service Bulletin SD360-55-20, Revision 2, dated March 29, 2007; specify to contact the manufacturer for disposition of certain conditions while refitting, obtain further disposition instructions from the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent).
Parts Installation
(k) As of August 3, 2004, no person may install on any airplane a balance weight bracket unless the welded joint has been inspected in accordance with paragraph (g) of this AD.
Restatement of Requirements of AD 2005-04-13, Amendment 39-13985, With Revised Service Information
Return of Parts to Manufacturer Not Required
(l) Although the Accomplishment Instructions of Short Brothers Alert Service Bulletin SD360-55-A21, dated December 16, 2004; or Shorts Alert Service Bulletin SD360-55-A21, Revision 1, dated March 29, 2007; specify to return subject parts to the manufacturer, this AD does not include that requirement.
Repetitive Inspections
(m) For airplanes equipped with balance weight brackets of the elevator trim tabs having part number SD3-07-6011xA, and having a serial number beginning with "X3'' or "X4'': Prior to the accumulation of 250 flight hours since installation of the subject balance weight bracket of the elevator trim tab, or within 30 flight hours after March 14, 2005 (the effective date of AD 2005-04-13), whichever is later, do a dye penetrant inspection for cracking of the balance weight brackets for the left and right elevator trim tabs, in accordance with Short Brothers Alert Service Bulletin SD360-55-A21, dated December 16, 2004; or Shorts Alert Service Bulletin SD360-55-A21, Revision 1, dated March 29, 2007.
(1) For a balance weight bracket on which no cracking is found: Do paragraph (o) of this AD, and repeat the inspection thereafter at intervals not to exceed 250 flight hours until paragraph (n) of this AD is accomplished.
(2) For a balance weight bracket on which any cracking is found: Before further flight, replace the bracket with a new or reworked balance weight bracket that conforms to the approved design standard, in accordance with Short Brothers Alert Service Bulletin SD360-55-A21, dated December 16, 2004; or Shorts Alert Service Bulletin SD360-55-A21, Revision 1, dated March 29, 2007; and do paragraph (o) of this AD.
Optional Terminating Action
(n) For airplanes equipped with balanceweight brackets of the elevator trim tabs having part number SD3-07-6011xA, and having a serial number beginning with "X3'' or "X4'': Replacement of any subject balance weight bracket with a new or reworked balance weight bracket that conforms to the approved design standard, in accordance with the Accomplishment Instructions of Short Brothers Alert Service Bulletin SD360-55-A21, dated December 16, 2004; or Shorts Alert Service Bulletin SD360-55-A21, Revision 1, dated March 29, 2007; constitutes terminating action for the repetitive inspections required by paragraph (m) of this AD for the replaced bracket.
Refitting
(o) For airplanes equipped with balance weight brackets of the elevator trim tabs having part number SD3-07-6011xA, and having a serial number beginning with "X3'' or "X4:'' Before further flight following any inspection or replacement of a bracket in accordance with paragraphs (m) and (n) of this AD: Refit the balance weights, covers, and trim tabs, in accordancewith the Accomplishment Instructions of Short Brothers Alert Service Bulletin SD360-55-A21, dated December 16, 2004; or Shorts Alert Service Bulletin SD360-55- A21, Revision 1, dated March 29, 2007. Where the Accomplishment Instructions of Short Brothers Alert Service Bulletin SD360-55-A21, dated December 16, 2004; or Shorts Alert Service Bulletin SD360-55- A21, Revision 1, dated March 29, 2007; specify to contact the manufacturer for disposition of certain conditions while refitting, obtain further disposition instructions from the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent).
Parts Installation
(p) For all airplanes: As of March 14, 2005, no person may install, on any airplane subject to this AD, a balance weight bracket having part number SD3-07-6011xA, and having a serial number beginning with "X3'' or "X4,'' unless the bracket is also marked "Rework batch number R-Bxxxxx'' (where "xxxxx'' is a number).
Restatement of Requirements of AD 2008-16-09, Amendment 39-15627, With Extended Repetitive Interval in Paragraph (q)(2) of This AD
Inspection(s) and Replacements
(q) For airplanes equipped with balance weight brackets of the elevator trim tabs having part number SD3-07-6011xA manufactured in the year 2003 or 2004, including reworked brackets, installed in accordance with paragraph (h)(2), (i)(2), or (n) of this AD, as applicable: Do the actions specified in paragraphs (q)(1) and (q)(2) of this AD in accordance with Parts A and B of the Accomplishment Instructions of Shorts Alert Service Bulletin SD360-55-A21, Revision 1, dated March 29, 2007.
(1) Within 30 flight hours after September 15, 2008 (the effective date of AD 2008-16-09) or within 250 flight hours since installation of the balance weight brackets of the elevator trim tabs or since the last inspection required by paragraph (g), (h)(1), (i)(1), or (m) of this AD, whichever occurslater: Do a dye penetrant inspection to detect cracks of the balance weight brackets of the elevator trim tabs.
(i) If no crack is detected, repeat the dye penetrant inspection at intervals not to exceed 250 flight hours, until the replacement required by paragraph (q)(2) of this AD is done.
(ii) If any crack is detected, before further flight, do the replacement specified in paragraph (q)(2) of this AD.
(2) Before the accumulation of 1,750 flight hours since installation of the balance weight brackets of the elevator trim tabs, or within 180 days after September 15, 2008, whichever occurs later: Replace the balance weight brackets with new balance weight brackets manufactured in 2005 or later. Thereafter, replace any balance weight bracket with a new bracket manufactured in 2005 or later at intervals not to exceed the accumulation of 28,800 flight hours on that bracket. Accomplishment of the initial replacement ends the repetitive inspection requirements of this AD.
(r) For airplanes equipped with balance weight brackets of the elevator trim tabs having part number SD3-31-6213xB inspected in accordance with paragraph (g), (h)(1), or (i)(1) of this AD and retained or refitted following approved repair in accordance with paragraph (j) of this AD: Do the actions specified in paragraphs (r)(1) and (r)(2) of this AD in accordance with Parts A and B of the Accomplishment Instructions of Shorts Alert Service Bulletin SD360- 55-20, Revision 2, dated March 29, 2007.
(1) Within 4,800 flight hours since last inspection, or within 180 days after September 15, 2008, whichever occurs later, and thereafter at intervals not to exceed 4,800 flight hours: Do a dye penetrant inspection to detect cracks of the balance weight brackets of the elevator trim tabs.
(i) If no crack is detected, repeat the dye penetrant inspection at intervals not to exceed 4,800 flight hours, until the replacement required by paragraph (r)(2) of this AD is done.
(ii) If any crack is detected, before further flight, do the replacement specified in paragraph (r)(2) of this AD.
(2) Before the accumulation of 28,800 flight hours since any balance weight bracket of the elevator trim tabs is new, or within 180 days after September 15, 2008, whichever occurs later: Replace the balance weight brackets with new balance weight brackets manufactured in 2005 or later. Thereafter, replace any balance weight bracket with a new bracket manufactured in 2005 or later at intervals not to exceed the accumulation of 28,800 flight hours on that bracket. Accomplishment of the initial replacement ends the repetitive inspection requirements of this AD.
Part Installation
(s) For all airplanes: As of September 15, 2008, no person may install, on any airplane, a balance weight bracket of the elevator trim tab manufactured earlier than 2005.
FAA AD Differences
Note 1: This AD differs from the MCAI and/or service information as follows: No differences.
Other FAA AD Provisions
(t) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Todd Thompson, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-1175; fax (425) 227-1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office.
(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approvedif they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120- 0056.
Related Information
(u) Refer to MCAI EASA Airworthiness Directive 2007-0107-E, dated April 18, 2007, and the service bulletins identified in Table 1 of this AD for related information.
Table 1--Related Service Information
Document
Revision
Date
Short Brothers Alert Service Bulletin SD360-55-A21
Original
December 16, 2004
Short Brothers Service Bulletin SD360-55-20
Original
June 26, 2003
Shorts Alert Service Bulletin SD360-55-A21
1
March 29, 2007
Shorts Service Bulletin SD360-55-20
1
June 20, 2005
Shorts Service Bulletin SD360-55-20
2
March 29, 2007
Material Incorporated by Reference
(v) You must use the service information contained in Table 2 of this AD to do the actions required by this AD, unless the AD specifies otherwise. If you do the optional terminating action specified in this AD, you must use the service information specified in Table 3 of this AD to do that action, unless the AD specifies otherwise.
Table 2--Material Incorporated by Reference for Required Actions
Document
Revision
Date
Short Brothers Alert Service Bulletin SD360-55-A21
Original
December 16, 2004
Short Brothers Service Bulletin SD360-55-20
Original
June 26, 2003
Shorts Alert Service Bulletin SD360-55-A21
1
March 29, 2007
Shorts Service Bulletin SD360-55-20
1
June 20, 2005
Shorts Service Bulletin SD360-55-20
2
March 29, 2007
Table 3--Material Incorporated by Reference for Optional Actions
Document
Revision
Date
Short Brothers Alert Service Bulletin SD360-55-A21
Original
December 16, 2004
Shorts Alert Service Bulletin SD360-55-A21
1
March 29, 2007
(1) On September 15, 2008 (73 FR 46543, August 11, 2008), the Director of the Federal Register previously approved the incorporation by reference of Shorts Alert Service Bulletin SD360- 55-A21, Revision 1, dated March 29, 2007; Shorts Service Bulletin SD360-55-20, Revision 1, dated June 20, 2005; and Shorts Service Bulletin SD360-55-20, Revision 2, dated March 29, 2007.
(2) On March 14, 2005 (70 FR 9212, February 25, 2005), the Director of the Federal Register previously approved the incorporation by reference of Short Brothers Alert Service Bulletin SD360-55-A21, dated December 16, 2004.
(3) On August 3, 2004 (69 FR 38813, June 29, 2004), the Director of the Federal Register previously approved the incorporation by reference of Short Brothers Service Bulletin SD360-55-20, dated June 26, 2003.
(4) For service information identified in this AD, contact Short Brothers PLC, Airworthiness, P.O. Box 241, Airport Road, Belfast BT3 9DZ, Northern Ireland; telephone +44(0)2890-462469; fax +44(0)2890- 468444; e-mail michael.mulholland@aero.bombardier.com; Internet http://www.bombardier.com.
(5) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425-227-1221 or 425-227-1152.
(6) You may also review copies of the service information that is incorporated by reference 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.