Airworthiness Directives; Short Brothers Model SD3-60 Airplanes, 46543-46546 [E8-17744]

Download as PDF Federal Register / Vol. 73, No. 155 / Monday, August 11, 2008 / Rules and Regulations DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0375; Directorate Identifier 2007–NM–272–AD; Amendment 39–15627; AD 2008–16–09] RIN 2120–AA64 Airworthiness Directives; Short Brothers Model SD3–60 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is superseding two existing airworthiness directives (ADs), which apply to all Short Brothers Model SD3–60 airplanes. One of the ADs currently requires inspection of the welded joints of the balance weight brackets for the elevator trim tabs for cracking; repetitive inspections, as applicable; and corrective actions including the eventual replacement of all brackets. The other AD currently requires, for certain airplanes, repetitive inspections for cracking of the balance weight brackets and replacement of any cracked bracket, and provides for an optional terminating action for the repetitive inspections. This new AD requires an additional inspection to detect cracks of the balance weight brackets, applicable related investigative and corrective actions, and replacement of a certain balance weight bracket when it has reached its maximum life limit. This AD results from a report indicating that several reworked balance weight brackets have exhibited signs of premature failure. We are issuing this AD to prevent failure of the balance weight brackets of the elevator trim tabs, which could cause loss of the balance weight. This could result in incorrect trim during takeoff and landing, and reduced controllability of the airplane. DATES: This AD becomes effective September 15, 2008. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of September 15, 2008. On March 14, 2005 (70 FR 9212, February 25, 2005), the Director of the Federal Register approved the incorporation by reference of Short Brothers Alert Service Bulletin SD360– 55–A21, dated December 16, 2004. On August 3, 2004 (69 FR 38813, June 29, 2004), the Director of the Federal Register approved the incorporation by reference of Short Brothers Service Bulletin SD360–55–20, dated June 26, 2003. ADDRESSES: For service information identified in this AD, contact Short Brothers, Airworthiness & Engineering Quality, P.O. Box 241, Airport Road, Belfast BT3 9DZ, Northern Ireland. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is the Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, 46543 International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1175; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that supersedes AD 2004–13–08, amendment 39–13690 (69 FR 38813, June 29, 2004); and AD 2005–04–13, amendment 39– 13985 (70 FR 9212, February 25, 2005). The existing ADs apply to all Short Brothers Model SD3–60 airplanes. That NPRM was published in the Federal Register on April 1, 2008 (73 FR 17260). That NPRM proposed to retain the requirements of the existing ADs. That NPRM also proposed to require an additional inspection to detect cracks of the balance weight brackets, applicable related investigative and corrective actions, and replacement of a certain balance weight bracket when it has reached its maximum life limit. Comments We provided the public the opportunity to participate in the development of this AD. No comments have been received on the NPRM or on the determination of the cost to the public. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance The following table provides the estimated costs for U.S. operators to comply with this AD. ESTIMATED COSTS Action jlentini on PROD1PC65 with RULES Inspections (required by AD 2004–13–08). Replacement (required by AD 2004–13–08). Inspections (required by AD 2005–04–13). Inspection (new required action). Replacement (new required action). Average labor rate per hour Work hours Parts Cost per airplane 12 $80 (1) 8 80 $632 12 80 12 8 Number of U.S.registered airplanes Fleet cost $960, per inspection cycle 21 $20,160, per inspection cycle. $1,272 ............................... 21 $26,712. (1) $960, per inspection cycle 21 $20,160, per inspection cycle. 80 (1) $960, per inspection cycle 21 $20,160, per inspection cycle. 80 864 $1,504, per replacement cycle. 21 $31,584, per replacement cycle. 1 None. VerDate Aug<31>2005 15:34 Aug 08, 2008 Jkt 214001 PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 E:\FR\FM\11AUR1.SGM 11AUR1 46544 Federal Register / Vol. 73, No. 155 / Monday, August 11, 2008 / Rules and Regulations Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in subtitle VII, part A, subpart III, section 44701, ‘‘General Requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings 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. 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 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 regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. 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 FAA amends 14 CFR part 39 as follows: jlentini on PROD1PC65 with RULES I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I VerDate Aug<31>2005 15:34 Aug 08, 2008 Jkt 214001 Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendments 39–13690 (69 FR 38813, June 29, 2004), and 39–13985 (70 FR 9212, February 25, 2005), and by adding the following new airworthiness directive (AD): I 2008–16–09 Short Brothers PLC: Amendment 39–15627. Docket No. FAA–2008–0375; Directorate Identifier 2007–NM–272–AD. Effective Date (a) This AD becomes effective September 15, 2008. Affected ADs (b) This AD supersedes ADs 2004–13–08 and 2005–04–13. Applicability (c) This AD applies to all Short Brothers Model SD3–60 airplanes, certificated in any category. Unsafe Condition (d) This AD results from a report indicating that several reworked balance weight brackets have exhibited signs of premature failure. We are issuing this AD to prevent failure of the balance weight bracket of the elevator trim tab, which could cause loss of the balance weight. This could result in incorrect trim during takeoff and landing, and reduced controllability of the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Requirements of AD 2004–13–08 Service Bulletin Reference (f) The term ‘‘service bulletin,’’ as used in paragraphs (g) through (j) of this AD, means the Accomplishment Instructions of Short Brothers Service Bulletin SD360–55–20, dated June 26, 2003; or Revision 1, dated June 20, 2005. Initial Inspection (g) Within 2 months after August 3, 2004 (the effective date of AD 2004–13–08): 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 (h) If no cracking is found during the inspection required by paragraph (g) of this AD, do the actions 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 PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 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 service bulletin. 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 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 (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 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 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. Requirements of AD 2005–04–13 Service Bulletin Reference (l) The following information applies to the service bulletin referenced in paragraphs (l) through (o) of this AD: (1) The term ‘‘service bulletin,’’ as used in paragraphs (l) through (o) of this AD, means E:\FR\FM\11AUR1.SGM 11AUR1 46545 Federal Register / Vol. 73, No. 155 / Monday, August 11, 2008 / Rules and Regulations the Accomplishment Instructions of Short Brothers Alert Service Bulletin SD360–55– A21, dated December 16, 2004. (2) Although the service bulletin specifies 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 the service bulletin. (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 the service bulletin, and do paragraph (o) of this AD. Optional Terminating Action (n) 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’’: 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 service bulletin, 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 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 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). New Requirements 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 the effective date of this AD, 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 occurs later: 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 the effective date of this AD, 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 1,750 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 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 the effective date of this AD, 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 the effective date of this AD, 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 the effective date of this AD, no person may install, on any airplane, a balance weight bracket of the elevator trim tab manufactured earlier than 2005. Alternative Methods of Compliance (AMOCs) (t) 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, FAA, Transport Airplane Directorate, 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 appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Related Information (u) European Aviation Safety Agency emergency airworthiness directive 2007– 0107–E, dated April 18, 2007, also addresses the subject of this AD. Material Incorporated by Reference (v) You must use the service bulletins specified in Table 1 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. TABLE 1—MATERIAL INCORPORATED BY REFERENCE jlentini on PROD1PC65 with RULES Service Bulletin Revision level Date Short Brothers Alert Service Bulletin SD360–55–A21 .............................................................................. Short Brothers Service Bulletin SD360–55–20 ......................................................................................... Shorts Alert Service Bulletin SD360–55–A21 ........................................................................................... Shorts Service Bulletin SD360–55–20 ...................................................................................................... Original ............... Original ............... Revision 1 ........... Revision 1 ........... December 16, 2004. June 26, 2003. March 29, 2007. June 20, 2005. VerDate Aug<31>2005 15:34 Aug 08, 2008 Jkt 214001 PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 E:\FR\FM\11AUR1.SGM 11AUR1 46546 Federal Register / Vol. 73, No. 155 / Monday, August 11, 2008 / Rules and Regulations TABLE 1—MATERIAL INCORPORATED BY REFERENCE—Continued Service Bulletin Revision level Shorts Service Bulletin SD360–55–20 ...................................................................................................... Revision 2 ........... (1) The Director of the Federal Register 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 Alert Service Bulletin SD360–55–20, Revision 2, dated March 29, 2007; in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) On March 14, 2005 (70 FR 9212, February 25, 2005), the Director of the Federal Register 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 approved the incorporation by reference of Short Brothers Service Bulletin SD360–55– 20, dated June 26, 2003. (4) Contact Short Brothers, Airworthiness & Engineering Quality, P.O. Box 241, Airport Road, Belfast BT3 9DZ, Northern Ireland, for a copy of this service information. You may review copies 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: https://www.archives.gov/federal-register/ cfr/ibr-locations.html. Issued in Renton, Washington, on July 23, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–17744 Filed 8–8–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0450; Directorate Identifier 2007–SW–39–AD; Amendment 39– 15634; AD 2008–16–16] RIN 2120–AA64 Airworthiness Directives; Bell Helicopter Textron Canada (BHTC) Model 230 Helicopters Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. jlentini on PROD1PC65 with RULES AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for BHTC Model 230 helicopters. This AD results from mandatory continuing VerDate Aug<31>2005 15:34 Aug 08, 2008 Jkt 214001 airworthiness information (MCAI) issued by the aviation authority of Canada which indicates that the existing rigging procedures for the tail rotor pitch change mechanism have to be changed due to the possibility of parts interference. The cumulative effect of individual part tolerances resulting in the total assemblage of those parts being out of tolerance could result in the tail rotor yoke striking another part other than the flapping stop (parts interference) as cited in the MCAI. Also, the misalignment of the tail rotor counterweight bellcrank may result in higher tail rotor pedal forces and a higher pilot workload after failure of the No. 1 hydraulic system. Both parts interference and the misaligned counterweight bellcrank create an unsafe condition. This AD requires actions that are intended to address these unsafe conditions. DATES: This AD becomes effective on September 15, 2008. The incorporation by reference of certain publications is approved by the Director of the Federal Register as of September 15, 2008. ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the Docket Operations office, U.S. Department of Transportation, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC between 9 a.m. and 5 p.m. Monday through Friday, except Federal holidays. You may get the service information identified in this AD from Bell Helicopter Textron Canada, 12,800 Rue de l’Avenir, Mirabel, Quebec J7J1R4, telephone (450) 437–2862 or (800) 363– 8023, fax (450) 433–0272. Examining the Ad Docket: The AD docket contains the Notice of proposed rulemaking (NPRM), the economic evaluation, any comments received, and other information. The street address and operating hours for the Docket Operations office (telephone (800) 647– 5527) are in the ADDRESSES section of this AD. Comments will be available in the AD docket shortly after they are received. FOR FURTHER INFORMATION CONTACT: Tyrone Millard, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 Date March 29, 2007. Texas 76193–0111, telephone (817) 222–5439, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: Discussion We issued an NPRM to amend 14 CFR part 39 to include an AD that would apply to the BHTC Model 230 helicopters on April 14, 2008. That NPRM was published in the Federal Register on April 23, 2008 (73 FR 21855). That NPRM proposed to require, within the next 150 hours time-inservice (TIS) or at the next annual inspection, whichever occurs first, adjusting the rigging of the tail rotor pitch change mechanism, and if a gap exists between the tail rotor yoke and the flapping stop, replacing the tail rotor yoke with an airworthy tail rotor yoke. If no gap exists between the tail rotor yoke and the flapping stop at either full right or full left pedal position, adjusting the tail rotor pitch change mechanism and the tail rotor pedal forces was proposed. Comments By publishing the NPRM, we gave the public an opportunity to participate in developing this AD. However, we received no comment on the NPRM or on our determination of the cost to the public. Therefore, based on our review and evaluation of the available data, we have determined that air safety and the public interest require adopting the AD as proposed. Related Service Information Bell Helicopter Textron has issued Alert Service Bulletin 230–07–36, dated January 9, 2007. The actions described in the MCAI are intended to correct the same unsafe condition as that identified in the service information. Differences Between This AD and the MCAI The compliance times in this AD differ from the MCAI in that compliance is required within the next 150 hours TIS or at the next annual inspection, whichever occurs first, instead of ‘‘at the next 150 hour or annual inspection but no later than 31 December 2007.’’ Costs of Compliance We estimate that this AD will affect about 20 helicopters of U.S. registry. We also estimate that it will take 2 workhours per helicopter to adjust the E:\FR\FM\11AUR1.SGM 11AUR1

Agencies

[Federal Register Volume 73, Number 155 (Monday, August 11, 2008)]
[Rules and Regulations]
[Pages 46543-46546]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-17744]



[[Page 46543]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0375; Directorate Identifier 2007-NM-272-AD; 
Amendment 39-15627; AD 2008-16-09]
RIN 2120-AA64


Airworthiness Directives; Short Brothers Model SD3-60 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is superseding two existing airworthiness directives 
(ADs), which apply to all Short Brothers Model SD3-60 airplanes. One of 
the ADs currently requires inspection of the welded joints of the 
balance weight brackets for the elevator trim tabs for cracking; 
repetitive inspections, as applicable; and corrective actions including 
the eventual replacement of all brackets. The other AD currently 
requires, for certain airplanes, repetitive inspections for cracking of 
the balance weight brackets and replacement of any cracked bracket, and 
provides for an optional terminating action for the repetitive 
inspections. This new AD requires an additional inspection to detect 
cracks of the balance weight brackets, applicable related investigative 
and corrective actions, and replacement of a certain balance weight 
bracket when it has reached its maximum life limit. This AD results 
from a report indicating that several reworked balance weight brackets 
have exhibited signs of premature failure. We are issuing this AD to 
prevent failure of the balance weight brackets of the elevator trim 
tabs, which could cause loss of the balance weight. This could result 
in incorrect trim during takeoff and landing, and reduced 
controllability of the airplane.

DATES: This AD becomes effective September 15, 2008.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of September 15, 
2008.
    On March 14, 2005 (70 FR 9212, February 25, 2005), the Director of 
the Federal Register approved the incorporation by reference of Short 
Brothers Alert Service Bulletin SD360-55-A21, dated December 16, 2004.
    On August 3, 2004 (69 FR 38813, June 29, 2004), the Director of the 
Federal Register approved the incorporation by reference of Short 
Brothers Service Bulletin SD360-55-20, dated June 26, 2003.

ADDRESSES: For service information identified in this AD, contact Short 
Brothers, Airworthiness & Engineering Quality, P.O. Box 241, Airport 
Road, Belfast BT3 9DZ, Northern Ireland.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (telephone 800-647-5527) is the Document Management 
Facility, U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-1175; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 2004-13-08, amendment 
39-13690 (69 FR 38813, June 29, 2004); and AD 2005-04-13, amendment 39-
13985 (70 FR 9212, February 25, 2005). The existing ADs apply to all 
Short Brothers Model SD3-60 airplanes. That NPRM was published in the 
Federal Register on April 1, 2008 (73 FR 17260). That NPRM proposed to 
retain the requirements of the existing ADs. That NPRM also proposed to 
require an additional inspection to detect cracks of the balance weight 
brackets, applicable related investigative and corrective actions, and 
replacement of a certain balance weight bracket when it has reached its 
maximum life limit.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. No comments have been received on the NPRM or 
on the determination of the cost to the public.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD as proposed.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this AD.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                 Average                                      Number of
                                        Work      labor                                         U.S.-
               Action                  hours     rate per    Parts      Cost per airplane     registered                    Fleet cost
                                                   hour                                       airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
 Inspections (required by AD 2004-          12        $80        (1)   $960, per inspection           21   $20,160, per inspection cycle.
 13-08).                                                               cycle.
 Replacement (required by AD 2004-           8         80       $632   $1,272..............           21   $26,712.
 13-08).
 Inspections (required by AD 2005-          12         80        (1)   $960, per inspection           21   $20,160, per inspection cycle.
 04-13).                                                               cycle.
 Inspection (new required action)..         12         80        (1)   $960, per inspection           21   $20,160, per inspection cycle.
                                                                       cycle.
 Replacement (new required action).          8         80        864   $1,504, per                    21   $31,584, per replacement cycle.
                                                                       replacement cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------
\1\ None.


[[Page 46544]]

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
Requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    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.
    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 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 regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

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 FAA amends 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. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendments 39-13690 (69 FR 38813, June 29, 2004), and 39-13985 
(70 FR 9212, February 25, 2005), and by adding the following new 
airworthiness directive (AD):

2008-16-09 Short Brothers PLC: Amendment 39-15627. Docket No. FAA-
2008-0375; Directorate Identifier 2007-NM-272-AD.

Effective Date

    (a) This AD becomes effective September 15, 2008.

Affected ADs

    (b) This AD supersedes ADs 2004-13-08 and 2005-04-13.

Applicability

    (c) This AD applies to all Short Brothers Model SD3-60 
airplanes, certificated in any category.

Unsafe Condition

    (d) This AD results from a report indicating that several 
reworked balance weight brackets have exhibited signs of premature 
failure. We are issuing this AD to prevent failure of the balance 
weight bracket of the elevator trim tab, which could cause loss of 
the balance weight. This could result in incorrect trim during 
takeoff and landing, and reduced controllability of the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Requirements of AD 2004-13-08

Service Bulletin Reference

    (f) The term ``service bulletin,'' as used in paragraphs (g) 
through (j) of this AD, means the Accomplishment Instructions of 
Short Brothers Service Bulletin SD360-55-20, dated June 26, 2003; or 
Revision 1, dated June 20, 2005.

Initial Inspection

    (g) Within 2 months after August 3, 2004 (the effective date of 
AD 2004-13-08): 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

    (h) If no cracking is found during the inspection required by 
paragraph (g) of this AD, do the actions 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 service bulletin. 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 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 (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 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 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.

Requirements of AD 2005-04-13

Service Bulletin Reference

    (l) The following information applies to the service bulletin 
referenced in paragraphs (l) through (o) of this AD:
    (1) The term ``service bulletin,'' as used in paragraphs (l) 
through (o) of this AD, means

[[Page 46545]]

the Accomplishment Instructions of Short Brothers Alert Service 
Bulletin SD360-55-A21, dated December 16, 2004.
    (2) Although the service bulletin specifies 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 the service bulletin.
    (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 the service bulletin, and do paragraph (o) of 
this AD.

Optional Terminating Action

    (n) 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'': 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 service bulletin, 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 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 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).

New Requirements 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 the effective date of this AD, 
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 occurs later: 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 the effective date of this AD, 
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 
1,750 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 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 the effective date of this AD, 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 the effective date of this AD, 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 the effective date of this AD, no 
person may install, on any airplane, a balance weight bracket of the 
elevator trim tab manufactured earlier than 2005.

Alternative Methods of Compliance (AMOCs)

    (t) 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, FAA, Transport Airplane Directorate, 
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 appropriate 
principal inspector (PI) in the FAA Flight Standards District Office 
(FSDO), or lacking a PI, your local FSDO.

Related Information

    (u) European Aviation Safety Agency emergency airworthiness 
directive 2007-0107-E, dated April 18, 2007, also addresses the 
subject of this AD.

Material Incorporated by Reference

    (v) You must use the service bulletins specified in Table 1 of 
this AD to perform the actions that are required by this AD, unless 
the AD specifies otherwise.

                                   Table 1--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
             Service Bulletin                       Revision level                           Date
----------------------------------------------------------------------------------------------------------------
Short Brothers Alert Service Bulletin      Original........................  December 16, 2004.
 SD360-55-A21.
Short Brothers Service Bulletin SD360-55-  Original........................  June 26, 2003.
 20.
Shorts Alert Service Bulletin SD360-55-    Revision 1......................  March 29, 2007.
 A21.
Shorts Service Bulletin SD360-55-20......  Revision 1......................  June 20, 2005.

[[Page 46546]]

 
Shorts Service Bulletin SD360-55-20......  Revision 2......................  March 29, 2007.
----------------------------------------------------------------------------------------------------------------

    (1) The Director of the Federal Register 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 Alert 
Service Bulletin SD360-55-20, Revision 2, dated March 29, 2007; in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) On March 14, 2005 (70 FR 9212, February 25, 2005), the 
Director of the Federal Register 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 approved the incorporation by reference of 
Short Brothers Service Bulletin SD360-55-20, dated June 26, 2003.
    (4) Contact Short Brothers, Airworthiness & Engineering Quality, 
P.O. Box 241, Airport Road, Belfast BT3 9DZ, Northern Ireland, for a 
copy of this service information. You may review copies 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: https://www.archives.gov/federal-
register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on July 23, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E8-17744 Filed 8-8-08; 8:45 am]
BILLING CODE 4910-13-P

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