Airworthiness Directives; Bombardier, Inc. Airplanes, 71998-72001 [2013-28104]

Download as PDF 71998 Federal Register / Vol. 78, No. 231 / Monday, December 2, 2013 / Rules and Regulations accumulation of 3,000 total flight cycles since first flight of the airplane, or within 90 days after the effective date of this AD, whichever occurs later. (3) For Model A319 airplanes, manufacturer serial numbers 4151, 4228, and 4319 (post-modification 28238, 28162, and 28342): Inspect before the accumulation of 2,500 total flight cycles since first flight of the airplane, or within 90 days after the effective date of this AD, whichever occurs later. sroberts on DSK5SPTVN1PROD with RULES (h) Measurements and Corrective Actions If, during any inspection required by paragraph (g) of this AD, the fastener is determined to be missing, within the applicable compliance time specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD: Measure the hole dimensions of the five holes surrounding the missing fastener, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–53–1242, dated May 22, 2012; except where the service bulletin specifies to contact Airbus, before further flight, repair using a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent). Do all applicable related investigative and corrective actions before further flight. (i) Other FAA AD Provisions 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. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; telephone (425) 227–1405; fax (425) 227–1149. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. (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-approved if 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. (j) Related Information Refer to Mandatory Continuing Airworthiness Information EASA Airworthiness Directive 2012–0132, dated VerDate Mar<15>2010 19:14 Nov 29, 2013 Jkt 232001 July 19, 2012, for related information, which can be found in the AD docket on the Internet at http://www.regulations.gov/ #!documentDetail;D=FAA-2013-0096-0002. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Service Bulletin A320–53–1242, dated May 22, 2012. (ii) Reserved. (3) For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet http://www.airbus.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may view this 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/cfr/ibrlocations.html. inspections for cracking and damage of both pilot-side rudder pedal tubes, and replacement of affected pilot-side rudder bar assemblies if necessary. We are issuing this AD to detect and correct cracking of both pilot-side rudder pedal tubes, which could result in loss of pilot rudder pedal input causing reduced yaw controllability or a runway excursion. This AD becomes effective January 6, 2014. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 6, 2014. DATES: Issued in Renton, Washington, on August 9, 2013. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. You may examine the AD on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2013-0700 or in person at the U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. For service information identified in this AD, contact Bombardier, Inc., 400 ˆ ´ Cote-Vertu Road West, Dorval, Quebec H4S 1Y9, Canada; telephone 514–855– 5000; fax 514–855–7401; email thd.crj@ aero.bombardier.com; Internet http:// www.bombardier.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. [FR Doc. 2013–28170 Filed 11–29–13; 8:45 am] FOR FURTHER INFORMATION CONTACT: BILLING CODE 4910–13–P Ricardo Garcia, Aerospace Engineer, Airframe and Propulsion Branch, ANE– 171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228–7331; fax (516) 794–5531. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 SUPPLEMENTARY INFORMATION: [Docket No. FAA–2013–0700; Directorate Identifier 2013–NM–102–AD; Amendment 39–17676; AD 2013–24–02] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by reports of fractured rudder pedal tubes installed on the pilot-side rudder bar assembly. This AD requires repetitive SUMMARY: PO 00000 Frm 00012 Fmt 4700 ADDRESSES: Sfmt 4700 Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. The NPRM was published in the Federal Register on August 26, 2013 (78 FR 52712). The NPRM proposed to correct an unsafe condition for the specified products. Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF– 2013–12, dated May 14, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: E:\FR\FM\02DER1.SGM 02DER1 Federal Register / Vol. 78, No. 231 / Monday, December 2, 2013 / Rules and Regulations There have been two in-service reports of fracture of rudder pedal tubes installed on the pilot-side rudder bar assembly. Laboratory examination of the fractured rudder pedal tubes found that in both cases, the fatigue cracks initiated at the aft taper pin holes where the connecting rod fitting is attached. Fatigue testing of the rudder pedal tubes confirmed that the fatigue cracking is due to loads induced during parking brake application. Therefore, only the rudder pedal tubes on the pilot’s side are vulnerable to fatigue cracking as the parking brake is primarily applied by the pilot. Loss of pilot rudder pedal input during flight would result in reduced yaw controllability of the aeroplane. Loss of pilot rudder pedal input during takeoff or landing may lead to a runway excursion. This [Canadian] AD mandates initial and repetitive [detailed or eddy current] inspections [for cracking and damage and replacement if necessary] of the pilot-side rudder * * * [bar assembly], until the terminating action is accomplished. 71999 Conclusion Required actions also include repairing damage. The terminating action is replacement of both pilot-side rudder bar assemblies. You may obtain further information by examining the MCAI in the AD docket on the Internet at http://www.regulations.gov/ #!documentDetail;D=FAA-2013-07000002. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (78 FR 52712, August 26, 2013) or on the determination of the cost to the public. We reviewed the available data and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (78 FR 52712, August 26, 2013) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (78 FR 52712, August 26, 2013). Costs of Compliance We estimate that this AD affects 529 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Inspection ...................... 3 work-hours × $85 per hour = $255 per inspection cycle. We estimate the following costs to do any necessary replacement that would Parts cost $0 Cost per product $255 per inspection cycle. be required based on the results of the inspection. We have no way of Cost on U.S. operators $134,895 per inspection cycle. determining the number of aircraft that might need this repair: ON-CONDITION COSTS Action Labor cost Replacement ...................................... 6 work-hours × $85 per hour = $510 ............................................................. sroberts on DSK5SPTVN1PROD with RULES We have received no definitive data that would enable us to provide a cost estimate for the repair specified in this AD. According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. 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 VerDate Mar<15>2010 19:14 Nov 29, 2013 Jkt 232001 Parts cost Cost per product $2,850 $3,360 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. 3. Will not affect intrastate aviation in Alaska; and 4. 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. Regulatory Findings You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2013-0700; or in person at the Docket Operations office 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 street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. We 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 the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 Examining the AD Docket List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. E:\FR\FM\02DER1.SGM 02DER1 72000 Federal Register / Vol. 78, No. 231 / Monday, December 2, 2013 / Rules and Regulations Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ 2013–24–02 Bombardier, Inc.: Amendment 39–17676. Docket No. FAA–2013–0700; Directorate Identifier 2013–NM–102–AD. (a) Effective Date This airworthiness directive (AD) becomes effective January 6, 2014. (b) Affected ADs None. (c) Applicability This AD applies to Bombardier, Inc. Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes, certificated in any category, serial numbers 7003 and subsequent. (d) Subject Air Transport Association (ATA) of America Code 27, Flight controls. (e) Reason This AD was prompted by reports of fractured rudder pedal tubes installed on the pilot-side rudder bar assembly. We are issuing this AD to detect and correct cracking of both pilot-side rudder pedal tubes, which could result in loss of pilot rudder pedal input causing reduced yaw controllability or a runway excursion. sroberts on DSK5SPTVN1PROD with RULES (f) Compliance You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. (g) Initial Inspections At the applicable time specified in paragraphs (g)(1) through (g)(6) of this AD, do a detailed or eddy current inspection for cracking and damage (i.e., corrosion or cracking) of both pilot-side rudder pedal tubes having part number (P/N) 600–90204– 3, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 601R–27–162, including Appendix A, dated April 5, 2013. (1) For airplanes that have accumulated less than 20,000 total flight cycles as of the effective date of this AD: Do the inspection before the accumulation of 23,000 total flight cycles. (2) For airplanes that have accumulated 20,000 total flight cycles or more, but less than 25,000 total flight cycles as of the effective date of this AD: Do the inspection within 3,000 flight cycles after the effective VerDate Mar<15>2010 19:14 Nov 29, 2013 Jkt 232001 date of this AD, but not to exceed 26,300 total flight cycles. (3) For airplanes that have accumulated 25,000 total flight cycles or more, but less than 30,000 total flight cycles as of the effective date of this AD: Do the inspection within 1,300 flight cycles after the effective date of this AD, but not to exceed 30,800 total flight cycles. (4) For airplanes that have accumulated 30,000 total flight cycles or more, but less than 33,000 total flight cycles as of the effective date of this AD: Do the inspection within 800 flight cycles after the effective date of this AD, but not to exceed 33,500 total flight cycles. (5) For airplanes that have accumulated 33,000 total flight cycles or more, but less than 37,000 total flight cycles as of the effective date of this AD: Do the inspection within 500 flight cycles after the effective of this AD, but not to exceed 37,300 total flight cycles. (6) For airplanes that have accumulated 37,000 total flight cycles or more as of the effective date of this AD: Do the inspection within 300 flight cycles after the effective date of this AD. (h) Inspection Definition For the purposes of this AD, a detailed inspection is an intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as a mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required. (i) Repetitive Inspections For any tube on which no cracking and no damage is found during any inspection required by paragraph (g) of this AD: At the applicable time specified in paragraph (i)(1) or (i)(2) of this AD, repeat the detailed or eddy current inspection for cracking of the pilot-side rudder pedal tubes, specified in paragraph (g) of this AD, until the terminating action specified in paragraph (k) of this AD has been accomplished. (1) If the most recent inspection was a detailed inspection: Repeat the inspection within 600 flight cycles thereafter. (2) If the most recent inspection was an eddy current inspection: Repeat the inspection within 1,000 flight cycles thereafter. (j) Corrective Actions (1) If any cracking is found around the aft tapered holes during any inspection required by paragraph (g) or (i) of this AD, before further flight, replace the affected rudder bar assemblies, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 601R–27–162, including Appendix A, dated April 5, 2013. (2) If any other damage (i.e., corrosion or cracking), other than that specified in paragraph (j)(1) of this AD, is found during any inspection required by paragraph (g) or (i) of this AD, before further flight, repair using a method approved by either the Manager, New York Aircraft Certification Office (ACO), ANE–170, FAA; or Transport PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 Canada Civil Aviation (TCCA) (or its delegated agent). (k) Optional Terminating Action Replacement of both pilot-side rudder bar assemblies, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 601R–27–162, including Appendix A, dated April 5, 2013, terminates the inspections required by paragraphs (g) and (i) of this AD. (l) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office (ACO), ANE–170, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; fax 516–794–5531. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. (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-approved if 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. (m) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2013–12, dated May 14, 2013, for related information, which can be found in the AD docket on the internet at http://www.regulations.gov/ #!documentDetail;D=FAA-2013-0700-0002. (n) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Bombardier Service Bulletin 601R–27– 162, including Appendix A, dated April 5, 2013. (ii) Reserved. (3) For service information identified in ˆ this AD, contact Bombardier, Inc., 400 Cote´ Vertu Road West, Dorval, Quebec H4S 1Y9, Canada; telephone 514–855–5000; fax 514– 855–7401; email thd.crj@ aero.bombardier.com; Internet http:// www.bombardier.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, E:\FR\FM\02DER1.SGM 02DER1 Federal Register / Vol. 78, No. 231 / Monday, December 2, 2013 / Rules and Regulations 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may view this 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/cfr/ibrlocations.html. Issued in Renton, Washington, on November 15, 2013. John Piccola, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–28104 Filed 11–29–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2013–0449; Airspace Docket No. 13–AEA–8] Amendment of Class D and E Airspace, and Establishment of Class E Airspace; Salisbury, MD Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: This action amends Class D and Class E airspace, and establishes Class E airspace at Salisbury-Ocean City Wicomico Regional Airport, Salisbury, MD, due to the decommissioning of the Salisbury VHF Omnidirectional Radio Range Tactical Air Navigation Aid (VORTAC) and cancellation of the VOR approach. This enhances the safety and management of aircraft operations at the airport. This action also updates the geographic coordinates of the airport, and changes the Class D city designator. DATES: Effective 0901 UTC, February 6, 2014. The Director of the Federal Register approves this incorporation by reference action under title 1, Code of Federal Regulations, part 51, subject to the annual revision of FAA Order 7400.9 and publication of conforming amendments. SUMMARY: John Fornito, Operations Support Group, Eastern Service Center, Federal Aviation Administration, P.O. Box 20636, Atlanta, Georgia 30320; telephone (404) 305–6364. SUPPLEMENTARY INFORMATION: sroberts on DSK5SPTVN1PROD with RULES FOR FURTHER INFORMATION CONTACT: History On August 22, 2013, the FAA published in the Federal Register a notice of proposed rulemaking (NPRM) VerDate Mar<15>2010 19:14 Nov 29, 2013 Jkt 232001 to amend Class D and Class E surface area, and establish Class E airspace designated as an extension to a Class D surface area at Salisbury-Ocean City Wicomico Regional Airport, Salisbury, MD. (78 FR, 52109). Interested parties were invited to participate in this rulemaking effort by submitting written comments on the proposal to the FAA. No comments were received. Class D and Class E airspace designations are published in paragraphs 5000, 6002, 6004, and 6005, respectively, of FAA Order 7400.9X dated August 7, 2013, and effective September 15, 2013, which is incorporated by reference in 14 CFR 71.1. The Class D and E airspace designations listed in this document will be published subsequently in the Order. The Rule This amendment to Title 14, Code of Federal Regulations (14 CFR) part 71 amends Class D airspace and Class E surface airspace to within a 4.3-mile radius of the airport. Class E airspace extending upward from 700 feet above the surface is amended to within a 7mile radius of the airport. Class E airspace designated as an extension to a Class D surface area airspace is established within a 4.3-mile radius of the airport, with segments extending 7 miles southeast, northeast, and southwest of the airport. The geographic coordinates of the airport are adjusted to coincide with the FAA’s aeronautical database. The Class D city designation is changed from Salisbury-Ocean City Wicomico Regional Airport, MD, to Salisbury, MD. The FAA has determined that this regulation only involves an established body of technical regulations for which frequent and routine amendments are necessary to keep them operationally current, is non-controversial and unlikely to result in adverse or negative comments. It, therefore, (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) does not warrant preparation of a Regulatory Evaluation as the anticipated impact is so minimal. Since this is a routine matter that only affects air traffic procedures and air navigation, it is certified that this rule, when promulgated, does not have a significant economic impact on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. The FAA’s authority to issue rules regarding aviation safety is found in Title 49 of the United States Code. PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 72001 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. This rulemaking is promulgated under the authority described in Subtitle VII, Part A, Subpart I, Section 40103. Under that section, the FAA is charged with prescribing regulations to assign the use of airspace necessary to ensure the safety of aircraft and the efficient use of airspace. This regulation is within the scope of that authority as it amends controlled airspace at Salisbury-Ocean City Wicomico Regional Airport, Salisbury, MD. Environmental Review The FAA has determined that this action qualifies for categorical exclusion under the National Environmental Policy Act in accordance with FAA Order 1050.1E, ‘‘Environmental Impacts: Policies and Procedures,’’ paragraph 311a. This airspace action is not expected to cause any potentially significant environmental impacts, and no extraordinary circumstances exist that warrant preparation of an environmental assessment. Lists of Subjects in 14 CFR Part 71 Airspace, Incorporation by reference, Navigation (Air). Adoption of the Amendment In consideration of the foregoing, the Federal Aviation Administration amends 14 CFR Part 71 as follows: PART 71—DESIGNATION OF CLASS A, B, C, D, AND E AIRSPACE AREAS; AIR TRAFFIC SERVICE ROUTES; AND REPORTING POINTS 1. The authority citation for Part 71 continues to read as follows: ■ Authority: 49 U.S.C. 106(g); 40103, 40113, 40120; E.O. 10854, 24 FR 9565, 3 CFR, 1959– 1963 Comp., p. 389. § 71.1 [Amended] 2. The incorporation by reference in 14 CFR 71.1 of Federal Aviation Administration Order 7400.9X Airspace Designations and Reporting Points, dated August 7, 2013, effective September 15, 2013, is amended as follows: ■ Paragraph 5000 Class D Airspace * * * * * AEA MD D Salisbury, MD [Amended] Salisbury-Ocean City Wicomico Regional Airport, MD (Lat. 38°20′25″ N., long. 75°30′34″ W.) That airspace extending upward from the surface to and including 2,500 feet MSL E:\FR\FM\02DER1.SGM 02DER1

Agencies

[Federal Register Volume 78, Number 231 (Monday, December 2, 2013)]
[Rules and Regulations]
[Pages 71998-72001]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-28104]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0700; Directorate Identifier 2013-NM-102-AD; 
Amendment 39-17676; AD 2013-24-02]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc. Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) 
airplanes. This AD was prompted by reports of fractured rudder pedal 
tubes installed on the pilot-side rudder bar assembly. This AD requires 
repetitive inspections for cracking and damage of both pilot-side 
rudder pedal tubes, and replacement of affected pilot-side rudder bar 
assemblies if necessary. We are issuing this AD to detect and correct 
cracking of both pilot-side rudder pedal tubes, which could result in 
loss of pilot rudder pedal input causing reduced yaw controllability or 
a runway excursion.

DATES: This AD becomes effective January 6, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 6, 
2014.

ADDRESSES: You may examine the AD on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2013-0700 or in person at the 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 
Washington, DC.
    For service information identified in this AD, contact Bombardier, 
Inc., 400 C[ocirc]te-Vertu Road West, Dorval, Qu[eacute]bec H4S 1Y9, 
Canada; telephone 514-855-5000; fax 514-855-7401; email 
thd.crj@aero.bombardier.com; Internet http://www.bombardier.com. You 
may view this referenced service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221.

FOR FURTHER INFORMATION CONTACT: Ricardo Garcia, Aerospace Engineer, 
Airframe and Propulsion Branch, ANE-171, FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New 
York 11590; telephone (516) 228-7331; fax (516) 794-5531.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
The NPRM was published in the Federal Register on August 26, 2013 (78 
FR 52712). The NPRM proposed to correct an unsafe condition for the 
specified products. Transport Canada Civil Aviation (TCCA), which is 
the aviation authority for Canada, has issued Canadian Airworthiness 
Directive CF-2013-12, dated May 14, 2013 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for the specified products. The MCAI 
states:


[[Page 71999]]


    There have been two in-service reports of fracture of rudder 
pedal tubes installed on the pilot-side rudder bar assembly.
    Laboratory examination of the fractured rudder pedal tubes found 
that in both cases, the fatigue cracks initiated at the aft taper 
pin holes where the connecting rod fitting is attached. Fatigue 
testing of the rudder pedal tubes confirmed that the fatigue 
cracking is due to loads induced during parking brake application. 
Therefore, only the rudder pedal tubes on the pilot's side are 
vulnerable to fatigue cracking as the parking brake is primarily 
applied by the pilot.
    Loss of pilot rudder pedal input during flight would result in 
reduced yaw controllability of the aeroplane. Loss of pilot rudder 
pedal input during takeoff or landing may lead to a runway 
excursion.
    This [Canadian] AD mandates initial and repetitive [detailed or 
eddy current] inspections [for cracking and damage and replacement 
if necessary] of the pilot-side rudder * * * [bar assembly], until 
the terminating action is accomplished.

    Required actions also include repairing damage. The terminating 
action is replacement of both pilot-side rudder bar assemblies. You may 
obtain further information by examining the MCAI in the AD docket on 
the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-
0700-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD.
    We received no comments on the NPRM (78 FR 52712, August 26, 2013) 
or on the determination of the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting this AD as proposed except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (78 FR 52712, August 26, 2013) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 52712, August 26, 2013).

Costs of Compliance

    We estimate that this AD affects 529 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                      Labor cost          Parts cost    Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection......................  3 work-hours x $85 per             $0  $255 per inspection  $134,895 per
                                   hour = $255 per                        cycle.               inspection cycle.
                                   inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacement 
that would be required based on the results of the inspection. We have 
no way of determining the number of aircraft that might need this 
repair:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                       Cost per
                    Action                                    Labor cost                 Parts cost    product
----------------------------------------------------------------------------------------------------------------
Replacement...................................  6 work-hours x $85 per hour = $510....       $2,850       $3,360
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
a cost estimate for the repair specified in this AD.
    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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 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 the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2013-0700; or in person at the 
Docket Operations office 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 street address for the Docket Operations office (telephone (800) 
647-5527) is in the ADDRESSES section.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

[[Page 72000]]

Adoption of the Amendment

    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 FAA amends Sec.  39.13 by adding the following new AD:

2013-24-02 Bombardier, Inc.: Amendment 39-17676. Docket No. FAA-
2013-0700; Directorate Identifier 2013-NM-102-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective January 6, 
2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Bombardier, Inc. Model CL-600-2B19 (Regional 
Jet Series 100 & 440) airplanes, certificated in any category, 
serial numbers 7003 and subsequent.

(d) Subject

    Air Transport Association (ATA) of America Code 27, Flight 
controls.

(e) Reason

    This AD was prompted by reports of fractured rudder pedal tubes 
installed on the pilot-side rudder bar assembly. We are issuing this 
AD to detect and correct cracking of both pilot-side rudder pedal 
tubes, which could result in loss of pilot rudder pedal input 
causing reduced yaw controllability or a runway excursion.

(f) Compliance

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

(g) Initial Inspections

    At the applicable time specified in paragraphs (g)(1) through 
(g)(6) of this AD, do a detailed or eddy current inspection for 
cracking and damage (i.e., corrosion or cracking) of both pilot-side 
rudder pedal tubes having part number (P/N) 600-90204-3, in 
accordance with the Accomplishment Instructions of Bombardier 
Service Bulletin 601R-27-162, including Appendix A, dated April 5, 
2013.
    (1) For airplanes that have accumulated less than 20,000 total 
flight cycles as of the effective date of this AD: Do the inspection 
before the accumulation of 23,000 total flight cycles.
    (2) For airplanes that have accumulated 20,000 total flight 
cycles or more, but less than 25,000 total flight cycles as of the 
effective date of this AD: Do the inspection within 3,000 flight 
cycles after the effective date of this AD, but not to exceed 26,300 
total flight cycles.
    (3) For airplanes that have accumulated 25,000 total flight 
cycles or more, but less than 30,000 total flight cycles as of the 
effective date of this AD: Do the inspection within 1,300 flight 
cycles after the effective date of this AD, but not to exceed 30,800 
total flight cycles.
    (4) For airplanes that have accumulated 30,000 total flight 
cycles or more, but less than 33,000 total flight cycles as of the 
effective date of this AD: Do the inspection within 800 flight 
cycles after the effective date of this AD, but not to exceed 33,500 
total flight cycles.
    (5) For airplanes that have accumulated 33,000 total flight 
cycles or more, but less than 37,000 total flight cycles as of the 
effective date of this AD: Do the inspection within 500 flight 
cycles after the effective of this AD, but not to exceed 37,300 
total flight cycles.
    (6) For airplanes that have accumulated 37,000 total flight 
cycles or more as of the effective date of this AD: Do the 
inspection within 300 flight cycles after the effective date of this 
AD.

(h) Inspection Definition

    For the purposes of this AD, a detailed inspection is an 
intensive examination of a specific item, installation, or assembly 
to detect damage, failure, or irregularity. Available lighting is 
normally supplemented with a direct source of good lighting at an 
intensity deemed appropriate. Inspection aids such as a mirror, 
magnifying lenses, etc., may be necessary. Surface cleaning and 
elaborate procedures may be required.

(i) Repetitive Inspections

    For any tube on which no cracking and no damage is found during 
any inspection required by paragraph (g) of this AD: At the 
applicable time specified in paragraph (i)(1) or (i)(2) of this AD, 
repeat the detailed or eddy current inspection for cracking of the 
pilot-side rudder pedal tubes, specified in paragraph (g) of this 
AD, until the terminating action specified in paragraph (k) of this 
AD has been accomplished.
    (1) If the most recent inspection was a detailed inspection: 
Repeat the inspection within 600 flight cycles thereafter.
    (2) If the most recent inspection was an eddy current 
inspection: Repeat the inspection within 1,000 flight cycles 
thereafter.

(j) Corrective Actions

    (1) If any cracking is found around the aft tapered holes during 
any inspection required by paragraph (g) or (i) of this AD, before 
further flight, replace the affected rudder bar assemblies, in 
accordance with the Accomplishment Instructions of Bombardier 
Service Bulletin 601R-27-162, including Appendix A, dated April 5, 
2013.
    (2) If any other damage (i.e., corrosion or cracking), other 
than that specified in paragraph (j)(1) of this AD, is found during 
any inspection required by paragraph (g) or (i) of this AD, before 
further flight, repair using a method approved by either the 
Manager, New York Aircraft Certification Office (ACO), ANE-170, FAA; 
or Transport Canada Civil Aviation (TCCA) (or its delegated agent).

(k) Optional Terminating Action

    Replacement of both pilot-side rudder bar assemblies, in 
accordance with the Accomplishment Instructions of Bombardier 
Service Bulletin 601R-27-162, including Appendix A, dated April 5, 
2013, terminates the inspections required by paragraphs (g) and (i) 
of this AD.

(l) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York Aircraft Certification Office (ACO), ANE-170, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the ACO, send it to ATTN: Program Manager, Continuing 
Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 
410, Westbury, NY 11590; telephone 516-228-7300; fax 516-794-5531. 
Before using any approved AMOC, notify your appropriate principal 
inspector, or lacking a principal inspector, the manager of the 
local flight standards district office/certificate holding district 
office. The AMOC approval letter must specifically reference this 
AD.
    (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-approved if 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.

(m) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
Canadian Airworthiness Directive CF-2013-12, dated May 14, 2013, for 
related information, which can be found in the AD docket on the 
internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-
0700-0002.

(n) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Bombardier Service Bulletin 601R-27-162, including Appendix 
A, dated April 5, 2013.
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, 
Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-
7401; email thd.crj@aero.bombardier.com; Internet http://www.bombardier.com.
    (4) You may view this service information at the FAA, Transport 
Airplane Directorate,

[[Page 72001]]

1601 Lind Avenue SW., Renton, WA. For information on the 
availability of this material at the FAA, call 425-227-1221.
    (5) You may view this 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/cfr/ibr-locations.html.

    Issued in Renton, Washington, on November 15, 2013.
John Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-28104 Filed 11-29-13; 8:45 am]
BILLING CODE 4910-13-P