Airworthiness Directives; Bombardier, Inc. Airplanes, 24200-24207 [2015-07802]

Download as PDF 24200 Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations (j) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2014–16, dated June 11, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov/ #!documentDetail;D=FAA-2015-0074-0003. (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) Bombardier Temporary Revision ALI– 0472, dated February 27, 2014, to Section 1– 32 of Part 2, Airworthiness Limitations, of the Bombardier CRJ Series Regional Jet Maintenance Requirements Manual, CSP B– 053. (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, 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 April 14, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–09813 Filed 4–29–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0491; Directorate Identifier 2014–NM–023–AD; Amendment 39–18130; AD 2015–07–02] rmajette on DSK2VPTVN1PROD with RULES RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: VerDate Sep<11>2014 14:33 Apr 29, 2015 Jkt 235001 We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL–600–1A11 (CL–600), CL–600–2A12 (CL–601), and CL–600–2B16 (CL–601–3A, CL–601–3R, and CL–604 Variants) airplanes. This AD was prompted by a determination that the forward lugs of the flap hinge box might not conform to engineering drawings, which could result in premature fatigue cracking. This AD requires revising the maintenance or inspection program to include new airworthiness limitations tasks; and measuring the forward lug edge distance of each flap hinge box, inspecting for cracking and damage (i.e., deformation or bearing failure) of the forward lug edge of each flap hinge box, and repairing any cracking or damage if necessary. We are issuing this AD to detect and correct non-conforming flap hinge box forward lugs, which could result in failure of the lugs and detachment of the flap hinge box and consequent detachment of the flap surface. DATES: This AD becomes effective June 4, 2015. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of June 4, 2015. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2014-0491 or in person at the Docket 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. 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. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0491. FOR FURTHER INFORMATION CONTACT: Ricardo Garcia, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7331; fax 516–794–5531. SUMMARY: PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Bombardier, Inc. Model CL–600–1A11 (CL–600), CL–600–2A12 (CL–601), and CL–600–2B16 (CL–601– 3A, CL–601–3R, and CL–604 Variants) airplanes. The NPRM published in the Federal Register on August 4, 2014 (79 FR 45140). The NPRM was prompted by a determination that the forward lugs of the flap hinge box might not conform to engineering drawings, which could result in premature fatigue cracking. The NPRM proposed to require revising the maintenance or inspection program to include new airworthiness limitations tasks; and measuring the forward lug edge distance of each flap hinge box, inspecting for cracking and damage (i.e., deformation or bearing failure) of the forward lug edge of each flap hinge box, and repairing any cracking or damage if necessary. We are issuing this AD to detect and correct non-conforming flap hinge box forward lugs, which could result in failure of the lugs and detachment of the flap hinge box and consequent detachment of the flap surface. Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2014–01, dated January 3, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Bombardier, Inc. Model CL– 600–1A11 (CL–600), CL–600–2A12 (CL– 601), and CL–600–2B16 (CL–601–3A, CL–601–3R, and CL–604 Variants) airplanes. The MCAI states: The aeroplane manufacturer has determined that the flap hinge box forward lugs edge distance may not conform to the engineering drawings. Non-conforming flap hinge box forward lugs may result in premature fatigue cracking. Failure of the lugs could lead to the detachment of the flap hinge box and consequently the detachment of the flap surface. The loss of a flap surface could adversely affect the continued safe operation of the aeroplane. This [Canadian] AD mandates the incorporation of new Time Limits/ Maintenance Checks (TLMC) Airworthiness Limitations (AWL) tasks, and the measurement [and inspection for cracking and damage] of the forward lug edge distance of each flap hinge-box and rectification as required. Corrective actions include repairing damage and cracking. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/ E:\FR\FM\30APR1.SGM 30APR1 Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations #!documentDetail;D=FAA-2014-04910002. Explanation of Additional Change Made to This Final Rule Comments We have removed Note 1 to paragraph (g) from this final rule. Instead, we have included that information in paragraph (g) of this AD. We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (79 FR 45140, August 4, 2014) and the FAA’s response to each comment. Request To Include Latest Revision of Service Information Bombardier, Inc. requested that we revise the NPRM (79 FR 45140, August 4, 2014) to reflect the latest revisions of certain service information. We agree to include the latest revisions of certain service information. Bombardier has issued Service Bulletin 604–57–007, Revision 01, dated November 12, 2014 (for Model CL–600– 2B16 airplanes); and Service Bulletin 605–57–005, Revision 01, dated November 12, 2014 (for Model CL–600– 2B16 airplanes). This new service information does not add new work for the affected airplanes and was revised to update labor hours needed to perform the work and clarify work instructions. We have changed this AD to reference Bombardier Service Bulletin 604–57– 007, Revision 01, dated November 12, 2014; and Bombardier Service Bulletin 605–57–005, Revision 01, dated November 12, 2014, throughout. We have also added a new paragraph (k) to this AD to give credit for actions performed before the effective date of this AD using Bombardier Service Bulletin 604–57–007, dated September 26, 2013; and Bombardier Service Bulletin 605–57–005, dated September 26, 2013. We redesignated subsequent paragraphs accordingly. rmajette on DSK2VPTVN1PROD with RULES Request To Correct Typographical Errors Bombardier, Inc., and an FAA airframe and powerplant mechanic noted typographical errors in Table 1 of the NPRM (79 FR 45140, August 4, 2014) and requested they be corrected. We agree that there are typographical errors. We have revised table 1 to paragraph (g) of this AD. The temporary revision (TR) number has been corrected to read ‘‘5–275,’’ in certain rows of table 1 to paragraph (g) of this AD, where in the NPRM (79 FR 45140, August 4, 2014) the previous TR number read ‘‘5– 276.’’ The revision of Bombardier CL– 604 Time Limits/Maintenance Checks Manual, dated July 8, 2013, was corrected from revision ‘‘8’’ to revision ‘‘20.’’ VerDate Sep<11>2014 14:33 Apr 29, 2015 Jkt 235001 Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (79 FR 45140, August 4, 2014) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 45140, August 4, 2014). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 Bombardier has issued the following service information. • Bombardier Service Bulletin 600– 0762, dated September 26, 2013. This service information describes procedures for measuring the edge-toedge distance of the forward lugs for the flap hinge boxes and contacting the manufacturer for corrective actions for Bombardier, Inc. Model CL–600–1A11 (CL–600) airplanes. Bombardier Service Bulletin 601– 0631, dated September 26, 2013. This service information describes procedures for measuring the edge-toedge distance of the forward lugs for the flap hinge boxes and contacting the manufacturer for corrective actions for Bombardier, Inc. Model CL–600–2A12 (CL–601 Variant) and CL–600–2B16 (CL–601–3A and –3R Variant) airplanes. • Bombardier Service Bulletin 604– 57–007, Revision 01, dated November 12, 2014. This service information describes procedures for measuring the edge-to-edge distance of the forward lugs for the flap hinge boxes and contacting the manufacturer for corrective actions for Bombardier, Inc. Model CL–600–2B16 (CL–604 Variant) airplanes having serial numbers (S/Ns) 5301 through 5665 inclusive. • Bombardier Service Bulletin 605– 57–005, Revision 01, dated November 12, 2014. This service information describes procedures for measuring the edge-to-edge distance of the forward lugs for the flap hinge boxes and PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 24201 contacting the manufacturer for corrective actions for Bombardier, Inc. Model CL–600–2B16 (CL–604 Variant) airplanes having S/Ns 5701 through 5953 inclusive. • Canadair Challenger Temporary Revision 5–157, dated July 8, 2013, to Outboard Flap—Hinge Box Forward Lugs, to Canadair Challenger Time Limits/Maintenance Checks Manual, PSP 605. This service information describes an airworthiness limitations task and compliance times for inspecting the forward lugs of the outboard flap hinge box for Bombardier, Inc. Model CL–600–1A11 (CL–600) airplanes. Canadair Challenger Temporary Revision 5–158, Inboard Flap—Hinge Box Forward Lugs, dated July 8, 2013, to Canadair Challenger Time Limits/ Maintenance Checks Manual, PSP 605. This service information describes an airworthiness limitations task and compliance times for inspecting the forward lugs of the inboard flap hinge box for Bombardier, Inc. Model CL– 600–1A11 (CL–600) airplanes. • Canadair Challenger Temporary Revision 5–262, Outboard and Inboard Flap—Hinge Box Forward Lugs, dated July 8, 2013, to Canadian Challenger Time Limits/Maintenance Checks Manual PSP 601. This service information describes airworthiness limitations tasks and compliance times for inspecting the forward lugs of the outboard and inboard flap hinge boxes for Bombardier, Inc. Model CL–600– 2A12 (CL–601) airplanes. • Canadair Challenger Temporary Revision 5–275, Outboard Flap—Hinge Box Forward Lugs, dated July 8, 2013, to Canadian Challenger Time Limits/ Maintenance Checks Manual PSP 601A–5. This service information describes an airworthiness limitations task and compliance times for inspecting the forward lugs of the outboard flap hinge box for Bombardier, Inc. Model CL–600–2B16 (CL–601–3A Variants) airplanes. • Canadair Challenger Temporary Revision 5–276, Inboard Flap—Hinge Box Forward Lugs, dated July 8, 2013, to Canadian Challenger Time Limits/ Maintenance Checks Manual PSP 601A–5. This service information describes an airworthiness limitations task and compliance times for inspecting the forward lugs of the inboard flap hinge box for Bombardier, Inc. Model CL–600–2B16 (CL–601–3A and CL–601–3R Variant) airplanes. • Task 57–50–00–121, Special Detailed Inspection of the Forward Lugs of the Inboard Flap Hinge Box, of Section 5–10–30 of Part 2, ‘‘Airworthiness Limitations,’’ of E:\FR\FM\30APR1.SGM 30APR1 24202 Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations Bombardier CL–605 Time Limits/ Maintenance Checks Manual, Revision 8, dated July 8, 2013. This service information describes an airworthiness limitations task and compliance times for inspecting the forward lugs of the inboard flap hinge box for Bombardier, Inc. Model CL–600–2B16 (CL–604 Variant) airplanes, having S/Ns 5701 through 5953 inclusive. • Task 57–50–00–121, Special Detailed Inspection of the Forward Lugs of the Inboard Flap Hinge Box, of Section 5–10–30 of Part 2, ‘‘Airworthiness Limitations,’’ of Bombardier CL–604 Time Limits/ Maintenance Checks Manual, Revision 20, dated July 8, 2013. This service information describes an airworthiness limitations task and compliance times for inspecting the forward lugs of the inboard flap hinge box of Bombardier, Inc. Model CL–600–2B16 (CL–604 Variant) airplanes, having S/Ns 5301 through 5665 inclusive. • Task 57–52–01–102, Special Detailed Inspection of the Hinge—Box Forward Lugs of the Outboard Flap, of Section 5–10–30 of Part 2, ‘‘Airworthiness Limitations,’’ of Bombardier CL–605 Time Limits/ Maintenance Checks Manual, Revision 8, dated July 8, 2013. This service information describes an airworthiness limitations task and compliance times for inspecting the forward lugs of the outboard flap hinge box of Bombardier, Inc. Model CL–600–2B16 (CL–604 Variant) airplanes, having S/Ns 5701 through 5953 inclusive. • Task 57–52–01–102, Special Detailed Inspection of the Hinge—Box Forward Lugs of the Outboard Flap, of Section 5–10–30 of Part 2, ‘‘Airworthiness Limitations,’’ of Bombardier CL–604 Time Limits/ Maintenance Checks Manual, Revision 20, dated July 8, 2013. This service information describes an airworthiness limitations task and compliance times for inspecting the forward lugs of the outboard flap hinge box of Bombardier, Inc. Model CL–600–2B16 (CL–604 Variant) airplanes, having S/Ns 5301 through 5665 inclusive. This service information is reasonably available; see ADDRESSES for ways to access this service information. rmajette on DSK2VPTVN1PROD with RULES Costs of Compliance We estimate that this AD affects 105 airplanes of U.S. registry. We also estimate that it will take about 45 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. VerDate Sep<11>2014 14:33 Apr 29, 2015 Jkt 235001 operators to be $401,625, or $3,825 per product. We have received no definitive data that would enable us to provide cost estimates for the cost of parts or oncondition actions specified in this AD. 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-2014-0491; 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 street address for the PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 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. 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 airworthiness directive (AD): ■ 2015–07–02 Bombardier, Inc.: Amendment 39–18130. Docket No. FAA–2014–0491; Directorate Identifier 2014–NM–023–AD. (a) Effective Date This AD becomes effective June 4, 2015. (b) Affected ADs None. (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category. (1) Bombardier, Inc. Model CL–600–1A11 (CL–600) airplanes, serial numbers 1004 through 1085 inclusive. (2) Bombardier, Inc. Model CL–600–2A12 (CL–601) airplanes, serial numbers 3001 through 3066 inclusive. (3) Bombardier, Inc. Model CL–600–2B16 (CL–601–3A and CL–601–3R Variants) airplanes, serial numbers 5001 through 5194 inclusive. (4) Bombardier, Inc. Model CL–600–2B16 (CL–604 Variants) airplanes, serial numbers 5301 through 5665 inclusive, and 5701 through 5953 inclusive. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by a determination that the forward lugs of the flap hinge box might not conform to engineering drawings, which could result in premature fatigue cracking. We are issuing this AD to detect and correct non-conforming flap hinge box forward lugs, which could result in failure of the lugs and detachment of the flap hinge box and consequent detachment of the flap surface. E:\FR\FM\30APR1.SGM 30APR1 Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Maintenance or Inspection Program Revision Within 60 days after the effective date of this AD, revise the maintenance or inspection program, as applicable, by incorporating the applicable airworthiness limitation (AWL) tasks as specified in table 1 to this paragraph. The initial compliance time for doing the task is at the applicable times specified in table 1 to this paragraph. For the incorporation of tasks specified in the temporary revisions (TRs) specified in table 1 to this paragraph of this AD that are a part of the maintenance or inspection program revision required by this paragraph, such incorporation may be done by inserting a copy of the applicable TRs specified in table 24203 1 to this paragraph into the applicable ‘‘time limits/maintenance checks’’ (TLMC) manuals specified in table 1 to this paragraph. When the applicable TRs specified in table 1 to this paragraph have been included in general revisions of the applicable TLMC manual specified in table 1 to this paragraph, the general revisions may be inserted in the applicable TLMC manual specified in table 1 to this paragraph. TABLE 1 TO PARAGRAPH (g) OF THIS AD—TASKS Affected airplanes Task No. Canadair service information Initial compliance time 57–40–00–186 Canadair Challenger TR 5–158, Inboard Flap—Hinge Box Forward Lugs, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 605. Within 500 flight cycles after the effective date of this AD, but not later than 15,100 total flight cycles. 57–40–00–186 57–40–00–186 Model CL–600–1A11 (CL–600 Variant) airplanes with outboard flaps having greater than 7,500 total flight cycles, but equal to or less than 11,350 total flight cycles as of the effective date of this AD. Model CL–600–1A11 (CL–600 Variant) airplanes with outboard flaps having greater than 11,350 total flight cycles as of the effective date of this AD. 57–40–00–160 Canadair Challenger TR 5–158, Inboard Flap—Hinge Box Forward Lugs, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 605. Canadair Challenger TR 5–158, Inboard Flap—Hinge Box Forward Lugs, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 605. Canadair Challenger TR 5–157, Outboard Flap—Hinge Box Forward Lugs, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 605. Within 250 flight cycles after the effective date of this AD. Model CL–600–1A11 (CL–600 Variant) airplanes with inboard flaps having equal to or less than 7,400 total flight cycles. 57–40–00–160 Model CL–600–2A12 (CL–601 Variant) airplanes with inboard flaps having greater than 7,400 total flight cycles, but equal to or less than 14,850 total flight cycles, as of the effective date of this AD. Model CL–600–2A12 (CL–601 Variant) airplanes with inboard flaps with greater than 14,850 total flight cycles as of the effective date of this AD. 57–40–01–101 Canadair Challenger TR 5–157, Outboard Flap—Hinge Box Forward Lugs, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 605. Canadair Challenger TR 5–157, Outboard Flap—Hinge Box Forward Lugs, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 605. Canadair Challenger TR 5–262, Inboard Flap—Hinge Box Forward Lugs, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601–5. Within 250 flight cycles after the effective date of this AD. Model CL–600–1A11 (CL–600 Variant) airplanes with outboard flaps having equal to or less than 7,500 total flight cycles. rmajette on DSK2VPTVN1PROD with RULES Model CL–600–1A11 (CL–600 Variant) airplanes with inboard flaps having greater than 7,400 total flight cycles but equal to or less than 14,850 total flight cycles as of the effective date of this AD. Model CL–600–1A11 (CL–600 Variant) airplanes with inboard flaps having greater than 14,850 total flight cycles as of the effective date of this AD. Within 250 flight cycles after the effective date of this AD. Model CL–600–2A12 (CL–601 Variant) airplanes with inboard flaps with equal to or less than 7,400 total flight cycles as of the effective date of this AD. Model CL–600–2A12 (CL–601 Variant) airplanes with outboard flaps with greater than 7,500 total flight cycles but equal to or less than 11,350 total flight cycles as of the effective date of this AD. Model CL–600–2A12 (CL–601 Variant) airplanes with outboard flaps having greater than 11,350 total flight cycles as of the effective date of this AD. 57–40–01–101 Canadair Challenger TR 5–262, Inboard Flap—Hinge Box Forward Lugs, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601–5. Canadair Challenger TR 5–262, Inboard Flap—Hinge Box Forward Lugs, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601–5. Canadair Challenger TR 5–262, Outboard Flap—Hinge Box Forward Lugs, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601–5. Canadair Challenger TR 5–262, Outboard Flap—Hinge Box Forward Lugs, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601–5. Within 250 flight cycles after the effective date of this AD. VerDate Sep<11>2014 14:33 Apr 29, 2015 Jkt 235001 57–40–00–160 57–40–01–101 57–40–00–175 57–40–00–175 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 E:\FR\FM\30APR1.SGM Before the accumulation of 7,900 total flight cycles. Within 500 flight cycles after the effective date of this AD, but no later than 11,600 total flight cycles. Before the accumulation of 8,000 total flight cycles. Within 500 flight cycles after the effective date of this AD, but no later than 15,100 total flight cycles. Before the accumulation of 7,900 total flight cycles. Within 500 flight cycles after the effective date of this AD, but not later than 11,600 total flight cycles. 30APR1 24204 Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations TABLE 1 TO PARAGRAPH (g) OF THIS AD—TASKS—Continued Affected airplanes Task No. Model CL–600–2A12 (CL–601 Variant) airplanes with outboard flaps having equal to or less than 7,500 total flight cycles as of the effective date of this AD. Model CL–600–2B16 (CL–601–3A and –3R Variant) airplanes having S/Ns 5001 through 5194 inclusive with inboard flaps having greater than 7,400 total flight cycles but equal to or less than 14,850 total flight cycles as of the effective date of this AD. Model CL–600–2B16 (CL–601–3A and –3R Variant) airplanes having S/Ns 5001 through 5194 inclusive, with inboard flaps having greater than 14,850 total flight cycles as of the effective date of this AD. Model CL–600–2B16 (CL–601–3A and –3R Variant) airplanes having S/Ns 5001 through 5194 inclusive, with inboard flaps having equal to or less than 7,400 total flight cycles as of the effective date of this AD. Model CL–600–2B16 (CL–601–3A and –3R Variant) airplanes having S/Ns 5001 through 5194 inclusive, with outboard flaps having greater than 7,500 total flight cycles but equal to or less than 11,350 total flight cycles as of the effective date of this AD. Model CL–600–2B16 (CL–601–3A and –3R Variant) airplanes having S/Ns 5001 through 5194 inclusive, with outboard flaps having greater than 11,350 total flight cycles as of the effective date of this AD. Model CL–600–2B16 (CL–601–3A and –3R Variant) airplanes having S/Ns 5001 through 5194 inclusive, with outboard flaps having equal to or less than 7,500 total flight cycles as of the effective date of this AD. Model CL–600–2B16 (CL–604 Variant) airplanes having S/Ns 5301 through 5665 inclusive, with inboard flaps. Canadair service information Initial compliance time Canadair Challenger TR 5–262, Outboard Flap—Hinge Box Forward Lugs, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601–5. Canadair Challenger TR 5–276, Inboard Flap—Hinge Box Forward Lugs, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601A–5. Before the accumulation of 8,000 total flight cycles. 57–40–01–101 Canadair Challenger TR 5–276, Inboard Flap—Hinge Box Forward Lugs, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601A–5. Within 250 flight cycles. 57–40–01–101 Canadair Challenger TR 5–276, Inboard Flap—Hinge Box Forward Lugs, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601A–5. Before the accumulation of 7,900 total flight cycles. 57–40–00–174 Canadair Challenger TR 5–275, Outboard Flap—Hinge Box Forward Lugs, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601A–5. Within 500 flight cycles after the effective date of this AD, but no later than 11,600 total flight cycles. 57–40–00–174 Canadair Challenger TR 5–275, Outboard Flap—Hinge Box Forward Lugs, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601A–5. Within 250 flight cycles after the effective date of this AD. 57–40–00–174 Canadair Challenger TR 5–275, Outboard Flap—Hinge Box Forward Lugs, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601A–5. Before the accumulation of 8,000 total flight cycles. 57–50–00–121 Section 5–10–30, Special Detailed Inspection of the Forward Lugs of the Inboard Flap Hinge Box, of Part 2, Airworthiness Limitations, of Bombardier CL–604 TLMC Manual, Revision 20, dated July 8, 2013. Section 5–10–30, Special Detailed Inspection of the Hinge—Box Forward Lugs of the Outboard Flap, of Part 2, Airworthiness Limitations, of Bombardier CL–604 TLMC Manual, Revision 20, dated July 8, 2013. Section 5–10–30, Special Detailed Inspection of the Forward Lugs of the Inboard Flap Hinge Box, of Part 2, Airworthiness Limitations, of Bombardier CL–605 TLMC Manual, Revision 8, dated July 8, 2013. Section 5–10–30, Special Detailed Inspection of the Hinge—Box Forward Lugs of the Outboard Flap, of Part 2, Airworthiness Limitations, of Bombardier CL–605 TLMC Manual, Revision 8, dated July 8, 2013. Before the accumulation of 7,800 total flight cycles, or within 500 flight cycles after the effective date of this AD, whichever occurs later. 57–40–00–175 57–40–01–101 57–52–01–102 Model CL–600–2B16 (CL–604 Variant) airplanes, S/Ns 5701 through 5953 inclusive. rmajette on DSK2VPTVN1PROD with RULES Model CL–600–2B16 (CL–604 Variant) airplanes, S/Ns 5301 through 5665 inclusive. 57–50–00–121 Model CL–600–2B16 (CL–604 Variant) airplanes, S/Ns 5701 through 5953 inclusive. 57–52–01–102 VerDate Sep<11>2014 14:33 Apr 29, 2015 Jkt 235001 PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 E:\FR\FM\30APR1.SGM Within 500 flight cycles after the effective date of this AD, but not later than 15,100 total flight cycles. Before the accumulation of 7,800 total flight cycles, or within 500 flight cycles after the effective date of this AD, whichever occurs later. Before the accumulation of 7,800 total flight cycles, or within 500 flight cycles after the effective date of this AD, whichever occurs later. Before the accumulation of 7,800 total flight cycles, or within 500 flight cycles after the effective date of this AD, whichever occurs later. 30APR1 Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations (h) Lug Edge Measurement and Inspection At the applicable times specified in table 2 to this paragraph and paragraph (i)(1) of this AD, measure the forward lug edge distance of all flap hinge boxes, and do a general visual inspection for cracking and damage (i.e., deformation or bearing failure) 24205 of the forward lug edge of all flap hinge boxes, in accordance with the applicable service bulletin specified in table 2 to this paragraph and paragraph (i)(1) of this AD. TABLE 2 TO PARAGRAPHS (h) AND (i)(1) OF THIS AD—COMPLIANCE TIMES FOR LUG EDGE MEASUREMENT AND INSPECTION Airplane models Affected flaps Compliance time Service information Model CL–600–1A11 (CL–600) airplanes having S/N 1004 through 1085 inclusive. Inboard flaps having less than or equal to 7,400 total flight cycles as of the effective date of this AD. Bombardier Service Bulletin 600– 0762, dated September 26, 2013. Model CL–600–1A11 (CL–600) airplanes having S/N 1004 through 1085 inclusive. Inboard flaps having greater than 7,400 total flight cycles, but equal to or less than 14,850 total flight cycles as of the effective date of this AD. Model CL–600–1A11 (CL–600) airplanes having S/N 1004 through 1085 inclusive. Inboard flaps having greater than 14,850 total flight cycles as of the effective date of this AD. Model CL–600–1A11 (CL–600) airplanes having S/N 1004 through 1085 inclusive. Outboard flaps having equal to or less than 7,500 total flight cycles as of the effective date of this AD. Model CL–600–1A11 (CL–600) airplanes having S/N 1004 through 1085 inclusive. Outboard flaps having greater than 7,500 total flight cycles but less than or equal to 11,350 total flight cycles as of the effective date of this AD. Outboard flaps having greater than 11,350 total flight cycles as of the effective date of this AD. Inboard flaps having less than or equal to 7,400 total flight cycles as of the effective date of this AD. Before the accumulation of 7,900 total flight cycles, or within 48 months after the effective date of this AD, whichever occurs first. Before the accumulation of 15,100 total flight cycles, or within 500 flight cycles or 48 months after the effective date of this AD, whichever occurs first. Within 250 flight cycles or 48 months after the effective date of this AD, whichever occurs first. Before the accumulation of 8,000 total flight cycles, or within 48 months after the effective date of this AD, whichever occurs first. Within 500 flight cycles or 48 months after the effective date of this AD, whichever occurs first; but not exceeding 11,600 total flight cycles. Within 250 flight cycles or within 48 months after the effective date of this AD, whichever occurs first. Before the accumulation of 7,900 total flight cycles, or within 48 months after the effective date of this AD, whichever occurs first. Inboard flaps having greater than 7,400 total flight cycles, but equal to or less than 14,850 total flight cycles, as of the effective date of this AD. Within 500 flight cycles or within 48 months after the effective date of this AD, whichever occurs first; but not exceeding 15,100 total flight cycles. Bombardier Service Bulletin 601– 0631, dated September 26, 2013. Inboard flaps having greater than 14,850 total flight cycles as of the effective date of this AD. Within 250 flight cycles or within 48 months after the effective date of this AD, whichever occurs first. Bombardier Service Bulletin 601– 0631, dated September 26, 2013. Outboard flaps having less than or equal to 7,500 total flight cycles as of the effective date of this AD. Before the accumulation of 8,000 total flight cycles, or within 48 months after the effective date of this AD, whichever occurs first. Bombardier Service Bulletin 601– 0631, dated September 26, 2013. Outboard flaps having greater than 7,500 total flight cycles, but equal to or less than 11,350 total flight cycles, as of the effective date of this AD. Within 500 flight cycles or within 48 months after the effective date of this AD; but not exceeding 11,600 total flight cycles. Bombardier Service Bulletin 601– 0631, dated September 26, 2013. Outboard flaps having greater than 11,350 total flight cycles as of the effective date of this AD. Within 250 flight cycles or 48 months after the effective date of this AD, whichever occurs first. Bombardier Service Bulletin 601– 0631, dated September 26, 2013. rmajette on DSK2VPTVN1PROD with RULES Model CL–600–1A11 (CL–600) airplanes having S/N 1004 through 1085 inclusive. Model CL–600–2A12 (CL–601 Variant) and CL–600–2B16 (CL– 601–3A and –3R Variants) airplanes having S/N 3001 through 3066 inclusive, and 5001 through 5194 inclusive. Model CL–600–2A12 (CL–601 Variant) and CL–600–2B16 (CL– 601–3A and –3R Variant) airplanes having S/N 3001 through 3066 inclusive, and 5001 through 5194 inclusive. Model CL–600–2A12 (CL–601 Variant) and CL–600–2B16 (CL– 601–3A and –3R Variant) airplanes having S/N 3001 through 3066 inclusive, and 5001 through 5194 inclusive. Model CL–600–2A12 (CL–601 Variant) and CL–600–2B16 (CL– 601–3A and –3R Variant) airplanes having S/N 3001 through 3066 inclusive, and 5001 through 5194 inclusive. Model CL–600–2A12 (CL–601 Variant) and CL–600–2B16 (CL– 601–3A and –3R Variant) airplanes having S/N 3001 through 3066 inclusive, and 5001 through 5194 inclusive. Model CL–600–2A12 (CL–601 Variant) and CL–600–2B16 (CL– 601–3A and –3R Variant) airplanes having S/N 3001 through 3066 inclusive, and 5001 through 5194 inclusive. VerDate Sep<11>2014 14:33 Apr 29, 2015 Jkt 235001 PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 E:\FR\FM\30APR1.SGM Bombardier Service Bulletin 600– 0762, dated September 26, 2013. Bombardier Service Bulletin 600– 0762, dated September 26, 2013. Bombardier Service Bulletin 600– 0762, dated September 26, 2013. Bombardier Service Bulletin 600– 0762, dated September 26, 2013. Bombardier Service Bulletin 600– 0762, dated September 26, 2013. Bombardier Service Bulletin 601– 0631, dated September 26, 2013. 30APR1 24206 Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations TABLE 2 TO PARAGRAPHS (h) AND (i)(1) OF THIS AD—COMPLIANCE TIMES FOR LUG EDGE MEASUREMENT AND INSPECTION—Continued Airplane models Affected flaps Compliance time Service information Model CL–600–2B16 (CL–604 Variant) airplanes having S/Ns 5301 through 5665 inclusive. Outboard and inboard flaps .......... Bombardier Service Bulletin 604– 57–007, Revision 01, dated November 12, 2014. Model CL–600–2B16 (CL–604 Variant) airplanes having S/Ns 5701 through 5953 inclusive. Outboard and inboard flaps .......... Before the accumulation of 7,800 total flight cycles or within 48 months after the effective date of this AD, whichever occurs first. Before the accumulation of 7,800 total flight cycles or within 48 months after the effective date of this AD, whichever occurs first. (i) Corrective Actions (1) If, during the measurement required by paragraph (h) of this AD, the lug edge distance is equal to or greater than the limit specified in the applicable service bulletin specified in table 2 to paragraph (h) of this AD and this paragraph, no further action is required by this paragraph. (2) If, during the measurement required by paragraph (h) of this AD, the lug edge distance is below the limit specified in the applicable service bulletin specified in table 2 to paragraphs (h) and (i)(1) of this AD, before further flight, repair using a method approved by the Manager, New York ACO, ANE–170, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.’s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. (3) If, during the inspection required by paragraph (h) of this AD, any cracking or damage is found, before further flight, repair using a method approved by the Manager, New York ACO, ANE–170, FAA; or TCCA; or Bombardier, Inc.’s TCCA DAO. If approved by the DAO, the approval must include the DAO-authorized signature. (j) No Alternative Actions or Intervals After accomplishing the revision required by paragraph (g) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance in accordance with the procedures specified in paragraph (l) of this AD. rmajette on DSK2VPTVN1PROD with RULES (k) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 604–57–007, dated September 26, 2013 (for Model CL–600–2B16 airplanes); or Bombardier Service Bulletin 605–57–005, dated September 26, 2013 (for Model CL–600–2B16 airplanes); which are not incorporated by reference in 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 ACO, ANE–170, FAA, has the authority to approve AMOCs for this AD, if requested using the VerDate Sep<11>2014 14:33 Apr 29, 2015 Jkt 235001 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) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, New York ACO, ANE–170, Engine and Propeller Directorate, FAA; or TCCA; or Bombardier, Inc.’s TCCA DAO. If approved by the DAO, the approval must include the DAO-authorized signature. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2014–01, dated January 3, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov/ #!documentDetail;D=FAA-2014-0491-0004. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (n)(3) and (n)(4) of this AD. (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 this AD specifies otherwise. (i) Bombardier Service Bulletin 600–0762, dated September 26, 2013. (ii) Bombardier Service Bulletin 601–0631, dated September 26, 2013. (iii) Bombardier Service Bulletin 604–57– 007, Revision 01, dated November 12, 2014. (iv) Bombardier Service Bulletin 605–57– 005, Revision 01, dated November 12, 2014. (v) Canadair Challenger Temporary Revision 5–157, Outboard Flap—Hinge Box PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 Bombardier Service Bulletin 605– 57–005, Revision 01, dated November 12, 2014. Forward Lugs, dated July 8, 2013, to Canadair Challenger Time Limits/Maintenance Checks Manual, PSP 605. (vi) Canadair Challenger Temporary Revision 5–158, Inboard Flap—Hinge Box Forward Lugs, dated July 8, 2013, to Canadair Challenger Time Limits/Maintenance Checks Manual, PSP 605. (vii) Canadair Challenger Temporary Revision 5–262, Outboard and Inboard Flap—Hinge Box Forward Lugs, dated July 8, 2013, to Canadian Challenger Time Limits/ Maintenance Checks Manual PSP 601. (viii) Canadair Challenger Temporary Revision 5–275, Outboard Flap—Hinge Box Forward Lugs, dated July 8, 2013, to Canadian Challenger Time Limits/ Maintenance Checks Manual PSP 601A–5. (ix) Canadair Challenger Temporary Revision 5–276, Inboard Flap—Hinge Box Forward Lugs, dated July 8, 2013, to Canadian Challenger Time Limits/ Maintenance Checks Manual PSP 601A–5. (x) Task 57–50–00–121 Special Detailed Inspection of the Forward Lugs of the Inboard Flap Hinge Box of Section 5–10–30 of Part 2, ‘‘Airworthiness Limitations,’’ of Bombardier CL–605 Time Limits/ Maintenance Checks Manual, Revision 8, dated July 8, 2013. (xi) Task 57–50–00–121 Special Detailed Inspection of the Forward Lugs of the Inboard Flap Hinge Box of Section 5–10–30 of Part 2, ‘‘Airworthiness Limitations,’’ of Bombardier CL–604 Time Limits/ Maintenance Checks Manual, Revision 20, dated July 8, 2013. (xii) Task 57–52–01–102 Special Detailed Inspection of the Hinge—Box Forward Lugs of the Outboard Flap of Section 5–10–30 of Part 2, ‘‘Airworthiness Limitations,’’ of Bombardier CL–605 Time Limits/ Maintenance Checks Manual, Revision 8, dated July 8, 2013. (xiii) Task 57–52–01–102 Special Detailed Inspection of the Hinge—Box Forward Lugs of the Outboard Flap of Section 5–10–30 of Part 2, ‘‘Airworthiness Limitations,’’ of Bombardier CL–604 Time Limits/ Maintenance Checks Manual, Revision 20, dated July 8, 2013. (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. E:\FR\FM\30APR1.SGM 30APR1 Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations (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. Federal Aviation Administration #!docketDetail;D=FAA-2014-0589 or in person at the Docket 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. 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.airwortheas@airbus.com; Internet http:// www.airbus.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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2014–0589. 14 CFR Part 39 FOR FURTHER INFORMATION CONTACT: Issued in Renton, Washington, on March 25, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–07802 Filed 4–29–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. [Docket No. FAA–2014–0589; Directorate Identifier 2014–NM–069–AD; Amendment 39–18148; AD 2015–09–03] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes SUPPLEMENTARY INFORMATION: Discussion Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318–111 and –112 airplanes and Model A319, A320, and A321 series airplanes. This AD was prompted by reports of cracks on the forward corner fittings of engine pylon aft secondary structures. This AD requires repetitive inspections of certain forward corner fittings of the pylon aft secondary structures, and corrective actions if necessary. This AD also provides optional terminating action for the repetitive inspections. We are issuing this AD to detect and correct detachment of the lower fairing attachment and/or loss of the aft fixed fairing with the movable fairing from the airplane in flight, which could result in damage to the airplane. DATES: This AD becomes effective June 4, 2015. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of June 4, 2015. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov/ rmajette on DSK2VPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 14:33 Apr 29, 2015 Jkt 235001 We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Airbus Model A318– 111 and –112 airplanes and Model A319, A320, and A321 series airplanes. The NPRM published in the Federal Register on September 3, 2014 (79 FR 52267). The NPRM was prompted by reports of cracks on the forward corner fittings of engine pylon aft secondary structures. The NPRM proposed to require repetitive inspections of certain forward corner fittings of the pylon aft secondary structures, and corrective actions if necessary. The NPRM also proposed to provide optional terminating action for the repetitive inspections. We are issuing this AD to detect and correct detachment of the lower fairing attachment and/or loss of the aft fixed fairing with the movable fairing from the airplane in flight, which could result in damage to the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0064, dated March 14, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition. The MCAI states: PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 24207 Several operators of A320 family aeroplanes have reported finding cracks on the forward corner fittings of engine pylon aft secondary structures, on the lateral face (lateral panel side). In some cases, these cracks had propagated onto the forward face (Rib 11 side). Investigation results have highlighted that these cracks are initiated by stress corrosion. This condition, if not detected and corrected, could lead to loss (i.e. detachment from the aeroplane) of the lower fairing attachment at Rib 10, and/or loss of the aft fixed fairing with the movable fairing, possibly resulting in * * * [damage to the airplane]. For the reasons described above, this [EASA] AD requires repetitive detailed inspections (DI) of the right hand (RH) Part Number (P/N) D54530014201 and left hand (LH) P/N D54530014200 corner fittings of engine pylon aft secondary structures (premod 38067 or pre-Airbus Service Bulletin (SB) A320–54–1019) to detect cracks or deformation in the splicing area with corner fitting between Ribs 11–12 and, depending on findings, replacement of the corner fittings. This [EASA] AD also recognizes that replacement of the corner fittings with improved parts (as per Airbus SB A320–54– 1019) constitutes a terminating action for the repetitive DI required by this [EASA] AD. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2014-05890003. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (79 FR 52267, September 3, 2014) and the FAA’s response to each comment. Requests to Reference Revised Service Bulletins United Airlines and US Airways requested that we revise the NPRM (79 FR 52267, September 3, 2014) to reference Airbus Service Bulletin A320– 54–1019, Revision 02, dated April 15, 2014, in lieu of Airbus Service Bulletin A320–54–1019, Revision 01, dated April 10, 2008. United Airlines also requested that we revise the NPRM to reference Airbus Service Bulletin A320–54–1022, Revision 03, dated April 15, 2014, in lieu of Airbus Service Bulletin A320– 54–1022, Revision 02, dated July 12, 2013. We agree with the commenters’ requests to reference revised service bulletins. Airbus Service Bulletin A320– 54–1019, Revision 02, dated April 15, 2014, improves the test procedures, and Airbus Service Bulletin A320–54–1022, Revision 03, dated April 15, 2014, specifies that certain actions in the Accomplishment Instructions are E:\FR\FM\30APR1.SGM 30APR1

Agencies

[Federal Register Volume 80, Number 83 (Thursday, April 30, 2015)]
[Rules and Regulations]
[Pages 24200-24207]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-07802]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0491; Directorate Identifier 2014-NM-023-AD; 
Amendment 39-18130; AD 2015-07-02]
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-600-1A11 (CL-600), CL-600-2A12 (CL-601), and 
CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants) airplanes. This 
AD was prompted by a determination that the forward lugs of the flap 
hinge box might not conform to engineering drawings, which could result 
in premature fatigue cracking. This AD requires revising the 
maintenance or inspection program to include new airworthiness 
limitations tasks; and measuring the forward lug edge distance of each 
flap hinge box, inspecting for cracking and damage (i.e., deformation 
or bearing failure) of the forward lug edge of each flap hinge box, and 
repairing any cracking or damage if necessary. We are issuing this AD 
to detect and correct non-conforming flap hinge box forward lugs, which 
could result in failure of the lugs and detachment of the flap hinge 
box and consequent detachment of the flap surface.

DATES: This AD becomes effective June 4, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of June 4, 2015.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0491 or in person at the 
Docket 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.
    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. It 
is also available on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2014-0491.

FOR FURTHER INFORMATION CONTACT: Ricardo Garcia, Aerospace Engineer, 
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 
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 by adding an AD that would apply to certain Bombardier, Inc. 
Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-
601-3A, CL-601-3R, and CL-604 Variants) airplanes. The NPRM published 
in the Federal Register on August 4, 2014 (79 FR 45140). The NPRM was 
prompted by a determination that the forward lugs of the flap hinge box 
might not conform to engineering drawings, which could result in 
premature fatigue cracking. The NPRM proposed to require revising the 
maintenance or inspection program to include new airworthiness 
limitations tasks; and measuring the forward lug edge distance of each 
flap hinge box, inspecting for cracking and damage (i.e., deformation 
or bearing failure) of the forward lug edge of each flap hinge box, and 
repairing any cracking or damage if necessary. We are issuing this AD 
to detect and correct non-conforming flap hinge box forward lugs, which 
could result in failure of the lugs and detachment of the flap hinge 
box and consequent detachment of the flap surface.
    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian Airworthiness Directive CF-
2014-01, dated January 3, 2014 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for certain Bombardier, Inc. Model CL-600-1A11 (CL-
600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and 
CL-604 Variants) airplanes. The MCAI states:

    The aeroplane manufacturer has determined that the flap hinge 
box forward lugs edge distance may not conform to the engineering 
drawings. Non-conforming flap hinge box forward lugs may result in 
premature fatigue cracking.
    Failure of the lugs could lead to the detachment of the flap 
hinge box and consequently the detachment of the flap surface. The 
loss of a flap surface could adversely affect the continued safe 
operation of the aeroplane.
    This [Canadian] AD mandates the incorporation of new Time 
Limits/Maintenance Checks (TLMC) Airworthiness Limitations (AWL) 
tasks, and the measurement [and inspection for cracking and damage] 
of the forward lug edge distance of each flap hinge-box and 
rectification as required.

    Corrective actions include repairing damage and cracking. You may 
examine the MCAI in the AD docket on the Internet at http://
www.regulations.gov/

[[Page 24201]]

#!documentDetail;D=FAA-2014-0491-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (79 
FR 45140, August 4, 2014) and the FAA's response to each comment.

Request To Include Latest Revision of Service Information

    Bombardier, Inc. requested that we revise the NPRM (79 FR 45140, 
August 4, 2014) to reflect the latest revisions of certain service 
information.
    We agree to include the latest revisions of certain service 
information. Bombardier has issued Service Bulletin 604-57-007, 
Revision 01, dated November 12, 2014 (for Model CL-600-2B16 airplanes); 
and Service Bulletin 605-57-005, Revision 01, dated November 12, 2014 
(for Model CL-600-2B16 airplanes). This new service information does 
not add new work for the affected airplanes and was revised to update 
labor hours needed to perform the work and clarify work instructions. 
We have changed this AD to reference Bombardier Service Bulletin 604-
57-007, Revision 01, dated November 12, 2014; and Bombardier Service 
Bulletin 605-57-005, Revision 01, dated November 12, 2014, throughout. 
We have also added a new paragraph (k) to this AD to give credit for 
actions performed before the effective date of this AD using Bombardier 
Service Bulletin 604-57-007, dated September 26, 2013; and Bombardier 
Service Bulletin 605-57-005, dated September 26, 2013. We redesignated 
subsequent paragraphs accordingly.

Request To Correct Typographical Errors

    Bombardier, Inc., and an FAA airframe and powerplant mechanic noted 
typographical errors in Table 1 of the NPRM (79 FR 45140, August 4, 
2014) and requested they be corrected.
    We agree that there are typographical errors. We have revised table 
1 to paragraph (g) of this AD. The temporary revision (TR) number has 
been corrected to read ``5-275,'' in certain rows of table 1 to 
paragraph (g) of this AD, where in the NPRM (79 FR 45140, August 4, 
2014) the previous TR number read ``5-276.'' The revision of Bombardier 
CL-604 Time Limits/Maintenance Checks Manual, dated July 8, 2013, was 
corrected from revision ``8'' to revision ``20.''

 Explanation of Additional Change Made to This Final Rule

    We have removed Note 1 to paragraph (g) from this final rule. 
Instead, we have included that information in paragraph (g) of this AD.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (79 FR 45140, August 4, 2014) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 45140, August 4, 2014).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    Bombardier has issued the following service information.
     Bombardier Service Bulletin 600-0762, dated September 26, 
2013. This service information describes procedures for measuring the 
edge-to-edge distance of the forward lugs for the flap hinge boxes and 
contacting the manufacturer for corrective actions for Bombardier, Inc. 
Model CL-600-1A11 (CL-600) airplanes.
    Bombardier Service Bulletin 601-0631, dated September 26, 2013. 
This service information describes procedures for measuring the edge-
to-edge distance of the forward lugs for the flap hinge boxes and 
contacting the manufacturer for corrective actions for Bombardier, Inc. 
Model CL-600-2A12 (CL-601 Variant) and CL-600-2B16 (CL-601-3A and -3R 
Variant) airplanes.
     Bombardier Service Bulletin 604-57-007, Revision 01, dated 
November 12, 2014. This service information describes procedures for 
measuring the edge-to-edge distance of the forward lugs for the flap 
hinge boxes and contacting the manufacturer for corrective actions for 
Bombardier, Inc. Model CL-600-2B16 (CL-604 Variant) airplanes having 
serial numbers (S/Ns) 5301 through 5665 inclusive.
     Bombardier Service Bulletin 605-57-005, Revision 01, dated 
November 12, 2014. This service information describes procedures for 
measuring the edge-to-edge distance of the forward lugs for the flap 
hinge boxes and contacting the manufacturer for corrective actions for 
Bombardier, Inc. Model CL-600-2B16 (CL-604 Variant) airplanes having S/
Ns 5701 through 5953 inclusive.
     Canadair Challenger Temporary Revision 5-157, dated July 
8, 2013, to Outboard Flap--Hinge Box Forward Lugs, to Canadair 
Challenger Time Limits/Maintenance Checks Manual, PSP 605. This service 
information describes an airworthiness limitations task and compliance 
times for inspecting the forward lugs of the outboard flap hinge box 
for Bombardier, Inc. Model CL-600-1A11 (CL-600) airplanes.
    Canadair Challenger Temporary Revision 5-158, Inboard Flap--Hinge 
Box Forward Lugs, dated July 8, 2013, to Canadair Challenger Time 
Limits/Maintenance Checks Manual, PSP 605. This service information 
describes an airworthiness limitations task and compliance times for 
inspecting the forward lugs of the inboard flap hinge box for 
Bombardier, Inc. Model CL-600-1A11 (CL-600) airplanes.
     Canadair Challenger Temporary Revision 5-262, Outboard and 
Inboard Flap--Hinge Box Forward Lugs, dated July 8, 2013, to Canadian 
Challenger Time Limits/Maintenance Checks Manual PSP 601. This service 
information describes airworthiness limitations tasks and compliance 
times for inspecting the forward lugs of the outboard and inboard flap 
hinge boxes for Bombardier, Inc. Model CL-600-2A12 (CL-601) airplanes.
     Canadair Challenger Temporary Revision 5-275, Outboard 
Flap--Hinge Box Forward Lugs, dated July 8, 2013, to Canadian 
Challenger Time Limits/Maintenance Checks Manual PSP 601A-5. This 
service information describes an airworthiness limitations task and 
compliance times for inspecting the forward lugs of the outboard flap 
hinge box for Bombardier, Inc. Model CL-600-2B16 (CL-601-3A Variants) 
airplanes.
     Canadair Challenger Temporary Revision 5-276, Inboard 
Flap--Hinge Box Forward Lugs, dated July 8, 2013, to Canadian 
Challenger Time Limits/Maintenance Checks Manual PSP 601A-5. This 
service information describes an airworthiness limitations task and 
compliance times for inspecting the forward lugs of the inboard flap 
hinge box for Bombardier, Inc. Model CL-600-2B16 (CL-601-3A and CL-601-
3R Variant) airplanes.
     Task 57-50-00-121, Special Detailed Inspection of the 
Forward Lugs of the Inboard Flap Hinge Box, of Section 5-10-30 of Part 
2, ``Airworthiness Limitations,'' of

[[Page 24202]]

Bombardier CL-605 Time Limits/Maintenance Checks Manual, Revision 8, 
dated July 8, 2013. This service information describes an airworthiness 
limitations task and compliance times for inspecting the forward lugs 
of the inboard flap hinge box for Bombardier, Inc. Model CL-600-2B16 
(CL-604 Variant) airplanes, having S/Ns 5701 through 5953 inclusive.
     Task 57-50-00-121, Special Detailed Inspection of the 
Forward Lugs of the Inboard Flap Hinge Box, of Section 5-10-30 of Part 
2, ``Airworthiness Limitations,'' of Bombardier CL-604 Time Limits/
Maintenance Checks Manual, Revision 20, dated July 8, 2013. This 
service information describes an airworthiness limitations task and 
compliance times for inspecting the forward lugs of the inboard flap 
hinge box of Bombardier, Inc. Model CL-600-2B16 (CL-604 Variant) 
airplanes, having S/Ns 5301 through 5665 inclusive.
     Task 57-52-01-102, Special Detailed Inspection of the 
Hinge--Box Forward Lugs of the Outboard Flap, of Section 5-10-30 of 
Part 2, ``Airworthiness Limitations,'' of Bombardier CL-605 Time 
Limits/Maintenance Checks Manual, Revision 8, dated July 8, 2013. This 
service information describes an airworthiness limitations task and 
compliance times for inspecting the forward lugs of the outboard flap 
hinge box of Bombardier, Inc. Model CL-600-2B16 (CL-604 Variant) 
airplanes, having S/Ns 5701 through 5953 inclusive.
     Task 57-52-01-102, Special Detailed Inspection of the 
Hinge--Box Forward Lugs of the Outboard Flap, of Section 5-10-30 of 
Part 2, ``Airworthiness Limitations,'' of Bombardier CL-604 Time 
Limits/Maintenance Checks Manual, Revision 20, dated July 8, 2013. This 
service information describes an airworthiness limitations task and 
compliance times for inspecting the forward lugs of the outboard flap 
hinge box of Bombardier, Inc. Model CL-600-2B16 (CL-604 Variant) 
airplanes, having S/Ns 5301 through 5665 inclusive.
    This service information is reasonably available; see ADDRESSES for 
ways to access this service information.

Costs of Compliance

    We estimate that this AD affects 105 airplanes of U.S. registry.
    We also estimate that it will take about 45 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Based on these figures, we estimate the cost 
of this AD on U.S. operators to be $401,625, or $3,825 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the cost of parts or on-condition actions specified 
in this AD.

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-2014-0491; 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 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.

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 airworthiness 
directive (AD):

2015-07-02 Bombardier, Inc.: Amendment 39-18130. Docket No. FAA-
2014-0491; Directorate Identifier 2014-NM-023-AD.

(a) Effective Date

    This AD becomes effective June 4, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
through (c)(4) of this AD, certificated in any category.
    (1) Bombardier, Inc. Model CL-600-1A11 (CL-600) airplanes, 
serial numbers 1004 through 1085 inclusive.
    (2) Bombardier, Inc. Model CL-600-2A12 (CL-601) airplanes, 
serial numbers 3001 through 3066 inclusive.
    (3) Bombardier, Inc. Model CL-600-2B16 (CL-601-3A and CL-601-3R 
Variants) airplanes, serial numbers 5001 through 5194 inclusive.
    (4) Bombardier, Inc. Model CL-600-2B16 (CL-604 Variants) 
airplanes, serial numbers 5301 through 5665 inclusive, and 5701 
through 5953 inclusive.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by a determination that the forward lugs of 
the flap hinge box might not conform to engineering drawings, which 
could result in premature fatigue cracking. We are issuing this AD 
to detect and correct non-conforming flap hinge box forward lugs, 
which could result in failure of the lugs and detachment of the flap 
hinge box and consequent detachment of the flap surface.

[[Page 24203]]

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Maintenance or Inspection Program Revision

    Within 60 days after the effective date of this AD, revise the 
maintenance or inspection program, as applicable, by incorporating 
the applicable airworthiness limitation (AWL) tasks as specified in 
table 1 to this paragraph. The initial compliance time for doing the 
task is at the applicable times specified in table 1 to this 
paragraph. For the incorporation of tasks specified in the temporary 
revisions (TRs) specified in table 1 to this paragraph of this AD 
that are a part of the maintenance or inspection program revision 
required by this paragraph, such incorporation may be done by 
inserting a copy of the applicable TRs specified in table 1 to this 
paragraph into the applicable ``time limits/maintenance checks'' 
(TLMC) manuals specified in table 1 to this paragraph. When the 
applicable TRs specified in table 1 to this paragraph have been 
included in general revisions of the applicable TLMC manual 
specified in table 1 to this paragraph, the general revisions may be 
inserted in the applicable TLMC manual specified in table 1 to this 
paragraph.

                                   Table 1 to Paragraph (g) of This AD--Tasks
----------------------------------------------------------------------------------------------------------------
                                                              Canadair service
         Affected airplanes               Task No.              information            Initial compliance time
----------------------------------------------------------------------------------------------------------------
Model CL-600-1A11 (CL-600 Variant)        57-40-00-186  Canadair Challenger TR 5-    Within 500 flight cycles
 airplanes with inboard flaps                            158, Inboard Flap--Hinge     after the effective date
 having greater than 7,400 total                         Box Forward Lugs, dated      of this AD, but not later
 flight cycles but equal to or less                      July 8, 2013, of the         than 15,100 total flight
 than 14,850 total flight cycles as                      Canadair Challenger TLMC     cycles.
 of the effective date of this AD.                       Manual, PSP 605.
Model CL-600-1A11 (CL-600 Variant)        57-40-00-186  Canadair Challenger TR 5-    Within 250 flight cycles
 airplanes with inboard flaps                            158, Inboard Flap--Hinge     after the effective date
 having greater than 14,850 total                        Box Forward Lugs, dated      of this AD.
 flight cycles as of the effective                       July 8, 2013, of the
 date of this AD.                                        Canadair Challenger TLMC
                                                         Manual, PSP 605.
Model CL-600-1A11 (CL-600 Variant)        57-40-00-186  Canadair Challenger TR 5-    Before the accumulation of
 airplanes with inboard flaps                            158, Inboard Flap--Hinge     7,900 total flight cycles.
 having equal to or less than 7,400                      Box Forward Lugs, dated
 total flight cycles.                                    July 8, 2013, of the
                                                         Canadair Challenger TLMC
                                                         Manual, PSP 605.
Model CL-600-1A11 (CL-600 Variant)        57-40-00-160  Canadair Challenger TR 5-    Within 500 flight cycles
 airplanes with outboard flaps                           157, Outboard Flap--Hinge    after the effective date
 having greater than 7,500 total                         Box Forward Lugs, dated      of this AD, but no later
 flight cycles, but equal to or                          July 8, 2013, of the         than 11,600 total flight
 less than 11,350 total flight                           Canadair Challenger TLMC     cycles.
 cycles as of the effective date of                      Manual, PSP 605.
 this AD.
Model CL-600-1A11 (CL-600 Variant)        57-40-00-160  Canadair Challenger TR 5-    Within 250 flight cycles
 airplanes with outboard flaps                           157, Outboard Flap--Hinge    after the effective date
 having greater than 11,350 total                        Box Forward Lugs, dated      of this AD.
 flight cycles as of the effective                       July 8, 2013, of the
 date of this AD.                                        Canadair Challenger TLMC
                                                         Manual, PSP 605.
Model CL-600-1A11 (CL-600 Variant)        57-40-00-160  Canadair Challenger TR 5-    Before the accumulation of
 airplanes with outboard flaps                           157, Outboard Flap--Hinge    8,000 total flight cycles.
 having equal to or less than 7,500                      Box Forward Lugs, dated
 total flight cycles.                                    July 8, 2013, of the
                                                         Canadair Challenger TLMC
                                                         Manual, PSP 605.
Model CL-600-2A12 (CL-601 Variant)        57-40-01-101  Canadair Challenger TR 5-    Within 500 flight cycles
 airplanes with inboard flaps                            262, Inboard Flap--Hinge     after the effective date
 having greater than 7,400 total                         Box Forward Lugs, dated      of this AD, but no later
 flight cycles, but equal to or                          July 8, 2013, of the         than 15,100 total flight
 less than 14,850 total flight                           Canadair Challenger TLMC     cycles.
 cycles, as of the effective date                        Manual, PSP 601-5.
 of this AD.
Model CL-600-2A12 (CL-601 Variant)        57-40-01-101  Canadair Challenger TR 5-    Within 250 flight cycles
 airplanes with inboard flaps with                       262, Inboard Flap--Hinge     after the effective date
 greater than 14,850 total flight                        Box Forward Lugs, dated      of this AD.
 cycles as of the effective date of                      July 8, 2013, of the
 this AD.                                                Canadair Challenger TLMC
                                                         Manual, PSP 601-5.
Model CL-600-2A12 (CL-601 Variant)        57-40-01-101  Canadair Challenger TR 5-    Before the accumulation of
 airplanes with inboard flaps with                       262, Inboard Flap--Hinge     7,900 total flight cycles.
 equal to or less than 7,400 total                       Box Forward Lugs, dated
 flight cycles as of the effective                       July 8, 2013, of the
 date of this AD.                                        Canadair Challenger TLMC
                                                         Manual, PSP 601-5.
Model CL-600-2A12 (CL-601 Variant)        57-40-00-175  Canadair Challenger TR 5-    Within 500 flight cycles
 airplanes with outboard flaps with                      262, Outboard Flap--Hinge    after the effective date
 greater than 7,500 total flight                         Box Forward Lugs, dated      of this AD, but not later
 cycles but equal to or less than                        July 8, 2013, of the         than 11,600 total flight
 11,350 total flight cycles as of                        Canadair Challenger TLMC     cycles.
 the effective date of this AD.                          Manual, PSP 601-5.
Model CL-600-2A12 (CL-601 Variant)        57-40-00-175  Canadair Challenger TR 5-    Within 250 flight cycles
 airplanes with outboard flaps                           262, Outboard Flap--Hinge    after the effective date
 having greater than 11,350 total                        Box Forward Lugs, dated      of this AD.
 flight cycles as of the effective                       July 8, 2013, of the
 date of this AD.                                        Canadair Challenger TLMC
                                                         Manual, PSP 601-5.

[[Page 24204]]

 
Model CL-600-2A12 (CL-601 Variant)        57-40-00-175  Canadair Challenger TR 5-    Before the accumulation of
 airplanes with outboard flaps                           262, Outboard Flap--Hinge    8,000 total flight cycles.
 having equal to or less than 7,500                      Box Forward Lugs, dated
 total flight cycles as of the                           July 8, 2013, of the
 effective date of this AD.                              Canadair Challenger TLMC
                                                         Manual, PSP 601-5.
Model CL-600-2B16 (CL-601-3A and -        57-40-01-101  Canadair Challenger TR 5-    Within 500 flight cycles
 3R Variant) airplanes having S/Ns                       276, Inboard Flap--Hinge     after the effective date
 5001 through 5194 inclusive with                        Box Forward Lugs, dated      of this AD, but not later
 inboard flaps having greater than                       July 8, 2013, of the         than 15,100 total flight
 7,400 total flight cycles but                           Canadair Challenger TLMC     cycles.
 equal to or less than 14,850 total                      Manual, PSP 601A-5.
 flight cycles as of the effective
 date of this AD.
Model CL-600-2B16 (CL-601-3A and -        57-40-01-101  Canadair Challenger TR 5-    Within 250 flight cycles.
 3R Variant) airplanes having S/Ns                       276, Inboard Flap--Hinge
 5001 through 5194 inclusive, with                       Box Forward Lugs, dated
 inboard flaps having greater than                       July 8, 2013, of the
 14,850 total flight cycles as of                        Canadair Challenger TLMC
 the effective date of this AD.                          Manual, PSP 601A-5.
Model CL-600-2B16 (CL-601-3A and -        57-40-01-101  Canadair Challenger TR 5-    Before the accumulation of
 3R Variant) airplanes having S/Ns                       276, Inboard Flap--Hinge     7,900 total flight cycles.
 5001 through 5194 inclusive, with                       Box Forward Lugs, dated
 inboard flaps having equal to or                        July 8, 2013, of the
 less than 7,400 total flight                            Canadair Challenger TLMC
 cycles as of the effective date of                      Manual, PSP 601A-5.
 this AD.
Model CL-600-2B16 (CL-601-3A and -        57-40-00-174  Canadair Challenger TR 5-    Within 500 flight cycles
 3R Variant) airplanes having S/Ns                       275, Outboard Flap--Hinge    after the effective date
 5001 through 5194 inclusive, with                       Box Forward Lugs, dated      of this AD, but no later
 outboard flaps having greater than                      July 8, 2013, of the         than 11,600 total flight
 7,500 total flight cycles but                           Canadair Challenger TLMC     cycles.
 equal to or less than 11,350 total                      Manual, PSP 601A-5.
 flight cycles as of the effective
 date of this AD.
Model CL-600-2B16 (CL-601-3A and -        57-40-00-174  Canadair Challenger TR 5-    Within 250 flight cycles
 3R Variant) airplanes having S/Ns                       275, Outboard Flap--Hinge    after the effective date
 5001 through 5194 inclusive, with                       Box Forward Lugs, dated      of this AD.
 outboard flaps having greater than                      July 8, 2013, of the
 11,350 total flight cycles as of                        Canadair Challenger TLMC
 the effective date of this AD.                          Manual, PSP 601A-5.
Model CL-600-2B16 (CL-601-3A and -        57-40-00-174  Canadair Challenger TR 5-    Before the accumulation of
 3R Variant) airplanes having S/Ns                       275, Outboard Flap--Hinge    8,000 total flight cycles.
 5001 through 5194 inclusive, with                       Box Forward Lugs, dated
 outboard flaps having equal to or                       July 8, 2013, of the
 less than 7,500 total flight                            Canadair Challenger TLMC
 cycles as of the effective date of                      Manual, PSP 601A-5.
 this AD.
Model CL-600-2B16 (CL-604 Variant)        57-50-00-121  Section 5-10-30, Special     Before the accumulation of
 airplanes having S/Ns 5301 through                      Detailed Inspection of the   7,800 total flight cycles,
 5665 inclusive, with inboard flaps.                     Forward Lugs of the          or within 500 flight
                                                         Inboard Flap Hinge Box, of   cycles after the effective
                                                         Part 2, Airworthiness        date of this AD, whichever
                                                         Limitations, of Bombardier   occurs later.
                                                         CL-604 TLMC Manual,
                                                         Revision 20, dated July 8,
                                                         2013.
Model CL-600-2B16 (CL-604 Variant)        57-52-01-102  Section 5-10-30, Special     Before the accumulation of
 airplanes, S/Ns 5301 through 5665                       Detailed Inspection of the   7,800 total flight cycles,
 inclusive.                                              Hinge--Box Forward Lugs of   or within 500 flight
                                                         the Outboard Flap, of Part   cycles after the effective
                                                         2, Airworthiness             date of this AD, whichever
                                                         Limitations, of Bombardier   occurs later.
                                                         CL-604 TLMC Manual,
                                                         Revision 20, dated July 8,
                                                         2013.
Model CL-600-2B16 (CL-604 Variant)        57-50-00-121  Section 5-10-30, Special     Before the accumulation of
 airplanes, S/Ns 5701 through 5953                       Detailed Inspection of the   7,800 total flight cycles,
 inclusive.                                              Forward Lugs of the          or within 500 flight
                                                         Inboard Flap Hinge Box, of   cycles after the effective
                                                         Part 2, Airworthiness        date of this AD, whichever
                                                         Limitations, of Bombardier   occurs later.
                                                         CL-605 TLMC Manual,
                                                         Revision 8, dated July 8,
                                                         2013.
Model CL-600-2B16 (CL-604 Variant)        57-52-01-102  Section 5-10-30, Special     Before the accumulation of
 airplanes, S/Ns 5701 through 5953                       Detailed Inspection of the   7,800 total flight cycles,
 inclusive.                                              Hinge--Box Forward Lugs of   or within 500 flight
                                                         the Outboard Flap, of Part   cycles after the effective
                                                         2, Airworthiness             date of this AD, whichever
                                                         Limitations, of Bombardier   occurs later.
                                                         CL-605 TLMC Manual,
                                                         Revision 8, dated July 8,
                                                         2013.
----------------------------------------------------------------------------------------------------------------

.
[[Page 24205]]

(h) Lug Edge Measurement and Inspection

    At the applicable times specified in table 2 to this paragraph 
and paragraph (i)(1) of this AD, measure the forward lug edge 
distance of all flap hinge boxes, and do a general visual inspection 
for cracking and damage (i.e., deformation or bearing failure) of 
the forward lug edge of all flap hinge boxes, in accordance with the 
applicable service bulletin specified in table 2 to this paragraph 
and paragraph (i)(1) of this AD.

    Table 2 to Paragraphs (h) and (i)(1) of This AD--Compliance Times for Lug Edge Measurement and Inspection
----------------------------------------------------------------------------------------------------------------
           Airplane models                  Affected flaps          Compliance time        Service information
----------------------------------------------------------------------------------------------------------------
Model CL-600-1A11 (CL-600) airplanes   Inboard flaps having     Before the accumulation  Bombardier Service
 having S/N 1004 through 1085           less than or equal to    of 7,900 total flight    Bulletin 600-0762,
 inclusive.                             7,400 total flight       cycles, or within 48     dated September 26,
                                        cycles as of the         months after the         2013.
                                        effective date of this   effective date of this
                                        AD.                      AD, whichever occurs
                                                                 first.
Model CL-600-1A11 (CL-600) airplanes   Inboard flaps having     Before the accumulation  Bombardier Service
 having S/N 1004 through 1085           greater than 7,400       of 15,100 total flight   Bulletin 600-0762,
 inclusive.                             total flight cycles,     cycles, or within 500    dated September 26,
                                        but equal to or less     flight cycles or 48      2013.
                                        than 14,850 total        months after the
                                        flight cycles as of      effective date of this
                                        the effective date of    AD, whichever occurs
                                        this AD.                 first.
Model CL-600-1A11 (CL-600) airplanes   Inboard flaps having     Within 250 flight        Bombardier Service
 having S/N 1004 through 1085           greater than 14,850      cycles or 48 months      Bulletin 600-0762,
 inclusive.                             total flight cycles as   after the effective      dated September 26,
                                        of the effective date    date of this AD,         2013.
                                        of this AD.              whichever occurs first.
Model CL-600-1A11 (CL-600) airplanes   Outboard flaps having    Before the accumulation  Bombardier Service
 having S/N 1004 through 1085           equal to or less than    of 8,000 total flight    Bulletin 600-0762,
 inclusive.                             7,500 total flight       cycles, or within 48     dated September 26,
                                        cycles as of the         months after the         2013.
                                        effective date of this   effective date of this
                                        AD.                      AD, whichever occurs
                                                                 first.
Model CL-600-1A11 (CL-600) airplanes   Outboard flaps having    Within 500 flight        Bombardier Service
 having S/N 1004 through 1085           greater than 7,500       cycles or 48 months      Bulletin 600-0762,
 inclusive.                             total flight cycles      after the effective      dated September 26,
                                        but less than or equal   date of this AD,         2013.
                                        to 11,350 total flight   whichever occurs
                                        cycles as of the         first; but not
                                        effective date of this   exceeding 11,600 total
                                        AD.                      flight cycles.
Model CL-600-1A11 (CL-600) airplanes   Outboard flaps having    Within 250 flight        Bombardier Service
 having S/N 1004 through 1085           greater than 11,350      cycles or within 48      Bulletin 600-0762,
 inclusive.                             total flight cycles as   months after the         dated September 26,
                                        of the effective date    effective date of this   2013.
                                        of this AD.              AD, whichever occurs
                                                                 first.
Model CL-600-2A12 (CL-601 Variant)     Inboard flaps having     Before the accumulation  Bombardier Service
 and CL-600-2B16 (CL-601-3A and -3R     less than or equal to    of 7,900 total flight    Bulletin 601-0631,
 Variants) airplanes having S/N 3001    7,400 total flight       cycles, or within 48     dated September 26,
 through 3066 inclusive, and 5001       cycles as of the         months after the         2013.
 through 5194 inclusive.                effective date of this   effective date of this
                                        AD.                      AD, whichever occurs
                                                                 first.
Model CL-600-2A12 (CL-601 Variant)     Inboard flaps having     Within 500 flight        Bombardier Service
 and CL-600-2B16 (CL-601-3A and -3R     greater than 7,400       cycles or within 48      Bulletin 601-0631,
 Variant) airplanes having S/N 3001     total flight cycles,     months after the         dated September 26,
 through 3066 inclusive, and 5001       but equal to or less     effective date of this   2013.
 through 5194 inclusive.                than 14,850 total        AD, whichever occurs
                                        flight cycles, as of     first; but not
                                        the effective date of    exceeding 15,100 total
                                        this AD.                 flight cycles.
Model CL-600-2A12 (CL-601 Variant)     Inboard flaps having     Within 250 flight        Bombardier Service
 and CL-600-2B16 (CL-601-3A and -3R     greater than 14,850      cycles or within 48      Bulletin 601-0631,
 Variant) airplanes having S/N 3001     total flight cycles as   months after the         dated September 26,
 through 3066 inclusive, and 5001       of the effective date    effective date of this   2013.
 through 5194 inclusive.                of this AD.              AD, whichever occurs
                                                                 first.
Model CL-600-2A12 (CL-601 Variant)     Outboard flaps having    Before the accumulation  Bombardier Service
 and CL-600-2B16 (CL-601-3A and -3R     less than or equal to    of 8,000 total flight    Bulletin 601-0631,
 Variant) airplanes having S/N 3001     7,500 total flight       cycles, or within 48     dated September 26,
 through 3066 inclusive, and 5001       cycles as of the         months after the         2013.
 through 5194 inclusive.                effective date of this   effective date of this
                                        AD.                      AD, whichever occurs
                                                                 first.
Model CL-600-2A12 (CL-601 Variant)     Outboard flaps having    Within 500 flight        Bombardier Service
 and CL-600-2B16 (CL-601-3A and -3R     greater than 7,500       cycles or within 48      Bulletin 601-0631,
 Variant) airplanes having S/N 3001     total flight cycles,     months after the         dated September 26,
 through 3066 inclusive, and 5001       but equal to or less     effective date of this   2013.
 through 5194 inclusive.                than 11,350 total        AD; but not exceeding
                                        flight cycles, as of     11,600 total flight
                                        the effective date of    cycles.
                                        this AD.
Model CL-600-2A12 (CL-601 Variant)     Outboard flaps having    Within 250 flight        Bombardier Service
 and CL-600-2B16 (CL-601-3A and -3R     greater than 11,350      cycles or 48 months      Bulletin 601-0631,
 Variant) airplanes having S/N 3001     total flight cycles as   after the effective      dated September 26,
 through 3066 inclusive, and 5001       of the effective date    date of this AD,         2013.
 through 5194 inclusive.                of this AD.              whichever occurs first.

[[Page 24206]]

 
Model CL-600-2B16 (CL-604 Variant)     Outboard and inboard     Before the accumulation  Bombardier Service
 airplanes having S/Ns 5301 through     flaps.                   of 7,800 total flight    Bulletin 604-57-007,
 5665 inclusive.                                                 cycles or within 48      Revision 01, dated
                                                                 months after the         November 12, 2014.
                                                                 effective date of this
                                                                 AD, whichever occurs
                                                                 first.
Model CL-600-2B16 (CL-604 Variant)     Outboard and inboard     Before the accumulation  Bombardier Service
 airplanes having S/Ns 5701 through     flaps.                   of 7,800 total flight    Bulletin 605-57-005,
 5953 inclusive.                                                 cycles or within 48      Revision 01, dated
                                                                 months after the         November 12, 2014.
                                                                 effective date of this
                                                                 AD, whichever occurs
                                                                 first.
----------------------------------------------------------------------------------------------------------------

(i) Corrective Actions

    (1) If, during the measurement required by paragraph (h) of this 
AD, the lug edge distance is equal to or greater than the limit 
specified in the applicable service bulletin specified in table 2 to 
paragraph (h) of this AD and this paragraph, no further action is 
required by this paragraph.
    (2) If, during the measurement required by paragraph (h) of this 
AD, the lug edge distance is below the limit specified in the 
applicable service bulletin specified in table 2 to paragraphs (h) 
and (i)(1) of this AD, before further flight, repair using a method 
approved by the Manager, New York ACO, ANE-170, FAA; or Transport 
Canada Civil Aviation (TCCA); or Bombardier, Inc.'s TCCA Design 
Approval Organization (DAO). If approved by the DAO, the approval 
must include the DAO-authorized signature.
    (3) If, during the inspection required by paragraph (h) of this 
AD, any cracking or damage is found, before further flight, repair 
using a method approved by the Manager, New York ACO, ANE-170, FAA; 
or TCCA; or Bombardier, Inc.'s TCCA DAO. If approved by the DAO, the 
approval must include the DAO-authorized signature.

(j) No Alternative Actions or Intervals

    After accomplishing the revision required by paragraph (g) of 
this AD, no alternative actions (e.g., inspections) or intervals may 
be used unless the actions or intervals are approved as an 
alternative method of compliance in accordance with the procedures 
specified in paragraph (l) of this AD.

(k) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g) and (h) of this AD, if those actions were performed 
before the effective date of this AD using Bombardier Service 
Bulletin 604-57-007, dated September 26, 2013 (for Model CL-600-2B16 
airplanes); or Bombardier Service Bulletin 605-57-005, dated 
September 26, 2013 (for Model CL-600-2B16 airplanes); which are not 
incorporated by reference in 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 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) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, New York ACO, 
ANE-170, Engine and Propeller Directorate, FAA; or TCCA; or 
Bombardier, Inc.'s TCCA DAO. If approved by the DAO, the approval 
must include the DAO-authorized signature.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian Airworthiness Directive CF-2014-01, dated January 3, 
2014, for related information. This MCAI may be found in the AD 
docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0491-0004.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (n)(3) and (n)(4) of this AD.

(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 this AD specifies otherwise.
    (i) Bombardier Service Bulletin 600-0762, dated September 26, 
2013.
    (ii) Bombardier Service Bulletin 601-0631, dated September 26, 
2013.
    (iii) Bombardier Service Bulletin 604-57-007, Revision 01, dated 
November 12, 2014.
    (iv) Bombardier Service Bulletin 605-57-005, Revision 01, dated 
November 12, 2014.
    (v) Canadair Challenger Temporary Revision 5-157, Outboard 
Flap--Hinge Box Forward Lugs, dated July 8, 2013, to Canadair 
Challenger Time Limits/Maintenance Checks Manual, PSP 605.
    (vi) Canadair Challenger Temporary Revision 5-158, Inboard 
Flap--Hinge Box Forward Lugs, dated July 8, 2013, to Canadair 
Challenger Time Limits/Maintenance Checks Manual, PSP 605.
    (vii) Canadair Challenger Temporary Revision 5-262, Outboard and 
Inboard Flap--Hinge Box Forward Lugs, dated July 8, 2013, to 
Canadian Challenger Time Limits/Maintenance Checks Manual PSP 601.
    (viii) Canadair Challenger Temporary Revision 5-275, Outboard 
Flap--Hinge Box Forward Lugs, dated July 8, 2013, to Canadian 
Challenger Time Limits/Maintenance Checks Manual PSP 601A-5.
    (ix) Canadair Challenger Temporary Revision 5-276, Inboard 
Flap--Hinge Box Forward Lugs, dated July 8, 2013, to Canadian 
Challenger Time Limits/Maintenance Checks Manual PSP 601A-5.
    (x) Task 57-50-00-121 Special Detailed Inspection of the Forward 
Lugs of the Inboard Flap Hinge Box of Section 5-10-30 of Part 2, 
``Airworthiness Limitations,'' of Bombardier CL-605 Time Limits/
Maintenance Checks Manual, Revision 8, dated July 8, 2013.
    (xi) Task 57-50-00-121 Special Detailed Inspection of the 
Forward Lugs of the Inboard Flap Hinge Box of Section 5-10-30 of 
Part 2, ``Airworthiness Limitations,'' of Bombardier CL-604 Time 
Limits/Maintenance Checks Manual, Revision 20, dated July 8, 2013.
    (xii) Task 57-52-01-102 Special Detailed Inspection of the 
Hinge--Box Forward Lugs of the Outboard Flap of Section 5-10-30 of 
Part 2, ``Airworthiness Limitations,'' of Bombardier CL-605 Time 
Limits/Maintenance Checks Manual, Revision 8, dated July 8, 2013.
    (xiii) Task 57-52-01-102 Special Detailed Inspection of the 
Hinge--Box Forward Lugs of the Outboard Flap of Section 5-10-30 of 
Part 2, ``Airworthiness Limitations,'' of Bombardier CL-604 Time 
Limits/Maintenance Checks Manual, Revision 20, dated July 8, 2013.
    (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.

[[Page 24207]]

    (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/ibr-locations.html.

    Issued in Renton, Washington, on March 25, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-07802 Filed 4-29-15; 8:45 am]
 BILLING CODE 4910-13-P