Airworthiness Directives; Bombardier, Inc. Airplanes, 45140-45146 [2014-18401]

Download as PDF 45140 Federal Register / Vol. 79, No. 149 / Monday, August 4, 2014 / Proposed Rules (i) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency Airworthiness Directive 2013–0140, dated July 12, 2013, for related information. This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2014–0492. (2) For service information identified in this AD, contact Fokker Services B.V., Technical Services Dept., P.O. Box 1357, 2130 EL Hoofddorp, the Netherlands; telephone +31 (0)88–6280–350; fax +31 (0)88–6280–111; email technicalservices@ fokker.com; Internet https:// www.myfokkerfleet.com. 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. Issued in Renton, Washington, on July 23, 2014. John P. Piccola, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–18373 Filed 8–1–14; 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] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes 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: We must receive comments on this proposed AD by September 18, 2014. You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Bombardier, ˆ 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 https://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. ADDRESSES: AGENCY: Examining the AD Docket We propose to adopt 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 proposed 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 proposed AD would 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, and inspecting for cracking and damage (i.e., deformation or bearing failure) of the forward lug edge of each flap hinge box, and repair if necessary. We are proposing this AD to detect and correct non-conforming flap hinge box You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. 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 proposed 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. Comments will be available in the AD docket shortly after receipt. 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: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). mstockstill on DSK4VPTVN1PROD with PROPOSALS SUMMARY: VerDate Mar<15>2010 17:11 Aug 01, 2014 Jkt 232001 PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2014–0491; Directorate Identifier 2014–NM–023–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion 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 the specified products. 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 https://www.regulations.gov by searching for and locating Docket No. FAA–2014–0491. Relevant Service Information Bombardier has issued the following service information. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. • Bombardier Service Bulletin 600– 0762, dated September 26, 2013 (for Model CL–600–1A11 airplanes). E:\FR\FM\04AUP1.SGM 04AUP1 Federal Register / Vol. 79, No. 149 / Monday, August 4, 2014 / Proposed Rules mstockstill on DSK4VPTVN1PROD with PROPOSALS • Bombardier Service Bulletin 601– 0631, dated September 26, 2013 (for Models CL–600–2A12 and CL–600– 2B16 airplanes). • Bombardier Service Bulletin 604– 57–007, dated September 26, 2013 (for Model CL–600–2B16 airplanes). • Bombardier Service Bulletin 605– 57–005, dated September 26, 2013 (for Model CL–600–2B16 airplanes). • Canadair Challenger Temporary Revision 5–157, dated July 8, 2013, to Canadair Challenger Time Limits/ Maintenance Checks Manual, PSP 605. • Canadair Challenger Temporary Revision 5–158, dated July 8, 2013, to Canadair Challenger Time Limits/ Maintenance Checks Manual, PSP 605. • Canadair Challenger Temporary Revision 5–262, dated July 8, 2013, to Canadian Challenger Time Limits/ Maintenance Checks Manual PSP 601. • Canadair Challenger Temporary Revision 5–275, dated July 8, 2013, to Canadian Challenger Time Limits/ Maintenance Checks Manual PSP 601A. • Canadair Challenger Temporary Revision 5–276, dated July 8, 2013, to Canadian Challenger Time Limits/ Maintenance Checks Manual PSP 601A. • Tasks 57–50–00–121 and 57–52– 01–102 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. • Tasks 57–50–00–121 and 57–52– 01–102 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. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type designs. This AD requires revisions to certain operator maintenance documents to include new actions (e.g., inspections). Compliance with these actions is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by this AD, the operator may not be able to accomplish the actions described in the revisions. In VerDate Mar<15>2010 17:11 Aug 01, 2014 Jkt 232001 this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (k) of this AD. The request should include a description of changes to the required actions that will ensure the continued damage tolerance of the affected structure. ‘‘Contacting the Manufacturer’’ Paragraph in This Proposed AD Since late 2006, we have included a standard paragraph titled ‘‘Airworthy Product’’ in all MCAI ADs in which the FAA develops an AD based on a foreign authority’s AD. The MCAI or referenced service information in an FAA AD often directs the owner/operator to contact the manufacturer for corrective actions, such as a repair. Briefly, the Airworthy Product paragraph allowed owners/ operators to use corrective actions provided by the manufacturer if those actions were FAA-approved. In addition, the paragraph stated that any actions approved by the State of Design Authority (or its delegated agent) are considered to be FAA-approved. In an NPRM having Directorate Identifier 2012–NM–101–AD (78 FR 78285, December 26, 2013), we proposed to prevent the use of repairs that were not specifically developed to correct the unsafe condition, by requiring that the repair approval provided by the State of Design Authority or its delegated agent specifically refer to the FAA AD. This change was intended to clarify the method of compliance and to provide operators with better visibility of repairs that are specifically developed and approved to correct the unsafe condition. In addition, we proposed to change the phrase ‘‘its delegated agent’’ to include a design approval holder (DAH) with State of Design Authority design organization approval (DOA), as applicable, to refer to a DAH authorized to approve required repairs for the proposed AD. One commenter to the NPRM having Directorate Identifier 2012–NM–101–AD (78 FR 78285, December 26, 2013) stated the following: ‘‘The proposed wording, being specific to repairs, eliminates the interpretation that Airbus messages are acceptable for approving minor deviations (corrective actions) needed during accomplishment of an AD mandated Airbus service bulletin.’’ This comment has made the FAA aware that some operators have misunderstood or misinterpreted the Airworthy Product paragraph to allow the owner/operator to use messages provided by the manufacturer as PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 45141 approval of deviations during the accomplishment of an AD-mandated action. The Airworthy Product paragraph does not approve messages or other information provided by the manufacturer for deviations to the requirements of the AD-mandated actions. The Airworthy Product paragraph only addresses the requirement to contact the manufacturer for corrective actions for the identified unsafe condition and does not cover deviations from other AD requirements. However, deviations to AD-required actions are addressed in 14 CFR 39.17, and anyone may request the approval for an alternative method of compliance to the AD-required actions using the procedures found in 14 CFR 39.19. To address this misunderstanding and misinterpretation of the Airworthy Product paragraph, we have changed the paragraph and retitled it ‘‘Contacting the Manufacturer.’’ This paragraph now clarifies that for any requirement in this proposed AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the FAA, TCCA, or Bombardier, Inc.’s TCCA Design Approval Organization (DAO). The Contacting the Manufacturer paragraph also clarifies that, if approved by the DAO, the approval must include the DAO-authorized signature. The DAO signature indicates that the data and information contained in the document are TCCA-approved, which is also FAAapproved. Messages and other information provided by the manufacturer that do not contain the DAO-authorized signature approval are not TCCA-approved, unless TCCA directly approves the manufacturer’s message or other information. This clarification does not remove flexibility previously afforded by the Airworthy Product paragraph. Consistent with long-standing FAA policy, such flexibility was never intended for required actions. This is also consistent with the recommendation of the Airworthiness Directive Implementation Aviation Rulemaking Committee to increase flexibility in complying with ADs by identifying those actions in manufacturers’ service instructions that are ‘‘Required for Compliance’’ with ADs. We continue to work with manufacturers to implement this recommendation. But once we determine that an action is required, any deviation from the requirement must be approved as an alternative method of compliance. E:\FR\FM\04AUP1.SGM 04AUP1 45142 Federal Register / Vol. 79, No. 149 / Monday, August 4, 2014 / Proposed Rules Costs of Compliance We estimate that this proposed AD affects 105 airplanes of U.S. registry. We also estimate that it would take about 45 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed 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 oncondition actions specified in this proposed 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 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 proposed 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation: The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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): ■ Bombardier, Inc.: Docket No. FAA–2014– 0491; Directorate Identifier 2014–NM– 023–AD. (a) Comments Due Date We must receive comments by September 18, 2014. (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 flap hinge box forward lugs edge distance 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. (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 paragraph (g) of this AD. The initial compliance time for doing the task is at the applicable times specified in table 1 to paragraph (g) of this AD. Note 1 to paragraph (g) of this AD: For the incorporation of tasks specified in the temporary revisions (TRs) specified in table 1 to paragraph (g) of this AD that are a part of the maintenance or inspection program revision required by paragraph (g) of this AD, such incorporation may be done by inserting a copy of the applicable TRs specified in table 1 to paragraph (g) of this AD into the applicable ‘‘time limits/maintenance checks’’ (TLMC) manuals specified in table 1 to paragraph (g) of this AD. When the applicable TRs specified in table 1 to paragraph (g) of this AD have been included in general revisions of the applicable TLMC manual specified in table 1 to paragraph (g) of this AD, the general revisions may be inserted in the applicable TLMC manual specified in table 1 to paragraph (g) of this AD. TABLE 1 TO PARAGRAPH (g) OF THIS AD—TASKS mstockstill on DSK4VPTVN1PROD with PROPOSALS Affected airplanes Task No. 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 CL600–1A11 (CL–600 Variant) airplanes with inboard flaps having greater than 14,850 total flight cycles as of the effective date of this AD. VerDate Mar<15>2010 17:11 Aug 01, 2014 Jkt 232001 Canadair service information Initial compliance time 57–40–00–186 Canadair Challenger Temporary Revision (TR) 5–158, dated July 8, 2013, of the Canadair Challenger Time Limits/Maintenance Checks (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 Canadair Challenger TR 5–158, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 605. Within 250 flight cycles after the effective date of this AD. PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 E:\FR\FM\04AUP1.SGM 04AUP1 Federal Register / Vol. 79, No. 149 / Monday, August 4, 2014 / Proposed Rules 45143 TABLE 1 TO PARAGRAPH (g) OF THIS AD—TASKS—Continued mstockstill on DSK4VPTVN1PROD with PROPOSALS Affected airplanes Task No. Model CL–600–1A11 (CL–600 Variant) airplanes with inboard flaps having equal to or less than 7,400 total flight cycles. 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. Model CL–600–1A11 (CL–600 Variant) airplanes with outboard flaps having equal to or less than 7,500 total flight cycles. 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. 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. 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. VerDate Mar<15>2010 17:11 Aug 01, 2014 Jkt 232001 Canadair service information Initial compliance time 57–40–00–186 Canadair Challenger TR 5–158, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 605. Before the accumulation of 7,900 total flight cycles. 57–40–00–160 Canadair Challenger TR 5–157, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 605. Within 500 flight cycles after the effective date of this AD, but no later than 11,600 total flight cycles. 57–40–00–160 Canadair Challenger TR 5–157, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 605. Within 250 flight cycles after the effective date of this AD. 57–40–00–160 Canadair Challenger TR 5–157, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 605. Before the accumulation of 8,000 total flight cycles. 57–40–01–101 Canadair Challenger TR 5–262, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601–5. Within 500 flight cycles after the effective date of this AD, but no later than 15,100 total flight cycles. 57–40–01–101 Canadair Challenger TR 5–262, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601–5. Within 250 flight cycles after the effective date of this AD. 57–40–01–101 Canadair Challenger TR 5–262, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601–5. Before the accumulation of 7,900 total flight cycles. 57–40–00–175 Canadair Challenger TR 5–262, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601–5. Within 500 flight cycles after the effective date of this AD, but not later than 11,600 total flight cycles. 57–40–00–175 Canadair Challenger TR 5–262, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601–5. Within 250 flight cycles after the effective date of this AD. 57–40–00–175 Canadair Challenger TR 5–262, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601–5. Before the accumulation of 8,000 total flight cycles. 57–40–00–101 Canadair Challenger TR 5–276, 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 not later than 15,100 total flight cycles. 57–40–00–101 Canadair Challenger TR 5–276, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601A–5. Within 250 flight cycles. 57–40–00–101 Canadair Challenger TR 5–276, dated July 8, 2013, of the Canadair Challenger TLMC Manual, PSP 601A–5. Before the accumulation of 7,900 total flight cycles. PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 E:\FR\FM\04AUP1.SGM 04AUP1 45144 Federal Register / Vol. 79, No. 149 / Monday, August 4, 2014 / Proposed Rules TABLE 1 TO PARAGRAPH (g) OF THIS AD—TASKS—Continued Affected airplanes Task No. Canadair service information Initial compliance time 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 with inboard and outboard flaps. 57–40–00–174 Canadair Challenger TR 5–276, 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 5–276, 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 5–276, 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 Model CL–600–2B16 (CL–604 Variant) airplanes, S/Ns 5301 through 5665 inclusive. 57–52–01–102 Before the accumulation of 7,800 total flight cycles, or within 500 flight cycles after the effective date of this AD, whichever occurs later. At the time specified in the task. Model CL–600–2B16 (CL–604 Variant) airplanes, S/Ns 5701 through 5953 inclusive. 57–50–00–121 and 57–52–01– 102 Section 5–10–30 of Part 2, ‘‘Airworthiness Limitations,’’ of Bombardier CL– 604 TLMC Manual, Revision 8, dated July 8, 2013. Section 5–10–30 of Part 2, ‘‘Airworthiness Limitations,’’ of Bombardier CL– 604 TLMC Manual, Revision 8, dated July 8, 2013. Section 5–10–30 of Part 2, ‘‘Airworthiness Limitations,’’ of Bombardier CL– 605 TLMC Manual, Revision 8, dated July 8, 2013. (h) Lug Edge Measurement and Inspection At the applicable times specified in table 2 to paragraphs (h) and (i)(1) of this AD, measure the forward lug edge distance of all flap hinge boxes, in accordance with the applicable service bulletin specified in paragraphs (h) and (i)(1) of this AD; and do At the applicable time specified in the tasks. a general visual inspection for cracking and damage (i.e., deformation or bearing failure) of the forward lug edge of all flap hinge boxes. TABLE 2 TO PARAGRAPHS (h) AND (i)(1) OF THIS AD—COMPLIANCE TIMES FOR LUG EDGE MEASUREMENT AND INSPECTION 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. 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. 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. Bombardier Service Bulletin 600– 0762, dated September 26, 2013. Model CL–600–1A11 (CL–600) airplanes having S/N 1004 through 1085 inclusive. mstockstill on DSK4VPTVN1PROD with PROPOSALS Airplane models VerDate Mar<15>2010 17:11 Aug 01, 2014 Jkt 232001 PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 E:\FR\FM\04AUP1.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. 04AUP1 Federal Register / Vol. 79, No. 149 / Monday, August 4, 2014 / Proposed Rules 45145 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–600–1A11 (CL–600) airplanes having S/N 1004 through 1085 inclusive. 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. 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. Bombardier Service Bulletin 600– 0762, dated September 26, 2013. 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. 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. Bombardier Service Bulletin 604– 57–007, dated October 2, 2013. 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. Model CL–600–2B16 (CL–604 Variant) airplanes having S/Ns 5301 through 5665 inclusive. Model CL–600–2B16 (CL–604 Variant) airplanes having S/Ns 5701 through 5953 inclusive. Outboard and inboard flaps .......... mstockstill on DSK4VPTVN1PROD with PROPOSALS (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 paragraphs (h) and (i)(1) of this AD, 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 3 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, Engine and Propeller Directorate, FAA; or Transport Canada Civil Aviation VerDate Mar<15>2010 17:11 Aug 01, 2014 Jkt 232001 (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, Engine and Propeller Directorate, FAA; or TCCA; or Bombardier, Inc.’s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAOauthorized signature. (j) No Alternative Actions or Intervals After accomplishing the revision required by paragraph (g) of this AD, no alternative PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 Bombardier Service Bulletin 601– 0631, dated September 26, 2013. Bombardier Service Bulletin 605– 57–005, dated November 15, 2013. actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (k) of this AD. (k) 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 E:\FR\FM\04AUP1.SGM 04AUP1 45146 Federal Register / Vol. 79, No. 149 / Monday, August 4, 2014 / Proposed Rules 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 Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. (l) 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 https://www.regulations.gov by searching for and locating Docket No. FAA– 2014–0491. (2) 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 https:// www.bombardier.com. 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. Issued in Renton, Washington, on July 23, 2014. John P. Piccola, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–18401 Filed 8–1–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Highway Administration 23 CFR Part 790 [FHWA Docket No. FHWA–2013–0018] RIN 2125–AF63 mstockstill on DSK4VPTVN1PROD with PROPOSALS Congestion Mitigation and Air Quality Improvement (CMAQ) Program Federal Highway Administration (FHWA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The CMAQ program provides funding to State and local governments for transportation projects and programs SUMMARY: VerDate Mar<15>2010 17:31 Aug 01, 2014 Jkt 232001 to help meet the requirements of the Clean Air Act (CAA). Funding is available to reduce congestion and improve air quality for areas that do not meet the National Ambient Air Quality Standards (NAAQS) for ozone, carbon monoxide (CO), or particulate matter (nonattainment areas) and for areas that were out of compliance but have now met the standards (maintenance areas). The Moving Ahead for Progress in the 21st Century Act (MAP–21) requires priority use of CMAQ funds in areas that are designated nonattainment or maintenance for fine particulate matter (PM2.5) NAAQS under the CAA. Specifically, an amount equal to 25 percent of the CMAQ funds apportioned to each State for a nonattainment or maintenance area that is based all or in part on the weighted population of the PM2.5 nonattainment area shall be obligated to projects that reduce PM2.5 emissions in such area. These projects include diesel retrofits for on-road and some off-road applications, as well as for diesel equipment operated on a highway construction project within PM2.5 nonattainment and maintenance areas. Although the MAP–21 language for the CMAQ funds that must be obligated for PM2.5 projects (referred to in this NPRM as a ‘‘set-aside’’) instructs that the set-aside be calculated based on ‘‘weighted population’’ for PM2.5, the statute does not specify the values to be applied to determine the weighted population. In this proposed rule, FHWA is requesting comments on a proposed weighting factor of 5, to be used in determining the weighted population of a PM2.5 nonattainment area. DATES: Comments must be received on or before October 3, 2014. Late-filed comments will be considered to the extent practicable. ADDRESSES: Mail or hand deliver comments to the U.S. Department of Transportation, Dockets Management Facility, 1200 New Jersey Avenue SE., Washington, DC 20590, or submit electronically at www.regulations.gov or fax comments to 202–493–2251. All comments should include the docket number that appears in the heading of this document. All comments received will be available for examination and copying at the above address from 9 a.m. to 5 p.m., e.t., Monday through Friday, except Federal holidays. Those desiring notification of receipt of comments must include a selfaddressed, stamped postcard or you may print the acknowledgment page that appears after submitting comments electronically. Anyone is able to search PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 the electronic form of all comments in any one of our dockets by the name of the individual submitting the comment (or signing the comment, if submitted on behalf of an association, business, or labor union). You may review DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (Volume 65, Number 70, Pages 19477–78). FOR FURTHER INFORMATION CONTACT: Ms. Cecilia Ho, Office of Natural Environment, HEPN, 202–366–9862, or Ms. Janet Myers, Office of the Chief Counsel, 202–366–2019, Federal Highway Administration, 1200 New Jersey Avenue SE., Washington, DC 20590–0001. Office hours are from 8:00 a.m. to 4:30 p.m., e.t., Monday through Friday, except Federal holidays. SUPPLEMENTARY INFORMATION: Electronic Access and Filing You may submit or retrieve comments online through the Document Management System at: https:// www.regulations.gov. Electronic submission and retrieval help and guidelines are available under the help section of the Web site. It is available 24 hours each day, 365 days each year. Please follow the instructions. An electronic copy of this document may also be downloaded by accessing the Federal Register’s home page at: https:// www.federalregister.gov. Executive Summary I. Purpose of the Regulatory Action This regulation seeks to establish a proposed weighting factor of 5, to be used in determining the weighted population of a PM2.5 nonattainment area. Although the MAP–21 language for the CMAQ funds that must be obligated for PM2.5 projects instructs that the setaside be calculated based on ‘‘weighted population’’ for PM2.5, the statute does not specify the values to be applied to determine the weighted population. Section 1113(b)(6) of MAP–21 amends 23 U.S.C. 149 by adding subsection (k)(1) that requires priority use of CMAQ funds in areas that are designated nonattainment or maintenance for the PM2.5 NAAQS.1 Specifically, 23 U.S.C. 149(k)(1) states that an amount equal to 25 percent of the funds attributed to PM2.5 nonattainment in each of the affected States must be used for projects that reduced PM2.5 emissions in those nonattainment and maintenance areas. Although this MAP–21 language states that the PM2.5 set-aside must be 1 The EPA has set both an annual and a 24-hour NAAQS for PM2.5 (40 CFR 50.7). E:\FR\FM\04AUP1.SGM 04AUP1

Agencies

[Federal Register Volume 79, Number 149 (Monday, August 4, 2014)]
[Proposed Rules]
[Pages 45140-45146]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-18401]

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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]
RIN 2120-AA64

Airworthiness Directives; Bombardier, Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt 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 proposed 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
proposed AD would 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, and inspecting
for cracking and damage (i.e., deformation or bearing failure) of the
forward lug edge of each flap hinge box, and repair if necessary. We
are proposing 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: We must receive comments on this proposed AD by September 18,
2014.

ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed 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 https://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.

Examining the AD Docket

You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. 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 proposed 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.
Comments will be available in the AD docket shortly after receipt.

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:

Comments Invited

We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2014-0491;
Directorate Identifier 2014-NM-023-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.

Discussion

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 the specified products. 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 https://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0491.

Relevant Service Information

Bombardier has issued the following service information. The
actions described in this service information are intended to correct
the unsafe condition identified in the MCAI.
Bombardier Service Bulletin 600-0762, dated September 26,
2013 (for Model CL-600-1A11 airplanes).

[[Page 45141]]

Bombardier Service Bulletin 601-0631, dated September 26,
2013 (for Models CL-600-2A12 and CL-600-2B16 airplanes).
Bombardier Service Bulletin 604-57-007, dated September
26, 2013 (for Model CL-600-2B16 airplanes).
Bombardier Service Bulletin 605-57-005, dated September
26, 2013 (for Model CL-600-2B16 airplanes).
Canadair Challenger Temporary Revision 5-157, dated July
8, 2013, to Canadair Challenger Time Limits/Maintenance Checks Manual,
PSP 605.
Canadair Challenger Temporary Revision 5-158, dated July
8, 2013, to Canadair Challenger Time Limits/Maintenance Checks Manual,
PSP 605.
Canadair Challenger Temporary Revision 5-262, dated July
8, 2013, to Canadian Challenger Time Limits/Maintenance Checks Manual
PSP 601.
Canadair Challenger Temporary Revision 5-275, dated July
8, 2013, to Canadian Challenger Time Limits/Maintenance Checks Manual
PSP 601A.
Canadair Challenger Temporary Revision 5-276, dated July
8, 2013, to Canadian Challenger Time Limits/Maintenance Checks Manual
PSP 601A.
Tasks 57-50-00-121 and 57-52-01-102 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.
Tasks 57-50-00-121 and 57-52-01-102 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.

FAA's Determination and Requirements of This Proposed AD

This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type designs.
This AD requires revisions to certain operator maintenance
documents to include new actions (e.g., inspections). Compliance with
these actions is required by 14 CFR 91.403(c). For airplanes that have
been previously modified, altered, or repaired in the areas addressed
by this AD, the operator may not be able to accomplish the actions
described in the revisions. In this situation, to comply with 14 CFR
91.403(c), the operator must request approval for an alternative method
of compliance according to paragraph (k) of this AD. The request should
include a description of changes to the required actions that will
ensure the continued damage tolerance of the affected structure.

``Contacting the Manufacturer'' Paragraph in This Proposed AD

Since late 2006, we have included a standard paragraph titled
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD
based on a foreign authority's AD.
The MCAI or referenced service information in an FAA AD often
directs the owner/operator to contact the manufacturer for corrective
actions, such as a repair. Briefly, the Airworthy Product paragraph
allowed owners/operators to use corrective actions provided by the
manufacturer if those actions were FAA-approved. In addition, the
paragraph stated that any actions approved by the State of Design
Authority (or its delegated agent) are considered to be FAA-approved.
In an NPRM having Directorate Identifier 2012-NM-101-AD (78 FR
78285, December 26, 2013), we proposed to prevent the use of repairs
that were not specifically developed to correct the unsafe condition,
by requiring that the repair approval provided by the State of Design
Authority or its delegated agent specifically refer to the FAA AD. This
change was intended to clarify the method of compliance and to provide
operators with better visibility of repairs that are specifically
developed and approved to correct the unsafe condition. In addition, we
proposed to change the phrase ``its delegated agent'' to include a
design approval holder (DAH) with State of Design Authority design
organization approval (DOA), as applicable, to refer to a DAH
authorized to approve required repairs for the proposed AD.
One commenter to the NPRM having Directorate Identifier 2012-NM-
101-AD (78 FR 78285, December 26, 2013) stated the following: ``The
proposed wording, being specific to repairs, eliminates the
interpretation that Airbus messages are acceptable for approving minor
deviations (corrective actions) needed during accomplishment of an AD
mandated Airbus service bulletin.''
This comment has made the FAA aware that some operators have
misunderstood or misinterpreted the Airworthy Product paragraph to
allow the owner/operator to use messages provided by the manufacturer
as approval of deviations during the accomplishment of an AD-mandated
action. The Airworthy Product paragraph does not approve messages or
other information provided by the manufacturer for deviations to the
requirements of the AD-mandated actions. The Airworthy Product
paragraph only addresses the requirement to contact the manufacturer
for corrective actions for the identified unsafe condition and does not
cover deviations from other AD requirements. However, deviations to AD-
required actions are addressed in 14 CFR 39.17, and anyone may request
the approval for an alternative method of compliance to the AD-required
actions using the procedures found in 14 CFR 39.19.
To address this misunderstanding and misinterpretation of the
Airworthy Product paragraph, we have changed the paragraph and retitled
it ``Contacting the Manufacturer.'' This paragraph now clarifies that
for any requirement in this proposed AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the FAA, TCCA, or Bombardier, Inc.'s TCCA Design Approval
Organization (DAO).
The Contacting the Manufacturer paragraph also clarifies that, if
approved by the DAO, the approval must include the DAO-authorized
signature. The DAO signature indicates that the data and information
contained in the document are TCCA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer
that do not contain the DAO-authorized signature approval are not TCCA-
approved, unless TCCA directly approves the manufacturer's message or
other information.
This clarification does not remove flexibility previously afforded
by the Airworthy Product paragraph. Consistent with long-standing FAA
policy, such flexibility was never intended for required actions. This
is also consistent with the recommendation of the Airworthiness
Directive Implementation Aviation Rulemaking Committee to increase
flexibility in complying with ADs by identifying those actions in
manufacturers' service instructions that are ``Required for
Compliance'' with ADs. We continue to work with manufacturers to
implement this recommendation. But once we determine that an action is
required, any deviation from the requirement must be approved as an
alternative method of compliance.

[[Page 45142]]

Costs of Compliance

We estimate that this proposed AD affects 105 airplanes of U.S.
registry.
We also estimate that it would take about 45 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of this proposed 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 proposed 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 proposed 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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
regulation:
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.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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):

Bombardier, Inc.: Docket No. FAA-2014-0491; Directorate Identifier
2014-NM-023-AD.

(a) Comments Due Date

We must receive comments by September 18, 2014.

(b) Affected ADs

None.

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 flap hinge box
forward lugs edge distance 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.

(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 paragraph (g) of this AD. The initial compliance time for
doing the task is at the applicable times specified in table 1 to
paragraph (g) of this AD.

Note 1 to paragraph (g) of this AD: For the incorporation of
tasks specified in the temporary revisions (TRs) specified in table
1 to paragraph (g) of this AD that are a part of the maintenance or
inspection program revision required by paragraph (g) of this AD,
such incorporation may be done by inserting a copy of the applicable
TRs specified in table 1 to paragraph (g) of this AD into the
applicable ``time limits/maintenance checks'' (TLMC) manuals
specified in table 1 to paragraph (g) of this AD. When the
applicable TRs specified in table 1 to paragraph (g) of this AD have
been included in general revisions of the applicable TLMC manual
specified in table 1 to paragraph (g) of this AD, the general
revisions may be inserted in the applicable TLMC manual specified in
table 1 to paragraph (g) of this AD.

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 Within 500 flight cycles
airplanes with inboard flaps having Temporary Revision (TR) 5- after the effective date
greater than 7,400 total flight cycles 158, dated July 8, 2013, of this AD, but not
but equal to or less than 14,850 total of the Canadair later than 15,100 total
flight cycles as of the effective date Challenger Time Limits/ flight cycles.
of this AD. Maintenance Checks (TLMC)
Manual, PSP 605.
Model CL600-1A11 (CL-600 Variant) 57-40-00-186 Canadair Challenger TR 5- Within 250 flight cycles
airplanes with inboard flaps having 158, dated July 8, 2013, after the effective date
greater than 14,850 total flight of the Canadair of this AD.
cycles as of the effective date of Challenger TLMC Manual,
this AD. PSP 605.

[[Page 45143]]

Model CL-600-1A11 (CL-600 Variant) 57-40-00-186 Canadair Challenger TR 5- Before the accumulation
airplanes with inboard flaps having 158, dated July 8, 2013, of 7,900 total flight
equal to or less than 7,400 total of the Canadair cycles.
flight cycles. 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 having 157, dated July 8, 2013, after the effective date
greater than 7,500 total flight of the Canadair of this AD, but no later
cycles, but equal to or less than Challenger TLMC Manual, than 11,600 total flight
11,350 total flight cycles as of the PSP 605. cycles.
effective date of 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 having 157, dated July 8, 2013, after the effective date
greater than 11,350 total flight of the Canadair of this AD.
cycles as of the effective date of Challenger TLMC Manual,
this AD. PSP 605.
Model CL-600-1A11 (CL-600 Variant) 57-40-00-160 Canadair Challenger TR 5- Before the accumulation
airplanes with outboard flaps having 157, dated July 8, 2013, of 8,000 total flight
equal to or less than 7,500 total of the Canadair cycles.
flight cycles. 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 having 262, dated July 8, 2013, after the effective date
greater than 7,400 total flight of the Canadair of this AD, but no later
cycles, but equal to or less than Challenger TLMC Manual, than 15,100 total flight
14,850 total flight cycles, as of the PSP 601-5. cycles.
effective date 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, dated July 8, 2013, after the effective date
greater than 14,850 total flight of the Canadair of this AD.
cycles as of the effective date of Challenger TLMC Manual,
this AD. PSP 601-5.
Model CL-600-2A12 (CL-601 Variant) 57-40-01-101 Canadair Challenger TR 5- Before the accumulation
airplanes with inboard flaps with 262, dated July 8, 2013, of 7,900 total flight
equal to or less than 7,400 total of the Canadair cycles.
flight cycles as of the effective date Challenger TLMC Manual,
of this AD. 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, dated July 8, 2013, after the effective date
greater than 7,500 total flight cycles of the Canadair of this AD, but not
but equal to or less than 11,350 total Challenger TLMC Manual, later than 11,600 total
flight cycles as of the effective date PSP 601-5. flight cycles.
of this AD.
Model CL-600-2A12 (CL-601 Variant) 57-40-00-175 Canadair Challenger TR 5- Within 250 flight cycles
airplanes with outboard flaps having 262, dated July 8, 2013, after the effective date
greater than 11,350 total flight of the Canadair of this AD.
cycles as of the effective date of Challenger TLMC Manual,
this AD. PSP 601-5.
Model CL-600-2A12 (CL-601 Variant) 57-40-00-175 Canadair Challenger TR 5- Before the accumulation
airplanes with outboard flaps having 262, dated July 8, 2013, of 8,000 total flight
equal to or less than 7,500 total of the Canadair cycles.
flight cycles as of the effective date Challenger TLMC Manual,
of this AD. PSP 601-5.
Model CL-600-2B16 (CL-601-3A and -3R 57-40-00-101 Canadair Challenger TR 5- Within 500 flight cycles
Variant) airplanes having S/Ns 5001 276, dated July 8, 2013, after the effective date
through 5194 inclusive with inboard of the Canadair of this AD, but not
flaps having greater than 7,400 total Challenger TLMC Manual, later than 15,100 total
flight cycles but equal to or less PSP 601A-5. flight cycles.
than 14,850 total flight cycles as of
the effective date of this AD.
Model CL-600-2B16 (CL-601-3A and -3R 57-40-00-101 Canadair Challenger TR 5- Within 250 flight cycles.
Variant) airplanes having S/Ns 5001 276, dated July 8, 2013,
through 5194 inclusive, with inboard of the Canadair
flaps having greater than 14,850 total Challenger TLMC Manual,
flight cycles as of the effective date PSP 601A-5.
of this AD.
Model CL-600-2B16 (CL-601-3A and -3R 57-40-00-101 Canadair Challenger TR 5- Before the accumulation
Variant) airplanes having S/Ns 5001 276, dated July 8, 2013, of 7,900 total flight
through 5194 inclusive, with inboard of the Canadair cycles.
flaps having equal to or less than Challenger TLMC Manual,
7,400 total flight cycles as of the PSP 601A-5.
effective date of this AD.

[[Page 45144]]

Model CL-600-2B16 (CL-601-3A and -3R 57-40-00-174 Canadair Challenger TR 5- Within 500 flight cycles
Variant) airplanes having S/Ns 5001 276, dated July 8, 2013, after the effective date
through 5194 inclusive, with outboard of the Canadair of this AD, but no later
flaps having greater than 7,500 total Challenger TLMC Manual, than 11,600 total flight
flight cycles but equal to or less PSP 601A-5. cycles.
than 11,350 total flight cycles as of
the effective date of this AD.
Model CL-600-2B16 (CL-601-3A and -3R 57-40-00-174 Canadair Challenger TR 5- Within 250 flight cycles
Variant) airplanes having S/Ns 5001 276, dated July 8, 2013, after the effective date
through 5194 inclusive, with outboard of the Canadair of this AD.
flaps having greater than 11,350 total Challenger TLMC Manual,
flight cycles as of the effective date PSP 601A-5.
of this AD.
Model CL-600-2B16 (CL-601-3A and -3R 57-40-00-174 Canadair Challenger TR 5- Before the accumulation
Variant) airplanes having S/Ns 5001 276, dated July 8, 2013, of 8,000 total flight
through 5194 inclusive, with outboard of the Canadair cycles.
flaps having equal to or less than Challenger TLMC Manual,
7,500 total flight cycles as of the PSP 601A-5.
effective date of this AD.
Model CL-600-2B16 (CL-604 Variant) 57-50-00-121 Section 5-10-30 of Part 2, Before the accumulation
airplanes with inboard and outboard ``Airworthiness of 7,800 total flight
flaps. Limitations,'' of cycles, or within 500
Bombardier CL-604 TLMC flight cycles after the
Manual, Revision 8, dated effective date of this
July 8, 2013. AD, whichever occurs
later.
Model CL-600-2B16 (CL-604 Variant) 57-52-01-102 Section 5-10-30 of Part 2, At the time specified in
airplanes, S/Ns 5301 through 5665 ``Airworthiness the task.
inclusive. Limitations,'' of
Bombardier CL-604 TLMC
Manual, Revision 8, dated
July 8, 2013.
Model CL-600-2B16 (CL-604 Variant) 57-50-00-121 and Section 5-10-30 of Part 2, At the applicable time
airplanes, S/Ns 5701 through 5953 57-52-01-102 ``Airworthiness specified in the tasks.
inclusive. Limitations,'' of
Bombardier CL-605 TLMC
Manual, Revision 8, dated
July 8, 2013.
----------------------------------------------------------------------------------------------------------------

(h) Lug Edge Measurement and Inspection

At the applicable times specified in table 2 to paragraphs (h)
and (i)(1) of this AD, measure the forward lug edge distance of all
flap hinge boxes, in accordance with the applicable service bulletin
specified in paragraphs (h) and (i)(1) of this AD; 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.

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.

[[Page 45145]]

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.
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 dated October 2, 2013.
months after the
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 dated November 15,
months after the 2013.
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
paragraphs (h) and (i)(1) of this AD, 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 3 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, Engine and Propeller
Directorate, 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,
Engine and Propeller Directorate, FAA; or TCCA; or Bombardier,
Inc.'s TCCA Design Approval Organization (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 (AMOC) in accordance with the
procedures specified in paragraph (k) of this AD.

(k) 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

[[Page 45146]]

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 Design Approval Organization (DAO). If
approved by the DAO, the approval must include the DAO-authorized
signature.

(l) 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 https://www.regulations.gov by searching
for and locating Docket No. FAA-2014-0491.
(2) 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 https://www.bombardier.com. 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.

Issued in Renton, Washington, on July 23, 2014.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-18401 Filed 8-1-14; 8:45 am]
BILLING CODE 4910-13-P

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