80 FR 24200 - Airworthiness Directives; Bombardier, Inc. Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 83 (April 30, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 83 (April 30, 2015)
| Page Range | 24200-24207 | |
| FR Document | 2015-07802 |
[Federal Register Volume 80, Number 83 (Thursday, April 30, 2015)] [Rules and Regulations] [Pages 24200-24207] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-07802] ----------------------------------------------------------------------- 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
![24200 Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations
(j) Related Information SUMMARY: We are adopting a new SUPPLEMENTARY INFORMATION:
Refer to Mandatory Continuing airworthiness directive (AD) for certain
Discussion
Airworthiness Information (MCAI) Canadian Bombardier, Inc. Model CL–600–1A11
Airworthiness Directive CF–2014–16, dated (CL–600), CL–600–2A12 (CL–601), and We issued a notice of proposed
June 11, 2014, for related information. This CL–600–2B16 (CL–601–3A, CL–601–3R, rulemaking (NPRM) to amend 14 CFR
MCAI may be found in the AD docket on the and CL–604 Variants) airplanes. This part 39 by adding an AD that would
Internet at http://www.regulations.gov/ AD was prompted by a determination apply to certain Bombardier, Inc. Model
#!documentDetail;D=FAA-2015-0074-0003. CL–600–1A11 (CL–600), CL–600–2A12
that the forward lugs of the flap hinge
(k) Material Incorporated by Reference box might not conform to engineering (CL–601), and CL–600–2B16 (CL–601–
(1) The Director of the Federal Register drawings, which could result in 3A, CL–601–3R, and CL–604 Variants)
approved the incorporation by reference premature fatigue cracking. This AD airplanes. The NPRM published in the
(IBR) of the service information listed in this requires revising the maintenance or Federal Register on August 4, 2014 (79
paragraph under 5 U.S.C. 552(a) and 1 CFR inspection program to include new FR 45140). The NPRM was prompted by
part 51. airworthiness limitations tasks; and a determination that the forward lugs of
(2) You must use this service information measuring the forward lug edge distance the flap hinge box might not conform to
as applicable to do the actions required by of each flap hinge box, inspecting for engineering drawings, which could
this AD, unless this AD specifies otherwise. result in premature fatigue cracking.
cracking and damage (i.e., deformation
(i) Bombardier Temporary Revision ALI–
0472, dated February 27, 2014, to Section 1– or bearing failure) of the forward lug The NPRM proposed to require revising
32 of Part 2, Airworthiness Limitations, of edge of each flap hinge box, and the maintenance or inspection program
the Bombardier CRJ Series Regional Jet repairing any cracking or damage if to include new airworthiness
Maintenance Requirements Manual, CSP B– necessary. We are issuing this AD to limitations tasks; and measuring the
053. detect and correct non-conforming flap forward lug edge distance of each flap
(ii) Reserved. hinge box forward lugs, which could hinge box, inspecting for cracking and
(3) For service information identified in result in failure of the lugs and damage (i.e., deformation or bearing
this AD, contact Bombardier, Inc., 400 Côte- detachment of the flap hinge box and failure) of the forward lug edge of each
Vertu Road West, Dorval, Québec H4S 1Y9, consequent detachment of the flap flap hinge box, and repairing any
Canada; telephone 514–855–5000; fax 514–
surface. cracking or damage if necessary. We are
855–7401; email thd.crj@
aero.bombardier.com; Internet http:// DATES: This AD becomes effective June issuing this AD to detect and correct
www.bombardier.com. 4, 2015. non-conforming flap hinge box forward
(4) You may view this service information The Director of the Federal Register lugs, which could result in failure of the
at the FAA, Transport Airplane Directorate, approved the incorporation by reference lugs and detachment of the flap hinge
1601 Lind Avenue SW., Renton, WA. For of certain publications listed in this AD box and consequent detachment of the
information on the availability of this as of June 4, 2015. flap surface.
material at the FAA, call 425–227–1221. Transport Canada Civil Aviation
(5) You may view this service information ADDRESSES: You may examine the AD
docket on the Internet at http:// (TCCA), which is the aviation authority
that is incorporated by reference at the
www.regulations.gov/ for Canada, has issued Canadian
National Archives and Records
Administration (NARA). For information on #!docketDetail;D=FAA-2014-0491 or in Airworthiness Directive CF–2014–01,
the availability of this material at NARA, call person at the Docket Management dated January 3, 2014 (referred to after
202–741–6030, or go to: http:// Facility, U.S. Department of this as the Mandatory Continuing
www.archives.gov/federal-register/cfr/ibr- Transportation, Docket Operations, M– Airworthiness Information, or ‘‘the
locations.html. 30, West Building Ground Floor, Room MCAI’’), to correct an unsafe condition
Issued in Renton, Washington, on April 14, W12–140, 1200 New Jersey Avenue SE., for certain Bombardier, Inc. Model CL–
2015. Washington, DC. 600–1A11 (CL–600), CL–600–2A12 (CL–
Michael Kaszycki, For service information identified in 601), and CL–600–2B16 (CL–601–3A,
Acting Manager, Transport Airplane this AD, contact Bombardier, Inc., 400 CL–601–3R, and CL–604 Variants)
Directorate, Aircraft Certification Service. Côte-Vertu Road West, Dorval, Québec airplanes. The MCAI states:
[FR Doc. 2015–09813 Filed 4–29–15; 8:45 am] H4S 1Y9, Canada; telephone 514–855– The aeroplane manufacturer has
BILLING CODE 4910–13–P
5000; fax 514–855–7401; email thd.crj@ determined that the flap hinge box forward
aero.bombardier.com; Internet http:// lugs edge distance may not conform to the
www.bombardier.com. You may view engineering drawings. Non-conforming flap
this referenced service information at hinge box forward lugs may result in
DEPARTMENT OF TRANSPORTATION premature fatigue cracking.
the FAA, Transport Airplane Failure of the lugs could lead to the
Federal Aviation Administration Directorate, 1601 Lind Avenue SW., detachment of the flap hinge box and
Renton, WA. For information on the consequently the detachment of the flap
14 CFR Part 39 availability of this material at the FAA, surface. The loss of a flap surface could
call 425–227–1221. It is also available adversely affect the continued safe operation
[Docket No. FAA–2014–0491; Directorate on the Internet at http:// of the aeroplane.
Identifier 2014–NM–023–AD; Amendment This [Canadian] AD mandates the
www.regulations.gov by searching for
39–18130; AD 2015–07–02] incorporation of new Time Limits/
and locating Docket No. FAA–2014–
Maintenance Checks (TLMC) Airworthiness
RIN 2120–AA64 0491. Limitations (AWL) tasks, and the
FOR FURTHER INFORMATION CONTACT: measurement [and inspection for cracking
Airworthiness Directives; Bombardier, Ricardo Garcia, Aerospace Engineer, and damage] of the forward lug edge distance
rmajette on DSK2VPTVN1PROD with RULES
Inc. Airplanes Airframe and Mechanical Systems of each flap hinge-box and rectification as
Branch, ANE–171, FAA, New York required.
AGENCY: Federal Aviation
Administration (FAA), Department of Aircraft Certification Office, 1600 Corrective actions include repairing
Transportation (DOT). Stewart Avenue, Suite 410, Westbury, damage and cracking. You may examine
NY 11590; telephone 516–228–7331; fax the MCAI in the AD docket on the
ACTION: Final rule.
516–794–5531. Internet at http://www.regulations.gov/
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![24202 Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations
Bombardier CL–605 Time Limits/ operators to be $401,625, or $3,825 per Docket Operations office (telephone
Maintenance Checks Manual, Revision product. 800–647–5527) is in the ADDRESSES
8, dated July 8, 2013. This service We have received no definitive data section.
information describes an airworthiness that would enable us to provide cost
estimates for the cost of parts or on- List of Subjects in 14 CFR Part 39
limitations task and compliance times
for inspecting the forward lugs of the condition actions specified in this AD. Air transportation, Aircraft, Aviation
inboard flap hinge box for Bombardier, safety, Incorporation by reference,
Authority for This Rulemaking
Inc. Model CL–600–2B16 (CL–604 Safety.
Variant) airplanes, having S/Ns 5701 Title 49 of the United States Code
through 5953 inclusive. specifies the FAA’s authority to issue Adoption of the Amendment
• Task 57–50–00–121, Special rules on aviation safety. Subtitle I,
section 106, describes the authority of Accordingly, under the authority
Detailed Inspection of the Forward Lugs
the FAA Administrator. ‘‘Subtitle VII: delegated to me by the Administrator,
of the Inboard Flap Hinge Box, of
Aviation Programs,’’ describes in more the FAA amends 14 CFR part 39 as
Section 5–10–30 of Part 2,
detail the scope of the Agency’s follows:
‘‘Airworthiness Limitations,’’ of
Bombardier CL–604 Time Limits/ authority.
We are issuing this rulemaking under PART 39—AIRWORTHINESS
Maintenance Checks Manual, Revision DIRECTIVES
20, dated July 8, 2013. This service the authority described in ‘‘Subtitle VII,
information describes an airworthiness Part A, Subpart III, Section 44701:
General requirements.’’ Under that ■ 1. The authority citation for part 39
limitations task and compliance times continues to read as follows:
for inspecting the forward lugs of the section, Congress charges the FAA with
inboard flap hinge box of Bombardier, promoting safe flight of civil aircraft in Authority: 49 U.S.C. 106(g), 40113, 44701.
Inc. Model CL–600–2B16 (CL–604 air commerce by prescribing regulations
for practices, methods, and procedures § 39.13 [Amended]
Variant) airplanes, having S/Ns 5301
through 5665 inclusive. the Administrator finds necessary for ■ 2. The FAA amends § 39.13 by adding
• Task 57–52–01–102, Special safety in air commerce. This regulation the following new airworthiness
Detailed Inspection of the Hinge—Box is within the scope of that authority directive (AD):
Forward Lugs of the Outboard Flap, of because it addresses an unsafe condition
that is likely to exist or develop on 2015–07–02 Bombardier, Inc.: Amendment
Section 5–10–30 of Part 2, 39–18130. Docket No. FAA–2014–0491;
‘‘Airworthiness Limitations,’’ of products identified in this rulemaking
action. Directorate Identifier 2014–NM–023–AD.
Bombardier CL–605 Time Limits/
Maintenance Checks Manual, Revision (a) Effective Date
Regulatory Findings
8, dated July 8, 2013. This service This AD becomes effective June 4, 2015.
We determined that this AD will not
information describes an airworthiness (b) Affected ADs
have federalism implications under
limitations task and compliance times
Executive Order 13132. This AD will None.
for inspecting the forward lugs of the
not have a substantial direct effect on
outboard flap hinge box of Bombardier, (c) Applicability
the States, on the relationship between
Inc. Model CL–600–2B16 (CL–604 This AD applies to the airplanes identified
the national government and the States,
Variant) airplanes, having S/Ns 5701 in paragraphs (c)(1) through (c)(4) of this AD,
or on the distribution of power and
through 5953 inclusive. certificated in any category.
responsibilities among the various
• Task 57–52–01–102, Special (1) Bombardier, Inc. Model CL–600–1A11
levels of government.
Detailed Inspection of the Hinge—Box For the reasons discussed above, I (CL–600) airplanes, serial numbers 1004
Forward Lugs of the Outboard Flap, of certify that this AD: through 1085 inclusive.
Section 5–10–30 of Part 2, 1. Is not a ‘‘significant regulatory (2) Bombardier, Inc. Model CL–600–2A12
‘‘Airworthiness Limitations,’’ of (CL–601) airplanes, serial numbers 3001
action’’ under Executive Order 12866;
Bombardier CL–604 Time Limits/ through 3066 inclusive.
2. Is not a ‘‘significant rule’’ under the
Maintenance Checks Manual, Revision (3) Bombardier, Inc. Model CL–600–2B16
DOT Regulatory Policies and Procedures (CL–601–3A and CL–601–3R Variants)
20, dated July 8, 2013. This service (44 FR 11034, February 26, 1979);
information describes an airworthiness airplanes, serial numbers 5001 through 5194
3. Will not affect intrastate aviation in inclusive.
limitations task and compliance times Alaska; and (4) Bombardier, Inc. Model CL–600–2B16
for inspecting the forward lugs of the 4. Will not have a significant (CL–604 Variants) airplanes, serial numbers
outboard flap hinge box of Bombardier, economic impact, positive or negative, 5301 through 5665 inclusive, and 5701
Inc. Model CL–600–2B16 (CL–604 on a substantial number of small entities through 5953 inclusive.
Variant) airplanes, having S/Ns 5301 under the criteria of the Regulatory
through 5665 inclusive. (d) Subject
Flexibility Act.
This service information is reasonably Air Transport Association (ATA) of
available; see ADDRESSES for ways to Examining the AD Docket America Code 57, Wings.
access this service information. You may examine the AD docket on (e) Reason
the Internet at http://
Costs of Compliance This AD was prompted by a determination
www.regulations.gov/
that the forward lugs of the flap hinge box
We estimate that this AD affects 105 #!docketDetail;D=FAA-2014-0491; or in
might not conform to engineering drawings,
airplanes of U.S. registry. person at the Docket Management
rmajette on DSK2VPTVN1PROD with RULES
which could result in premature fatigue
We also estimate that it will take Facility between 9 a.m. and 5 p.m., cracking. We are issuing this AD to detect
about 45 work-hours per product to Monday through Friday, except Federal and correct non-conforming flap hinge box
comply with the basic requirements of holidays. The AD docket contains this forward lugs, which could result in failure of
this AD. The average labor rate is $85 AD, the regulatory evaluation, any the lugs and detachment of the flap hinge box
per work-hour. Based on these figures, comments received, and other and consequent detachment of the flap
we estimate the cost of this AD on U.S. information. The street address for the surface.
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![Federal Register / Vol. 80, No. 83 / Thursday, April 30, 2015 / Rules and Regulations 24207
(4) You may view this service information #!docketDetail;D=FAA-2014-0589 or in Several operators of A320 family
at the FAA, Transport Airplane Directorate, person at the Docket Management aeroplanes have reported finding cracks on
1601 Lind Avenue SW., Renton, WA. For Facility, U.S. Department of the forward corner fittings of engine pylon aft
information on the availability of this secondary structures, on the lateral face
Transportation, Docket Operations, M– (lateral panel side). In some cases, these
material at the FAA, call 425–227–1221.
(5) You may view this service information
30, West Building Ground Floor, Room cracks had propagated onto the forward face
that is incorporated by reference at the W12–140, 1200 New Jersey Avenue SE., (Rib 11 side). Investigation results have
National Archives and Records Washington, DC. highlighted that these cracks are initiated by
Administration (NARA). For information on For service information identified in stress corrosion.
the availability of this material at NARA, call this AD, contact Airbus, Airworthiness This condition, if not detected and
202–741–6030, or go to: http:// corrected, could lead to loss (i.e. detachment
Office—EIAS, 1 Rond Point Maurice
www.archives.gov/federal-register/cfr/ibr- from the aeroplane) of the lower fairing
Bellonte, 31707 Blagnac Cedex, France; attachment at Rib 10, and/or loss of the aft
locations.html.
telephone +33 5 61 93 36 96; fax +33 5 fixed fairing with the movable fairing,
Issued in Renton, Washington, on March 61 93 44 51; email account.airworth- possibly resulting in * * * [damage to the
25, 2015. eas@airbus.com; Internet http:// airplane].
Michael Kaszycki, www.airbus.com. You may view this For the reasons described above, this
Acting Manager, Transport Airplane referenced service information at the [EASA] AD requires repetitive detailed
Directorate, Aircraft Certification Service. FAA, Transport Airplane Directorate, inspections (DI) of the right hand (RH) Part
Number (P/N) D54530014201 and left hand
[FR Doc. 2015–07802 Filed 4–29–15; 8:45 am] 1601 Lind Avenue SW., Renton, WA.
(LH) P/N D54530014200 corner fittings of
BILLING CODE 4910–13–P For information on the availability of engine pylon aft secondary structures (pre-
this material at the FAA, call 425–227– mod 38067 or pre-Airbus Service Bulletin
1221. It is also available on the Internet (SB) A320–54–1019) to detect cracks or
DEPARTMENT OF TRANSPORTATION at http://www.regulations.gov by deformation in the splicing area with corner
searching for and locating Docket No. fitting between Ribs 11–12 and, depending
Federal Aviation Administration FAA–2014–0589. on findings, replacement of the corner
fittings.
14 CFR Part 39 FOR FURTHER INFORMATION CONTACT: This [EASA] AD also recognizes that
Sanjay Ralhan, Aerospace Engineer, replacement of the corner fittings with
[Docket No. FAA–2014–0589; Directorate International Branch, ANM–116, improved parts (as per Airbus SB A320–54–
Identifier 2014–NM–069–AD; Amendment Transport Airplane Directorate, FAA, 1019) constitutes a terminating action for the
39–18148; AD 2015–09–03] repetitive DI required by this [EASA] AD.
1601 Lind Avenue SW., Renton, WA
RIN 2120–AA64 98057–3356; telephone 425–227–1405; You may examine the MCAI in the
fax 425–227–1149. AD docket on the Internet at http://
Airworthiness Directives; Airbus www.regulations.gov/
Airplanes SUPPLEMENTARY INFORMATION:
#!documentDetail;D=FAA-2014-0589-
Discussion 0003.
AGENCY: Federal Aviation
Administration (FAA), Department of We issued a notice of proposed Comments
Transportation (DOT). rulemaking (NPRM) to amend 14 CFR We gave the public the opportunity to
ACTION: Final rule. part 39 by adding an AD that would participate in developing this AD. The
apply to certain Airbus Model A318– following presents the comments
SUMMARY: We are adopting a new 111 and –112 airplanes and Model
airworthiness directive (AD) for certain received on the NPRM (79 FR 52267,
A319, A320, and A321 series airplanes. September 3, 2014) and the FAA’s
Airbus Model A318–111 and –112 The NPRM published in the Federal
airplanes and Model A319, A320, and response to each comment.
Register on September 3, 2014 (79 FR
A321 series airplanes. This AD was 52267). The NPRM was prompted by Requests to Reference Revised Service
prompted by reports of cracks on the reports of cracks on the forward corner Bulletins
forward corner fittings of engine pylon fittings of engine pylon aft secondary United Airlines and US Airways
aft secondary structures. This AD structures. The NPRM proposed to requested that we revise the NPRM (79
requires repetitive inspections of certain require repetitive inspections of certain FR 52267, September 3, 2014) to
forward corner fittings of the pylon aft forward corner fittings of the pylon aft reference Airbus Service Bulletin A320–
secondary structures, and corrective secondary structures, and corrective 54–1019, Revision 02, dated April 15,
actions if necessary. This AD also actions if necessary. The NPRM also 2014, in lieu of Airbus Service Bulletin
provides optional terminating action for proposed to provide optional A320–54–1019, Revision 01, dated April
the repetitive inspections. We are terminating action for the repetitive 10, 2008. United Airlines also requested
issuing this AD to detect and correct inspections. We are issuing this AD to that we revise the NPRM to reference
detachment of the lower fairing detect and correct detachment of the Airbus Service Bulletin A320–54–1022,
attachment and/or loss of the aft fixed lower fairing attachment and/or loss of Revision 03, dated April 15, 2014, in
fairing with the movable fairing from the aft fixed fairing with the movable lieu of Airbus Service Bulletin A320–
the airplane in flight, which could result fairing from the airplane in flight, which 54–1022, Revision 02, dated July 12,
in damage to the airplane. could result in damage to the airplane. 2013.
DATES: This AD becomes effective June The European Aviation Safety Agency We agree with the commenters’
4, 2015. (EASA), which is the Technical Agent requests to reference revised service
The Director of the Federal Register for the Member States of the European bulletins. Airbus Service Bulletin A320–
rmajette on DSK2VPTVN1PROD with RULES
approved the incorporation by reference Union, has issued EASA Airworthiness 54–1019, Revision 02, dated April 15,
of certain publications listed in this AD Directive 2014–0064, dated March 14, 2014, improves the test procedures, and
as of June 4, 2015. 2014 (referred to after this as the Airbus Service Bulletin A320–54–1022,
ADDRESSES: You may examine the AD Mandatory Continuing Airworthiness Revision 03, dated April 15, 2014,
docket on the Internet at http:// Information, or ‘‘the MCAI’’), to correct specifies that certain actions in the
www.regulations.gov/ an unsafe condition. The MCAI states: Accomplishment Instructions are
VerDate Sep<11>2014 14:33 Apr 29, 2015 Jkt 235001 PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 E:\FR\FM\30APR1.SGM 30APR1](https://thefederalregister.org/doc/80_FR_24283/page/8.svg)
Document Created: 2018-02-21 10:15:02
Document Modified: 2018-02-21 10:15:02
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD becomes effective June 4, 2015. | |
| 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. | |
| FR Citation | 80 FR 24200 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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