Airworthiness Directives; Bombardier, Inc. Airplanes, 20181-20185 [2015-08463]

Download as PDF Federal Register / Vol. 80, No. 72 / Wednesday, April 15, 2015 / Proposed Rules mstockstill on DSK4VPTVN1PROD with PROPOSALS (iii) If the minimum thickness of the wall is 0.130 inch or greater and less than 0.140 inch and the machining defect is not present, within 48 months or 3,000 flight cycles after the effective date of this AD, whichever occurs first, replace the inboard actuator attach fitting of the outboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2343, Revision 1, dated June 23, 2014. (iv) If the minimum thickness of the wall is 0.130 inch or greater and less than 0.140 inch and the machining defect is present, before further flight, replace the inboard actuator attach fitting of the outboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2343, Revision 1, dated June 23, 2014. (2) Replace the inboard actuator attach fitting of the outboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2343, Revision 1, dated June 23, 2014. (k) New Inspection or Replacement for Certain Fittings That Were Previously Inspected For airplanes with any inboard actuator attach fitting having P/N 65B08564–7 installed and the fitting was inspected in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2343, dated September 12, 2013: Within 24 months after the effective date of this AD, do the actions specified in paragraph (k)(1) or (k)(2) of this AD. (1) Do a detailed inspection of the inner conical section for machining defects only, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2343, Revision 1, dated June 23, 2014. (i) If any machining defect is found and the minimum thickness of the wall is 0.140 inch or greater: Before further flight, do the actions specified in paragraph (k)(1)(i)(A) or (k)(1)(i)(B) of this AD. (A) Overhaul the inboard actuator attach fitting of the outboard flap, in accordance with Part 5 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2343, Revision 1, dated June 23, 2014. (B) Replace the inboard actuator attach fitting of the outboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2343, Revision 1, dated June 23, 2014. (ii) If any machining defect is found and the minimum thickness of the wall is 0.130 inch or greater and less than 0.140 inch: Before further flight, replace the inboard actuator attach fitting of the outboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2343, Revision 1, dated June 23, 2014. (iii) If no machining defect is found and the minimum thickness of the wall is 0.130 inch or greater and less than 0.140 inch: Within 48 months or 3,000 flight cycles after VerDate Sep<11>2014 17:16 Apr 14, 2015 Jkt 235001 the effective date of this AD, whichever occurs first, replace the inboard actuator attach fitting of the outboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2343, Revision 1, dated June 23, 2014. (iv) If a machining defect is or is not found and the minimum thickness of the wall is less than 0.130 inch: Before further flight, replace the inboard actuator attach fitting of the outboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2343, Revision 1, dated June 23, 2014. (2) Replace the inboard actuator attach fitting of the outboard flap, in accordance with Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2343, Revision 1, dated June 23, 2014. (l) Part Installation Limitation As of the effective date of this AD, no actuator attach fitting having P/N 65B08564– 7 that meets the requirements of CONDITION 5 or CONDITION 6 defined in Boeing Alert Service Bulletin 747–57A2343, dated September 12, 2013, may be installed on any airplane unless the inspection specified in paragraph (k)(1) of this AD is done and the applicable actions in paragraphs (k)(1)(i), (k)(1)(ii), (k)(1)(iii), and (k)(1)(iv) are done within the applicable times specified in paragraphs (k)(1)(i), (k)(1)(ii), (k)(1)(iii), and (k)(1)(iv) of this AD. (m) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), 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 manager of the ACO, send it to the attention of the person identified in paragraph (n)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. (2) 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. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) If any service information contains steps that are identified as RC (Required for Compliance), those steps must be done to comply with this AD; any steps that are not identified as RC are recommended. Those steps that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 20181 approval of an AMOC provided the steps identified as RC can be done and the airplane can be put back in a serviceable condition. Any substitutions or changes to steps identified as RC require approval of an AMOC. (5) AMOCs approved for AD 2013–23–03, Amendment 39–17658 (78 FR 68345, November 14, 2013) are approved as AMOCs for the corresponding provisions of this AD. (n) Related Information (1) For more information about this AD, contact Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057– 3356; phone: 425–917–6428; fax: 425–917– 6590; email: nathan.p.weigand@faa.gov. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206– 544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on April 6, 2015. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–08464 Filed 4–14–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0827; Directorate Identifier 2014–NM–008–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2011–07– 10, for certain Bombardier, Inc. Model BD–100–1A10 (Challenger 300) airplanes. AD 2011–07–10 currently requires revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness; doing detailed visual inspections; removing discrepant material; cleaning the surfaces of the valves, the plug of the sensing port, and the cabin pressuresensing port plug; securing the insulation; installing a new safety valve, SUMMARY: E:\FR\FM\15APP1.SGM 15APP1 20182 Federal Register / Vol. 80, No. 72 / Wednesday, April 15, 2015 / Proposed Rules and replacing certain cabin pressuresensing port plugs. Since we issued AD 2011–07–10, we have received reports of in-flight loss of cabin pressurization that was attributed to partial blockage of a safety valve cabin pressure-sensing port in conjunction with a failed safety valve manometric capsule. This proposed AD would retain all requirements of AD 2011–07–10. This proposed AD would also require a detailed visual inspection of both safety valves and the surrounding area for foreign material, room temperature vulcanizing (RTV) silicone, contamination, foam on the bulkhead structure, tape or insulation, and loose material; and corrective actions if necessary. We are proposing this AD to detect and correct blockage of a safety valve cabin pressure-sensing port, which could result in loss of cabin pressure. We must receive comments on this proposed AD by June 1, 2015. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://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 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. DATES: mstockstill on DSK4VPTVN1PROD with PROPOSALS Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 0827; 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 VerDate Sep<11>2014 17:16 Apr 14, 2015 Jkt 235001 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: Luke Walker, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, NY Aircraft Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7363; 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–2015–0827; Directorate Identifier 2014–NM–008–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 http:// 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 On March 21, 2011, we issued AD 2011–07–10, Amendment 39–16647 (76 FR 17758, March 31, 2011). AD 2011– 07–10 requires actions intended to address an unsafe condition on certain Bombardier, Inc. Model BD–100–1A10 (Challenger 300) airplanes. AD 2011– 07–10 superseded AD 2010–10–18, Amendment 39 16297 (75 FR 27406, May 17, 2010). Since we issued AD 2011–07–10, Amendment 39–16647 (76 FR 17758, March 31, 2011), we have received reports of in-flight loss of cabin pressurization that were attributed to partial blockage of a safety valve cabin pressure-sensing port in conjunction with a failed safety valve manometric capsule. Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2010–06R1, dated August 8, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 Investigation of a high altitude loss of cabin pressurization on a BD–100–1A10 aeroplane determined that it was caused by a partial blockage of a safety valve cabin pressure-sensing port, in conjunction with a dormant failure/leakage of the safety valve manometric capsule. The blockage, caused by accumulation of lint/dust on the grid of the port plug, did not allow sufficient airflow through the cabin pressure-sensing port to compensate for the rate of leakage from the manometric capsule, resulting in the opening of the safety valve. It was also determined that failure of the manometric capsule alone would not result in the opening of the safety valve. The original issue of this [Canadian] AD mandated a revision of the maintenance schedule, the cleaning of the safety valves, the removal of material from the area surrounding the safety valves and the modification of the safety valves with a gridless cabin pressure-sensing port plug. Since the original issue of this [Canadian] AD, there have been two additional reported events of in-flight loss of cabin pressurization that were attributed to partial blockage of a safety valve cabin pressure-sensing port in conjunction with a failed safety valve manometric capsule. Bombardier Aerospace has determined that aeroplanes with a particular interior installation require improved instructions to clean the safety valves and their surrounding area. In addition, Aircraft Maintenance Manual tasks have been updated to ensure that inspection of the safety valves and their surrounding is carried out after any maintenance action. Revision 1 of this [Canadian] AD is issued to mandate inspection and cleaning of the safety valves and their surrounding area on the affected aeroplanes. Corrective actions include removing foreign material, cleaning surfaces of the safety valve and bulkhead, installing a new safety valve, removing loose tape, and trimming insulation. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 0827. Related Service Information Under 1 CFR Part 51 Bombardier has issued Service Bulletin 100–25–21, Revision 02, dated July 25, 2013. The service information describes procedures for a detailed visual inspection of both safety valves and the surrounding area for foreign material, RTV silicone, contamination, foam on the bulkhead structure, tape or insulation, and loose material, and applicable corrective actions. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. This service information is reasonably available; see ADDRESSES for ways to access this service information. E:\FR\FM\15APP1.SGM 15APP1 Federal Register / Vol. 80, No. 72 / Wednesday, April 15, 2015 / Proposed Rules mstockstill on DSK4VPTVN1PROD with PROPOSALS 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 design. 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 (n)(1) of this AD. The request should include a description of changes to the required inspections that will ensure the continued operational safety of the airplane. Costs of Compliance We estimate that this proposed AD affects 67 airplanes of U.S. registry. The actions required by AD 2011–07– 10, Amendment 39–16647 (76 FR 17758, March 31, 2011), and retained in this proposed AD take about 10 workhours per product, at an average labor rate of $85 per work-hour. Required parts cost $0 per product. Based on these figures, the estimated cost of the actions that were required by AD 2011– 07–10 is $850 per product. We also estimate that it would take about 4 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 $22,780, or $340 per product. According to the manufacturer, all of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue VerDate Sep<11>2014 17:16 Apr 14, 2015 Jkt 235001 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 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 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 removing Airworthiness Directives (AD) ■ PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 20183 2011–07–10, Amendment 39–16647 (76 FR 17758, March 31, 2011), and adding the following new AD: Bombardier, Inc.: Docket No. FAA–2015– 0827; Directorate Identifier 2014–NM– 008–AD. (a) Comments Due Date We must receive comments by June 1, 2015. (b) Affected ADs This AD replaces AD 2011–07–10, Amendment 39–16647 (76 FR 17758, March 31, 2011). (c) Applicability This AD applies to Bombardier, Inc. Model BD–100–1A10 (Challenger 300) airplanes, certificated in any category, serial numbers 20001 through 20274. (d) Subject Air Transport Association (ATA) of America Code 25, Equipment/Furnishings. (e) Reason This AD was prompted by reports of inflight loss of cabin pressurization that were attributed to partial blockage of a safety valve cabin pressure-sensing port in conjunction with a failed safety valve manometric capsule. We are issuing this AD to detect and correct blockage of a safety valve cabin pressure-sensing port, which could result in loss of cabin pressure. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Revision This paragraph restates the requirements of paragraph (g) of AD 2011–07–10, Amendment 39–16647 (76 FR 17758, March 31, 2011), with no changes. For all airplanes: Within 30 days after June 1, 2010 (the effective date of AD 2010–10–18, Amendment 39–16297 (75 FR 27406, May 17, 2010)), revise the Airworthiness Limitations section of the Instructions for Continued Airworthiness by incorporating Tasks 21–31– 09–101 and 21–31–09–102 in the Bombardier Temporary Revision (TR) 5–2–53, dated October 1, 2009, to Section 5–10–40, ‘‘Certification Maintenance Requirements,’’ in Part 2 of Chapter 5 of Bombardier Challenger 300 BD–100 Time Limits/ Maintenance Checks. (1) For the new tasks identified in Bombardier TR 5–2–53, dated October 1, 2009: For airplanes identified in the ‘‘Phasein’’ section of Bombardier TR 5–2–53, dated October 1, 2009, the initial compliance with the new tasks must be carried out in accordance with the phase-in schedule detailed in Bombardier TR 5–2–53, dated October 1, 2009, except where that TR specifies a compliance time from the date of the TR, this AD requires compliance within the specified time after June 1, 2010 (the effective date of AD 2010–10–18, Amendment 39–16297 (75 FR 27406, May 17, 2010)). E:\FR\FM\15APP1.SGM 15APP1 20184 Federal Register / Vol. 80, No. 72 / Wednesday, April 15, 2015 / Proposed Rules mstockstill on DSK4VPTVN1PROD with PROPOSALS Thereafter, except as provided by paragraph (n)(1) of this AD, no alternative to the task intervals may be used. (2) When information in Bombardier TR 5– 2–53, dated October 1, 2009, has been included in the general revisions of the applicable Airworthiness Limitations section, that TR may be removed from that Airworthiness Limitations section of the Instructions for Continued Airworthiness. (h) Retained Inspection, Removal, Cleaning, and Installation This paragraph restates the requirements of paragraph (h) of AD 2011–07–10, Amendment 39–16647 (76 FR 17758, March 31, 2011), with certain clarified compliance times. For airplanes having S/Ns 20003 through 20173 inclusive, 20176, and 20177: Within 50 flight hours after June 1, 2010 (the effective date of AD 2010–10–18, Amendment 39–16297 (75 FR 27406, May 17, 2010)), do a detailed visual inspection of the safety valves and surrounding areas for discrepant material (e.g., foreign material surrounding the safety valves, room temperature vulcanizing (RTV) sealant on safety valves, RTV excess on the bulkhead, tape near the safety valve opening, and, on certain airplanes, insulation near the safety valve opening, and foam in the area surrounding the safety valves) and a detailed visual inspection for contamination (e.g., RTV, dust, or lint) in the safety valve pressure ports, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 100–25–14, dated June 30, 2008 (for airplanes having S/Ns 20124, 20125, 20128, 20134, 20139, 20143, 20146, 20148 through 20173 inclusive, 20176, and 20177); or Bombardier Service Bulletin 100– 25–21, dated June 30, 2008 (for airplanes having S/Ns 20003 through 20123 inclusive, 20126, 20127, 20129 to 20133 inclusive, 20135 to 20138 inclusive, 20140 through 20142 inclusive, 20144, 20145, and 20147). (1) If any discrepant material is found during the detailed visual inspection, before further flight, remove the discrepant material, clean the surfaces of the valves, and secure the insulation, as applicable, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 100–25–14, dated June 30, 2008 (for airplanes having S/Ns 20124, 20125, 20128, 20134, 20139, 20143, 20146, 20148 through 20173 inclusive, 20176, and 20177); or Bombardier Service Bulletin 100–25–21, dated June 30, 2008 (for airplanes having S/Ns 20003 through 20123 inclusive, 20126, 20127, 20129 through 20133 inclusive, 20135 through 20138 inclusive, 20140 through 20142 inclusive, 20144, 20145, and 20147). (2) If contamination (e.g., RTV, dust, or lint) is found on the safety valve pressure sensing ports, before further flight, do a detailed visual inspection of the outside and inside diameters of the pressure sensing port conduit for the presence of RTV; and before further flight do the actions specified in paragraph (h)(2)(i) and (h)(2)(ii) of this AD, as applicable; in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 100–25–14, dated June 30, 2008 (for airplanes having S/Ns 20124, 20125, 20128, 20134, 20139, 20143, 20146, VerDate Sep<11>2014 17:16 Apr 14, 2015 Jkt 235001 20148 through 20173 inclusive, 20176, and 20177); or Bombardier Service Bulletin 100– 25–21, dated June 30, 2008 (for airplanes having S/Ns 20003 through 20123 inclusive, 20126, 20127, 20129 through 20133 inclusive, 20135 through 20138 inclusive, 20140 through 20142 inclusive, 20144, 20145, and 20147). (i) If no RTV is found, clean the plug of the sensing port. (ii) If any RTV is found, install a new safety valve. (i) Retained Cleaning for Certain Airplanes This paragraph restates the requirements of paragraph (i) of AD 2011–07–10, Amendment 39–16647 (76 FR 17758, March 31, 2011), with no changes. For airplanes having S/Ns 20174, 20175, 20178 through 20189 inclusive, 20191 through 20228 inclusive, 20230 through 20232 inclusive, 20235, 20237, 20238, 20241, 20244, 20247, 20249 through 20251 inclusive, 20254, 20256 and 20259: Within 50 flight hours after June 1, 2010 (the effective date of AD 2010–10–18, Amendment 39–16297 (75 FR 27406, May 17, 2010)), clean the cabin pressure-sensing port plug in both safety valves, in accordance with Paragraph 2.B., ‘‘Part A—Modification— Cleaning,’’ of the Accomplishment Instructions of Bombardier Service Bulletin A100–21–08, dated June 18, 2009. (j) Retained Cleaning for Certain Other Airplanes This paragraph restates the requirements of paragraph (j) of AD 2011–07–10, Amendment 39–16647 (76 FR 17758, March 31, 2011), with no changes. For airplanes having S/Ns 20003 through 20189 inclusive, 20191 through 20228 inclusive, 20230 through 20232 inclusive, 20235, 20237, 20238, 20241, 20244, 20247, 20249 through 20251 inclusive, 20254, 20256, and 20259: Within 50 flight hours after June 1, 2010 (the effective date of AD 2010–10–18, Amendment 39–16297 (75 FR 27406, May 17, 2010)), clean the cabin pressure-sensing port plug in both safety valves, in accordance with Paragraph 2.B., ‘‘Part A—Modification— Cleaning,’’ of the Accomplishment Instructions of Bombardier Service Bulletin A100–21–08, dated June 18, 2009. Repeat the cleaning thereafter at intervals not to exceed 50 flight hours until the actions specified by paragraph (k) of this AD are completed. (k) Retained Replacement This paragraph restates the requirements of paragraph (k) of AD 2011–07–10, Amendment 39–16647 (76 FR 17758, March 31, 2011), with no changes. For airplanes having S/Ns 20003 through 20189 inclusive, 20191 through 20228 inclusive, 20230 through 20232 inclusive, 20235, 20237, 20238, 20241, 20244, 20247, 20249 through 20251 inclusive, 20254, 20256, and 20259: Within 12 months after May 5, 2011 (the effective date of AD 2011–07–10), replace the cabin pressure-sensing port plug having part number (P/N) 2844–060 in both safety valves with a new gridless plug having P/N 2844– 19 and re-identify the safety valves, in accordance with Paragraph 2.C., ‘‘Part B— Modification—Replacement,’’ of the Accomplishment Instructions of Bombardier Service Bulletin A100–21–08, dated June 18, PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 2009. Doing the actions in paragraph (k) of this AD terminates the repetitive cleanings required by paragraph (j) of this AD. (l) New Requirement of This AD: Inspection and Cleaning For airplanes having S/Ns 20003 through 20123 inclusive, 20126, 20127, 20129 through 20133 inclusive, 20135 through 20138 inclusive, 20140 through 20142 inclusive, 20144, 20145, and 20147: Within 500 flight hours or 15 months after the effective date of this AD, whichever occurs first, do a detailed visual inspection of both safety valves and the surrounding area for foreign material, RTV silicone, contamination, foam on the bulkhead structure, tape or insulation, and loose material, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 100–25–21, Revision 02, dated July 25, 2013. Do all applicable corrective actions before further flight, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 100–25–21, Revision 02, dated July 25, 2013. (m) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (l) of this AD, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 100–25–21, Revision 01, dated February 26, 2013, which is not incorporated by reference in this AD. (n) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office (ACO), ANE–170, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the New York 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: As of the effective date of this AD, 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, 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. (o) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2010–06R1, dated August 8, 2013, for related information. E:\FR\FM\15APP1.SGM 15APP1 Federal Register / Vol. 80, No. 72 / Wednesday, April 15, 2015 / Proposed Rules This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2015–0827. (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 http:// 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 April 6, 2015. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–08463 Filed 4–14–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF LABOR Occupational Safety and Health Administration 29 CFR 1910, 1926 [Docket No. OSHA–2014–0018] RIN 1218–AC90 Communication Tower Safety Occupational Safety and Health Administration (OSHA), Labor. ACTION: Request for Information (RFI). AGENCY: OSHA is aware of employee safety risks in communication tower construction and maintenance activities and is requesting information from the public on these risks. This RFI requests information that will assist the Agency in determining what steps, if any, it can take to prevent injuries and fatalities during tower work. DATES: Comments and other information must be submitted (postmarked, sent, or received) by June 15, 2015. All submissions must bear a postmark or provide other evidence of the submission date. ADDRESSES: Submit comments and additional materials, identified by Docket No. OSHA–2014–0018, using any of the following methods: Electronically: Submit comments and attachments electronically at http:// www.regulations.gov, which is the Federal eRulemaking Portal. Follow the instructions online for making electronic submissions. Facsimile: Commenters may fax submissions, including attachments, that are no longer than 10 pages in length to the OSHA Docket Office at mstockstill on DSK4VPTVN1PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 17:16 Apr 14, 2015 Jkt 235001 (202) 693–1648; OSHA does not require hard copies of these documents. Commenters must submit lengthy attachments that supplement these documents (e.g., studies, journal articles), by the applicable deadline, to the OSHA Docket Office, Technical Data Center, Room N–2625, U.S. Department of Labor, 200 Constitution Avenue NW., Washington, DC 20210. These attachments must clearly identify the commenter’s name, the date of submission, the title of this RFI (Communication Tower Safety), and the docket number (OSHA–2014–0018) so the Agency can attach them to the appropriate facsimile submission. Regular mail, express delivery, hand (courier) delivery, or messenger service: Submit a copy of comments and any additional material (e.g., studies, journal articles) to the OSHA Docket Office, Docket No. OSHA–2014–0018, Technical Data Center, Room N–2625, U.S. Department of Labor, 200 Constitution Avenue NW., Washington, DC 20210; telephone (202) 693–2350 (TTY number: (877) 889–5627). Note that security procedures may significantly delay the Agency’s receipt of comments and other written materials sent by regular mail. Contact the OSHA Docket Office for information about security procedures concerning delivery of materials by express delivery, hand delivery, or messenger service. The hours of operation for the OSHA Docket Office are 8:15 a.m.—4:45 p.m., E.T. Instructions: All submissions must include the Agency’s name (OSHA), the title of this RFI (Communication Tower Safety), and the docket number (OSHA– 2014–0018). The Agency places all submissions, including any personal information provided, in the public docket without change; this information will be available online at http:// www.regulations.gov. Therefore, the Agency cautions commenters about submitting materials that they do not want made available to the public or that contain personal information (either about themselves or others) such as Social Security numbers, birth dates, and medical data. Docket: To read or download submissions or other material in the docket, go to: http:// www.regulations.gov, or to the OSHA Docket Office at the address above. While the electronic docket at http:// www.regulations.gov lists documents in the docket, some information (e.g., copyrighted material) is not publicly available to read or download through this Web site. All submissions, including copyrighted material, are available for inspection at the OSHA Docket Office. Contact the OSHA Docket PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 20185 Office for assistance in locating docket submissions. FOR FURTHER INFORMATION CONTACT: Information regarding this Request for Information is available from the following sources: Press inquiries: Contact Frank Meilinger, Director, OSHA Office of Communications, Room N–3647, U.S. Department of Labor, 200 Constitution Avenue NW., Washington, DC 20210; email: meilinger.francis2@dol.gov; telephone: (202) 693–1999. General and technical information: Contact Erin Patterson or Jessica Douma, Office of Construction Standards and Guidance, OSHA Directorate of Construction, Room N–3468, U.S. Department of Labor, 200 Constitution Avenue NW., Washington, DC 20210; emails: Patterson.Erin@dol.gov or Douma.Jessica@dol.gov; telephone: (202) 693–2020; fax: (202) 693–1689. Copies of this Federal Register notice: Electronic copies are available at http://www.regulations.gov. This Federal Register notice, as well as news releases and other relevant information, also are available at OSHA’s Web page at http://www.osha.gov. SUPPLEMENTARY INFORMATION: Table of Contents I. Exhibits Referenced in This RFI II. Background A. Introduction B. Hazards and Incidents C. Training and Certification D. Applicable OSHA Standards E. Consensus Standards and State Standards III. Request for Data, Information, and Comments IV. Authority and Signature I. Exhibits Referenced in This RFI Documents referenced by OSHA in this request for information, other than OSHA standards and Federal Register notices, are in Docket No. OSHA–2014– 0018 (Communication Tower Safety). The docket is available at http:// www.regulations.gov, the Federal eRulemaking Portal. For additional information on submitting items to, or accessing items in, the docket, please refer to the Addresses section of this RFI. II. Background A. Introduction Communication towers are tall structures that carry antennas for wireless, cellular, radio, or broadcast television communications. There are three common types of communication towers: free-standing or lattice towers, guyed towers, and monopole towers. E:\FR\FM\15APP1.SGM 15APP1

Agencies

[Federal Register Volume 80, Number 72 (Wednesday, April 15, 2015)]
[Proposed Rules]
[Pages 20181-20185]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-08463]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0827; Directorate Identifier 2014-NM-008-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 supersede Airworthiness Directive (AD) 2011-07-
10, for certain Bombardier, Inc. Model BD-100-1A10 (Challenger 300) 
airplanes. AD 2011-07-10 currently requires revising the Airworthiness 
Limitations section of the Instructions for Continued Airworthiness; 
doing detailed visual inspections; removing discrepant material; 
cleaning the surfaces of the valves, the plug of the sensing port, and 
the cabin pressure-sensing port plug; securing the insulation; 
installing a new safety valve,

[[Page 20182]]

and replacing certain cabin pressure-sensing port plugs. Since we 
issued AD 2011-07-10, we have received reports of in-flight loss of 
cabin pressurization that was attributed to partial blockage of a 
safety valve cabin pressure-sensing port in conjunction with a failed 
safety valve manometric capsule. This proposed AD would retain all 
requirements of AD 2011-07-10. This proposed AD would also require a 
detailed visual inspection of both safety valves and the surrounding 
area for foreign material, room temperature vulcanizing (RTV) silicone, 
contamination, foam on the bulkhead structure, tape or insulation, and 
loose material; and corrective actions if necessary. We are proposing 
this AD to detect and correct blockage of a safety valve cabin 
pressure-sensing port, which could result in loss of cabin pressure.

DATES: We must receive comments on this proposed AD by June 1, 2015.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://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 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
0827; 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: Luke Walker, Aerospace Engineer, 
Airframe and Mechanical Systems Branch, ANE-171, FAA, NY Aircraft 
Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, 
NY 11590; telephone 516-228-7363; 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-2015-0827; 
Directorate Identifier 2014-NM-008-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 http://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

    On March 21, 2011, we issued AD 2011-07-10, Amendment 39-16647 (76 
FR 17758, March 31, 2011). AD 2011-07-10 requires actions intended to 
address an unsafe condition on certain Bombardier, Inc. Model BD-100-
1A10 (Challenger 300) airplanes. AD 2011-07-10 superseded AD 2010-10-
18, Amendment 39 16297 (75 FR 27406, May 17, 2010).
    Since we issued AD 2011-07-10, Amendment 39-16647 (76 FR 17758, 
March 31, 2011), we have received reports of in-flight loss of cabin 
pressurization that were attributed to partial blockage of a safety 
valve cabin pressure-sensing port in conjunction with a failed safety 
valve manometric capsule.
    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian Airworthiness Directive CF-
2010-06R1, dated August 8, 2013 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for the specified products. The MCAI 
states:

    Investigation of a high altitude loss of cabin pressurization on 
a BD-100-1A10 aeroplane determined that it was caused by a partial 
blockage of a safety valve cabin pressure-sensing port, in 
conjunction with a dormant failure/leakage of the safety valve 
manometric capsule. The blockage, caused by accumulation of lint/
dust on the grid of the port plug, did not allow sufficient airflow 
through the cabin pressure-sensing port to compensate for the rate 
of leakage from the manometric capsule, resulting in the opening of 
the safety valve. It was also determined that failure of the 
manometric capsule alone would not result in the opening of the 
safety valve.
    The original issue of this [Canadian] AD mandated a revision of 
the maintenance schedule, the cleaning of the safety valves, the 
removal of material from the area surrounding the safety valves and 
the modification of the safety valves with a gridless cabin 
pressure-sensing port plug.
    Since the original issue of this [Canadian] AD, there have been 
two additional reported events of in-flight loss of cabin 
pressurization that were attributed to partial blockage of a safety 
valve cabin pressure-sensing port in conjunction with a failed 
safety valve manometric capsule.
    Bombardier Aerospace has determined that aeroplanes with a 
particular interior installation require improved instructions to 
clean the safety valves and their surrounding area. In addition, 
Aircraft Maintenance Manual tasks have been updated to ensure that 
inspection of the safety valves and their surrounding is carried out 
after any maintenance action.
    Revision 1 of this [Canadian] AD is issued to mandate inspection 
and cleaning of the safety valves and their surrounding area on the 
affected aeroplanes.

    Corrective actions include removing foreign material, cleaning 
surfaces of the safety valve and bulkhead, installing a new safety 
valve, removing loose tape, and trimming insulation. You may examine 
the MCAI in the AD docket on the Internet at http://www.regulations.gov 
by searching for and locating Docket No. FAA-2015-0827.

Related Service Information Under 1 CFR Part 51

    Bombardier has issued Service Bulletin 100-25-21, Revision 02, 
dated July 25, 2013. The service information describes procedures for a 
detailed visual inspection of both safety valves and the surrounding 
area for foreign material, RTV silicone, contamination, foam on the 
bulkhead structure, tape or insulation, and loose material, and 
applicable corrective actions. The actions described in this service 
information are intended to correct the unsafe condition identified in 
the MCAI. This service information is reasonably available; see 
ADDRESSES for ways to access this service information.

[[Page 20183]]

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 design.
    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 (n)(1) of this AD. The request 
should include a description of changes to the required inspections 
that will ensure the continued operational safety of the airplane.

Costs of Compliance

    We estimate that this proposed AD affects 67 airplanes of U.S. 
registry.
    The actions required by AD 2011-07-10, Amendment 39-16647 (76 FR 
17758, March 31, 2011), and retained in this proposed AD take about 10 
work-hours per product, at an average labor rate of $85 per work-hour. 
Required parts cost $0 per product. Based on these figures, the 
estimated cost of the actions that were required by AD 2011-07-10 is 
$850 per product.
    We also estimate that it would take about 4 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 $22,780, or $340 
per product.
    According to the manufacturer, all of the costs of this proposed AD 
may be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

Authority for This Rulemaking

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

Regulatory Findings

    We determined that this 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 removing Airworthiness Directives (AD) 
2011-07-10, Amendment 39-16647 (76 FR 17758, March 31, 2011), and 
adding the following new AD:

Bombardier, Inc.: Docket No. FAA-2015-0827; Directorate Identifier 
2014-NM-008-AD.

(a) Comments Due Date

    We must receive comments by June 1, 2015.

(b) Affected ADs

    This AD replaces AD 2011-07-10, Amendment 39-16647 (76 FR 17758, 
March 31, 2011).

(c) Applicability

    This AD applies to Bombardier, Inc. Model BD-100-1A10 
(Challenger 300) airplanes, certificated in any category, serial 
numbers 20001 through 20274.

(d) Subject

    Air Transport Association (ATA) of America Code 25, Equipment/
Furnishings.

(e) Reason

    This AD was prompted by reports of in-flight loss of cabin 
pressurization that were attributed to partial blockage of a safety 
valve cabin pressure-sensing port in conjunction with a failed 
safety valve manometric capsule. We are issuing this AD to detect 
and correct blockage of a safety valve cabin pressure-sensing port, 
which could result in loss of cabin pressure.

(f) Compliance

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

(g) Retained Revision

    This paragraph restates the requirements of paragraph (g) of AD 
2011-07-10, Amendment 39-16647 (76 FR 17758, March 31, 2011), with 
no changes. For all airplanes: Within 30 days after June 1, 2010 
(the effective date of AD 2010-10-18, Amendment 39-16297 (75 FR 
27406, May 17, 2010)), revise the Airworthiness Limitations section 
of the Instructions for Continued Airworthiness by incorporating 
Tasks 21-31-09-101 and 21-31-09-102 in the Bombardier Temporary 
Revision (TR) 5-2-53, dated October 1, 2009, to Section 5-10-40, 
``Certification Maintenance Requirements,'' in Part 2 of Chapter 5 
of Bombardier Challenger 300 BD-100 Time Limits/Maintenance Checks.
    (1) For the new tasks identified in Bombardier TR 5-2-53, dated 
October 1, 2009: For airplanes identified in the ``Phase-in'' 
section of Bombardier TR 5-2-53, dated October 1, 2009, the initial 
compliance with the new tasks must be carried out in accordance with 
the phase-in schedule detailed in Bombardier TR 5-2-53, dated 
October 1, 2009, except where that TR specifies a compliance time 
from the date of the TR, this AD requires compliance within the 
specified time after June 1, 2010 (the effective date of AD 2010-10-
18, Amendment 39-16297 (75 FR 27406, May 17, 2010)).

[[Page 20184]]

    Thereafter, except as provided by paragraph (n)(1) of this AD, 
no alternative to the task intervals may be used.
    (2) When information in Bombardier TR 5-2-53, dated October 1, 
2009, has been included in the general revisions of the applicable 
Airworthiness Limitations section, that TR may be removed from that 
Airworthiness Limitations section of the Instructions for Continued 
Airworthiness.

(h) Retained Inspection, Removal, Cleaning, and Installation

    This paragraph restates the requirements of paragraph (h) of AD 
2011-07-10, Amendment 39-16647 (76 FR 17758, March 31, 2011), with 
certain clarified compliance times. For airplanes having S/Ns 20003 
through 20173 inclusive, 20176, and 20177: Within 50 flight hours 
after June 1, 2010 (the effective date of AD 2010-10-18, Amendment 
39-16297 (75 FR 27406, May 17, 2010)), do a detailed visual 
inspection of the safety valves and surrounding areas for discrepant 
material (e.g., foreign material surrounding the safety valves, room 
temperature vulcanizing (RTV) sealant on safety valves, RTV excess 
on the bulkhead, tape near the safety valve opening, and, on certain 
airplanes, insulation near the safety valve opening, and foam in the 
area surrounding the safety valves) and a detailed visual inspection 
for contamination (e.g., RTV, dust, or lint) in the safety valve 
pressure ports, in accordance with the Accomplishment Instructions 
of Bombardier Service Bulletin 100-25-14, dated June 30, 2008 (for 
airplanes having S/Ns 20124, 20125, 20128, 20134, 20139, 20143, 
20146, 20148 through 20173 inclusive, 20176, and 20177); or 
Bombardier Service Bulletin 100-25-21, dated June 30, 2008 (for 
airplanes having S/Ns 20003 through 20123 inclusive, 20126, 20127, 
20129 to 20133 inclusive, 20135 to 20138 inclusive, 20140 through 
20142 inclusive, 20144, 20145, and 20147).
    (1) If any discrepant material is found during the detailed 
visual inspection, before further flight, remove the discrepant 
material, clean the surfaces of the valves, and secure the 
insulation, as applicable, in accordance with the Accomplishment 
Instructions of Bombardier Service Bulletin 100-25-14, dated June 
30, 2008 (for airplanes having S/Ns 20124, 20125, 20128, 20134, 
20139, 20143, 20146, 20148 through 20173 inclusive, 20176, and 
20177); or Bombardier Service Bulletin 100-25-21, dated June 30, 
2008 (for airplanes having S/Ns 20003 through 20123 inclusive, 
20126, 20127, 20129 through 20133 inclusive, 20135 through 20138 
inclusive, 20140 through 20142 inclusive, 20144, 20145, and 20147).
    (2) If contamination (e.g., RTV, dust, or lint) is found on the 
safety valve pressure sensing ports, before further flight, do a 
detailed visual inspection of the outside and inside diameters of 
the pressure sensing port conduit for the presence of RTV; and 
before further flight do the actions specified in paragraph 
(h)(2)(i) and (h)(2)(ii) of this AD, as applicable; in accordance 
with the Accomplishment Instructions of Bombardier Service Bulletin 
100-25-14, dated June 30, 2008 (for airplanes having S/Ns 20124, 
20125, 20128, 20134, 20139, 20143, 20146, 20148 through 20173 
inclusive, 20176, and 20177); or Bombardier Service Bulletin 100-25-
21, dated June 30, 2008 (for airplanes having S/Ns 20003 through 
20123 inclusive, 20126, 20127, 20129 through 20133 inclusive, 20135 
through 20138 inclusive, 20140 through 20142 inclusive, 20144, 
20145, and 20147).
    (i) If no RTV is found, clean the plug of the sensing port.
    (ii) If any RTV is found, install a new safety valve.

(i) Retained Cleaning for Certain Airplanes

    This paragraph restates the requirements of paragraph (i) of AD 
2011-07-10, Amendment 39-16647 (76 FR 17758, March 31, 2011), with 
no changes. For airplanes having S/Ns 20174, 20175, 20178 through 
20189 inclusive, 20191 through 20228 inclusive, 20230 through 20232 
inclusive, 20235, 20237, 20238, 20241, 20244, 20247, 20249 through 
20251 inclusive, 20254, 20256 and 20259: Within 50 flight hours 
after June 1, 2010 (the effective date of AD 2010-10-18, Amendment 
39-16297 (75 FR 27406, May 17, 2010)), clean the cabin pressure-
sensing port plug in both safety valves, in accordance with 
Paragraph 2.B., ``Part A--Modification--Cleaning,'' of the 
Accomplishment Instructions of Bombardier Service Bulletin A100-21-
08, dated June 18, 2009.

(j) Retained Cleaning for Certain Other Airplanes

    This paragraph restates the requirements of paragraph (j) of AD 
2011-07-10, Amendment 39-16647 (76 FR 17758, March 31, 2011), with 
no changes. For airplanes having S/Ns 20003 through 20189 inclusive, 
20191 through 20228 inclusive, 20230 through 20232 inclusive, 20235, 
20237, 20238, 20241, 20244, 20247, 20249 through 20251 inclusive, 
20254, 20256, and 20259: Within 50 flight hours after June 1, 2010 
(the effective date of AD 2010-10-18, Amendment 39-16297 (75 FR 
27406, May 17, 2010)), clean the cabin pressure-sensing port plug in 
both safety valves, in accordance with Paragraph 2.B., ``Part A--
Modification--Cleaning,'' of the Accomplishment Instructions of 
Bombardier Service Bulletin A100-21-08, dated June 18, 2009. Repeat 
the cleaning thereafter at intervals not to exceed 50 flight hours 
until the actions specified by paragraph (k) of this AD are 
completed.

(k) Retained Replacement

    This paragraph restates the requirements of paragraph (k) of AD 
2011-07-10, Amendment 39-16647 (76 FR 17758, March 31, 2011), with 
no changes. For airplanes having S/Ns 20003 through 20189 inclusive, 
20191 through 20228 inclusive, 20230 through 20232 inclusive, 20235, 
20237, 20238, 20241, 20244, 20247, 20249 through 20251 inclusive, 
20254, 20256, and 20259: Within 12 months after May 5, 2011 (the 
effective date of AD 2011-07-10), replace the cabin pressure-sensing 
port plug having part number (P/N) 2844-060 in both safety valves 
with a new gridless plug having P/N 2844-19 and re-identify the 
safety valves, in accordance with Paragraph 2.C., ``Part B--
Modification--Replacement,'' of the Accomplishment Instructions of 
Bombardier Service Bulletin A100-21-08, dated June 18, 2009. Doing 
the actions in paragraph (k) of this AD terminates the repetitive 
cleanings required by paragraph (j) of this AD.

(l) New Requirement of This AD: Inspection and Cleaning

    For airplanes having S/Ns 20003 through 20123 inclusive, 20126, 
20127, 20129 through 20133 inclusive, 20135 through 20138 inclusive, 
20140 through 20142 inclusive, 20144, 20145, and 20147: Within 500 
flight hours or 15 months after the effective date of this AD, 
whichever occurs first, do a detailed visual inspection of both 
safety valves and the surrounding area for foreign material, RTV 
silicone, contamination, foam on the bulkhead structure, tape or 
insulation, and loose material, in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 100-25-
21, Revision 02, dated July 25, 2013. Do all applicable corrective 
actions before further flight, in accordance with the Accomplishment 
Instructions of Bombardier Service Bulletin 100-25-21, Revision 02, 
dated July 25, 2013.

(m) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(l) of this AD, if those actions were performed before the effective 
date of this AD using Bombardier Service Bulletin 100-25-21, 
Revision 01, dated February 26, 2013, which is not incorporated by 
reference in this AD.

(n) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York Aircraft Certification Office (ACO), ANE-170, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the New York 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: As of the effective date of 
this AD, 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, 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.

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian Airworthiness Directive CF-2010-06R1, dated August 
8, 2013, for related information.

[[Page 20185]]

This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-
2015-0827.
    (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 http://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 April 6, 2015.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-08463 Filed 4-14-15; 8:45 am]
 BILLING CODE 4910-13-P