81 FR 55353 - Airworthiness Directives; Bombardier, Inc. Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 161 (August 19, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 161 (August 19, 2016)
| Page Range | 55353-55358 | |
| FR Document | 2016-19480 |
[Federal Register Volume 81, Number 161 (Friday, August 19, 2016)] [Rules and Regulations] [Pages 55353-55358] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-19480] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-3986; Directorate Identifier 2015-NM-057-AD; Amendment 39-18613; AD 2016-16-15] RIN 2120-AA64 Airworthiness Directives; Bombardier, Inc. Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400, -401, and -402 airplanes. This AD was prompted by reports of chafing damage due to insufficient clearance on the main landing gear (MLG) stabilizer brace, the nacelle A-frame structure, and the adjacent electrical wiring harnesses. An insufficient fillet radius may also exist on certain airplanes. This AD requires, depending on airplane configuration, an inspection of the nacelle A-frame structure for insufficient fillet radius; an inspection for cracking of affected structure, and rework or repair if necessary, and rework of the nacelle A-frame structure; repetitive inspections of the nacelle A-frame structure and the MLG stabilizer brace for insufficient clearance and damage, and repair if necessary, and rework of the nacelle A-frame structure, which would terminate the repetitive inspections; installation of new stop brackets and a shim on each MLG stabilizer brace assembly; and rework of the electrical wiring harnesses in the nacelle area. We are issuing this AD to [[Page 55354]] detect and correct chafing damage and subsequent premature cracking and fracture of the nacelle A-frame structure, which could result in failure of the MLG stabilizer brace and loss of the MLG down-lock indication, which could adversely affect the safe landing of the airplane. DATES: This AD is effective September 23, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of September 23, 2016. ADDRESSES: For Bombardier service information identified in this final rule, contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375- 4000; fax 416-375-4539; email [email protected]; Internet http://www.bombardier.com. For Goodrich service information identified in this AD, contact Goodrich Corporation, Landing Gear, 1400 South Service Road, West Oakville, ON, Canada L6L 5Y7; phone: 905-825-1568; email: [email protected]; Internet: http://www.goodrich.com/TechPubs. 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-2015- 3986. 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- 3986; 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 Office (telephone 800-647-5527) is 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 20590. FOR FURTHER INFORMATION CONTACT: Aziz Ahmed, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7329; 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 DHC-8-400, -401, and -402 airplanes. The NPRM published in the Federal Register on October 19, 2015 (80 FR 63147) (``the NPRM''). The NPRM was prompted by reports of chafing damage due to insufficient clearance on the MLG stabilizer brace, the nacelle A-frame structure, and the adjacent electrical wiring harnesses. An insufficient fillet radius may also exist on certain airplanes. The NPRM proposed to require, depending on airplane configuration, an inspection of the nacelle A-frame structure for insufficient fillet radius; an inspection for cracking of affected structure, and rework or repair if necessary, and rework of the nacelle A-frame structure; repetitive inspections of the nacelle A-frame structure and the MLG stabilizer brace for insufficient clearance and damage, and repair if necessary, and rework of the nacelle A-frame structure, which would terminate the repetitive inspections; installation of new stop brackets and a shim on each MLG stabilizer brace assembly; and rework of the electrical wiring harnesses in the nacelle area. We are issuing this AD to detect and correct chafing damage and subsequent premature cracking and fracture of the nacelle A-frame structure, which could result in failure of the MLG stabilizer brace and loss of the MLG down-lock indication, which could adversely affect the safe landing of the airplane. Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF- 2014-45, dated December 23, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition on certain Bombardier, Inc. Model DHC-8- 400, -401, and -402 airplanes. The MCAI states: The aeroplane manufacturer has discovered that an insufficient fillet radius may exist on the flange of the nacelle A-frame structure on certain aeroplanes. There have also been several in- service reports of chafing damage on the main landing gear (MLG) stabilizer brace, the nacelle A-frame structure and its adjacent electrical wiring harnesses due to insufficient clearance. An insufficient fillet radius and chafing damage on the nacelle A-frame structure and MLG stabilizer brace could lead to premature cracking. Fracture of the nacelle A-frame structure or failure of the MLG stabilizer brace could adversely affect the safe landing of the aeroplane. The damage to the electrical wiring harnesses could result in the loss of the MLG downlock indication. This [Canadian] AD mandates the inspection and rework of the nacelle A-frame structure, and the rework of the forward MLG stabilizer brace assembly and the electrical harnesses in the nacelle area adjacent to the A-frame structure. The following actions are required, depending on airplane configuration.A detailed inspection of the nacelle A-frame structure for insufficient fillet radius, an eddy current or fluorescent dye penetrant inspection for cracking of affected structure, and rework or repair if necessary. Rework of the left-hand (LH) side and right-hand (RH) side nacelle A-frame structure, including doing a measurement of the clearance between the fasteners/A-frame structure and MLG stabilizer brace assembly and making sure no fouling condition exists, and repair if necessary. Repetitive detailed inspections of the nacelle A-frame structure and the MLG stabilizer brace for insufficient clearance and damage, and repair if necessary. Rework of the nacelle A-frame structure, including a measurement of the clearance between the A-frame structure and MLG stabilizer brace assembly, and a fluorescent dye penetrant inspection or high frequency eddy current inspection for cracking and repair if necessary, which would terminate the repetitive inspections. Installation of new stop brackets and a shim on each MLG stabilizer brace assembly. Rework of the electrical wiring harnesses in the nacelle area. The rework includes a detailed inspection of the conduit assembly for certain conditions and repair if any condition is found, replacement of damaged conduit, a measurement of the clearance between the stabilizer brace and electrical harness on both LH and RH nacelles to make sure there is 0.100 inch (2.54 millimeters (mm)) minimum clearance between the MLG stabilizer brace, and a check for damage on the A-frame structure and MLG stabilizer brace and repair if necessary. 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- 3986. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. [[Page 55355]] Request To Incorporate Revised Service Information and Provide Credit Horizon Air asked that the following revised service information be included in the proposed AD for the applicable actions: Bombardier Service Bulletin 84-54-20, Revision C, dated March 5, 2015. Bombardier Service Bulletin 84-32-112, Revision C, dated April 2, 2015. Bombardier Service Bulletin 84-32-114, Revision B, dated February 3, 2015. Goodrich Service Bulletin 46400-32-102 R2, Revision 2, dated February 17, 2015. Horizon Air pointed out that several of the service documents specified in the proposed AD have been updated, and asserted that the proposed AD should be revised to reference the updated service information. Horizon Air also asked that credit be given for actions done using the previous revisions of the revised service information. We agree with the commenter's requests. No new work is specified by the revised service information; therefore, we have revised the ``Related Service Information under 1 CFR part 51'' section and the applicable requirements of this AD to refer to the updated service information. We have also revised paragraph (m) of this AD to provide credit for certain actions required by this AD, if those actions were performed before the effective date of this AD using earlier revisions of the service information identified previously. Request To Omit Job Set-Up and Close Out Actions Horizon Air asked that we not mandate the ``Job Set-up'' and ``Close Out'' sections of the Accomplishment Instructions of certain service information referenced in the NPRM. Horizon Air stated that these instructions do not directly correct the unsafe condition, but they do restrict an operator's ability to perform other maintenance in conjunction with the instructions that correct the unsafe condition. Horizon Air added that only the section in the Accomplishment Instructions that directly corrects the unsafe condition should be required. We agree with the commenter's request to exclude the ``Job Set-up'' and ``Close Out'' sections of the Accomplishment Instructions of certain service information identified in this AD. Paragraphs (g), (h), (i), and (j) of this AD already identify the specific sections of the Accomplishment Instructions of the applicable service information for doing only the actions that directly address the unsafe condition; therefore, there are no changes necessary in those paragraphs in this regard. However, we have revised paragraph (k) of this AD to specify doing only the actions provided in ``Part B--Procedure,'' of the Accomplishment Instructions of Bombardier Service Bulletin 84-32-114, Revision B, dated February 3, 2015, for the required actions specified in that paragraph. Request To Clarify a Certain Reference Horizon Air asked that we revise the paragraph references in paragraph (l)(1) of the proposed AD for clarity. Horizon Air stated that paragraph (l)(1) of the proposed AD refers to Bombardier ModSum IS4Q5450002, Revision B, dated June 22, 2012, as acceptable for compliance with the actions specified in paragraph (g) of the proposed AD. Horizon Air noted that for greater clarity, the reference should be to paragraph (g)(2) of the proposed AD. We agree with the commenter's request for the reasons provided. We have changed paragraph (l)(1) of this AD to specify that installing specified fasteners on the MLG A-frame, in both LH and RH nacelles, in accordance with Bombardier ModSum IS4Q5450002, Revision B, dated June 22, 2012, is acceptable for compliance with the actions specified in paragraph (g)(2) 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 for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. 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. ModSum IS4Q2400028, Revision B, dated December 11, 2012; and ModSum IS4Q2400029, Revision A, dated July 6, 2012. These modsums describe procedures for rerouting certain electrical harnesses and installing grommets. ModSum IS4Q5450002, Revision B, dated June 22, 2012. This modsum describes procedures for installing specified fasteners on the MLG A-frame, in both the LH and RH nacelles. ModSum IS4Q5450003, Revision C, dated November 29, 2012. This modsum describes procedures for trimming the horizontal and vertical stiffeners on the MLG A frame in both the LH and RH nacelles. Service Bulletin 84-32-112, Revision C, dated April 2, 2015. This service information describes procedures for incorporating Bombardier ModSum 4-902416 by installing new stop brackets and new stop shims for all MLG stabilizer brace assemblies. Service Bulletin 84-32-114, Revision B, dated February 3, 2015. This service information describes procedures for rework of the electrical wiring harnesses in the nacelle area. The rework includes a detailed inspection of the conduit assembly for certain conditions, and repair, replacement of damaged conduit, a measurement of the clearance to make sure there is 0.100 inch (2.54 mm) minimum clearance between the MLG stabilizer brace, and a check for damage on the A-frame structure and MLG stabilizer brace and repair. Service Bulletin 84-54-19, dated April 18, 2013. This service information describes procedures for detailed inspections of the nacelle A-frame structure for insufficient fillet radius, an eddy current or fluorescent dye penetrant inspection for cracking of affected structure, and rework or repair. Service Bulletin 84-54-20, Revision C, dated March 5, 2015. This service information describes procedures for detailed inspections of the nacelle A-frame structure and the MLG stabilizer brace for insufficient clearance and damage, and repair. This service information also describes procedures for rework of the nacelle A-frame structure, including a measurement of the clearance between the A-frame structure and MLG stabilizer brace assembly, and a fluorescent dye penetrant inspection or high frequency eddy current inspection for cracking and repair, which would end the inspections. Service Bulletin 84-54-21, dated May 9, 2013. This service information describes procedures for rework of the LH side and RH side nacelle A-frame structure, including a measurement of the clearance between the fasteners/A-frame structure and MLG stabilizer brace assembly and to make sure no fouling condition exists, and repair. Goodrich has issued the following service information. [[Page 55356]] Service Bulletin 46400-32-102 R2, Revision 2, dated February 17, 2015. This service information describes procedures for installing new stop brackets and new stop shims for all MLG stabilizer brace assemblies. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 80 airplanes of U.S. registry. We also estimate that it takes up to 50 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts will cost $8,452 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be up to $1,016,160, or $12,702 per product. We have received no definitive data that would enable us to provide cost estimates for the 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. 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): 2016-16-15 Bombardier, Inc.: Amendment 39-18613; Docket No. FAA- 2015-3986; Directorate Identifier 2015-NM-057-AD. (a) Effective Date This AD is effective September 23, 2016. (b) Affected ADs None. (c) Applicability This AD applies to Bombardier, Inc. Model DHC-8-400, -401, and - 402 airplanes, certificated in any category, serial numbers (S/Ns) 4001 through 4431 inclusive. (d) Subject Air Transport Association (ATA) of America Code 32, Landing Gear. (e) Reason This AD was prompted by reports of chafing damage due to insufficient clearance on the main landing gear (MLG) stabilizer brace, the nacelle A-frame structure, and the adjacent electrical wiring harnesses. An insufficient fillet radius might also exist on certain airplanes. We are issuing this AD to detect and correct chafing damage and subsequent premature cracking and fracture of the nacelle A-frame structure, which could result in failure of the MLG stabilizer brace and loss of the MLG down-lock indication, which could adversely affect the safe landing of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection, Corrective Actions, and Rework For airplanes having S/Ns 4001 through 4055 inclusive: Do the actions required by paragraphs (g)(1) and (g)(2) of this AD. (1) Within 600 flight hours or 100 days after the effective date of this AD, whichever occurs first: Do a detailed inspection of the left-hand (LH) side and right-hand (RH) side nacelle A-frame structure for insufficient fillet radius, in accordance with ``Part A--Inspection'' of the Accomplishment Instructions of Bombardier Service Bulletin 84-54-19, dated April 18, 2013. If an insufficient fillet radius exists, before further flight, do an eddy current or fluorescent dye penetrant inspection for cracking, in accordance with ``Part A--Inspection'' of the Accomplishment Instructions of Bombardier Service Bulletin 84-54-19, dated April 18, 2013. (i) If any cracking is found: Before further flight, repair using a method approved by the Manager, New York Aircraft Certification Office (ACO), ANE-170, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.'s TCCA Design Approval Organization (DAO). (ii) If no cracking is found: Before further flight, rework the structure, in accordance with ``Part B--Rectification'' of the Accomplishment Instructions of Bombardier Service Bulletin 84-54-19, dated April 18, 2013. (2) Within 6,000 flight hours or 36 months after the effective date of this AD, whichever occurs first: Rework the LH side and RH side nacelle A-frame structure, including doing a measurement of the clearance between the fasteners/A-frame structure and MLG stabilizer brace assembly and making sure no fouling condition exists, in accordance with paragraph 3.B., ``Procedure,'' of the Accomplishment Instructions of Bombardier Service Bulletin 84-54-21, dated May 9, 2013. If the clearance is found to be less than 0.100 inch (2.54 millimeters (mm)) between the fasteners/A-frame structure and MLG stabilizer brace assembly after the rework is done, or a fouling condition exists during the extension of the MLG after rework is done, 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. (h) Repetitive Inspections and Corrective Actions For airplanes having S/Ns 4056 through 4426 inclusive: Within 600 flight hours or 100 days after the effective date of this AD, whichever occurs first, do a detailed inspection of the LH side and RH side nacelle A-frame structure and upper surface of the MLG stabilizer brace for insufficient clearance and damage (e.g., cracking), in accordance with ``Part A--Inspection'' of the Accomplishment Instructions of Bombardier Service Bulletin 84-54-20, Revision C, dated March 5, 2015. If no damage is found and clearance is sufficient: Repeat the inspection thereafter at intervals not to exceed 600 flight hours until the terminating action required by paragraph (i) of this AD has been done. (1) If a clearance less than 0.100 inch (2.54 mm) exists between the A-frame structure [[Page 55357]] and the MLG stabilizer brace assembly in the retracted position, after the rework is done, 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. (2) If any 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. (i) Terminating Action for Certain Airplanes For airplanes having S/Ns 4056 through 4426 inclusive: Within 6,000 flight hours or 36 months after the effective date of this AD, whichever occurs first, rework the LH side and RH side nacelle A- frame structure, including doing a measurement of the clearance between the A-frame structure and MLG stabilizer brace assembly and doing a fluorescent dye penetrant inspection or high frequency eddy current inspection for cracking, in accordance with ``Part B-- Rework'' of the Accomplishment Instructions of Bombardier Service Bulletin 84-54-20, Revision C, dated March 5, 2015. Accomplishment of the actions required by this paragraph terminates the repetitive inspections required by paragraph (h) of this AD. (1) If a clearance less than 0.100 inch (2.54 mm) exists between the A-frame structure and the MLG stabilizer brace assembly in the retracted position, after the rework is done, 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. (2) If any cracking 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. (j) Modification of MLG Stabilizer Brace Assembly For airplanes having S/Ns 4001 through 4431 inclusive with a MLG stabilizer brace assembly having part number (P/N) 46400-27 installed: Within 6,000 flight hours or 36 months after the effective date of this AD, whichever occurs first, incorporate Bombardier ModSum 4-902416 by installing new stop brackets and a new shim on each MLG stabilizer brace assembly, in accordance with paragraph 3.B., ``Procedure,'' of the Accomplishment Instructions of Bombardier Service Bulletin 84-32-112, Revision C, dated April 2, 2015; and Goodrich Service Bulletin 46400-32-102 R2, Revision 2, dated February 17, 2015. (k) Rework of the Electrical Wiring Harnesses For airplanes having S/Ns 4001 through 4411 inclusive: Within 6,000 flight hours or 36 months after the effective date of this AD, whichever occurs first, rework the LH and RH sides of the electrical wiring harnesses in the nacelle area adjacent to the A-frame structure, including doing the actions specified in paragraphs (k)(1) through (k)(4) of this AD, in accordance with ``Part B-- Procedure'' of the Accomplishment Instructions of Bombardier Service Bulletin 84-32-114, Revision B, dated February 3, 2015. If any damage is found on the A-frame structure or MLG stabilizer brace, 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. (1) Doing a detailed inspection of the conduit assembly for the conditions specified in Bombardier Service Bulletin 84-32-114, Revision B, dated February 3, 2015, and, before further flight, repairing if any condition is found. (2) Replacing damaged conduit. (3) Measuring the clearance between the stabilizer brace and electrical harness on both LH and RH nacelles to make sure there is 0.100 inch (2.54 mm) minimum clearance between the MLG stabilizer brace. (4) Checking for damage on the A-frame structure and MLG stabilizer brace. (l) Optional Installations (1) Installing specified fasteners on the MLG A-frame, in both LH and RH nacelles, in accordance with Bombardier ModSum IS4Q5450002, Revision B, dated June 22, 2012, is acceptable for compliance with the actions specified in paragraph (g)(2) of this AD, provided the actions specified in Bombardier ModSum IS4Q5450002 are done within the applicable compliance time specified in paragraph (g) of this AD, except where ModSum IS4Q5450002, Revision B, dated June 22, 2012, specifies to contact Bombardier for reduced clearances, 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. (2) Trimming the horizontal and vertical stiffeners on the MLG A-frame in both LH and RH nacelles, in accordance with Bombardier ModSum IS4Q5450003, Revision C, dated November 29, 2012, is acceptable for compliance with the actions specified in paragraph (i) of this AD, provided the actions specified in Bombardier ModSum IS4Q5450003 are done within the compliance time specified in paragraph (i) of this AD, except where ModSum IS4Q5450003, Revision C, released November 29, 2012, specifies to contact Bombardier for reduced clearances, 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. (3) Rerouting certain electrical harnesses and installing grommets, in accordance with Bombardier ModSum IS4Q2400028, Revision B, dated December 11, 2012 (for S/Ns 4001 through 4098 inclusive); or Bombardier ModSum IS4Q2400029, Revision A, dated July 6, 2012 (for S/Ns 4090 through 4411 inclusive); is acceptable for compliance with the actions specified in paragraph (k) of this AD, provided the actions specified in the applicable modsum are done within the compliance time specified in paragraph (k) of this AD, except where Bombardier ModSum IS4Q2400028, Revision B, dated December 11, 2012; and Bombardier ModSum IS4Q2400029, Revision A, dated July 6, 2012; specify to contact Bombardier to report stabilizer brace or structural damaged findings, 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. (m) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraph (i) of this AD, if those actions were performed before the effective date of this AD using the applicable service information specified in paragraph (m)(1)(i), (m)(1)(ii), or (m)(1)(iii) of this AD. This service information is not incorporated by reference in this AD. (i) Bombardier Service Bulletin 84-54-20, dated April 25, 2013. (ii) Bombardier Service Bulletin 84-54-20, Revision A, dated April 9, 2014. (iii) Bombardier Service Bulletin 84-54-20, Revision B, dated October 2, 2014. (2) This paragraph provides credit for actions required by paragraph (j) of this AD, if those actions were performed before the effective date of this AD using the applicable service information specified in paragraph (m)(2)(i), (m)(2)(ii), (m)(2)(iii), or (m)(2)(iv) of this AD. This service information is not incorporated by reference in this AD. (i) Bombardier Service Bulletin 84-32-112, dated December 20, 2012. (ii) Bombardier Service Bulletin 84-32-112, Revision A, dated April 16, 2014. (iii) Bombardier Service Bulletin 84-32-112, Revision B, dated September 12, 2014. (iv) Goodrich Service Bulletin 46400-32-102 R1, Revision 1, dated June 24, 2013. (3) This paragraph provides credit for actions required by paragraph (k) of this AD, if those actions were performed before the effective date of this AD using the applicable service information specified in paragraph (m)(3)(i) or (m)(3)(ii) of this AD. This service information is not incorporated by reference in this AD. (i) Bombardier Service Bulletin 84-32-114, dated June 6, 2013. (ii) Bombardier Service Bulletin 84-32-114, Revision A, dated September 18, 2013. (n) 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. (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, FAA; or TCCA; or Bombardier, Inc.'s TCCA DAO. If approved by the DAO, the approval must include the DAO-authorized signature. [[Page 55358]] (o) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF-2014-45, dated December 23, 2014, for related information. 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-2015-3986. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (p)(3), (p)(4), and (p)(5) of this AD. (p) 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 ModSum IS4Q2400028, Revision B, dated December 11, 2012. (This document has 33 pages; the first page of the modsum indicates that there are 32 pages.) (ii) Bombardier ModSum IS4Q2400029, Revision A, dated July 6, 2012. (iii) Bombardier ModSum IS4Q5450002, Revision B, dated June 22, 2012. (iv) Bombardier ModSum IS4Q5450003, Revision C, dated November 29, 2012. (v) Bombardier Service Bulletin 84-32-112, Revision C, dated April 2, 2015. (vi) Bombardier Service Bulletin 84-32-114, Revision B, dated February 3, 2015. (vii) Bombardier Service Bulletin 84-54-19, dated April 18, 2013. (viii) Bombardier Service Bulletin 84-54-20, Revision C, dated March 5, 2015. (ix) Bombardier Service Bulletin 84-54-21, dated May 9, 2013. (x) Goodrich Service Bulletin 46400-32-102 R2, Revision 2, dated February 17, 2015. (3) For Bombardier service information identified in this AD, contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; fax 416-375-4539; email [email protected]; Internet http://www.bombardier.com. (4) For Goodrich service information identified in this AD, contact Goodrich Corporation, Landing Gear, 1400 South Service Road, West Oakville, ON, Canada L6L 5Y7; phone: 905-825-1568; email: [email protected]; Internet: http://www.goodrich.com/TechPubs. (5) 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. (6) 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 August 4, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-19480 Filed 8-18-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 161 / Friday, August 19, 2016 / Rules and Regulations 55353
their comment on special conditions no. rechargeable lithium battery 8. Have a means for the flightcrew or
25–612–SC. We provided a detailed installations where the only change is maintenance personnel to determine the
response in special conditions no. 25– either cosmetic or relocating the battery charge state if the battery’s
612–SC and have now clearly defined installation to improve the safety of the function is required for safe operation of
the applicability for these Boeing 737– airplane and occupants. The FAA the airplane.
8 special conditions. One aspect of determined that this exclusion is in the Note: A battery system consists of the
Boeing’s comment that we did not public interest because the need to meet battery and any protective, monitoring, and
address in special conditions no. 25– all of the special conditions might alerting circuitry or hardware inside or
612–SC is that some design changes otherwise deter such design changes outside of the battery. It also includes vents
may not change a lithium battery that involve relocating batteries. A (where necessary) and packaging. For the
installation but affect it, which results cosmetic change is a change in purpose of these special conditions, a
in these special conditions being appearance only, and does not change ‘‘battery’’ and ‘‘battery system’’ are referred to
applicable. For example, adding a heat any function or safety characteristic of as a battery.
source next to a lithium battery can the battery installation. Issued in Renton, Washington, on August
increase its possibility of entering into 12, 2016.
Conclusion
thermal runaway. Lithium battery Michael Kaszycki,
installations affected by design changes This action affects only certain novel
Assistant Manager, Transport Airplane
must meet these special conditions. or unusual design features on one model
Directorate, Aircraft Certification Service.
Some examples of changes that affect of airplane. It is not a rule of general
[FR Doc. 2016–19856 Filed 8–18–16; 8:45 am]
lithium battery installations are those applicability.
BILLING CODE 4910–13–P
that: List of Subjects in 14 CFR Part 25
• Increase the temperatures or
pressures in a battery, Aircraft, Aviation safety, Reporting
and recordkeeping requirements. DEPARTMENT OF TRANSPORTATION
• Increase the electrical load on a
battery, ■ The authority citation for these Federal Aviation Administration
• Increase potential for imbalance special conditions is as follows:
between battery cells, Authority: 49 U.S.C. 106(g), 40113, 44701, 14 CFR Part 39
• Modify protective circuitry for a 44702, 44704.
lithium battery, [Docket No. FAA–2015–3986; Directorate
• Increase the airplane level risk due The Special Conditions Identifier 2015–NM–057–AD; Amendment
to the location of an existing lithium 39–18613; AD 2016–16–15]
Accordingly, the following special
battery. An example is installation of a conditions are part of the type RIN 2120–AA64
new oxygen line next to an existing part certification basis for the Boeing Model
that has a lithium battery. The airplane 737–8 airplane. Airworthiness Directives; Bombardier,
level risk may increase due to the Inc. Airplanes
potential hazard of a lithium battery fire Non-Rechargeable Lithium Battery
in the proximity of oxygen. Installations AGENCY: Federal Aviation
The FAA has determined that Administration (FAA), DOT.
In lieu of § 25.1353(b)(1) through
‘‘uncontrolled’’ in special condition 2 (b)(4) at Amendment 25–123, each non- ACTION: Final rule.
should be ‘‘uncontrollable’’ to more rechargeable lithium battery installation
accurately describe the concern. This SUMMARY: We are adopting a new
must: airworthiness directive (AD) for certain
revision does not change the intended 1. Maintain safe cell temperatures and
meaning of this special condition. Bombardier, Inc. Model DHC–8–400,
pressures under all foreseeable
Except as discussed above, the special –401, and –402 airplanes. This AD was
operating conditions to prevent fire and
conditions are adopted as proposed. prompted by reports of chafing damage
explosion.
2. Prevent the occurrence of self- due to insufficient clearance on the
Applicability main landing gear (MLG) stabilizer
sustaining, uncontrollable increases in
As discussed above, these special temperature or pressure. brace, the nacelle A-frame structure, and
conditions are applicable to the Model 3. Not emit explosive or toxic gases, the adjacent electrical wiring harnesses.
737–8 airplane. Should the applicant either in normal operation or as a result An insufficient fillet radius may also
apply at a later date for a change to the of its failure, that may accumulate in exist on certain airplanes. This AD
type certificate to include another hazardous quantities within the requires, depending on airplane
model incorporating the same novel or airplane. configuration, an inspection of the
unusual design feature, or should any 4. Meet the requirements of § 25.863. nacelle A-frame structure for
other model already included on the 5. Not damage surrounding structure insufficient fillet radius; an inspection
same type certificate be modified to or adjacent systems, equipment, or for cracking of affected structure, and
incorporate the same novel or unusual electrical wiring from corrosive fluids or rework or repair if necessary, and
design feature, these special conditions gases that may escape in such a way as rework of the nacelle A-frame structure;
would apply to that model as well. to cause a major or more-severe failure repetitive inspections of the nacelle A-
These special conditions are only condition. frame structure and the MLG stabilizer
applicable to design changes applied for 6. Have provisions to prevent any brace for insufficient clearance and
after the effective date of the special hazardous effect on airplane structure or damage, and repair if necessary, and
jstallworth on DSK7TPTVN1PROD with RULES
conditions. The existing airplane fleet systems caused by the maximum rework of the nacelle A-frame structure,
and follow-on deliveries of airplanes amount of heat it can generate due to which would terminate the repetitive
with previously certified non- any failure of it or its individual cells. inspections; installation of new stop
rechargeable lithium battery 7. Have a failure sensing and warning brackets and a shim on each MLG
installations are not affected. system to alert the flightcrew if its stabilizer brace assembly; and rework of
These special conditions are not failure affects safe operation of the the electrical wiring harnesses in the
applicable to previously certified non- airplane. nacelle area. We are issuing this AD to
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![55354 Federal Register / Vol. 81, No. 161 / Friday, August 19, 2016 / Rules and Regulations
detect and correct chafing damage and SUPPLEMENTARY INFORMATION: of the aeroplane. The damage to the electrical
subsequent premature cracking and wiring harnesses could result in the loss of
Discussion the MLG downlock indication.
fracture of the nacelle A-frame structure,
which could result in failure of the MLG We issued a notice of proposed This [Canadian] AD mandates the
rulemaking (NPRM) to amend 14 CFR inspection and rework of the nacelle A-frame
stabilizer brace and loss of the MLG structure, and the rework of the forward MLG
down-lock indication, which could part 39 by adding an AD that would
stabilizer brace assembly and the electrical
adversely affect the safe landing of the apply to certain Bombardier, Inc. Model harnesses in the nacelle area adjacent to the
airplane. DHC–8–400, –401, and –402 airplanes. A-frame structure.
DATES: This AD is effective September
The NPRM published in the Federal
Register on October 19, 2015 (80 FR The following actions are required,
23, 2016. depending on airplane configuration.
The Director of the Federal Register 63147) (‘‘the NPRM’’). The NPRM was
prompted by reports of chafing damage • A detailed inspection of the nacelle
approved the incorporation by reference A-frame structure for insufficient fillet
of certain publications listed in this AD due to insufficient clearance on the
MLG stabilizer brace, the nacelle A- radius, an eddy current or fluorescent
as of September 23, 2016. dye penetrant inspection for cracking of
frame structure, and the adjacent
ADDRESSES: For Bombardier service affected structure, and rework or repair
electrical wiring harnesses. An
information identified in this final rule, if necessary.
insufficient fillet radius may also exist
contact Bombardier, Inc., Q-Series
on certain airplanes. The NPRM • Rework of the left-hand (LH) side
Technical Help Desk, 123 Garratt and right-hand (RH) side nacelle A-
proposed to require, depending on
Boulevard, Toronto, Ontario M3K 1Y5, frame structure, including doing a
airplane configuration, an inspection of
Canada; telephone 416–375–4000; fax measurement of the clearance between
the nacelle A-frame structure for
416–375–4539; email the fasteners/A-frame structure and
insufficient fillet radius; an inspection
thd.qseries@aero.bombardier.com; MLG stabilizer brace assembly and
for cracking of affected structure, and
Internet http://www.bombardier.com. making sure no fouling condition exists,
rework or repair if necessary, and
For Goodrich service information and repair if necessary.
rework of the nacelle A-frame structure;
identified in this AD, contact Goodrich
repetitive inspections of the nacelle A- • Repetitive detailed inspections of
Corporation, Landing Gear, 1400 South the nacelle A-frame structure and the
frame structure and the MLG stabilizer
Service Road, West Oakville, ON, MLG stabilizer brace for insufficient
brace for insufficient clearance and
Canada L6L 5Y7; phone: 905–825–1568; clearance and damage, and repair if
damage, and repair if necessary, and
email: jean.breed@goodrich.com; necessary.
rework of the nacelle A-frame structure,
Internet: http://www.goodrich.com/
which would terminate the repetitive • Rework of the nacelle A-frame
TechPubs. You may view this structure, including a measurement of
inspections; installation of new stop
referenced service information at the the clearance between the A-frame
brackets and a shim on each MLG
FAA, Transport Airplane Directorate, structure and MLG stabilizer brace
stabilizer brace assembly; and rework of
1601 Lind Avenue SW., Renton, WA. assembly, and a fluorescent dye
the electrical wiring harnesses in the
For information on the availability of penetrant inspection or high frequency
nacelle area. We are issuing this AD to
this material at the FAA, call 425–227– eddy current inspection for cracking
detect and correct chafing damage and
1221. It is also available on the Internet and repair if necessary, which would
subsequent premature cracking and
at http://www.regulations.gov by terminate the repetitive inspections.
fracture of the nacelle A-frame structure,
searching for and locating Docket No. • Installation of new stop brackets
which could result in failure of the MLG
FAA–2015–3986. and a shim on each MLG stabilizer brace
stabilizer brace and loss of the MLG
assembly.
Examining the AD Docket down-lock indication, which could
• Rework of the electrical wiring
You may examine the AD docket on adversely affect the safe landing of the
harnesses in the nacelle area. The
the Internet at http:// airplane.
Transport Canada Civil Aviation rework includes a detailed inspection of
www.regulations.gov by searching for the conduit assembly for certain
(TCCA), which is the aviation authority
and locating Docket No. FAA–2015– conditions and repair if any condition is
for Canada, has issued Canadian
3986; or in person at the Docket found, replacement of damaged conduit,
Airworthiness Directive CF–2014–45,
Management Facility between 9 a.m. a measurement of the clearance between
dated December 23, 2014 (referred to
and 5 p.m., Monday through Friday, the stabilizer brace and electrical
after this as the Mandatory Continuing
except Federal holidays. The AD docket harness on both LH and RH nacelles to
Airworthiness Information, or ‘‘the
contains this AD, the regulatory make sure there is 0.100 inch (2.54
MCAI’’), to correct an unsafe condition
evaluation, any comments received, and millimeters (mm)) minimum clearance
on certain Bombardier, Inc. Model
other information. The street address for between the MLG stabilizer brace, and
DHC–8–400, –401, and –402 airplanes.
the Docket Office (telephone 800–647– a check for damage on the A-frame
The MCAI states:
5527) is Docket Management Facility, structure and MLG stabilizer brace and
U.S. Department of Transportation, The aeroplane manufacturer has repair if necessary.
Docket Operations, M–30, West discovered that an insufficient fillet radius
may exist on the flange of the nacelle A- You may examine the MCAI in the AD
Building Ground Floor, Room W12–140, docket on the Internet at http://
frame structure on certain aeroplanes. There
1200 New Jersey Avenue SE., have also been several in-service reports of www.regulations.gov by searching for
Washington, DC 20590. chafing damage on the main landing gear and locating Docket No. FAA–2015–
FOR FURTHER INFORMATION CONTACT: Aziz (MLG) stabilizer brace, the nacelle A-frame 3986.
jstallworth on DSK7TPTVN1PROD with RULES
Ahmed, Aerospace Engineer, Airframe structure and its adjacent electrical wiring
and Mechanical Systems Branch, ANE– harnesses due to insufficient clearance. Comments
171, FAA, New York Aircraft An insufficient fillet radius and chafing We gave the public the opportunity to
damage on the nacelle A-frame structure and
Certification Office, 1600 Stewart MLG stabilizer brace could lead to premature participate in developing this AD. The
Avenue, Suite 410, Westbury, NY cracking. Fracture of the nacelle A-frame following presents the comments
11590; telephone 516–228–7329; fax structure or failure of the MLG stabilizer received on the NPRM and the FAA’s
516–794–5531. brace could adversely affect the safe landing response to each comment.
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![55356 Federal Register / Vol. 81, No. 161 / Friday, August 19, 2016 / Rules and Regulations
• Service Bulletin 46400–32–102 R2, 2. Is not a ‘‘significant rule’’ under the (g) Inspection, Corrective Actions, and
Revision 2, dated February 17, 2015. DOT Regulatory Policies and Procedures Rework
This service information describes (44 FR 11034, February 26, 1979); For airplanes having S/Ns 4001 through
procedures for installing new stop 3. Will not affect intrastate aviation in 4055 inclusive: Do the actions required by
brackets and new stop shims for all Alaska; and paragraphs (g)(1) and (g)(2) of this AD.
MLG stabilizer brace assemblies. 4. Will not have a significant (1) Within 600 flight hours or 100 days
economic impact, positive or negative, after the effective date of this AD, whichever
This service information is reasonably occurs first: Do a detailed inspection of the
available because the interested parties on a substantial number of small entities left-hand (LH) side and right-hand (RH) side
have access to it through their normal under the criteria of the Regulatory nacelle A-frame structure for insufficient
course of business or by the means Flexibility Act. fillet radius, in accordance with ‘‘Part A—
identified in the ADDRESSES section. List of Subjects in 14 CFR Part 39 Inspection’’ of the Accomplishment
Instructions of Bombardier Service Bulletin
Costs of Compliance Air transportation, Aircraft, Aviation 84–54–19, dated April 18, 2013. If an
We estimate that this AD affects 80 safety, Incorporation by reference, insufficient fillet radius exists, before further
Safety. flight, do an eddy current or fluorescent dye
airplanes of U.S. registry. penetrant inspection for cracking, in
We also estimate that it takes up to 50 Adoption of the Amendment accordance with ‘‘Part A—Inspection’’ of the
work-hours per product to comply with Accomplishment Instructions of Bombardier
Accordingly, under the authority
the basic requirements of this AD. The Service Bulletin 84–54–19, dated April 18,
delegated to me by the Administrator, 2013.
average labor rate is $85 per work-hour.
the FAA amends 14 CFR part 39 as (i) If any cracking is found: Before further
Required parts will cost $8,452 per
follows: flight, repair using a method approved by the
product. Based on these figures, we
Manager, New York Aircraft Certification
estimate the cost of this AD on U.S. PART 39—AIRWORTHINESS Office (ACO), ANE–170, FAA; or Transport
operators to be up to $1,016,160, or DIRECTIVES Canada Civil Aviation (TCCA); or
$12,702 per product. Bombardier, Inc.’s TCCA Design Approval
We have received no definitive data ■ 1. The authority citation for part 39 Organization (DAO).
that would enable us to provide cost continues to read as follows: (ii) If no cracking is found: Before further
estimates for the on-condition actions flight, rework the structure, in accordance
Authority: 49 U.S.C. 106(g), 40113, 44701.
specified in this AD. with ‘‘Part B—Rectification’’ of the
§ 39.13 [Amended] Accomplishment Instructions of Bombardier
Authority for This Rulemaking Service Bulletin 84–54–19, dated April 18,
■ 2. The FAA amends § 39.13 by adding 2013.
Title 49 of the United States Code the following new airworthiness (2) Within 6,000 flight hours or 36 months
specifies the FAA’s authority to issue directive (AD): after the effective date of this AD, whichever
rules on aviation safety. Subtitle I, occurs first: Rework the LH side and RH side
section 106, describes the authority of 2016–16–15 Bombardier, Inc.: Amendment
nacelle A-frame structure, including doing a
39–18613; Docket No. FAA–2015–3986;
the FAA Administrator. ‘‘Subtitle VII: measurement of the clearance between the
Directorate Identifier 2015–NM–057–AD.
Aviation Programs,’’ describes in more fasteners/A-frame structure and MLG
detail the scope of the Agency’s (a) Effective Date stabilizer brace assembly and making sure no
fouling condition exists, in accordance with
authority. This AD is effective September 23, 2016.
paragraph 3.B., ‘‘Procedure,’’ of the
We are issuing this rulemaking under (b) Affected ADs Accomplishment Instructions of Bombardier
the authority described in ‘‘Subtitle VII, Service Bulletin 84–54–21, dated May 9,
None.
Part A, Subpart III, Section 44701: 2013. If the clearance is found to be less than
General requirements.’’ Under that (c) Applicability 0.100 inch (2.54 millimeters (mm)) between
section, Congress charges the FAA with This AD applies to Bombardier, Inc. Model the fasteners/A-frame structure and MLG
promoting safe flight of civil aircraft in DHC–8–400, –401, and –402 airplanes, stabilizer brace assembly after the rework is
air commerce by prescribing regulations certificated in any category, serial numbers done, or a fouling condition exists during the
for practices, methods, and procedures (S/Ns) 4001 through 4431 inclusive. extension of the MLG after rework is done,
before further flight, repair using a method
the Administrator finds necessary for (d) Subject approved by the Manager, New York ACO,
safety in air commerce. This regulation ANE–170, FAA; or TCCA; or Bombardier,
Air Transport Association (ATA) of
is within the scope of that authority America Code 32, Landing Gear. Inc.’s TCCA DAO.
because it addresses an unsafe condition
that is likely to exist or develop on (e) Reason (h) Repetitive Inspections and Corrective
Actions
products identified in this rulemaking This AD was prompted by reports of
action. chafing damage due to insufficient clearance For airplanes having S/Ns 4056 through
on the main landing gear (MLG) stabilizer 4426 inclusive: Within 600 flight hours or
Regulatory Findings brace, the nacelle A-frame structure, and the 100 days after the effective date of this AD,
adjacent electrical wiring harnesses. An whichever occurs first, do a detailed
We determined that this AD will not inspection of the LH side and RH side nacelle
insufficient fillet radius might also exist on
have federalism implications under certain airplanes. We are issuing this AD to A-frame structure and upper surface of the
Executive Order 13132. This AD will detect and correct chafing damage and MLG stabilizer brace for insufficient
not have a substantial direct effect on subsequent premature cracking and fracture clearance and damage (e.g., cracking), in
the States, on the relationship between of the nacelle A-frame structure, which could accordance with ‘‘Part A—Inspection’’ of the
the national government and the States, result in failure of the MLG stabilizer brace Accomplishment Instructions of Bombardier
jstallworth on DSK7TPTVN1PROD with RULES
or on the distribution of power and and loss of the MLG down-lock indication, Service Bulletin 84–54–20, Revision C, dated
responsibilities among the various which could adversely affect the safe landing March 5, 2015. If no damage is found and
of the airplane. clearance is sufficient: Repeat the inspection
levels of government.
thereafter at intervals not to exceed 600 flight
For the reasons discussed above, I (f) Compliance hours until the terminating action required
certify that this AD: Comply with this AD within the by paragraph (i) of this AD has been done.
1. Is not a ‘‘significant regulatory compliance times specified, unless already (1) If a clearance less than 0.100 inch (2.54
action’’ under Executive Order 12866; done. mm) exists between the A-frame structure
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![55358 Federal Register / Vol. 81, No. 161 / Friday, August 19, 2016 / Rules and Regulations
(o) Related Information Issued in Renton, Washington, on August The Director of the Federal Register
(1) Refer to Mandatory Continuing 4, 2016. approved the incorporation by reference
Airworthiness Information (MCAI) Canadian Michael Kaszycki, of certain publications listed in this AD
Airworthiness Directive CF–2014–45, dated Acting Manager, Transport Airplane as of September 23, 2016.
December 23, 2014, for related information. Directorate, Aircraft Certification Service. The Director of the Federal Register
This MCAI may be found in the AD docket [FR Doc. 2016–19480 Filed 8–18–16; 8:45 am] approved the incorporation by reference
on the Internet at http://www.regulations.gov BILLING CODE 4910–13–P of certain publications listed in this AD
by searching for and locating Docket No. as of August 9, 2005 (70 FR 38580, July
FAA–2015–3986.
5, 2005).
(2) Service information identified in this DEPARTMENT OF TRANSPORTATION The Director of the Federal Register
AD that is not incorporated by reference is
available at the addresses specified in approved the incorporation by reference
Federal Aviation Administration of a certain other publication listed in
paragraphs (p)(3), (p)(4), and (p)(5) of this
AD. this AD as of January 22, 2004 (68 FR
14 CFR Part 39 70431, December 18, 2003).
(p) Material Incorporated by Reference
[Docket No. FAA–2016–4226; Directorate ADDRESSES: For service information
(1) The Director of the Federal Register Identifier 2015–NM–095–AD; Amendment identified in this final rule, contact
approved the incorporation by reference 39–18616; AD 2016–17–03] Airbus, Airworthiness Office—EIAS, 1
(IBR) of the service information listed in this
RIN 2120–AA64 Rond Point Maurice Bellonte, 31707
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51. Blagnac Cedex, France; telephone +33 5
(2) You must use this service information
Airworthiness Directives; Airbus 61 93 36 96; fax +33 5 61 93 44 51; email
as applicable to do the actions required by Airplanes account.airworth-eas@airbus.com;
this AD, unless this AD specifies otherwise. AGENCY: Federal Aviation Internet http://www.airbus.com. You
(i) Bombardier ModSum IS4Q2400028, Administration (FAA), Department of may view this referenced service
Revision B, dated December 11, 2012. (This
Transportation (DOT). information at the FAA, Transport
document has 33 pages; the first page of the Airplane Directorate, 1601 Lind Avenue
modsum indicates that there are 32 pages.) ACTION: Final rule.
SW., Renton, WA. For information on
(ii) Bombardier ModSum IS4Q2400029, SUMMARY: We are superseding the availability of this material at the
Revision A, dated July 6, 2012. FAA, call 425–227–1221. It is also
Airworthiness Directive (AD) 2003–25–
(iii) Bombardier ModSum IS4Q5450002,
07 for certain Airbus Model A319 and available on the Internet at http://
Revision B, dated June 22, 2012.
(iv) Bombardier ModSum IS4Q5450003, A320 series airplanes, and AD 2005–13– www.regulations.gov by searching for
Revision C, dated November 29, 2012. 39 for certain Airbus Model A321 series and locating Docket No. FAA–2016–
(v) Bombardier Service Bulletin 84–32– airplanes. AD 2003–25–07 required a 4226.
112, Revision C, dated April 2, 2015. revision to the airplane flight manual Examining the AD Docket
(vi) Bombardier Service Bulletin 84–32– (AFM) and replacement of both elevator
114, Revision B, dated February 3, 2015. aileron computers (ELACs) having L80 You may examine the AD docket on
(vii) Bombardier Service Bulletin 84–54– standards with new ELACs having L81 the Internet at http://
19, dated April 18, 2013. standards. AD 2005–13–39 required a www.regulations.gov by searching for
(viii) Bombardier Service Bulletin 84–54– revision to the AFM, replacement of and locating Docket No. FAA–2016–
20, Revision C, dated March 5, 2015. existing ELACs with ELACs having L83 4226; or in person at the Docket
(ix) Bombardier Service Bulletin 84–54–21, or L91 standards, as applicable; and a Management Facility between 9 a.m.
dated May 9, 2013. and 5 p.m., Monday through Friday,
concurrent action. Since we issued AD
(x) Goodrich Service Bulletin 46400–32–
2003–25–07 and AD 2005–13–39, we except Federal holidays. The AD docket
102 R2, Revision 2, dated February 17, 2015.
(3) For Bombardier service information have determined that new ELAC contains this AD, the regulatory
identified in this AD, contact Bombardier, standards must be incorporated. The evaluation, any comments received, and
Inc., Q-Series Technical Help Desk, 123 ELAC standards have been upgraded to other information. The address for the
Garratt Boulevard, Toronto, Ontario M3K version L97+, which implements Docket Office (telephone 800–647–5527)
1Y5, Canada; telephone 416–375–4000; fax enhanced angle-of-attack (AOA) is Docket Management Facility, U.S.
416–375–4539; email monitoring to better detect AOA Department of Transportation, Docket
thd.qseries@aero.bombardier.com; Internet blockage, including multiple AOA Operations, M–30, West Building
http://www.bombardier.com. blockages. This AD requires replacing Ground Floor, Room W12–140, 1200
(4) For Goodrich service information existing ELACs with new ELACs having New Jersey Avenue SE., Washington,
identified in this AD, contact Goodrich L97+ standards or revising the software DC 20590.
Corporation, Landing Gear, 1400 South in an existing ELAC to the L97+
Service Road, West Oakville, ON, Canada FOR FURTHER INFORMATION CONTACT:
standards, as applicable, which Sanjay Ralhan, Aerospace Engineer,
L6L 5Y7; phone: 905–825–1568; email:
jean.breed@goodrich.com; Internet: http://
terminates the requirements of AD International Branch, ANM–116,
www.goodrich.com/TechPubs. 2003–25–07 and AD 2005–13–39. This Transport Airplane Directorate, FAA,
(5) You may view this service information AD also expands the applicability to 1601 Lind Avenue SW., Renton, WA
at the FAA, Transport Airplane Directorate, include all Airbus Model A318, A319, 98057–3356; telephone 425–227–1405;
1601 Lind Avenue SW., Renton, WA. For A320, and A321 series airplanes. We are fax 425–227–1149.
information on the availability of this issuing this AD to prevent inadvertent SUPPLEMENTARY INFORMATION:
material at the FAA, call 425–227–1221. activation of the AOA protections.
jstallworth on DSK7TPTVN1PROD with RULES
(6) You may view this service information Inadvertent activation of the AOA Discussion
that is incorporated by reference at the protections could result in a continuous
National Archives and Records
We issued a notice of proposed
nose-down pitch rate that could result rulemaking (NPRM) to amend 14 CFR
Administration (NARA). For information on in reduced controllability of the
the availability of this material at NARA, call part 39 to supersede AD 2003–25–07,
airplane. Amendment 39–13390 (68 FR 70431,
202–741–6030, or go to: http://
www.archives.gov/federal-register/cfr/ibr- DATES: This AD is effective September December 18, 2003) (‘‘AD 2003–25–
locations.html. 23, 2016. 07’’); and AD 2005–13–39, Amendment
VerDate Sep<11>2014 14:10 Aug 18, 2016 Jkt 238001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 E:\FR\FM\19AUR1.SGM 19AUR1](https://thefederalregister.org/doc/81_FR_55514/page/6.svg)
Document Created: 2016-08-19 01:34:59
Document Modified: 2016-08-19 01:34:59
| 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 is effective September 23, 2016. | |
| Contact | Aziz Ahmed, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7329; fax 516-794-5531. | |
| FR Citation | 81 FR 55353 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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