80 FR 63147 - Airworthiness Directives; Bombardier, Inc. Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 201 (October 19, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 201 (October 19, 2015)
| Page Range | 63147-63151 | |
| FR Document | 2015-26217 |
[Federal Register Volume 80, Number 201 (Monday, October 19, 2015)] [Proposed Rules] [Pages 63147-63151] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-26217] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-3986; Directorate Identifier 2015-NM-057-AD] RIN 2120-AA64 Airworthiness Directives; Bombardier, Inc. Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400, -401, and -402 airplanes. This proposed 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 proposed AD would 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 proposing 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. DATES: We must receive comments on this proposed AD by December 3, 2015. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to 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., 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. 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- 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 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: 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: 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-2015-3986; Directorate Identifier 2015-NM-057-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, [[Page 63148]] 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 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. Required actions include, depending on airplane configuration, the following actions: 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. Related Service Information Under 1 CFR Part 51 Bombardier has issued the following service information. ModSum IS4Q2400028, Revision B, dated June 22, 2012; and ModSum IS4Q240029, Revision A, dated July 6, 2014. These modsums describe procedures for rerouting certain electrical harnesses and installing grommets. ModSum IS4Q5450002, Revision B, dated April 30, 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, released 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 B, dated September 12, 2014, and Goodrich Service Bulletin 46400-32-102R1, Revision 1, dated June 24, 2013, as referenced in Bombardier Service Bulletin 84- 32-112, Revision B, dated September 12, 2014. 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 A, dated September 18, 2013. 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 B, dated October 2, 2014. 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. 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 of this NPRM. 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 [[Page 63149]] develop on other products of the same type design. Costs of Compliance We estimate that this proposed AD affects 80 airplanes of U.S. registry. We also estimate that it would take up to 50 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost $8,452 per product. Based on these figures, we estimate the cost of this proposed 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 proposed AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): Bombardier, Inc.: Docket No. FAA-2015-3986; Directorate Identifier 2015-NM-057-AD. (a) Comments Due Date We must receive comments by December 3, 2015. (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 if Necessary, 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 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 ``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 if Necessary 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 B, dated October 2, 2014. 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 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 [[Page 63150]] 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 B, dated October 2, 2014. 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 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 the Accomplishment Instructions of Bombardier Service Bulletin 84-32-112, Revision B, dated September 12, 2014, and Goodrich Service Bulletin 46400-32- 102R1, Revision 1, dated June 24, 2013, as referenced in Bombardier Service Bulletin 84-32-112, Revision B, dated September 12, 2014. (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 the Accomplishment Instructions of Bombardier Service Bulletin 84-32- 114, Revision A, dated September 18, 2013. 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 A, dated September 18, 2013, 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 April 30, 2012, is acceptable for compliance with the actions specified in paragraph (g) of this AD, provided the actions specified in Bombardier ModSum IS4Q5450002 are done within the compliance time specified in paragraph (g) of this AD, except where ModSum IS4Q5450002, Revision B, dated April 30, 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 MLG A- frame in both LH and RH nacelles, in accordance with Bombardier ModSum IS4Q5450003, Revision C, released 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 June 22, 2012 (for S/Ns 4001 through 4098 inclusive) or Bombardier ModSum IS4Q2400029, Revision A, dated July 6, 2014 (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 June 22, 2012; and Bombardier ModSum IS4Q2400029, Revision A, dated July 6, 2014; 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) or (m)(1)(ii) 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. (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) or (m)(2)(ii) 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. (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 Bombardier Service Bulletin 84-32- 114, dated June 6, 2013. This service information 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 ACO, ANE-170, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228- 7300; fax 516-794-5531. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, New York ACO, ANE-170, FAA; or TCCA; or Bombardier, Inc.'s TCCA 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-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) For 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. You may view this service information at the FAA, Transport Airplane Directorate, 1601 [[Page 63151]] 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 October 5, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-26217 Filed 10-16-15; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 80, No. 201 / Monday, October 19, 2015 / Proposed Rules 63147
(d) Comments Due Date Issued in Fort Worth, Texas, on October 1, • Federal eRulemaking Portal: Go to
We must receive comments by December 2015. http://www.regulations.gov. Follow the
18, 2015. Lance T. Gant, instructions for submitting comments.
Manager, Rotorcraft Directorate, Aircraft • Fax: 202–493–2251.
(e) Compliance Certification Service. • Mail: U.S. Department of
You are responsible for performing each [FR Doc. 2015–26229 Filed 10–16–15; 8:45 am] Transportation, Docket Operations, M–
action required by this AD within the 30, West Building Ground Floor, Room
BILLING CODE 4910–13–P
specified compliance time unless it has
already been accomplished prior to that time.
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
(f) Required Actions DEPARTMENT OF TRANSPORTATION • Hand Delivery: U.S. Department of
Before further flight: Transportation, Docket Operations, M–
(1) Revise the airspeed operating limitation Federal Aviation Administration 30, West Building Ground Floor, Room
in the Limitations section of the Rotorcraft W12–140, 1200 New Jersey Avenue SE.,
Flight Manual (RFM) by making pen and ink 14 CFR Part 39 Washington, DC, between 9 a.m. and 5
changes or by inserting a copy of this AD into [Docket No. FAA–2015–3986; Directorate p.m., Monday through Friday, except
the RFM stating: ‘‘The never-exceed speed Identifier 2015–NM–057–AD] Federal holidays.
(VNE) is limited to 150 knots indicated For service information identified in
airspeed (KIAS)’’ and ‘‘The rate-of-descent RIN 2120–AA64
(R/D) must not exceed 1,500 ft/min when the
this proposed AD, contact Bombardier,
airspeed is beyond 140 KIAS.’’ Airworthiness Directives; Bombardier, Inc., Q-Series Technical Help Desk, 123
(2) Install one or more self-adhesive Inc. Airplanes Garratt Boulevard, Toronto, Ontario
placards, with 6 millimeter red letters on M3K 1Y5, Canada; telephone 416–375–
AGENCY: Federal Aviation 4000; fax 416–375–4539; email
white background, on the cockpit instrument
panel in full view of the pilot and co-pilot
Administration (FAA), DOT. thd.qseries@aero.bombardier.com;
to read as follows: ‘‘VNE LIMITED TO 150 ACTION: Notice of proposed rulemaking Internet http://www.bombardier.com.
KIAS’’ and ‘‘R/D MUST NOT EXCEED 1,500 (NPRM). You may view this referenced service
ft/min when airspeed is beyond 140 KIAS’’ information at the FAA, Transport
SUMMARY: We propose to adopt a new
(g) Alternative Methods of Compliance airworthiness directive (AD) for certain Airplane Directorate, 1601 Lind Avenue
(AMOCs) Bombardier, Inc. Model DHC–8–400, SW., Renton, WA. For information on
(1) The Manager, Safety Management –401, and –402 airplanes. This proposed the availability of this material at the
Group, FAA, may approve AMOCs for this AD was prompted by reports of chafing FAA, call 425–227–1221.
AD. Send your proposal to: Robert Grant, damage due to insufficient clearance on Examining the AD Docket
Aviation Safety Engineer, Safety Management the main landing gear (MLG) stabilizer
Group, Rotorcraft Directorate, FAA, 10101 brace, the nacelle A-frame structure, and You may examine the AD docket on
Hillwood Pkwy, Fort Worth, Texas 76177;
the adjacent electrical wiring harnesses. the Internet at http://
telephone (817) 222–5110; email 9-asw-ftw- www.regulations.gov by searching for
amoc-requests@faa.gov. An insufficient fillet radius may also
exist on certain airplanes. This and locating Docket No. FAA–2015–
(2) For operations conducted under a 14 3986; or in person at the Docket
CFR part 119 operating certificate or under proposed AD would require, depending
on airplane configuration, an inspection Management Facility between 9 a.m.
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or of the nacelle A-frame structure for and 5 p.m., Monday through Friday,
lacking a principal inspector, the manager of insufficient fillet radius; an inspection except Federal holidays. The AD docket
the local flight standards district office or for cracking of affected structure, and contains this proposed AD, the
certificate holding district office before rework or repair if necessary, and regulatory evaluation, any comments
operating any aircraft complying with this rework of the nacelle A-frame structure; received, and other information. The
AD through an AMOC. repetitive inspections of the nacelle A- street address for the Docket Operations
(h) Additional Information frame structure and the MLG stabilizer office (telephone 800–647–5527) is in
brace for insufficient clearance and the ADDRESSES section. Comments will
(1) Eurocopter Emergency Alert Service
damage, and repair if necessary, and be available in the AD docket shortly
Bulletin (EASB) No. 01.00.60, 01.00.16, and
01.28, Revision 1, dated December 2, 2008, rework of the nacelle A-frame structure, after receipt.
which is not incorporated by reference, which would terminate the repetitive FOR FURTHER INFORMATION CONTACT: Aziz
contains additional information about the inspections; installation of new stop Ahmed, Aerospace Engineer, Airframe
subject of this AD. For service information brackets and a shim on each MLG and Mechanical Systems Branch, ANE–
identified in this AD, contact Airbus stabilizer brace assembly; and rework of 171, FAA, New York Aircraft
Helicopters, Inc., 2701 N. Forum Drive, the electrical wiring harnesses in the Certification Office, 1600 Stewart
Grand Prairie, TX 75052; telephone (972) nacelle area. We are proposing this AD Avenue, Suite 410, Westbury, NY
641–0000 or (800) 232–0323; fax (972) 641–
to detect and correct chafing damage 11590; telephone 516–228–7329; fax
3775. You may review a copy of the service
information at the FAA, Office of the
and subsequent premature cracking and 516–794–5531.
Regional Counsel, Southwest Region, 10101 fracture of the nacelle A-frame structure, SUPPLEMENTARY INFORMATION:
Hillwood Pkwy., Room 6N–321, Fort Worth, which could result in failure of the MLG
Texas 76177. stabilizer brace and loss of the MLG Comments Invited
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
(2) The subject of this AD is addressed in down-lock indication, which could We invite you to send any written
European Aviation Safety Agency (EASA) AD adversely affect the safe landing of the relevant data, views, or arguments about
No. 2008–0204R1, dated May 21, 2014. You airplane. this proposed AD. Send your comments
may view the EASA AD on the Internet at DATES: We must receive comments on to an address listed under the
http://www.regulations.gov in Docket No. this proposed AD by December 3, 2015. ADDRESSES section. Include ‘‘Docket No.
FAA–2015–4112.
ADDRESSES: You may send comments, FAA–2015–3986; Directorate Identifier
(j) Subject using the procedures found in 14 CFR 2015–NM–057–AD’’ at the beginning of
Joint Aircraft Service Component (JASC) 11.43 and 11.45, by any of the following your comments. We specifically invite
Code 5310: Horizontal Stabilizer Structure. methods: comments on the overall regulatory,
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![63148 Federal Register / Vol. 80, No. 201 / Monday, October 19, 2015 / Proposed Rules
economic, environmental, and energy • Rework of the nacelle A-frame This service information describes
aspects of this proposed AD. We will structure, including a measurement of procedures for rework of the electrical
consider all comments received by the the clearance between the A-frame wiring harnesses in the nacelle area.
closing date and may amend this structure and MLG stabilizer brace The rework includes a detailed
proposed AD based on those comments. assembly and a fluorescent dye inspection of the conduit assembly for
We will post all comments we penetrant inspection or high frequency certain conditions and repair,
receive, without change, to http:// eddy current inspection for cracking replacement of damaged conduit, a
www.regulations.gov, including any and repair if necessary, which would measurement of the clearance to make
personal information you provide. We terminate the repetitive inspections. sure there is 0.100 inch (2.54 mm)
will also post a report summarizing each • Installation of new stop brackets minimum clearance between the MLG
substantive verbal contact we receive and a shim on each MLG stabilizer brace stabilizer brace, and a check for damage
about this proposed AD. assembly. on the A-frame structure and MLG
• Rework of the electrical wiring stabilizer brace and repair.
Discussion harnesses in the nacelle area. The • Service Bulletin 84–54–19, dated
Transport Canada Civil Aviation rework includes a detailed inspection of April 18, 2013. This service information
(TCCA), which is the aviation authority the conduit assembly for certain describes procedures for detailed
for Canada, has issued Canadian conditions and repair if any condition is inspections of the nacelle A-frame
Airworthiness Directive CF–2014–45, found, replacement of damaged conduit, structure for insufficient fillet radius, an
dated December 23, 2014 (referred to a measurement of the clearance between eddy current or fluorescent dye
after this as the Mandatory Continuing the stabilizer brace and electrical penetrant inspection for cracking of
Airworthiness Information, or ‘‘the harness on both LH and RH nacelles to affected structure, and rework or repair.
MCAI’’), to correct an unsafe condition make sure there is 0.100 inch (2.54 • Service Bulletin 84–54–20, Revision
on certain Bombardier, Inc. Model millimeters (mm)) minimum clearance B, dated October 2, 2014. This service
DHC–8–400, –401, and –402 airplanes. between the MLG stabilizer brace, and information describes procedures for
The MCAI states: a check for damage on the A-frame detailed inspections of the nacelle A-
The aeroplane manufacturer has structure and MLG stabilizer brace and frame structure and the MLG stabilizer
discovered that an insufficient fillet radius repair if necessary. brace for insufficient clearance and
may exist on the flange of the nacelle A- You may examine the MCAI in the AD
frame structure on certain aeroplanes. There
damage, and repair. This service
docket on the Internet at http:// information also describes procedures
have also been several in-service reports of www.regulations.gov by searching for
chafing damage on the main landing gear for rework of the nacelle A-frame
(MLG) stabilizer brace, the nacelle A-frame and locating Docket No. FAA–2015– structure, including a measurement of
structure and its adjacent electrical wiring 3986. the clearance between the A-frame
harnesses due to insufficient clearance. Related Service Information Under 1 structure and MLG stabilizer brace
An insufficient fillet radius and chafing assembly, and a fluorescent dye
damage on the nacelle A-frame structure and
CFR Part 51
penetrant inspection or high frequency
MLG stabilizer brace could lead to premature Bombardier has issued the following
cracking. Fracture of the nacelle A-frame eddy current inspection for cracking
service information.
structure or failure of the MLG stabilizer • ModSum IS4Q2400028, Revision B, and repair, which would end the
brace could adversely affect the safe landing dated June 22, 2012; and ModSum inspections.
of the aeroplane. The damage to the electrical
IS4Q240029, Revision A, dated July 6, • Service Bulletin 84–54–21, dated
wiring harnesses could result in the loss of May 9, 2013. This service information
the MLG downlock indication. 2014. These modsums describe
procedures for rerouting certain describes procedures for rework of the
This [Canadian] AD mandates the
inspection and rework of the nacelle A-frame electrical harnesses and installing LH side and RH side nacelle A-frame
structure, and the rework of the forward MLG grommets. structure, including a measurement of
stabilizer brace assembly and the electrical • ModSum IS4Q5450002, Revision B, the clearance between the fasteners/A-
harnesses in the nacelle area adjacent to the dated April 30, 2012. This modsum frame structure and MLG stabilizer
A-frame structure. describes procedures for installing brace assembly and to make sure no
Required actions include, depending specified fasteners on the MLG A-frame, fouling condition exists, and repair.
on airplane configuration, the following in both the LH and RH nacelles. This service information is reasonably
actions: • ModSum IS4Q5450003, Revision C, available because the interested parties
• A detailed inspection of the nacelle released November 29, 2012. This have access to it through their normal
A-frame structure for insufficient fillet modsum describes procedures for course of business or by the means
radius, an eddy current or fluorescent trimming the horizontal and vertical identified in the ADDRESSES section of
dye penetrant inspection for cracking of stiffeners on the MLG A frame in both this NPRM.
affected structure, and rework or repair the LH and RH nacelles. FAA’s Determination and Requirements
if necessary. • Service Bulletin 84–32–112,
of this Proposed AD
• Rework of the left-hand (LH) side Revision B, dated September 12, 2014,
and right-hand (RH) side nacelle A- and Goodrich Service Bulletin 46400– This product has been approved by
frame structure, including doing a 32–102R1, Revision 1, dated June 24, the aviation authority of another
measurement of the clearance between 2013, as referenced in Bombardier country, and is approved for operation
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
the fasteners/A-frame structure and Service Bulletin 84–32–112, Revision B, in the United States. Pursuant to our
MLG stabilizer brace assembly and dated September 12, 2014. This service bilateral agreement with the State of
making sure no fouling condition exists, information describes procedures for Design Authority, we have been notified
and repair if necessary. incorporating Bombardier ModSum 4– of the unsafe condition described in the
• Repetitive detailed inspections of 902416 by installing new stop brackets MCAI and service information
the nacelle A-frame structure and the and new stop shims for all MLG referenced above. We are proposing this
MLG stabilizer brace for insufficient stabilizer brace assemblies. AD because we evaluated all pertinent
clearance and damage, and repair if • Service Bulletin 84–32–114, information and determined an unsafe
necessary. Revision A, dated September 18, 2013. condition exists and is likely to exist or
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![Federal Register / Vol. 80, No. 201 / Monday, October 19, 2015 / Proposed Rules 63149
develop on other products of the same under the criteria of the Regulatory occurs first: Do a detailed inspection of the
type design. Flexibility Act. left-hand (LH) side and right-hand (RH) side
nacelle A-frame structure for insufficient
Costs of Compliance List of Subjects in 14 CFR Part 39 fillet radius, in accordance with ‘‘Part A—
We estimate that this proposed AD Inspection’’ of the Accomplishment
Air transportation, Aircraft, Aviation
Instructions of Bombardier Service Bulletin
affects 80 airplanes of U.S. registry. safety, Incorporation by reference, 84–54–19, dated April 18, 2013. If an
We also estimate that it would take up Safety. insufficient fillet radius exists, before further
to 50 work-hours per product to comply flight, do an eddy current or fluorescent dye
with the basic requirements of this The Proposed Amendment
penetrant inspection for cracking, in
proposed AD. The average labor rate is Accordingly, under the authority accordance with ‘‘Part A—Inspection’’ of the
$85 per work-hour. Required parts delegated to me by the Administrator, Accomplishment Instructions of Bombardier
would cost $8,452 per product. Based the FAA proposes to amend 14 CFR part Service Bulletin 84–54–19, dated April 18,
on these figures, we estimate the cost of 39 as follows: 2013.
(i) If any cracking is found: Before further
this proposed AD on U.S. operators to
PART 39—AIRWORTHINESS flight, repair using a method approved by the
be up to $1,016,160, or $12,702 per Manager, New York ACO, ANE–170, FAA; or
product. DIRECTIVES
Transport Canada Civil Aviation (TCCA); or
We have received no definitive data Bombardier, Inc.’s TCCA Design Approval
that would enable us to provide cost ■ 1. The authority citation for part 39
Organization (DAO).
estimates for the on-condition actions continues to read as follows:
(ii) If no cracking is found: Before further
specified in this proposed AD. Authority: 49 U.S.C. 106(g), 40113, 44701. flight, rework the structure, in accordance
‘‘Part B—Rectification’’ of the
Authority for This Rulemaking § 39.13 [Amended] Accomplishment Instructions of Bombardier
Title 49 of the United States Code ■ 2. The FAA amends § 39.13 by adding Service Bulletin 84–54–19, dated April 18,
specifies the FAA’s authority to issue the following new airworthiness 2013.
directive (AD): (2) Within 6,000 flight hours or 36 months
rules on aviation safety. Subtitle I,
after the effective date of this AD, whichever
section 106, describes the authority of Bombardier, Inc.: Docket No. FAA–2015– occurs first: Rework the LH side and RH side
the FAA Administrator. ‘‘Subtitle VII: 3986; Directorate Identifier 2015–NM–057– nacelle A-frame structure, including doing a
Aviation Programs,’’ describes in more AD. measurement of the clearance between the
detail the scope of the Agency’s (a) Comments Due Date fasteners/A-frame structure and MLG
authority. stabilizer brace assembly and making sure no
We must receive comments by December 3,
We are issuing this rulemaking under fouling condition exists, in accordance with
2015. paragraph 3.B. ‘‘Procedure,’’ of the
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701: (b) Affected ADs Accomplishment Instructions of Bombardier
General requirements.’’ Under that Service Bulletin 84–54–21, dated May 9,
None.
2013. If the clearance is found to be less than
section, Congress charges the FAA with 0.100 inch (2.54 millimeters (mm)) between
(c) Applicability
promoting safe flight of civil aircraft in the fasteners/A-frame structure and MLG
air commerce by prescribing regulations This AD applies to Bombardier, Inc. Model
DHC–8–400, –401, and –402 airplanes, stabilizer brace assembly after the rework is
for practices, methods, and procedures done, or a fouling condition exists during the
certificated in any category, serial numbers
the Administrator finds necessary for (S/Ns) 4001 through 4431 inclusive. extension of the MLG after rework is done,
safety in air commerce. This regulation before further flight, repair using a method
is within the scope of that authority (d) Subject approved by the Manager, New York ACO,
because it addresses an unsafe condition Air Transport Association (ATA) of ANE–170, FAA; or TCCA; or Bombardier,
that is likely to exist or develop on America Code 32, Landing Gear. Inc.’s TCCA DAO.
products identified in this rulemaking (e) Reason (h) Repetitive Inspections and Corrective
action. Actions if Necessary
This AD was prompted by reports of
Regulatory Findings 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
We determined that this proposed AD brace, the nacelle A-frame structure, and the 100 days after the effective date of this AD,
would not have federalism implications adjacent electrical wiring harnesses. An whichever occurs first: Do a detailed
under Executive Order 13132. This insufficient fillet radius might also exist on inspection of the LH side and RH side nacelle
proposed AD would not have a certain airplanes. We are issuing this AD to A-frame structure and upper surface of the
substantial direct effect on the States, on detect and correct chafing damage and MLG stabilizer brace for insufficient
subsequent premature cracking and fracture clearance and damage (e.g., cracking), in
the relationship between the national
of the nacelle A-frame structure, which could accordance with ‘‘Part A—Inspection,’’ of the
Government and the States, or on the Accomplishment Instructions of Bombardier
distribution of power and result in failure of the MLG stabilizer brace
and loss of the MLG down-lock indication, Service Bulletin 84–54–20, Revision B, dated
responsibilities among the various which could adversely affect the safe landing October 2, 2014. If no damage is found and
levels of government. of the airplane. clearance is sufficient: Repeat the inspection
For the reasons discussed above, I thereafter at intervals not to exceed 600 flight
certify this proposed regulation: (f) Compliance hours until the terminating action required
1. Is not a ‘‘significant regulatory Comply with this AD within the by paragraph (i) of this AD has been done.
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
action’’ under Executive Order 12866; compliance times specified, unless already (1) If a clearance less than 0.100 inch (2.54
2. Is not a ‘‘significant rule’’ under the done. mm) exists between the A-frame structure
DOT Regulatory Policies and Procedures and the MLG stabilizer brace assembly in the
(g) Inspection, Corrective Actions if retracted position, after the rework is done,
(44 FR 11034, February 26, 1979); Necessary, and Rework before further flight, repair using a method
3. Will not affect intrastate aviation in For airplanes having S/Ns 4001 through approved by the Manager, New York ACO,
Alaska; and 4055 inclusive: Do the actions required by ANE–170, FAA; or TCCA; or Bombardier,
4. Will not have a significant paragraphs (g)(1) and (g)(2) of this AD. Inc.’s TCCA DAO.
economic impact, positive or negative, (1) Within 600 flight hours or 100 days (2) If any damage is found: Before further
on a substantial number of small entities after the effective date of this AD, whichever flight, repair using a method approved by the
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![Federal Register / Vol. 80, No. 201 / Monday, October 19, 2015 / Proposed Rules 63151
Lind Avenue SW., Renton, WA. For p.m., Monday through Friday, except substantive verbal contact we receive
information on the availability of this Federal holidays. about this proposed AD.
material at the FAA, call 425–227–1221. For service information identified in
Issued in Renton, Washington, on October this proposed AD, contact Piper Discussion
5, 2015. Aircraft, Inc., Customer Service, 2926 We received a report of wing upper
Jeffrey E. Duven, Piper Drive, Vero Beach, Florida 32960; skin joints on Piper Aircraft, Inc. Model
Manager, Transport Airplane Directorate, telephone: (877) 879–0275; fax: none; PA–46–500TP airplanes being
Aircraft Certification Service. email: customer.service@piper.com; manufactured without sealant, which
[FR Doc. 2015–26217 Filed 10–16–15; 8:45 am] Internet: www.piper.com. You may allows water to enter and stay in sealed,
BILLING CODE 4910–13–P review the referenced service bonded stringers. This condition, if not
information at the FAA, Small Airplane corrected, could result in water entering
Directorate, 901 Locust, Kansas City, the stringers common to the upper wing
DEPARTMENT OF TRANSPORTATION Missouri 64106. For information on the skin. Left uncorrected, corrosion could
availability of this material at the FAA, develop, and freeze/thaw cycles of
Federal Aviation Administration call (816) 329–4148. water at this location could cause
Examining the AD Docket deformation of the skin with follow-on
14 CFR Part 39
You may examine the AD docket on disbonding between the stringer flanges
[Docket No. FAA–2015–4213; Directorate and the inner surface of the wing skin.
Identifier 2015–CE–022–AD]
the Internet at http://
www.regulations.gov by searching for Consequently, the corrosion or
RIN 2120–AA64 and locating Docket No. FAA–2015– disbonding could reduce the structural
4213; or in person at the Docket integrity of the wing.
Airworthiness Directives; Piper Management Facility between 9 a.m. Related Service Information Under 1
Aircraft, Inc. Airplanes and 5 p.m., Monday through Friday, CFR Part 51
AGENCY: Federal Aviation except Federal holidays. The AD docket
Administration (FAA), DOT. contains this proposed AD, the We reviewed Piper Aircraft, Inc.
ACTION: Notice of proposed rulemaking
regulatory evaluation, any comments Service Bulletin No. 1262B, dated April
(NPRM). received, and other information. The 23, 2015. The service bulletin provides
street address for the Docket Office instructions for inspecting the upper
SUMMARY: We propose to adopt a new (phone: 800–647–5527) is in the wing surface for sealant and sealing or
airworthiness directive (AD) for certain ADDRESSES section. Comments will be resealing (if necessary). This service
Piper Aircraft, Inc. Model PA–46–500TP available in the AD docket shortly after bulletin also provides instructions for
airplanes. This proposed AD was receipt. inspecting the wing stringers for water
prompted by a report of the wing upper FOR FURTHER INFORMATION CONTACT: intrusion, and, if water intrusion was
skin joints being manufactured without Gregory ‘‘Keith’’ Noles, Aerospace found as a result of the inspection,
sealant, which allows water to enter and Engineer, FAA, Atlanta Aircraft inspecting for corrosion or deformation.
stay in sealed, bonded stringers. This Certification Office, 1701 Columbia This service information is reasonably
proposed AD would require inspecting Avenue, College Park, Georgia 30337; available because the interested parties
the upper wing surface for sealant; phone: (404) 474–5551; fax: (404) 474– have access to it through their normal
inspecting the wing stringers for water 5606; email: gregory.noles@faa.gov. course of business or by the means
intrusion; inspecting for deformation SUPPLEMENTARY INFORMATION: identified in the ADDRESSES section of
and corrosion if evidence of water this NPRM.
intrusion exists; and taking corrective Comments Invited
FAA’s Determination
actions as necessary. We are proposing We invite you to send any written
this AD to correct the unsafe condition relevant data, views, or arguments about We are proposing this AD because we
on these products. this proposal. Send your comments to evaluated all the relevant information
DATES: We must receive comments on an address listed under the ADDRESSES and determined the unsafe condition
this proposed AD by December 3, 2015. section. Include ‘‘Docket No. FAA– described previously is likely to exist or
ADDRESSES: You may send comments, 2015–4213; Directorate Identifier 2015– develop in other products of the same
using the procedures found in 14 CFR CE–022–AD’’ at the beginning of your type design.
11.43 and 11.45, by any of the following comments. We specifically invite
comments on the overall regulatory, Proposed AD Requirements
methods:
• Federal eRulemaking Portal: Go to economic, environmental, and energy This proposed AD would require
http://www.regulations.gov. Follow the aspects of this proposed AD. We will accomplishing the actions specified in
instructions for submitting comments. consider all comments received by the the service information described
• Fax: 202–493–2251. closing date and may amend this previously.
• Mail: U.S. Department of proposed AD because of those
Transportation, Docket Operations, M– comments. Costs of Compliance
30, West Building Ground Floor, Room We will post all comments we
We estimate that this proposed AD
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
W12–140, 1200 New Jersey Avenue SE., receive, without change, to http://
Washington, DC 20590. www.regulations.gov, including any affects 440 airplanes of U.S. registry.
• Hand Delivery: Deliver to Mail personal information you provide. We We estimate the following costs to
address above between 9 a.m. and 5 will also post a report summarizing each comply with this proposed AD:
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Document Created: 2015-12-15 08:35:54
Document Modified: 2015-12-15 08:35:54
| 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 | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by December 3, 2015. | |
| 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 | 80 FR 63147 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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