81 FR 89367 - Airworthiness Directives; Bombardier, Inc. Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 238 (December 12, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 238 (December 12, 2016)
| Page Range | 89367-89371 | |
| FR Document | 2016-28597 |
[Federal Register Volume 81, Number 238 (Monday, December 12, 2016)] [Rules and Regulations] [Pages 89367-89371] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-28597] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-8178; Directorate Identifier 2015-NM-197-AD; Amendment 39-18721; AD 2016-24-04] RIN 2120-AA64 Airworthiness Directives; Bombardier, Inc. Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted [[Page 89368]] by a determination by the manufacturer that shims might not have been installed between certain longerons and longeron joint fittings. This AD requires various repetitive and detailed visual inspections of the affected areas and corrective actions if necessary. This AD also provides terminating action for certain repetitive inspections. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective January 17, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 17, 2017. ADDRESSES: For 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. 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-2016-8178. 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-2016- 8178; 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 (ACO), 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 series airplanes. The NPRM published in the Federal Register on July 15, 2016 (81 FR 45995) (``the NPRM''). The NPRM was prompted by a determination by the manufacturer that shims might not have been installed between certain longerons and longeron joint fittings. The NPRM proposed to require repetitive inspections of the external surface of the fuselage skin panel for loose or working fasteners, and corrective action if necessary; a detailed visual inspection of the longeron joint fittings for the existence of shims and, if necessary, repetitive inspections of the longeron and the longeron joint fittings for any cracking, and corrective action if necessary. We are issuing this AD to detect and correct missing shims between the longerons and longeron joint fittings, which could result in a gapping condition and lead to stress corrosion cracking of the longeron joint fittings, and could adversely affect the structural integrity of the wing-to-fuselage attachment joints. Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF- 2015-22, dated August 3, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Bombardier, Inc. Model DHC-8-400 series airplanes. The MCAI states: The aeroplane manufacturer has determined that shims may not have been installed between the longerons and longeron joint fittings at fuselage station X373-380, stringers 7 on the left and right hand side, on certain aeroplanes. The missing shims could result in a gapping condition and could lead to stress corrosion cracking of the longeron joint fittings. Failure of the longeron joint fitting could compromise the structural integrity of the wing-to-fuselage attachment joint. This [Canadian] AD mandates inspections in the area of the longeron joint fittings. Corrective actions include replacing any loose or working fasteners (fasteners that show signs of wear, fatigue, or corrosion), repairing any structural damage, and replacing any cracked longeron or longeron with an amplitude of 50% or more of the calibration signal. 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-2016- 8178. 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. Request To Incorporate Revised Service Information Horizon Air requested that we incorporate Bombardier Service Bulletin 84-53-65, Revision A, dated February 22, 2016. We agree with the commenter's request to incorporate the revised service information because Bombardier Service Bulletin 84-53-65, Revision A, dated February 22, 2016, is the latest revision. We have changed all service bulletin references in this final rule to Bombardier Service Bulletin 84-53-65, Revision A, dated February 22, 2016. Request To Provide Credit for Previous Actions Horizon Air requested that we add a paragraph addressing credit for previous actions. We agree. Since we have incorporated revised service information in this final rule, we agree to provide credit for required tasks performed before the effective date of this AD using Bombardier Service Bulletin 84-53-65, dated February 27, 2015. We have added a new paragraph (n) to this AD to provide credit for previous actions and redesignated subsequent paragraphs accordingly. Additional Changes to NPRM We have reformatted paragraph (l) in this AD to clarify the requirements. 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 We reviewed Bombardier Service Bulletin 84-53-65, Revision A, dated February 22, 2016. The service information describes procedures for [[Page 89369]] inspections of the external surface of the fuselage skin panel for loose or working fasteners; a detailed visual inspection of the longeron joint fittings for the existence of shims; high frequency eddy current inspections of the longeron and the longeron joint fittings for any cracking; and replacement of longeron fittings, shims, and fasteners. 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 76 airplanes of U.S. registry. We also estimate that it will take about 2 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $12,920, or $170 per product. In addition, we estimate that any necessary follow-on actions will take about 3 work-hours for the inspection for missing shims, 9 work- hours for the replacement of longeron fittings and shims, and 1 work- hour for a reporting requirement; and would require parts costing $3,222; for a cost of up to $4,327 per product. We have no way of determining the number of aircraft that might need these actions. We have received no definitive data that will enable us to provide cost estimates for repair of loose or working fasteners or structural damage specified in this AD. Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this AD is 2120- 0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information Collection Clearance Officer, AES-200. 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): 2016-24-04 Bombardier, Inc: Amendment 39-18721; Docket No. FAA-2016- 8178; Directorate Identifier 2015-NM-197-AD. (a) Effective Date This AD is effective January 17, 2017. (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 4156 through 4453 inclusive, 4456, and 4457. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by a determination by the manufacturer that shims might not have been installed between certain longerons and longeron joint fittings. We are issuing this AD to detect and correct missing shims between the longerons and longeron joint fittings, which could result in a gapping condition and lead to stress corrosion cracking of the longeron joint fittings, and could adversely affect the structural integrity of the wing-to-fuselage attachment joints. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection of the External Surface of the Fuselage Skin Panels At the time specified in paragraph (g)(1) or (g)(2) of this AD, as applicable, do a detailed visual inspection of the external surface of the fuselage skin panel for loose or working fasteners (fasteners that show signs of wear, fatigue, or corrosion) and structural damage, in accordance with paragraph 3.B. of the Accomplishment Instructions of Bombardier Service Bulletin 84-53-65, Revision A, dated February 22, 2016. (1) For airplanes that have accumulated less than 10,000 total flight hours, or less than 5 years in service since new, as of the effective date of this AD: Prior to accumulating 12,000 total flight hours or 6 years in service since new, whichever occurs first. (2) For airplanes that have accumulated 10,000 total flight hours or more, or 5 years or more in service since new, as of the effective date of this AD: Within 2,000 flight hours or 12 months after the effective date of this AD, whichever occurs first. (h) Corrective Actions If any loose or working fastener or any structural damage is found during any inspection required by this AD: Before further flight, repair using a method approved by the Manager, New York Aircraft Certification Office (ACO), FAA; or Transport Canada Civil Aviation (TCCA); or [[Page 89370]] Bombardier, Inc.'s TCCA Design Approval Organization (DAO); and thereafter do the inspections required by paragraph (i) of this AD. Accomplishment of a repair in accordance with a method approved by the Manager, New York ACO, FAA; or TCCA; or Bombardier, Inc.'s TCCA DAO terminates the repetitive inspections required by paragraph (i) of this AD for the repaired area only. (i) Repetitive Detailed Visual Inspections Repeat the detailed visual inspection required by the introductory text to paragraph (g) of this AD at intervals not to exceed 12 months or 2,000 flight cycles, whichever occurs first after accomplishment of the most recent inspection, until the actions required by the introductory text to paragraph (j) of this AD are done. (j) Inspection for Missing Shims At the time specified in paragraph (j)(1) or (j)(2) of this AD, as applicable, do a detailed visual inspection of the longeron joint fittings for the existence of shims, in accordance with paragraph 3.C. of the Accomplishment Instructions of Bombardier Service Bulletin 84-53-65, Revision A, dated February 22, 2016. (1) For airplanes that have accumulated less than 10,000 total flight hours, or less than 5 years in service since new, as of the effective date of this AD: Prior to accumulating 18,000 total flight hours or 9 years in service since new, whichever occurs first. (2) For airplanes that have accumulated 10,000 total flight hours or more, or 5 years or more in service since new, as of the effective date of this AD: Within 8,000 flight hours or 4 years after the effective date of this AD, whichever occurs first; but not to exceed 30,000 total flight hours or 144 months in service since new, whichever occurs first. (k) Airplanes With Installed Shims: No Further Action Required If the inspection required by the introductory text to paragraph (j) of this AD reveals that shims are installed in the longeron joint fittings, no further action is required by this AD. (l) Airplanes With Missing Shims: High Frequency Eddy Current (HFEC) Inspections and Corrective Actions If the inspection required by the introductory text to paragraph (j) of this AD reveals that any shim is missing from the longeron joint fittings: Before further flight, do a high frequency eddy current (HFEC) inspection of the longeron and the longeron joint fittings for any cracking, in accordance with paragraph 3.D. of the Accomplishment Instructions of Bombardier Service Bulletin 84-53-65, Revision A, dated February 22, 2016. (1) If any crack is found, or if any indication with an amplitude of 50% or more of the calibration signal is found, do the actions specified in paragraphs (l)(1)(i) and (l)(1)(ii) of this AD. (i) Before further flight: Replace the longeron joint fittings, in accordance with paragraph 3.E. of the Accomplishment Instructions of Bombardier Service Bulletin 84-53-65, Revision A, dated February 22, 2016. (ii) At the applicable time specified in paragraph (l)(1)(ii)(A) or (l)(1)(ii)(B) of this AD: Report the inspection results to 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. (A) If the inspection was done on or after the effective date of this AD: Report within 30 days after that inspection. (B) If the inspection was done before the effective date of this AD: Report within 30 days after the effective date of this AD. (2) If no crack or indication with an amplitude of 50% or more of the calibration signal is found: Repeat the HFEC inspection required by the introductory text to paragraph (l) of this AD at intervals not to exceed 12,000 flight hours or 6 years, whichever occurs first after accomplishment of the most recent HFEC inspection, in accordance with paragraph 3.D. of the Accomplishment Instructions of Bombardier Service Bulletin 84-53-65, Revision A, dated February 22, 2016. (m) Terminating Action for Repetitive HFEC Inspections Replacement of the longeron joint fittings, in accordance with paragraph 3.E. of the Accomplishment Instructions of Bombardier Service Bulletin 84-53-65, Revision A, dated February 22, 2016, constitutes terminating action for the repetitive HFEC inspections required by paragraph (l)(2) of this AD. (n) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (g), (i), (j), (k), (l), and (m) of this AD, if those actions were performed before the effective date of this AD using Bombardier Service Bulletin 84-53-65, dated February 27, 2015. (o) 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. (3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200. (p) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF-2015-22, dated August 3, 2015, 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-2016-8178. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (q)(3) and (q)(4) of this AD. (q) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Bombardier Service Bulletin 84-53-65, Revision A, dated February 22, 2016. (ii) Reserved. (3) 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. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. [[Page 89371]] Issued in Renton, Washington, on November 17, 2016. Phil Forde, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-28597 Filed 12-9-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 238 / Monday, December 12, 2016 / Rules and Regulations 89367
agency to take corrective action. OPM interest of the civil service for any other § 250.302 Survey requirements.
may suspend or revoke a delegation reason. (a) Each executive agency must
agreement established under 5 U.S.C. ■ 3. Subpart C is revised to read as
conduct an annual survey of its
1104(a)(2) at any time if it determines follows: employees to assess topics outlined in
that the agency is not adhering to the Subpart C—Employee Surveys the National Defense Authorization Act
provisions of the agreement. OPM may for Fiscal Year 2004, Public Law 108–
Sec.
suspend or withdraw any authority 250.301 Definitions. 136, sec. 1128, codified at 5 U.S.C. 7101.
granted under this chapter to an agency, 250.302 Survey requirements.
including any authority granted by 250.303 Availability of results. (1) Each executive agency may
delegation agreement, when OPM finds include additional survey questions
that the agency has not complied with Subpart C—Employee Surveys unique to the agency in addition to the
qualification standards OPM has issued, employee survey questions prescribed
instructions OPM has published, or the Authority: 5 U.S.C. 105; 5 U.S.C. 7101 by OPM under paragraph (a)(2) of this
note; Public Law 108–136 section.
regulations in this chapter of the
regulation. OPM also may suspend or § 250.301 Definitions. (2) The 16 prescribed survey
withdraw these authorities when it Agency means an Executive agency, questions are listed in the following
determines that doing so is in the as defined in 5 U.S.C. 105. table:
(i) Leadership and Management practices that contribute to agency performance
My work unit has the job-relevant skills necessary to accomplish organizational goals.
Managers communicate the goals of the organization.
I believe the results of this survey will be used to make my agency a better place to work.
(ii) Employee Satisfaction with—
(A) .............................. Leadership Policies and Practices:
How satisfied are you with your involvement in decisions that affect your work?
How satisfied are you with the information you receive from management on what is going on in your organization?
Considering everything, how satisfied are you with your organization?
(B) .............................. Work Environment:
The people I work with cooperate to get the job done.
My workload is reasonable.
Considering everything, how satisfied are you with your job?
I can disclose a suspected violation of any law, rule or regulation without fear of reprisal.
(C) .............................. Rewards and Recognition:
In my work unit, differences in performance are recognized in a meaningful way.
How satisfied are you with the recognition you receive for doing a good job?
(D) .............................. Opportunities for professional development and growth:
I am given a real opportunity to improve my skills in my organization.
My talents are used well in the workplace.
(E) .............................. Opportunity to contribute to achieving organizational mission:
I know how my work relates to the agency’s goals.
I recommend my organization as a good place to work.
§ 250.303 Availability of results. (6) The number of respondents for DEPARTMENT OF TRANSPORTATION
(a) Each agency will make the results each survey question and each response
of its annual survey available to the choice. Federal Aviation Administration
public and post the results on its Web (b) Data must be collected by
site unless the agency head determines 14 CFR Part 39
December 31 of each calendar year.
that doing so would jeopardize or Each agency must post the beginning [Docket No. FAA–2016–8178; Directorate
negatively impact national security. The and ending dates of its employee survey Identifier 2015–NM–197–AD; Amendment
posted survey results will include the and either the survey results described 39–18721; AD 2016–24–04]
following: in paragraph (a) of this section, or a RIN 2120–AA64
(1) The agency’s evaluation of its statement noting the decision not to
survey results; post, no later than 120 days after the Airworthiness Directives; Bombardier,
(2) How the survey was conducted; agency completes survey Inc. Airplanes
(3) Description of the employee administration. OPM may extend this AGENCY: Federal Aviation
sample, unless all employees are date under unusual circumstances. Administration (FAA), Department of
mstockstill on DSK3G9T082PROD with RULES
surveyed; [FR Doc. 2016–29600 Filed 12–9–16; 8:45 am] Transportation (DOT).
(4) The survey questions and response BILLING CODE 6325–39–P ACTION: Final rule.
choices with the prescribed questions
identified; SUMMARY: We are adopting a new
(5) The number of employees airworthiness directive (AD) for certain
surveyed and number of employees who Bombardier, Inc. Model DHC–8–400
completed the survey; and series airplanes. This AD was prompted
VerDate Sep<11>2014 16:18 Dec 09, 2016 Jkt 241001 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 E:\FR\FM\12DER1.SGM 12DER1](https://thefederalregister.org/doc/81_FR_89605/page/1.svg)
![89368 Federal Register / Vol. 81, No. 238 / Monday, December 12, 2016 / Rules and Regulations
by a determination by the manufacturer Discussion Comments
that shims might not have been installed We gave the public the opportunity to
We issued a notice of proposed
between certain longerons and longeron participate in developing this AD. The
rulemaking (NPRM) to amend 14 CFR
joint fittings. This AD requires various following presents the comments
part 39 by adding an AD that would
repetitive and detailed visual received on the NPRM and the FAA’s
apply to certain Bombardier, Inc. Model
inspections of the affected areas and response to each comment.
DHC–8–400 series airplanes. The NPRM
corrective actions if necessary. This AD
published in the Federal Register on Request To Incorporate Revised Service
also provides terminating action for
July 15, 2016 (81 FR 45995) (‘‘the Information
certain repetitive inspections. We are
NPRM’’). The NPRM was prompted by
issuing this AD to address the unsafe Horizon Air requested that we
a determination by the manufacturer
condition on these products. that shims might not have been installed incorporate Bombardier Service Bulletin
between certain longerons and longeron 84–53–65, Revision A, dated February
DATES: This AD is effective January 17,
joint fittings. The NPRM proposed to 22, 2016.
2017.
We agree with the commenter’s
The Director of the Federal Register require repetitive inspections of the
request to incorporate the revised
approved the incorporation by reference external surface of the fuselage skin
service information because Bombardier
of a certain publication listed in this AD panel for loose or working fasteners, and
Service Bulletin 84–53–65, Revision A,
as of January 17, 2017. corrective action if necessary; a detailed
dated February 22, 2016, is the latest
visual inspection of the longeron joint
ADDRESSES: For service information revision. We have changed all service
fittings for the existence of shims and,
identified in this final rule, contact bulletin references in this final rule to
if necessary, repetitive inspections of
Bombardier, Inc., Q-Series Technical Bombardier Service Bulletin 84–53–65,
the longeron and the longeron joint
Help Desk, 123 Garratt Boulevard, Revision A, dated February 22, 2016.
fittings for any cracking, and corrective
Toronto, Ontario M3K 1Y5, Canada; action if necessary. We are issuing this Request To Provide Credit for Previous
telephone 416–375–4000; fax 416–375– AD to detect and correct missing shims Actions
4539; email thd.qseries@ between the longerons and longeron Horizon Air requested that we add a
aero.bombardier.com; Internet http:// joint fittings, which could result in a paragraph addressing credit for previous
www.bombardier.com. You may view gapping condition and lead to stress actions.
this referenced service information at corrosion cracking of the longeron joint We agree. Since we have incorporated
the FAA, Transport Airplane fittings, and could adversely affect the revised service information in this final
Directorate, 1601 Lind Avenue SW., structural integrity of the wing-to- rule, we agree to provide credit for
Renton, WA. For information on the fuselage attachment joints. required tasks performed before the
availability of this material at the FAA, Transport Canada Civil Aviation effective date of this AD using
call 425–227–1221. It is also available (TCCA), which is the aviation authority Bombardier Service Bulletin 84–53–65,
on the Internet at http:// for Canada, has issued Canadian dated February 27, 2015. We have
www.regulations.gov by searching for Airworthiness Directive CF–2015–22, added a new paragraph (n) to this AD
and locating Docket No. FAA–2016– dated August 3, 2015 (referred to after to provide credit for previous actions
8178. this as the Mandatory Continuing and redesignated subsequent paragraphs
Airworthiness Information, or ‘‘the accordingly.
Examining the AD Docket MCAI’’), to correct an unsafe condition
for certain Bombardier, Inc. Model Additional Changes to NPRM
You may examine the AD docket on
the Internet at http:// DHC–8–400 series airplanes. The MCAI We have reformatted paragraph (l) in
www.regulations.gov by searching for states: this AD to clarify the requirements.
and locating Docket No. FAA–2016– The aeroplane manufacturer has Conclusion
8178; or in person at the Docket determined that shims may not have been
installed between the longerons and longeron We reviewed the relevant data,
Management Facility between 9 a.m.
joint fittings at fuselage station X373–380, considered the comments received, and
and 5 p.m., Monday through Friday,
stringers 7 on the left and right hand side, on determined that air safety and the
except Federal holidays. The AD docket certain aeroplanes. The missing shims could public interest require adopting this AD
contains this AD, the regulatory result in a gapping condition and could lead with the changes described previously
evaluation, any comments received, and to stress corrosion cracking of the longeron and minor editorial changes. We have
other information. The street address for joint fittings. determined that these minor changes:
the Docket Office (telephone 800–647– Failure of the longeron joint fitting could
• Are consistent with the intent that
5527) is Docket Management Facility, compromise the structural integrity of the
wing-to-fuselage attachment joint. was proposed in the NPRM for
U.S. Department of Transportation, correcting the unsafe condition; and
Docket Operations, M–30, West This [Canadian] AD mandates inspections
in the area of the longeron joint fittings. • Do not add any additional burden
Building Ground Floor, Room W12–140, upon the public than was already
1200 New Jersey Avenue SE., Corrective actions include replacing any proposed in the NPRM.
Washington, DC 20590. loose or working fasteners (fasteners We also determined that these
that show signs of wear, fatigue, or changes will not increase the economic
FOR FURTHER INFORMATION CONTACT: Aziz
corrosion), repairing any structural burden on any operator or increase the
Ahmed, Aerospace Engineer, Airframe
damage, and replacing any cracked scope of this AD.
and Mechanical Systems Branch, ANE–
mstockstill on DSK3G9T082PROD with RULES
longeron or longeron with an amplitude
171, FAA, New York Aircraft Related Service Information Under
of 50% or more of the calibration signal.
Certification Office (ACO), 1600 Stewart 1 CFR Part 51
You may examine the MCAI in the AD
Avenue, Suite 410, Westbury, NY
docket on the Internet at http:// We reviewed Bombardier Service
11590; telephone 516–228–7329; fax
www.regulations.gov by searching for Bulletin 84–53–65, Revision A, dated
516–794–5531.
and locating Docket No. FAA–2016– February 22, 2016. The service
SUPPLEMENTARY INFORMATION: 8178. information describes procedures for
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![Federal Register / Vol. 81, No. 238 / Monday, December 12, 2016 / Rules and Regulations 89369
inspections of the external surface of the Authority for This Rulemaking § 39.13 [Amended]
fuselage skin panel for loose or working ■ 2. The FAA amends § 39.13 by adding
Title 49 of the United States Code
fasteners; a detailed visual inspection of the following new airworthiness
specifies the FAA’s authority to issue
the longeron joint fittings for the directive (AD):
rules on aviation safety. Subtitle I,
existence of shims; high frequency eddy
section 106, describes the authority of 2016–24–04 Bombardier, Inc: Amendment
current inspections of the longeron and 39–18721; Docket No. FAA–2016–8178;
the FAA Administrator. ‘‘Subtitle VII:
the longeron joint fittings for any Directorate Identifier 2015–NM–197–AD.
Aviation Programs,’’ describes in more
cracking; and replacement of longeron
detail the scope of the Agency’s (a) Effective Date
fittings, shims, and fasteners. This
authority. This AD is effective January 17, 2017.
service information is reasonably
available because the interested parties We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII, (b) Affected ADs
have access to it through their normal None.
course of business or by the means Part A, Subpart III, Section 44701:
identified in the ADDRESSES section. General requirements.’’ Under that (c) Applicability
section, Congress charges the FAA with This AD applies to Bombardier, Inc. Model
Costs of Compliance promoting safe flight of civil aircraft in DHC–8–400, –401, and –402 airplanes,
We estimate that this AD affects 76 air commerce by prescribing regulations certificated in any category, serial numbers
airplanes of U.S. registry. for practices, methods, and procedures 4156 through 4453 inclusive, 4456, and 4457.
the Administrator finds necessary for
We also estimate that it will take (d) Subject
safety in air commerce. This regulation
about 2 work-hours per product to Air Transport Association (ATA) of
is within the scope of that authority
comply with the basic requirements of America Code 53, Fuselage.
because it addresses an unsafe condition
this AD. The average labor rate is $85
that is likely to exist or develop on (e) Reason
per work-hour. Based on these figures,
products identified in this rulemaking This AD was prompted by a determination
we estimate the cost of this AD on U.S.
action. by the manufacturer that shims might not
operators to be $12,920, or $170 per have been installed between certain
product. Regulatory Findings longerons and longeron joint fittings. We are
In addition, we estimate that any We determined that this AD will not issuing this AD to detect and correct missing
necessary follow-on actions will take have federalism implications under shims between the longerons and longeron
about 3 work-hours for the inspection joint fittings, which could result in a gapping
Executive Order 13132. This AD will condition and lead to stress corrosion
for missing shims, 9 work-hours for the not have a substantial direct effect on
replacement of longeron fittings and cracking of the longeron joint fittings, and
the States, on the relationship between could adversely affect the structural integrity
shims, and 1 work-hour for a reporting the national government and the States, of the wing-to-fuselage attachment joints.
requirement; and would require parts or on the distribution of power and
costing $3,222; for a cost of up to $4,327 (f) Compliance
responsibilities among the various
per product. We have no way of levels of government. Comply with this AD within the
determining the number of aircraft that compliance times specified, unless already
For the reasons discussed above, I done.
might need these actions. We have
certify that this AD:
received no definitive data that will (g) Inspection of the External Surface of the
enable us to provide cost estimates for 1. Is not a ‘‘significant regulatory Fuselage Skin Panels
repair of loose or working fasteners or action’’ under Executive Order 12866;
At the time specified in paragraph (g)(1) or
structural damage specified in this AD. 2. Is not a ‘‘significant rule’’ under the (g)(2) of this AD, as applicable, do a detailed
DOT Regulatory Policies and Procedures visual inspection of the external surface of
Paperwork Reduction Act (44 FR 11034, February 26, 1979); the fuselage skin panel for loose or working
A federal agency may not conduct or 3. Will not affect intrastate aviation in fasteners (fasteners that show signs of wear,
sponsor, and a person is not required to Alaska; and fatigue, or corrosion) and structural damage,
respond to, nor shall a person be subject 4. Will not have a significant in accordance with paragraph 3.B. of the
Accomplishment Instructions of Bombardier
to penalty for failure to comply with a economic impact, positive or negative, Service Bulletin 84–53–65, Revision A, dated
collection of information subject to the on a substantial number of small entities February 22, 2016.
requirements of the Paperwork under the criteria of the Regulatory (1) For airplanes that have accumulated
Reduction Act unless that collection of Flexibility Act. less than 10,000 total flight hours, or less
information displays a current valid than 5 years in service since new, as of the
List of Subjects in 14 CFR Part 39 effective date of this AD: Prior to
OMB control number. The control
number for the collection of information Air transportation, Aircraft, Aviation accumulating 12,000 total flight hours or 6
required by this AD is 2120–0056. The safety, Incorporation by reference, years in service since new, whichever occurs
Safety. first.
paperwork cost associated with this AD
(2) For airplanes that have accumulated
has been detailed in the Costs of 10,000 total flight hours or more, or 5 years
Adoption of the Amendment
Compliance section of this document or more in service since new, as of the
and includes time for reviewing Accordingly, under the authority effective date of this AD: Within 2,000 flight
instructions, as well as completing and delegated to me by the Administrator, hours or 12 months after the effective date of
reviewing the collection of information. the FAA amends 14 CFR part 39 as this AD, whichever occurs first.
Therefore, all reporting associated with follows: (h) Corrective Actions
mstockstill on DSK3G9T082PROD with RULES
this AD is mandatory. Comments
PART 39—AIRWORTHINESS If any loose or working fastener or any
concerning the accuracy of this burden
DIRECTIVES structural damage is found during any
and suggestions for reducing the burden inspection required by this AD: Before
should be directed to the FAA at 800 further flight, repair using a method
Independence Ave. SW., Washington, ■ 1. The authority citation for part 39
approved by the Manager, New York Aircraft
DC 20591, ATTN: Information continues to read as follows: Certification Office (ACO), FAA; or Transport
Collection Clearance Officer, AES–200. Authority: 49 U.S.C. 106(g), 40113, 44701. Canada Civil Aviation (TCCA); or
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![Federal Register / Vol. 81, No. 238 / Monday, December 12, 2016 / Rules and Regulations 89371
Issued in Renton, Washington, on call 425–227–1221. It is also available following presents the comments
November 17, 2016. on the Internet at http:// received on the NPRM and the FAA’s
Phil Forde, www.regulations.gov by searching for response to each comment.
Acting Manager, Transport Airplane and locating Docket No. FAA–2016–
Support for the NPRM
Directorate, Aircraft Certification Service. 5598.
[FR Doc. 2016–28597 Filed 12–9–16; 8:45 am] United Airlines stated that it concurs
Examining the AD Docket
BILLING CODE 4910–13–P with the NPRM.
You may examine the AD docket on
the Internet at http:// Request To Remove Redundant
DEPARTMENT OF TRANSPORTATION www.regulations.gov by searching for Requirements
and locating Docket No. FAA–2016– Boeing requested we change
Federal Aviation Administration 5598; or in person at the Docket paragraph (i) of the proposed AD to
Management Facility between 9 a.m. remove redundant language. Boeing
14 CFR Part 39 and 5 p.m., Monday through Friday, requested we remove the second half of
except Federal holidays. The AD docket the paragraph and subparagraphs (i)(1)
[Docket No. FAA–2016–5598; Directorate
contains this AD, the regulatory and (i)(2) of the proposed AD because
Identifier 2016–NM–001–AD; Amendment
39–18735; AD 2016–25–09]
evaluation, any comments received, and they include redundant requirements.
other information. The address for the Boeing also noted that the redundant
RIN 2120–AA64 Docket Office (phone: 800–647–5527) is requirements include an exception that
Docket Management Facility, U.S. does not apply to table 3 of paragraph
Airworthiness Directives; The Boeing Department of Transportation, Docket
Company Airplanes 1.E., ‘‘Compliance,’’ of Boeing Alert
Operations, M–30, West Building Service Bulletin 747–53A2784, Revision
AGENCY: Federal Aviation Ground Floor, Room W12–140, 1200 2, dated August 20, 2015.
Administration (FAA), DOT. New Jersey Avenue SE., Washington,
We agree to revise paragraph (i) of this
DC 20590.
ACTION: Final rule. AD for the reasons provided by Boeing.
FOR FURTHER INFORMATION CONTACT: Bill We have revised paragraph (i) of this AD
SUMMARY: We are superseding Ashforth, Aerospace Engineer, Airframe accordingly.
Airworthiness Directive (AD) 2012–22– Branch, ANM–120S, FAA, Seattle
02 for certain The Boeing Company Aircraft Certification Office (ACO), 1601 Conclusion
Model 747–400, –400D, and –400F Lind Avenue SW., Renton, WA 98057– We reviewed the relevant data,
series airplanes. AD 2012–22–02 3356; phone: 425–917–6432; fax: 425– considered the comments received, and
required measuring the web at station 917–6590; email: Bill.Ashforth@faa.gov. determined that air safety and the
(STA) 320 and, depending on findings, SUPPLEMENTARY INFORMATION: public interest require adopting this AD
various inspections for cracks and Discussion with the change described previously,
missing fasteners, web and fastener and minor editorial changes. We have
replacement, and related investigative We issued a notice of proposed
determined that these minor changes:
rulemaking (NPRM) to amend 14 CFR
and corrective actions if necessary. This
part 39 to supersede AD 2012–22–02, • Are consistent with the intent that
new AD requires, for certain airplanes, was proposed in the NPRM for
replacement of the web, including Amendment 39–17238 (77 FR 69739,
November 21, 2012) (‘‘AD 2012–22– correcting the unsafe condition; and
related investigative and corrective • Do not add any additional burden
actions if necessary. This AD was 02’’). AD 2012–22–02 applied to certain
The Boeing Company Model 747–400, upon the public than was already
prompted by a determination that there proposed in the NPRM.
were no inspection or repair procedures –400D, and –400F series airplanes. The
NPRM published in the Federal We also determined that these
included in AD 2012–22–02 for changes will not increase the economic
airplanes with a certain crown frame Register on April 28, 2016 (81 FR
25357) (‘‘the NPRM’’). The NPRM was burden on any operator or increase the
web thickness. We are issuing this AD scope of this AD.
to address the unsafe condition on these prompted by a determination that there
products. were no inspection or repair procedures Related Service Information Under 1
included in AD 2012–22–02 for CFR Part 51
DATES: This AD is effective January 17,
airplanes with a STA 320 crown frame
2017. web thickness less than 0.078 inch, or We reviewed Boeing Alert Service
The Director of the Federal Register greater than or equal to 0.084 inch and Bulletin 747–53A2784, Revision 2,
approved the incorporation by reference less than or equal to 0.135 inch. The dated August 20, 2015. The service
of a certain publication listed in this AD NPRM proposed to continue to require information describes procedures for
as of January 17, 2017. certain actions required by AD 2012– various inspections for cracks and
ADDRESSES: For service information 22–02. The NPRM also proposed to missing fasteners, web and fastener
identified in this final rule, contact require, for certain airplanes, replacement, and related investigative
Boeing Commercial Airplanes, replacement of the web, including and corrective actions, if necessary. This
Attention: Data & Services Management, related investigative and corrective service information is reasonably
P.O. Box 3707, MC 2H–65, Seattle, WA actions if necessary. We are issuing this available because the interested parties
98124–2207; telephone: 206–544–5000, AD to prevent complete fracture of the have access to it through their normal
extension 1; fax: 206–766–5680; crown frame assembly, and consequent course of business or by the means
mstockstill on DSK3G9T082PROD with RULES
Internet: https:// damage to the skin. Such damage could identified in the ADDRESSES section.
www.myboeingfleet.com. You may view result in in-flight decompression of the Costs of Compliance
this referenced service information at airplane.
the FAA, Transport Airplane We estimate that this AD affects 29
Directorate, 1601 Lind Avenue SW., Comments airplanes.
Renton, WA. For information on the We gave the public the opportunity to We estimate the following costs to
availability of this material at the FAA, participate in developing this AD. The comply with this AD:
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Document Created: 2018-02-14 09:05:18
Document Modified: 2018-02-14 09:05:18
| 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 January 17, 2017. | |
| Contact | Aziz Ahmed, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516-228-7329; fax 516-794-5531. | |
| FR Citation | 81 FR 89367 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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