Airworthiness Directives; Bombardier, Inc. Airplanes, 43481-43483 [2016-15357]

Download as PDF Federal Register / Vol. 81, No. 128 / Tuesday, July 5, 2016 / Rules and Regulations 2016, which contains the requirements of this AD. (d) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (e) Required Action Further flight is prohibited. (f) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Gary Roach, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email 9ASW-FTW-AMOC-Requests@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC. (g) Additional Information The subject of this AD is addressed in European Aviation Safety Agency (EASA) Emergency AD 2016–0104–E, dated June 2, 2016. You may view the EASA AD on the Internet at https://www.regulations.gov by searching for and locating it in Docket No. FAA–2016–8032. (h) Subject Joint Aircraft Service Component (JASC) Code: Main Rotor Gearbox: 6320. Issued in Fort Worth, Texas, on June 23, 2016. James A. Grigg, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2016–15624 Filed 7–1–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–7422; Directorate Identifier 2016–NM–079–AD; Amendment 39–18579; AD 2016–13–14] RIN 2120–AA64 sradovich on DSK3GDR082PROD with RULES Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for certain SUMMARY: VerDate Sep<11>2014 16:06 Jul 01, 2016 Jkt 238001 Bombardier, Inc. Model DHC–8–400 series airplanes. This AD requires an inspection to determine if certain left and right main landing gear (MLG) retract actuator rod ends are installed and repetitive liquid penetrant inspections (LPIs) of affected left and right MLG retract actuator rod ends, and corrective actions if necessary. This AD also provides optional terminating action for the inspections. This AD was prompted by a report of cracked MLG retract actuator rod ends. We are issuing this AD to detect and correct fatigue cracking of the left and right MLG retract actuator rod ends, which could lead to left or right MLG collapse. DATES: This AD becomes effective July 20, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 20, 2016. We must receive comments on this AD by August 19, 2016. 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 https://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 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: thd.qseries@aero.bombardier.com; Internet: https://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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 7422. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 43481 and locating Docket No. FAA–2016– 7422; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone: 800–647–5527) is in the ADDRESSES section. 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 (ACO), 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone: 516–228–7329; fax: 516–794–5531. SUPPLEMENTARY INFORMATION: Discussion Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian AD CF–2016–16, dated May 20, 2016 (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: There has been a single reported case of a cracked MLG retract actuator rod end in service. A supplier disclosure letter and subsequent Bombardier analysis indicate that the MLG retract actuator rod end P/N [part number] P3A2750 and P3A2750–1 may develop fatigue cracking. This condition, if not corrected, could lead to left hand (LH) or right hand (RH) MLG collapse. This [Canadian] AD mandates the inspection [to determine if certain left and right main landing gear MLG retract actuator rod ends are installed, repetitive LPIs of affected left and right MLG retract actuator rod ends, and corrective actions if necessary], and replacement of the LH and RH MLG retract actuator rod ends P/N P3A2750 and P3A2750–1 [which is terminating action for the repetitive LPIs]. Corrective actions includes replacing cracked MLG retract actuator rod ends. You may examine the MCAI on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2016–7422. Related Service Information Under 1 CFR Part 51 Bombardier, Inc. has issued Service Bulletin 84–32–142, dated May 4, 2016. The service information describes procedures for an inspection to determine if certain left and right MLG retract actuator rod ends are installed, repetitive LPIs of the left and right MLG retract actuator rod ends, and replacement of left and right MLG E:\FR\FM\05JYR1.SGM 05JYR1 43482 Federal Register / Vol. 81, No. 128 / Tuesday, July 5, 2016 / Rules and Regulations retract actuator rod ends. 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. FAA’s Determination and Requirements of This 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 issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. FAA’s Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because fatigue cracking of the left and right MLG retract actuator rod ends could lead to left or right MLG collapse. Therefore, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days. sradovich on DSK3GDR082PROD with RULES Interim Action We consider this AD interim action. We are currently considering requiring the replacement of affected left and right MLG retract actuator rod ends with P/N P3A6460, which will constitute terminating action for the inspections required by this AD. However, the planned compliance time for the replacement would allow enough time to provide notice and opportunity for prior public comment on the merits of the replacement. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2016–7422; Directorate Identifier 2016–NM–079– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, VerDate Sep<11>2014 16:06 Jul 01, 2016 Jkt 238001 environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. Costs of Compliance We estimate that this AD affects 52 airplanes of U.S. registry. We also estimate that it will take about 1 work-hour 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 $4,420, or $85 per product. In addition, we estimate that any necessary follow-on actions will take about 3 work-hours and require parts costing $2,019, for a cost of $2,274 per product. We have no way of determining the number of aircraft that might need these actions. According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2016–13–14 Bombardier, Inc.: Amendment 39–18579. Docket No. FAA–2016–7422; Directorate Identifier 2016–NM–079–AD. (a) Effective Date This AD becomes effective July 20, 2016. (b) Affected ADs None. (c) Applicability This AD applies to Bombardier, Inc. Model DHC–8–400, –401 and –402 airplanes, certificated in any category, serial numbers 4001, and 4003 through 4325 inclusive. (d) Subject Air Transport Association (ATA) of America Code 32, Landing gear. (e) Reason This AD was prompted by a report of cracked main landing gear (MLG) retract actuator rod ends. We are issuing this AD to detect and correct fatigue cracking of the left and right MLG retract actuator rod ends, which could lead to left or right MLG collapse. E:\FR\FM\05JYR1.SGM 05JYR1 Federal Register / Vol. 81, No. 128 / Tuesday, July 5, 2016 / Rules and Regulations (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Part Number Inspection Within 100 flight cycles after the effective date of this AD, inspect the left and right MLG retract actuator rod ends to determine if part number (P/N) P3A2750 or P3A2750– 1 is installed. A review of airplane maintenance records is acceptable in lieu of this inspection if the part number can be conclusively determined from that review. (h) Repetitive Liquid Penetrant Inspections (LPIs) For each left or right MLG retract actuator rod end having P/N P3A2750 or P3A2750–1: At the applicable time specified in paragraph (h)(1) or (h)(2) of this AD, do an LPI to detect cracks of the MLG retract actuator rod end, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–32–142, dated May 4, 2016, except as required by paragraph (k) of this AD. Thereafter, repeat the LPI at intervals not to exceed 600 flight cycles. (1) If the MLG retract actuator rod end has accumulated more than 6,000 flight cycles as of the effective date of this AD: Inspect within 100 flight cycles after the effective date of this AD. (2) If the MLG retract actuator rod end has accumulated 6,000 flight cycles or fewer as of the effective date of this AD: Inspect within 600 flight cycles after the effective date of this AD. (i) Corrective Action If any crack is found during any inspection required by paragraph (h) of this AD, before further flight replace the cracked MLG retract actuator rod end, P/N P3A2750 or P3A2750– 1, with a MLG retract actuator rod end, P/N P3A6460 in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–32–142, dated May 4, 2016, except as required by paragraph (k) of this AD. (j) Optional Replacement Replacement of the left and right side MLG retract actuator rod ends, P/N P3A2750 or P3A2750–1, with left and right MLG retract actuator rod ends, P/N P3A6460, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–32–142, dated May 4, 2016, except as required by paragraph (k) of this AD, constitutes terminating action for the actions required by paragraphs (g) and (h) of this AD for that airplane. sradovich on DSK3GDR082PROD with RULES (k) Exception to Paragraphs (h), (i), and (j) of This AD If it is not possible to complete all the instructions in Bombardier Service Bulletin 84–32–142, dated May 4, 2016 because of the configuration of the airplane: 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). VerDate Sep<11>2014 16:06 Jul 01, 2016 Jkt 238001 (l) Parts Installation Prohibition As of the effective date of this AD, no person may install a left or right MLG retract actuator rod end, P/N P3A2750 or P3A2750– 1, on any airplane. (m) 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: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, New York ACO, ANE–170, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.’s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. (n) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian AD CF–2016–16, dated May 20, 2016, for related information. You may examine the MCAI on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016–7422. (o) 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 84–32–142, dated May 4, 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: thd.qseries@ aero.bombardier.com; Internet: https:// 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 PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 43483 National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on June 22, 2016. Dorr M. Anderson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–15357 Filed 7–1–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–3628; Directorate Identifier 2015–NM–025–AD; Amendment 39–18574; AD 2016–13–10] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2012–12– 04, for certain The Boeing Company Model 737–300, –400, and –500 series airplanes. AD 2012–12–04 required repetitive external detailed inspections and nondestructive inspections to detect cracks in the fuselage skin along the chem-mill steps at stringers S–1 and S– 2R, between station (STA) 400 and STA 460, and repair if necessary. This new AD requires a preventive modification of the fuselage skin at crown stringers S–1 and S–2R. This new AD also reduces the inspection threshold for certain airplanes. This AD was prompted by a determination that, for certain airplanes, the skin pockets adjacent to the Air Traffic Control (ATC) antenna are susceptible to widespread fatigue damage. We are issuing this AD to detect and correct fatigue cracking of the fuselage skin panels at the chemmill steps, which could result in sudden fracture and failure of the fuselage skin panels, and consequent rapid decompression of the airplane. DATES: This AD is effective August 9, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 9, 2016. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in SUMMARY: E:\FR\FM\05JYR1.SGM 05JYR1

Agencies

[Federal Register Volume 81, Number 128 (Tuesday, July 5, 2016)]
[Rules and Regulations]
[Pages 43481-43483]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-15357]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-7422; Directorate Identifier 2016-NM-079-AD; 
Amendment 39-18579; AD 2016-13-14]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Bombardier, Inc. Model DHC-8-400 series airplanes. This AD requires an 
inspection to determine if certain left and right main landing gear 
(MLG) retract actuator rod ends are installed and repetitive liquid 
penetrant inspections (LPIs) of affected left and right MLG retract 
actuator rod ends, and corrective actions if necessary. This AD also 
provides optional terminating action for the inspections. This AD was 
prompted by a report of cracked MLG retract actuator rod ends. We are 
issuing this AD to detect and correct fatigue cracking of the left and 
right MLG retract actuator rod ends, which could lead to left or right 
MLG collapse.

DATES: This AD becomes effective July 20, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of July 20, 
2016.
    We must receive comments on this AD by August 19, 2016.

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 https://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 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: thd.qseries@aero.bombardier.com; Internet: https://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 https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
7422.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
7422; or in person at the Docket Operations office between 9 a.m. and 5 
p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Operations office 
(telephone: 800-647-5527) is in the ADDRESSES section. 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 (ACO), 1600 Stewart Avenue, Suite 410, Westbury, 
NY 11590; telephone: 516-228-7329; fax: 516-794-5531.

SUPPLEMENTARY INFORMATION: 

Discussion

    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian AD CF-2016-16, dated May 20, 
2016 (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:

    There has been a single reported case of a cracked MLG retract 
actuator rod end in service. A supplier disclosure letter and 
subsequent Bombardier analysis indicate that the MLG retract 
actuator rod end P/N [part number] P3A2750 and P3A2750-1 may develop 
fatigue cracking. This condition, if not corrected, could lead to 
left hand (LH) or right hand (RH) MLG collapse.
    This [Canadian] AD mandates the inspection [to determine if 
certain left and right main landing gear MLG retract actuator rod 
ends are installed, repetitive LPIs of affected left and right MLG 
retract actuator rod ends, and corrective actions if necessary], and 
replacement of the LH and RH MLG retract actuator rod ends P/N 
P3A2750 and P3A2750-1 [which is terminating action for the 
repetitive LPIs].

    Corrective actions includes replacing cracked MLG retract actuator 
rod ends. You may examine the MCAI on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
7422.

Related Service Information Under 1 CFR Part 51

    Bombardier, Inc. has issued Service Bulletin 84-32-142, dated May 
4, 2016. The service information describes procedures for an inspection 
to determine if certain left and right MLG retract actuator rod ends 
are installed, repetitive LPIs of the left and right MLG retract 
actuator rod ends, and replacement of left and right MLG

[[Page 43482]]

retract actuator rod ends. 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.

FAA's Determination and Requirements of This 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 issuing this AD because we 
evaluated all pertinent information and determined the unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because 
fatigue cracking of the left and right MLG retract actuator rod ends 
could lead to left or right MLG collapse. Therefore, we determined that 
notice and opportunity for public comment before issuing this AD are 
impracticable and that good cause exists for making this amendment 
effective in fewer than 30 days.

Interim Action

    We consider this AD interim action. We are currently considering 
requiring the replacement of affected left and right MLG retract 
actuator rod ends with P/N P3A6460, which will constitute terminating 
action for the inspections required by this AD. However, the planned 
compliance time for the replacement would allow enough time to provide 
notice and opportunity for prior public comment on the merits of the 
replacement.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2016-7422; Directorate 
Identifier 2016-NM-079-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD based on 
those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Costs of Compliance

    We estimate that this AD affects 52 airplanes of U.S. registry.
    We also estimate that it will take about 1 work-hour 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 $4,420, or $85 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 3 work-hours and require parts costing $2,019, for a cost of 
$2,274 per product. We have no way of determining the number of 
aircraft that might need these actions.
    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

Authority for This Rulemaking

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

Regulatory Findings

    We determined that this 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):

2016-13-14 Bombardier, Inc.: Amendment 39-18579. Docket No. FAA-
2016-7422; Directorate Identifier 2016-NM-079-AD.

(a) Effective Date

    This AD becomes effective July 20, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Bombardier, Inc. Model DHC-8-400, -401 and -
402 airplanes, certificated in any category, serial numbers 4001, 
and 4003 through 4325 inclusive.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Landing 
gear.

(e) Reason

    This AD was prompted by a report of cracked main landing gear 
(MLG) retract actuator rod ends. We are issuing this AD to detect 
and correct fatigue cracking of the left and right MLG retract 
actuator rod ends, which could lead to left or right MLG collapse.

[[Page 43483]]

(f) Compliance

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

(g) Part Number Inspection

    Within 100 flight cycles after the effective date of this AD, 
inspect the left and right MLG retract actuator rod ends to 
determine if part number (P/N) P3A2750 or P3A2750-1 is installed. A 
review of airplane maintenance records is acceptable in lieu of this 
inspection if the part number can be conclusively determined from 
that review.

(h) Repetitive Liquid Penetrant Inspections (LPIs)

    For each left or right MLG retract actuator rod end having P/N 
P3A2750 or P3A2750-1: At the applicable time specified in paragraph 
(h)(1) or (h)(2) of this AD, do an LPI to detect cracks of the MLG 
retract actuator rod end, in accordance with the Accomplishment 
Instructions of Bombardier Service Bulletin 84-32-142, dated May 4, 
2016, except as required by paragraph (k) of this AD. Thereafter, 
repeat the LPI at intervals not to exceed 600 flight cycles.
    (1) If the MLG retract actuator rod end has accumulated more 
than 6,000 flight cycles as of the effective date of this AD: 
Inspect within 100 flight cycles after the effective date of this 
AD.
    (2) If the MLG retract actuator rod end has accumulated 6,000 
flight cycles or fewer as of the effective date of this AD: Inspect 
within 600 flight cycles after the effective date of this AD.

(i) Corrective Action

    If any crack is found during any inspection required by 
paragraph (h) of this AD, before further flight replace the cracked 
MLG retract actuator rod end, P/N P3A2750 or P3A2750-1, with a MLG 
retract actuator rod end, P/N P3A6460 in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 84-32-
142, dated May 4, 2016, except as required by paragraph (k) of this 
AD.

(j) Optional Replacement

    Replacement of the left and right side MLG retract actuator rod 
ends, P/N P3A2750 or P3A2750-1, with left and right MLG retract 
actuator rod ends, P/N P3A6460, in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 84-32-
142, dated May 4, 2016, except as required by paragraph (k) of this 
AD, constitutes terminating action for the actions required by 
paragraphs (g) and (h) of this AD for that airplane.

(k) Exception to Paragraphs (h), (i), and (j) of This AD

    If it is not possible to complete all the instructions in 
Bombardier Service Bulletin 84-32-142, dated May 4, 2016 because of 
the configuration of the airplane: 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).

(l) Parts Installation Prohibition

    As of the effective date of this AD, no person may install a 
left or right MLG retract actuator rod end, P/N P3A2750 or P3A2750-
1, on any airplane.

(m) 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: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, New York ACO, ANE-170, FAA; or Transport 
Canada Civil Aviation (TCCA); or Bombardier, Inc.'s TCCA Design 
Approval Organization (DAO). If approved by the DAO, the approval 
must include the DAO-authorized signature.

(n) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
Canadian AD CF-2016-16, dated May 20, 2016, for related information. 
You may examine the MCAI on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-
2016-7422.

(o) 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 84-32-142, dated May 4, 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: thd.qseries@aero.bombardier.com; 
Internet: https://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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on June 22, 2016.
Dorr M. Anderson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-15357 Filed 7-1-16; 8:45 am]
 BILLING CODE 4910-13-P
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.