Document ID: FAA-2016-7422-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Bombardier, Inc. Airplanes
Posted Date: 2016-07-05T04:00Z

[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]

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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.

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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 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 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: 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-
7422.

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-
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 http://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 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 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 http://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: 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.

    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