Airworthiness Directives; Bombardier, Inc. Airplanes

[Federal Register Volume 78, Number 211 (Thursday, October 31, 2013)]
[Rules and Regulations]
[Pages 65176-65178]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-25305]



[[Page 65176]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1311; Directorate Identifier 2011-NM-204-AD; 
Amendment 39-17636; AD 2013-22-04]
RIN 2120-AA64


Airworthiness Directives; Bombardier, Inc. Airplanes

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

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Bombardier, Inc. Model DHC-8-102, -103, and -106 airplanes; and Model 
DHC-8-200, -300, and -400 series airplanes. This AD was prompted by 
reports of excessive wear found in the clevis (bolt) hole where the rod 
assembly attaches to the rudder/brake pedal bellcrank, due to prolonged 
fretting. This AD requires measuring the bellcrank clevis holes, 
inspecting for cracking of the bellcrank, and re-working the clevis 
holes with steel bushings, or replacing the bellcrank. We are issuing 
this AD to detect and correct a worn or cracked clevis hole, which 
could cause failure of the bellcrank on one side, with subsequent 
asymmetric braking and consequent runway excursion.

DATES: This AD becomes effective December 5, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of December 5, 
2013.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2012-1311; or in person at the 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 
Washington, DC.
    For service information identified in this AD, contact Bombardier, 
Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, 
Ontario M3K 1Y5, Canada; telephone 416-375-4000; fax 416-375-4539; 
email [email protected]; Internet http://www.bombardier.com. You may view this 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.

FOR FURTHER INFORMATION CONTACT: Luke Walker, Aerospace Engineer, 
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New 
York 11590; telephone (516) 228-7363; 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 the specified products. The 
NPRM was published in the Federal Register on December 26, 2012 (77 FR 
75906). The NPRM proposed to correct an unsafe condition for the 
specified products. Transport Canada Civil Aviation (TCCA), which is 
the aviation authority for Canada, issued Canadian Airworthiness 
Directive CF-2011-32, dated August 15, 2011 (referred to after this as 
the Mandatory Continuing Airworthiness Information, or ``the MCAI''), 
to correct an unsafe condition for the specified products. The MCAI 
states:

    There have been several in-service reports of excessive wear 
found in the bolt [clevis] hole where the rod assembly, Part Numbers 
(P/N) 82710795-001 or 82710024-003, is attached to the rudder/brake 
pedal bellcrank. An investigation revealed that the wear was 
attributed to prolonged fretting.
    Failure of the bellcrank on one side could lead to asymmetric 
braking and may lead to runway excursion.
    This [Canadian] directive mandates [measuring clevis holes for 
length, and, for certain bellcranks, doing a liquid penetrant 
inspection for cracking, and] the re-work [by installing steel 
bushings] or replacement of each bellcrank, P/N 82710022-001/-002, 
82710029-001/-002, 82710813-001/-002 and 82710814-001/-002, found 
with a worn [or cracked] bolt hole.

You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2012-1311-0002.

Revised Service Information

    Bombardier, Inc. has issued Service Bulletin 84-27-55, Revision A, 
dated February 22, 2012. The NPRM (77 FR 75906, December 26, 2012) 
referred to Bombardier Service Bulletin 84-27-55, dated June 15, 2011, 
in paragraphs (h) and (i) of the NPRM. In this final rule, we have 
revised the service bulletin references in those paragraphs 
accordingly, and have added new paragraph (j) to this final rule to 
give credit for actions done before the effective date of this AD in 
accordance with Bombardier Service Bulletin 84-27-55, dated June 15, 
2011 (and redesignated subsequent paragraphs accordingly).

Comments

    We gave the public the opportunity to participate in developing 
this AD. We have considered the comments received.

Request To Allow Use of Serviceable Parts

    An anonymous commenter requested that the references to ``new 
bellcrank'' in the NPRM (77 FR 75906, December 26, 2012) be changed to 
allow operators to install ``serviceable'' bellcranks (new bellcranks 
or ones that have been modified according to the applicable service 
information), thus giving equal safety, yet providing more flexibility 
and less recordkeeping for operators.
    We agree with the commenter's request for the reasons given. We 
have revised paragraphs (g)(2), (h)(2), (h)(3), (h)(4), (i)(2), (i)(3), 
and (i)(4) of this AD by specifying to replace the bellcrank with a new 
bellcrank ``or with a serviceable bellcrank with bushings having part 
number 82710297-101 installed.'' We have also clarified paragraphs 
(h)(1) and (i)(1) of this final rule by specifying to replace the 
bellcrank ``with a new or with a serviceable bellcrank with bushings 
having part number 82710297-101 installed.''

Request To Add Eddy Current Inspection Option

    The same anonymous commenter requested that we include an eddy 
current inspection option in this final rule to agree with parallel 
actions specified in Bombardier Service Bulletin 84-27-55, Revision A, 
dated February 22, 2012.
    We agree with the commenter's request because Bombardier added that 
inspection option in Bombardier Service Bulletin 84-27-55, Revision A, 
dated February 22, 2012. Accordingly, we have added the option in 
paragraphs (h) and (i) of this final rule.

Request To Clarify Compliance Times

    The same anonymous commenter, in an incomplete request, stated that 
the replacement times in paragraph (h) of the NPRM (77 FR 75906, 
December 26, 2012) do not sufficiently remove the identified unsafe 
condition. From the truncated statement, we cannot infer what part of 
paragraph (h) the commenter requested that we change. We have made no 
change to this final rule in this regard.

Conclusion

    We reviewed the available data, including the comments received, 
and

[[Page 65177]]

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 changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM (77 FR 75906, December 26, 2012) for correcting the unsafe 
condition; and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the NPRM (77 FR 75906, December 26, 2012).

Costs of Compliance

    We estimate that this AD will affect 178 products of U.S. registry. 
We also estimate that it will take 5 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 
to the U.S. operators to be $75,650, or $425 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 16 work-hours and require parts costing up to $2,532, for a 
cost of $3,892 per product. Where the service information lists 
required parts costs that are covered under warranty, we have assumed 
that there will be no charge for these parts. As we do not control 
warranty coverage for affected parties, some parties may incur costs 
higher than estimated here. We have no way of determining the number of 
products that may need these actions.

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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2012-1311-0002; 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 MCAI, 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.

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 AD:

2013-22-04 Bombardier, Inc.: Amendment 39-17636. Docket No. FAA-
2012-1311; Directorate Identifier 2011-NM-204-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective December 5, 
2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Bombardier, Inc. airplanes, certificated in 
any category, as specified in paragraphs (c)(1) and (c)(2) of this 
AD.
    (1) Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -
315 airplanes: Serial numbers 003 through 672 inclusive.
    (2) Model DHC-8-400, -401, and -402 airplanes: Serial numbers 
4003 through 4372 inclusive.

(d) Subject

    Air Transport Association (ATA) of America Code 27: Flight 
controls.

(e) Reason

    This AD was prompted by reports of excessive wear found in the 
clevis (bolt) hole where the rod assembly attaches to the rudder/
brake pedal bellcrank, due to prolonged fretting. We are issuing 
this AD to detect and correct a worn or cracked clevis hole, which 
could cause failure of the bellcrank on one side, with subsequent 
asymmetric braking and consequent runway excursion.

(f) Compliance

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) Actions for Model DHC-8-100, -200, and -300 Series Airplanes

    For Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -
315 airplanes: Within 6,000 flight hours or 24 months after the 
effective date of this AD, whichever occurs first, inspect each 
bellcrank for cracking using liquid penetrant, in accordance with 
the Accomplishment Instructions of Bombardier Service Bulletin 8-27-
111, dated June 15, 2011.
    (1) If no cracking is found: Before further flight, rework the 
bellcrank, in accordance with the Accomplishment Instructions of 
Bombardier Service Bulletin 8-27-111, dated June 15, 2011.
    (2) If any clevis hole is greater than 0.218 inch (measured 
edge-to-edge), or if any cracking is found: Before further flight, 
replace the bellcrank with a new bellcrank, or with a serviceable 
bellcrank with bushings having part number 82710297-101 installed, 
in accordance with the Accomplishment Instructions of Bombardier 
Service Bulletin 8-27-111, dated June 15, 2011.

(h) Actions for Certain Model DHC-8-400 Series Airplanes

    For Model DHC-8-400, -401, and -402 airplanes that have 
accumulated less than or equal to 15,000 total flight hours as of 
the effective date of this AD: Within 6,000 flight hours after the 
effective date of this AD, but not to exceed 15,600 total flight 
hours, measure the edge-to-edge length of the clevis holes of each 
bellcrank, and inspect each bellcrank for cracking using liquid 
penetrant or eddy current inspection method; in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 84-27-55, 
Revision A, dated February 22, 2012.

[[Page 65178]]

    (1) If no cracking is found, and the edge-to-edge length of all 
clevis holes is less than or equal to 0.218 inch: Within 6,000 
flight hours after the effective date of this AD, but not to exceed 
15,600 total flight hours, rework the bellcrank, or replace the 
bellcrank with a new bellcrank or with a serviceable bellcrank with 
bushings having part number 82710297-101 installed, in accordance 
with the Accomplishment Instructions of Bombardier Service Bulletin 
84-27-55, Revision A, dated February 22, 2012.
    (2) If no cracking is found, and any clevis hole edge-to-edge 
length is greater than 0.218 inch, but is less than or equal to 
0.248 inch: Within 6,000 flight hours after the effective date of 
this AD, replace the bellcrank with a new bellcrank, or with a 
serviceable bellcrank with bushings having part number 82710297-101 
installed, in accordance with the Accomplishment Instructions of 
Bombardier Service Bulletin 84-27-55, Revision A, dated February 22, 
2012.
    (3) If no cracking is found, and any clevis hole edge-to-edge 
length is greater than 0.248 inch, but is less than or equal to 
0.278 inch: Within 1,200 flight hours after doing the measurement/
inspection required by paragraph (h) of this AD, replace the 
bellcrank with a new bellcrank, or with a serviceable bellcrank with 
bushings having part number 82710297-101 installed, in accordance 
with the Accomplishment Instructions of Bombardier Service Bulletin 
84-27-55, Revision A, dated February 22, 2012.
    (4) If any cracking is found, or if any clevis hole edge-to-edge 
length exceeds 0.278 inch: Before further flight, replace the 
bellcrank with a new bellcrank, or with a serviceable bellcrank with 
bushings having part number 82710297-101 installed, in accordance 
with the Accomplishment Instructions of Bombardier Service Bulletin 
84-27-55, Revision A, dated February 22, 2012.

(i) Actions for Certain Other Model DHC-8-400 Series Airplanes

    For Model DHC-8-400, -401, and -402 airplanes that have 
accumulated more than 15,000 total flight hours as of the effective 
date of this AD: Within 600 flight hours after the effective date of 
this AD, measure the edge-to-edge length of the clevis holes of each 
bellcrank, and inspect each bellcrank for cracking using liquid 
penetrant or eddy current inspection method; in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 84-27-55, 
Revision A, dated February 22, 2012.
    (1) If no cracking is found, and the edge-to-edge length of all 
clevis holes is less than or equal to 0.218 inch: Within 1,200 
flight hours after the effective date of this AD, rework the 
bellcrank, or replace the bellcrank with a new bellcrank or with a 
serviceable bellcrank with bushings having part number 82710297-101 
installed, in accordance with the Accomplishment Instructions of 
Bombardier Service Bulletin 84-27-55, Revision A, dated February 22, 
2012.
    (2) If no cracking is found, and any clevis hole edge-to-edge 
length is greater than 0.218, inch but is less than or equal to 
0.248 inch: Within 6,000 flight hours after the effective date of 
this AD, replace the bellcrank with a new bellcrank, or with a 
serviceable bellcrank with bushings having part number 82710297-101 
installed, in accordance with the Accomplishment Instructions of 
Bombardier Service Bulletin 84-27-55, Revision A, dated February 22, 
2012.
    (3) If no cracking is found, and any clevis hole edge-to-edge 
length is greater than 0.248 inch, but is less than or equal to 
0.278 inch: Within 1,200 flight hours after the effective date of 
this AD, replace the bellcrank with a new bellcrank, or with a 
serviceable bellcrank with bushings having part number 82710297-101 
installed, in accordance with the Accomplishment Instructions of 
Bombardier Service Bulletin 84-27-55, Revision A, dated February 22, 
2012.
    (4) If any cracking is found, or any clevis hole edge-to-edge 
length exceeds 0.278 inch: Before further flight, replace the 
bellcrank with a new bellcrank, or with a serviceable bellcrank with 
bushings having part number 82710297-101 installed, in accordance 
with the Accomplishment Instructions of Bombardier Service Bulletin 
84-27-55, Revision A, dated February 22, 2012.

(j) Credit for Previous Actions

    This paragraph provides credit for the actions specified in 
paragraphs (h) and (i) of this AD, if those actions were performed 
before the effective date of this AD using the Accomplishment 
Instructions of Bombardier Service Bulletin 84-27-55, dated June 15, 
2011.

(k) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, New 
York Aircraft Certification Office (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, New York 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) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) Canadian Airworthiness Directive CF-2011-32, dated August 15, 
2011, for related information. The MCAI can be found in the AD 
docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2012-1311-0002.
    (2) Service information identified in this AD that is not 
incorporated by reference may be obtained at the addresses specified 
in paragraphs (m)(3) and (m)(4) of this AD.

(m) 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 the AD specifies otherwise.
    (i) Bombardier Service Bulletin 8-27-111, dated June 15, 2011.
    (ii) Bombardier Service Bulletin 84-27-55, Revision A, dated 
February 22, 2012.
    (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 review copies of the 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 September 30, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-25305 Filed 10-30-13; 8:45 am]
BILLING CODE 4910-13-P

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