Document ID: FAA-2012-1311-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Bombardier, Inc. Airplanes
Posted Date: 2012-12-26T05:00Z

[Federal Register Volume 77, Number 247 (Wednesday, December 26, 2012)]
[Proposed Rules]
[Pages 75906-75908]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-30925]

 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / 
Proposed Rules  

[[Page 75906]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1311; Directorate Identifier 2011-NM-204-AD]
RIN 2120-AA64

Airworthiness Directives; Bombardier, Inc. Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt 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 proposed 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 proposed AD would require 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 proposing 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: We must receive comments on this proposed AD by February 11, 
2013.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, 
Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; fax 416-375-
4539; email thd.qseries@aero.bombardier.com; Internet http://www.bombardier.com. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, Washington. For information on the availability of 
this material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; 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 proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (telephone (800) 647-5527) is 
in the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: 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:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2012-1311; 
Directorate Identifier 2011-NM-204-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    Transport Canada Civil Aviation (TCCA), which is the aviation 
authority for Canada, has issued Canadian AD CF-2011-32, dated August 
15, 2011 (referred to after this as ``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 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 obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Bombardier, Inc. has issued Service Bulletins 8-27-111 and 84-27-
55, both dated June 15, 2011. The actions described in this service 
information are intended to correct the unsafe condition identified in 
the MCAI.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would

[[Page 75907]]

affect about 178 products of U.S. registry. We also estimate that it 
would take about 5 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $85 per 
work-hour. Based on these figures, we estimate the cost of the proposed 
AD on 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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    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]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Bombardier, Inc.: Docket No. FAA-2012-1311; Directorate Identifier 
2011-NM-204-AD.

(a) Comments Due Date

    We must receive comments by February 11, 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, measure the edge-
to-edge length of the clevis holes of each bellcrank; and, if the 
length is less than or equal to 0.218 inch, inspect for cracking of 
each bellcrank 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, or if any 
cracking is found: Before further flight, replace the bellcrank with 
a new bellcrank, 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 for cracking of each bellcrank using liquid 
penetrant; in accordance with the Accomplishment Instructions of 
Bombardier Service Bulletin 84-27-55, dated June 15, 2011.
    (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 or replace the bellcrank, in 
accordance with the Accomplishment Instructions of Bombardier 
Service Bulletin 84-27-55, dated June 15, 2011.
    (2) If no cracking is found, and any clevis hole edge-to-edge 
length is greater than 0.218 inch but 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, in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 84-27-55, 
dated June 15, 2011.
    (3) If no cracking is found, and any clevis hole edge-to-edge 
length is greater than 0.248 inch but 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, in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 84-27-55, 
dated June 15, 2011.
    (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

[[Page 75908]]

with a new bellcrank, in accordance with the Accomplishment 
Instructions of Bombardier Service Bulletin 84-27-55, dated June 15, 
2011.

(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 for cracking of each bellcrank using liquid 
penetrant; in accordance with the Accomplishment Instructions of 
Bombardier Service Bulletin 84-27-55, dated June 15, 2011.
    (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: At the later of 
the compliance times specified in paragraphs (i)(1)(i) and 
(i)(1)(ii) of this AD, rework or replace the bellcrank, in 
accordance with the Accomplishment Instructions of Bombardier 
Service Bulletin 84-27-55, dated June 15, 2011.
    (i) Within 6,000 flight hours after the effective date of this 
AD, but not to exceed 15,600 total flight hours.
    (ii) Within 1,200 flight hours after the effective date of this 
AD.
    (2) If no cracking is found, and any clevis hole edge-to-edge 
length is greater than 0.218 inch but 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, in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 84-27-55, 
dated June 15, 2011.
    (3) If no cracking is found, and any clevis hole edge-to-edge 
length is greater than 0.248 inch but 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, in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 84-27-55, 
dated June 15, 2011.
    (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, in accordance with the 
Accomplishment Instructions of Bombardier Service Bulletin 84-27-55, 
dated June 15, 2011.

(j) 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.

(k) Related Information

    (1) Refer to MCAI Canadian Airworthiness Directive CF-2011-32, 
dated August 15, 2011, and the service bulletins specified in 
paragraphs (k)(1) (i) and (k)(1)(ii) of this AD, for related 
information.
    (i) Bombardier Service Bulletin 8-27-111, dated June 15, 2011.
    (ii) Bombardier Service Bulletin 84-27-55, dated June 15, 2011.
    (2) For service information identified in this AD, contact 
Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt 
Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; 
fax 416-375-4539; email thd.qseries@aero.bombardier.com; Internet 
http://www.bombardier.com. You may review copies of the 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.

    Issued in Renton, Washington, on December 17, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-30925 Filed 12-21-12; 8:45 am]
BILLING CODE 4910-13-P