[Federal Register Volume 77, Number 84 (Tuesday, May 1, 2012)]
[Proposed Rules]
[Pages 25642-25644]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-10483]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0422; Directorate Identifier 2011-NM-177-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 airplanes. This proposed AD was 
prompted by reports that various pushrods had been manufactured with 
tubes having the incorrect heat treatment. This proposed AD would 
require replacing the affected pushrod assembly. We are proposing this 
AD to prevent loss of rudder control, reduced directional control of 
the airplane on the ground, or a jammed nose landing gear (NLG) door 
that could prevent the NLG from retracting or extending.

DATES: We must receive comments on this proposed AD by June 15, 2012.

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 [email protected]; 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: Cesar Gomez, 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) 228-7318; 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-2012-0422; 
Directorate Identifier 2011-NM-177-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-2011-31, dated August 
15, 2011 (referred to after this as ``the MCAI''), to correct an unsafe 
condition for the specified products. The MCAI states:

    It was discovered that various pushrods installed on the DHC-8 
Series 100/200/300/400 aeroplanes had been manufactured with tubes 
having the incorrect heat treatment, using 6061-T4 instead of 6061-
T6. The incorrect heat treatment appreciably degrades the strength 
of these affected pushrods. Failure of these affected pushrods could 
result in a loss of rudder control, reduced directional control of 
the aeroplane on the ground or a jammed nose landing gear (NLG) door 
that could prevent the NLG from retracting or extending.
    This [TCCA] directive mandates the replacement of the affected 
pushrod assembly.

You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Bombardier has issued the following service bulletins. The actions 
described in this service information are intended to correct the 
unsafe condition identified in the MCAI.
     Service Bulletin 8-27-99, dated October 10, 2008;
     Service Bulletin 8-27-100, Revision A, dated March 22, 
2011;
     Service Bulletin 8-32-156, dated February 26, 2010;
     Service Bulletin 84-27-21, Revision A, dated March 22, 
2011;
     Service Bulletin 84-32-28, dated November 27, 2008; and
     Service Bulletin 84-32-75, dated June 1, 2010.

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.

Differences Between This AD and the MCAI or Service Information

    For certain actions on the same part, the MCAI specified both 3,000 
and 6,000 flight-hour compliance times. To reconcile that difference, 
this proposed AD has a compliance time of 3,000 flight hours after the 
effective date of the AD, for the action in paragraph (k) of this 
proposed AD. We have determined this compliance time is necessary to 
address the identified unsafe condition in a timely manner. This 
difference has been coordinated with TCCA.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 171 products of U.S. registry. We also estimate that 
it would take about 28 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $85 per 
work-hour. Required parts would cost about $6,504 per product. Where 
the service information lists required parts costs that are

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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. Based 
on these figures, we estimate the cost of the proposed AD on U.S. 
operators to be $1,519,164, or $8,884 per product.

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-2012-0422; Directorate Identifier 
2011-NM-177-AD.

(a) Comments Due Date

    We must receive comments by June 15, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Bombardier, Inc. airplanes, certificated 
in any category, as identified 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 413, 443, 450 through 452 inclusive, 456, 
458, 462 through 465 inclusive, 467 through 470 inclusive, and 473 
through 588 inclusive.
    (2) Model DHC-8-400,-401, and -402 airplanes, serial numbers 
4001, 4003 through 4006 inclusive, and 4008 through 4197 inclusive.

(d) Subject

    Air Transport Association (ATA) of America Code 27: Flight 
controls; and Code 32: Landing gear.

(e) Reason

    This AD was prompted by reports that various pushrods had been 
manufactured with tubes having the incorrect heat treatment. We are 
issuing this AD to prevent loss of rudder control, reduced 
directional control of the airplane on the ground, or a jammed nose 
landing gear (NLG) door that could prevent the NLG from retracting 
or extending.

(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) Replace Brake Rudder Control Pushrod--Model DHC-8-100, -200, -300

    For Model DHC-8-102,-103,-106,-201, -202,-301,-311, and -315 
airplanes, serial numbers 464, 508, 511 through 513 inclusive, and 
515 through 588 inclusive: Within 3,000 flight hours after the 
effective date of this AD, replace the affected brake rudder control 
pushrod, part number (P/N) 82710274-001, by incorporating Modsum 
8Q101334, in accordance with the Accomplishment Instructions of 
Bombardier Service Bulletin 8-27-100, Revision A, dated March 22, 
2011.

(h) Replace NLG Door Pushrod--Model DHC-8-200, -300

    For Model DHC-8-201, -202, -301, -311, and -315 airplanes, 
serial numbers 552 through 588 inclusive: Within 6,000 flight hours 
after the effective date of this AD, replace nose landing gear door 
pushrod, P/N 83232012-001, by incorporating Modsum 8Q101335, in 
accordance with the Accomplishment Instructions of Bombardier 
Service Bulletin 8-32-156, dated February 26, 2010.

(i) Replace NLG Door Pushrod--Model DHC-8-400

    For Model DHC-8-400, -401, and -402 airplanes, serial numbers 
4003 through 4005 inclusive, 4009 through 4011 inclusive, 4016, 
4017, and 4024 through 4072 inclusive: Within 6,000 flight hours 
after the effective date of this AD, replace nose landing gear door 
pushrod, P/N 83232012-001, by incorporating Modsum 4-113457, in 
accordance with the Accomplishment Instructions of Bombardier 
Service Bulletin 84-32-28, dated November 27, 2008.

(j) Replace Brake Rudder Control and Rudder Control Pushrods--Model 
DHC-8-400

    For Model DHC-8-400, -401, and -402 airplanes, serial numbers 
4001, 4003 through 4006 inclusive, and 4008 through 4072 inclusive: 
Within 3,000 flight hours after the effective date of this AD, 
replace brake rudder control pushrod, P/N 82710274-001, and rudder 
control pushrod, P/N 82710028-003, by incorporating Modsum 4-113455, 
in accordance with the Accomplishment Instructions of Bombardier 
Service Bulletin 84-27-21, Revision A, dated March 22, 2011.

(k) Replace Rudder Control Pushrod--Model DHC-8-100, -200, -300

    For Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -
315 airplanes, serial numbers 413, 443, 450 through 452 inclusive, 
456, 458, 462 through 465 inclusive, 467 through 470 inclusive, and 
473 through 588 inclusive: Within 3,000 flight hours after the 
effective date of this AD, replace rudder control pushrod, P/N 
82710028-003, by incorporating Modsum 8Q101333, in accordance with 
the Accomplishment Instructions of Bombardier Service Bulletin 8-27-
99, dated October 10, 2008.

(l) Inspect/Replace NLG Landing Gear Door Pushrod

    For Model DHC-8-400, -401, and -402 airplanes, serial numbers 
4006, 4008, 4012 through 4015 inclusive, 4018 through 4023 
inclusive, and 4073 through 4197 inclusive: Within 6,000 flight 
hours after the effective date of this AD, inspect the lot number of 
the pushrod, P/N 83232012-001, for the nose landing gear door 
mechanism, in accordance with Bombardier Service Bulletin 84-32-75, 
dated June 1, 2010.
    (1) If the lot number of the pushrod does not match any of those 
listed in the table in paragraph 3.B.(2) of Bombardier Service

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Bulletin 84-32-75, dated June 1, 2010, no further action is required 
by this paragraph.
    (2) If the lot number of the pushrod matches any of those listed 
in the table in paragraph 3.B.(2) of Bombardier Service Bulletin 84-
32-75, dated June 1, 2010, before further flight, replace the 
pushrod, in accordance with paragraph 3.B., Rectification, of 
Bombardier Service Bulletin 84-32-75, dated June 1, 2010.

(m) Parts Installation

    For Model DHC-8-400, -401, and -402 airplanes, serial numbers 
4006, 4008, 4012 through 4015 inclusive, 4018 through 4023 
inclusive, and 4073 through 4197 inclusive: As of the effective date 
of this AD, no person may install a pushrod, P/N 83232012-001, with 
the lot number listed in the table in paragraph 3.B.(2) of 
Bombardier Service Bulletin 84-32-75, dated June 1, 2010, on any 
airplane.

(n) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraphs (g) and (j) of this AD, if those actions were performed 
before the effective date of this AD using the service bulletins 
identified in paragraph (n)(1) or (n)(2) of this AD.
    (1) Bombardier Service Bulletin 8-27-100, dated October 10, 2008 
(for paragraph (g) of this AD).
    (2) Bombardier Service Bulletin 84-27-21, dated October 10, 2008 
(for paragraph (j) of this AD).

(o) 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.

(p) Related Information

    Refer to MCAI Canadian AD CF-2011-31, dated August 15, 2011, and 
the Bombardier service bulletins identified in paragraphs (p)(1) 
through (p)(6) of this AD, for related information.
    (1) Bombardier Service Bulletin 8-27-99, dated October 10, 2008.
    (2) Bombardier Service Bulletin 8-27-100, Revision A, dated 
March 22, 2011.
    (3) Bombardier Service Bulletin 8-32-156, dated February 26, 
2010.
    (4) Bombardier Service Bulletin 84-27-21, Revision A, dated 
March 22, 2011.
    (5) Bombardier Service Bulletin 84-32-28, dated November 27, 
2008.
    (6) Bombardier Service Bulletin 84-32-75, dated June 1, 2010.

    Issued in Renton, Washington, on April 24, 2012.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-10483 Filed 4-30-12; 8:45 am]
BILLING CODE 4910-13-P