Document ID: FAA-2012-0109-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Bombardier Inc. Airplanes
Posted Date: 2012-02-09T05:00Z

[Federal Register Volume 77, Number 27 (Thursday, February 9, 2012)]
[Proposed Rules]
[Pages 6688-6692]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-3031]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0109; Directorate Identifier 2010-NM-244-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 supersede an existing airworthiness directive 
(AD) that applies to certain Bombardier Inc. Model CL-215-1A10 and CL-
215-6B11 (CL-215T Variant) airplanes. The existing AD currently 
requires repetitive inspections to detect cracking of the lower cap of 
the wing front and rear spars at wing station (WS) 51.00, and the wing 
lower skin. Additional actions, if cracking is found, include reworking 
the lower cap of the front or rear spar, inspecting for cracking, and 
repairing any cracking. The existing AD also requires reporting 
inspection results. Since we issued that AD, we have received reports 
of cracking found outside the inspection area. This proposed AD would 
extend the inspection area of the rear spar lower cap from WS 51.00 to 
WS 49.50 and modify the ultrasonic inspection calibration procedure. We 
are proposing this AD to detect and correct cracking of the lower caps 
of the wing front spar and rear spar, and lower wing skin, which could 
result in reduced structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by March 26, 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., 400 C[ocirc]te-Vertu Road West, Dorval,

[[Page 6689]]

Qu[eacute]bec H4S 1Y9, Canada; phone: 514-855-5000; fax: 514-855-7401; 
email: thd.crj@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: George Duckett, Aerospace Engineer, 
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, Westbury, NY 11590; 
telephone (516) 228-7325; 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-2012-0109; 
Directorate Identifier 2010-NM-244-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

    On August 24, 2005, we issued AD 2005-18-05, Amendment 39-14245 (70 
FR 52009, September 1, 2005). That AD required actions intended to 
address an unsafe condition on Bombardier, Inc. Model CL-215-1A10, CL-
215-6B11 (CL-215T Variant), and CL-215-6B11 (CL-415 Variant) airplanes.
    Since we issued AD 2005-18-05, Amendment 39-14245 (70 FR 52009, 
September 1, 2005) Transport Canada Civil Aviation (TCCA), which is the 
airworthiness authority for Canada, has issued Airworthiness Directive 
CF-1992-26R2, dated September 1, 2010 (referred to after this as ``the 
MCAI''), to correct an unsafe condition for the specified products. The 
MCAI states:

    Cracks have been found in the rear spar of the left wing at Wing 
Station (WS) 51.00 on several aircraft in service. On some aircraft, 
the cracks propagated through the lower spar cap and fail-safe 
straps into the spar web and the lower wing skin. The cracks are not 
visible from outside the aircraft.
* * * * *
    Revision 2 of this [TCCA] AD is issued as a result of cracks 
found outside the inspection area specified in Revision 1. This 
revision extends the inspection area of the rear spar lower cap from 
WS 51.00 to WS 49.50 and to modify the ultrasonic inspection 
calibration procedure.

Cracking of the lower caps of the wing front spar and rear spar, and 
lower wing skin, could result in reduced structural integrity of the 
airplane. You may obtain further information by examining the MCAI in 
the AD docket.
    AD 2005-18-05, Amendment 39-14245 (70 FR 52009, September 1, 2005), 
specifies Model CL-215-6B11 (CL-415 Variant) airplanes in the 
applicability, but also specifies serial numbers 1001 though 1125. The 
serial numbers for Model CL-215-6B11 (CL-415 Variant) airplanes start 
at 2001. We have determined that Model CL-215-6B11 (CL-415 Variant) 
airplanes are not subject to the identified unsafe condition. 
Therefore, we have removed Model CL-215-6B11 (CL-415 Variant) airplanes 
from the applicability of this proposed AD.

Relevant Service Information

    Bombardier Inc. has issued Alert Service Bulletin 215-A454, 
Revision 4, dated November 18, 2009. 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 affect about 7 products of U.S. registry.
    The actions that are required by AD 2005-18-05, Amendment 39-14245 
(70 FR 52009, September 1, 2005) and retained in this proposed AD take 
about 17 work-hours per product, at an average labor rate of $85 per 
work hour. Based on these figures, the estimated cost of the currently 
required actions is $1,445 per product.
    We estimate that it would take about 6 work-hour per product to 
comply with the new 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 $3,570, or $510 per 
product.
    In addition, we estimate that any necessary follow-on actions would 
take about 480 work-hours for a cost of $40,800 per product. We have 
received no definitive data that would enable us to provide a parts 
cost estimate for the on-condition requirement specified in this 
proposed AD. 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

[[Page 6690]]

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); and
    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 removing Amendment 39-14245 (70 FR 
52009, September 1, 2005) and adding the following new AD:

Bombardier, Inc.: Docket No. FAA-2012-0109; Directorate Identifier 
2010-NM-244-AD.

(a) Comments Due Date

    We must receive comments by March 26, 2012.

(b) Affected ADs

    This AD supersedes AD 2005-18-05, Amendment 39-14245 (70 FR 
52009, September 1, 2005).

(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 CL-215-1A10 (Water Bomber) airplanes, serial numbers 
1001 through 1125 inclusive.
    (2) Model CL-215-6B11 (CL215T Variant) airplanes, serial numbers 
1056 through 1125 inclusive.

(d) Subject

    Air Transport Association (ATA) of America Code 57: Wings.

(e) Reason

    This AD was prompted by reports of cracking found outside the 
inspection area. We are proposing this AD to detect and correct 
cracking of the lower caps of the wing front spar and rear spar, and 
lower wing skin, which could result in reduced structural integrity 
of the airplane.

(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.

Restatement of Certain Requirements of AD 98-04-08, Amendment 39-10321 
(63 FR 7640, February 17, 1998), With New Service Information

(g) Initial Inspection of AD 98-04-08, Amendment 39-10321 (63 FR 7640, 
February 17, 1998), With New Threshold

    At the time specified in paragraph (h) of this AD: Perform an 
ultrasonic inspection to detect cracking of the lower cap of the 
wing front and rear spars at wing station 51, in accordance with the 
Accomplishment Instructions of Canadair Alert Service Bulletin 215-
A463, Revision 1, dated May 25, 1995, or Bombardier Alert Service 
Bulletin 215-A463, Revision 2, dated March 13, 2001 (for the front 
spar); and Canadair Alert Service Bulletin 215-A454, Revision 1, 
dated May 25, 1995, Bombardier Alert Service Bulletin 215-A454, 
Revision 2, dated January 27, 1999, Bombardier Alert Service 
Bulletin 215-A454, Revision 3, dated March 13, 2001, or Bombardier 
Alert Service Bulletin 215-A454, Revision 4, dated November 18, 2009 
(for the rear spar). As of the effective date of this AD, the 
inspection must be done in accordance with the Accomplishment 
Instructions of Bombardier Alert Service Bulletin 215-A463, Revision 
2, dated March 13, 2001 (for the front spar); and Bombardier Alert 
Service Bulletin 215-A454, Revision 3, dated March 13, 2001, or 
Bombardier Alert Service Bulletin 215-A454, Revision 4, dated 
November 18, 2009 (for the rear spar).

(h) Compliance Times

    Do the inspections required by paragraph (g) of this AD at the 
earlier of the times specified in paragraphs (h)(1) and (h)(2) of 
this AD.
    (1) Prior to the accumulation of 3,000 total flight hours, or 
within 25 flight hours after March 4, 1998 (the effective date of AD 
98-04-08, Amendment 39-10321 (63 FR 7640, February 17, 1998)), 
whichever occurs later.
    (2) At the later of the times specified in paragraphs (h)(2)(i) 
and (h)(2)(ii) of this AD.
    (i) Prior to the accumulation of 2,500 total flight hours, or 
8,000 total water drops, whichever occurs first.
    (ii) Within 50 flight hours or 150 water drops after October 6, 
2005 (the effective date of AD 2005-18-05, Amendment 39-14245 (70 FR 
52009, September 1, 2005), whichever occurs first.

(i) Repetitive Inspections With New Intervals

    Repeat the ultrasonic inspection specified in paragraph (g) of 
this AD at the times specified in paragraph (i)(1) or (i)(2) of this 
AD, as applicable.
    (1) For airplanes on which any ultrasonic inspection required by 
paragraph (a) of AD 98-04-08, Amendment 39-10321 (63 FR 7640, 
February 17, 1998), has been done before October 6, 2005: Within 600 
flight hours after the last ultrasonic inspection, do the ultrasonic 
inspection specified in paragraph (g) of this AD. Repeat the 
ultrasonic inspection specified in paragraph (g) of this AD 
thereafter at intervals not to exceed 600 flight hours or 2,000 
water drops, whichever occurs first.
    (2) For airplanes on which the ultrasonic inspection required by 
paragraph (a) of AD 98-04-08, Amendment 39-10321 (63 FR 7640, 
February 17, 1998), has not been done before October 6, 2005: After 
accomplishing the initial ultrasonic inspection specified in 
paragraph (g) of this AD, repeat the ultrasonic inspection specified 
in paragraph (g) of this AD thereafter at intervals not to exceed 
600 flight hours or 2,000 water drops, whichever occurs first.

Restatement of Requirements of AD 2005-18-05, Amendment 39-14245 (70 FR 
52009, September 1, 2005), With New Service Information

(j) Ultrasonic Inspection

    At the later of the times specified in paragraphs (j)(1) and 
(j)(2) of this AD, do an ultrasonic inspection for cracks of the 
wing lower skin, in accordance with the Accomplishment Instructions 
of Bombardier Alert Service Bulletin 215-A454, Revision 3, dated 
March 13, 2001; or Bombardier Alert Service Bulletin 215-A454, 
Revision 4, dated November 18, 2009. Thereafter, do the ultrasonic 
inspection for cracks of the wing lower skin at the times specified 
for the ultrasonic inspection in paragraph (i) of this AD.
    (1) Within 50 flight hours or 150 water drops after October 6, 
2005, whichever occurs first.
    (2) Before further flight after accomplishing the first 
ultrasonic inspection required by paragraph (g) or (i) of this AD 
after October 6, 2005.

(k) Cracking Detected

    If any cracking is detected during any inspection required by 
paragraph (g), (i), or (j) of this AD, before further flight, 
accomplish paragraphs (k)(1) and (k)(2) of this AD.
    (1) Rework the lower cap of the front or rear spar, as 
applicable, in accordance with the Accomplishment Instructions of 
Bombardier Alert Service Bulletin 215-A463, Revision 2, dated March 
13, 2001 (for the front spar); and Bombardier Alert Service Bulletin 
215-A454, Revision 3, dated March 13, 2001; or Bombardier Alert 
Service Bulletin 215-A454, Revision 4, dated November 18, 2009 (for 
the rear spar).
    (2) After doing the rework specified in paragraph (k)(1) of this 
AD, do a general visual inspection, from inside the wing box, to 
detect cracks of the front spar web or rear spar web, as applicable, 
and the lower skin area, in accordance with the Accomplishment 
Instructions of Bombardier Alert Service Bulletin 215-A463, Revision 
2,

[[Page 6691]]

dated March 13, 2001 (for the front spar); and Bombardier Alert 
Service Bulletin 215-A454, Revision 3, dated March 13, 2001 (for the 
rear spar); or Bombardier Alert Service Bulletin 215-A454, Revision 
4, dated November 18, 2009 (for the rear spar). If any cracking is 
detected: Before further flight, repair in accordance with a method 
approved by the Manager, New York Aircraft Certification Office 
(ACO), FAA; or Transport Canada Civil Aviation (TCCA) (or its 
delegated agent).

(l) Credit for Actions Accomplished in Accordance With Previous Service 
Information

    (l) Actions accomplished before October 6, 2005, in accordance 
with Canadair Alert Service Bulletin 215-A463, dated April 8, 1993; 
Canadair Alert Service Bulletin 215-A463, Revision 1, dated May 25, 
1995; Canadair Alert Service Bulletin 215-A454, dated October 13, 
1993; Canadair Alert Service Bulletin 215-A454, Revision 1, dated 
May 25, 1995; Bombardier Alert Service Bulletin 215-A454, Revision 
2, dated January 27, 1999; are considered acceptable for compliance 
with the corresponding actions specified in this AD.
    (2) Actions accomplished before October 6, 2005, in accordance 
with Bombardier Alert Wire 215-A454, dated December 23, 1992; and 
Bombardier Alert Wire 215-A463, dated March 26, 1993; are considered 
acceptable for compliance with the corresponding actions specified 
in this AD.

(m) Reporting Requirement

    For any inspection required by AD 2005-18-05, Amendment 39-14245 
(70 FR 52009, September 1, 2005), that is accomplished after October 
6, 2005, within 30 days after accomplishing the inspection, submit a 
report of any inspection results (both positive and negative 
findings) to Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 
6087, Station Centre-ville, Montreal, Quebec H3C 3G9, Canada; or to 
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, 
Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-
7401; email thd.crj@aero.bombardier.com; Internet http://www.bombardier.com. As of the effective date of this AD, submit 
reports to Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval, 
Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-
7401; email thd.crj@aero.bombardier.com; Internet http://www.bombardier.com.

New Requirements of This AD

(n) Ultrasonic Inspection of the Rear Spar Lower Cap

    Within the compliance time specified in paragraph (p) of this 
AD: Perform an ultrasonic inspection to detect cracking of the right 
and left wing rear spar lower cap between wing station (WS) 51.00 
and WS 49.50, in accordance with paragraph 2.C., ``Part A,'' of the 
Accomplishment Instructions of Bombardier Alert Service Bulletin 
215-A454, Revision 4, dated November 18, 2009. Repeat the ultrasonic 
inspection thereafter at intervals not to exceed 600 flight hours or 
2,000 water drops, whichever comes first. Accomplishment of the 
actions in this paragraph terminates the inspection requirements of 
the lower cap of the wing rear spars at wing station 51.00 of 
paragraph (g) of this AD. Accomplishment of the actions in this 
paragraph does not terminate the inspection requirements of the 
lower cap of the front wing spars at wing station 51.00 required by 
paragraph (g) of this AD.
    (1) If any crack is found in the rear spar lower cap, before 
further flight, do a general visual inspection for cracks from 
inside the wing box, of the areas of the rear spar web and the wing 
lower skin adjacent to the crack in the rear spar lower cap, in 
accordance with paragraph 2.C., ``Part A,'' of the Accomplishment 
Instructions of Bombardier Alert Service Bulletin 215-A454, Revision 
4, dated November 18, 2009.
    (2) If any cracking is detected during any ultrasonic or general 
visual inspection required by paragraph (n) of this AD, before 
further flight, repair in accordance with a method approved by the 
Manager, New York ACO, FAA; or TCCA (or its delegated agent).

(o) Ultrasonic Inspection of the Lower Wing Skin

    Within the compliance time specified in paragraph (p) of this 
AD: Perform an ultrasonic inspection to detect cracking of the wing 
lower skin underneath the drag angle between the front spar and the 
rear spar at the left and right WS 51.00, in accordance with 
paragraph 2.D., ``Part B,'' of the Accomplishment Instructions of 
Bombardier Alert Service Bulletin 215-A454, Revision 4, dated 
November 18, 2009. Do the ultrasonic inspection thereafter at 
intervals not to exceed 600 flight hours or 2,000 water drops, 
whichever comes first. Accomplishment of the actions in this 
paragraph terminates the requirements of paragraph (j) of this AD.
    (1) If any crack is found in the wing lower skin, before further 
flight, do a general visual inspection for cracks from inside the 
wing box, i.e., the stringers adjacent to the skin crack in 
accordance with paragraph 2.D., ``Part B,'' of the Accomplishment 
Instructions of Bombardier Alert Service Bulletin 215-A454, Revision 
4, dated November 18, 2009. .
    (2) If any cracking is detected during any ultrasonic or general 
visual inspection required by paragraph (o) of this AD, before 
further flight, repair in accordance with a method approved by the 
Manager, New York ACO, FAA; or TCCA (or its delegated agent).

(p) Compliance Times for Paragraphs (n) and (o) of This AD

    At the later of the times specified in paragraphs (p)(1) and 
(p)(2) of this AD.
    (1) Prior to the accumulation of 2,500 total flight hours, or 
8,000 total water drops, whichever occurs first.
    (2) Within 50 flight hours or 150 water drops after the 
effective date of this AD, whichever occurs first.

(q) Credit for Actions Accomplished in Accordance With Previous Service 
Information

    Inspections accomplished at WS 51.00 before the effective date 
of this AD in accordance with the Accomplishment Instructions of 
Bombardier Alert Service Bulletin 215-A454, Revision 3, dated March 
13, 2001, within the last 550 flight hours or 1,850 water drops, are 
considered acceptable for compliance with the corresponding action 
specified in paragraph (o) of this AD.

(r) Reporting Requirements With New Address

    At the applicable time specified in paragraph (r)(1) or (r)(2) 
of this AD, submit a report of the findings (both positive and 
negative) of the inspection required by paragraphs (n) and (o) of 
this AD to Bombardier, Inc., in accordance with Bombardier Alert 
Service Bulletin 215-A454, Revision 4, dated November 18, 2009.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 30 days after the effective date of 
this AD.

(s) 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 manager of the ACO, send it 
to ATTN: Program Manager, Continuing Operational Safety, FAA, New 
York ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; 
phone: 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.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should

[[Page 6692]]

be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 
20591, Attn: Information Collection Clearance Officer, AES-200.

(t) Related Information

    Refer to MCAI Airworthiness Directive CF-1992-26R2, dated 
September 1, 2010, and the following service information for related 
information.
    (1) Bombardier Alert Service Bulletin 215-A463, Revision 2, 
dated March 13, 2001.
    (2) Bombardier Alert Service Bulletin 215-A454, Revision 3, 
dated March 13, 2001.
    (3) Bombardier Alert Service Bulletin 215-A454, Revision 4, 
dated November 18, 2009.

    Issued in Renton, Washington, on January 26, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-3031 Filed 2-8-12; 8:45 am]
BILLING CODE 4910-13-P