[Federal Register Volume 77, Number 107 (Monday, June 4, 2012)]
[Rules and Regulations]
[Pages 32892-32895]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-12911]


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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; 
Amendment 39-17067; AD 2012-11-04]
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 superseding an existing airworthiness directive (AD) 
for certain Bombardier Inc. Model CL-215-1A10 and CL-215-6B11 (CL-215T 
Variant) airplanes. That 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. This new AD 
requires extending the inspection area of the rear spar lower cap from 
WS 51.00 to WS 49.50 and modifying the ultrasonic inspection 
calibration procedure. This AD was prompted by reports of cracking 
found outside the inspection area. We are issuing this AD to detect and 
correct cracking of the lower caps of the wing front and rear spars, 
and lower wing skin, which could result in reduced structural integrity 
of the airplane.

DATES: This AD becomes effective July 9, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of July 9, 
2012.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of October 
6, 2005 (70 FR 52009, September 1, 2005).
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of March 
4, 1998 (63 FR 7640, February 17, 1998).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov 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 FURTHER INFORMATION CONTACT: George Duckett, Aerospace Engineer, 
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft 
Certification Office, 1600 Stewart Avenue, Westbury, New York 11590; 
telephone (516) 228-7325; fax (516) 794-5531.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on February 9, 2012 (77 
FR 6688), and proposed to supersede AD 2005-18-05, Amendment 39-14245 
(70 FR 52009, September 1, 2005). That NPRM proposed 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 [Transport Canada Civil Aviation] 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 and rear spars, 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 AD.

[[Page 32893]]

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (77 FR 6688, February 9, 
2012) or on the determination of the cost to the public.

Explanation of Changes Made to This AD

    We have revised certain headers throughout this AD and changed the 
new reporting contact information in paragraph (m) of this AD.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed, except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (77 FR 6688, February 9, 2012) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (77 FR 6688, February 9, 2012).

Costs of Compliance

    We estimate that this AD will 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 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 will take about 6 work-hours per product to 
comply with the new 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 $3,570, or $510 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 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 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 the NPRM (77 FR 6688, February 9, 
2012), 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.

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 removing airworthiness directive (AD) 
2005-18-05, Amendment 39-14245 (70 FR 52009, September 1, 2005), and 
adding the following new AD:

2012-11-04 Bombardier, Inc.: Amendment 39-17067. Docket No. FAA-
2012-0109; Directorate Identifier 2010-NM-244-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective July 9, 
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 (CL-215T 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 issuing this AD to detect and correct 
cracking of the lower caps of the wing front and rear spars, 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.

(g) Retained Initial Inspection With New Service Information

    This paragraph restates the requirements of paragraph (f) of AD 
2005-18-05, Amendment 39-14245 (70 FR 52009, September 1, 2005), 
with new service information. 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

[[Page 32894]]

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) Retained Compliance Times

    This paragraph restates the requirements of paragraph (g) of AD 
2005-18-05, Amendment 39-14245 (70 FR 52009, September 1, 2005). 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) Retained Repetitive Inspections With New Intervals

    This paragraph restates the requirements of paragraph (h) of AD 
2005-18-05, Amendment 39-14245 (70 FR 52009, September 1, 2005), 
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.

(j) Retained Ultrasonic Inspection With New Service Information

    This paragraph restates the requirements of paragraph (i) of AD 
2005-18-05, Amendment 39-14245 (70 FR 52009, September 1, 2005), 
with new service information. 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) Retained Corrective Actions With New Service Information

    This paragraph restates the requirements of paragraph (j) of AD 
2005-18-05, Amendment 39-14245 (70 FR 52009, September 1, 2005), 
with new service information. 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, 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) Retained Credit for Previous Actions

    (l) This paragraph provides credit for the actions required by 
paragraphs (g) and (h) of this AD, if those actions were performed 
before October 6, 2005, using 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; or Bombardier Alert Service 
Bulletin 215-A454, Revision 2, dated January 27, 1999.
    (2) This paragraph provides credit for the actions required by 
paragraphs (g) and (h) of this AD, if those actions were performed 
before October 6, 2005, using Bombardier Alert Wire 215-A454, dated 
December 23, 1992; and Bombardier Alert Wire 215-A463, dated March 
26, 1993.

(m) Retained Reporting Requirement With New Contact Information

    This paragraph restates the requirements of paragraph (m) of AD 
2005-18-05, Amendment 39-14245 (70 FR 52009, September 1, 2005), 
with new contact information. For any inspection required by AD 
2005-18-05, 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 
[email protected]; Internet http://www.bombardier.com. As 
of the effective date of this AD, submit reports to Bombardier, 
Inc., in accordance with the contact information specified in 
Bombardier Alert Service Bulletin 215-A454, Revision 4, dated 
November 18, 2009.

(n) New 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 WS 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 wing 
front spars at WS 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) New 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

[[Page 32895]]

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 (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).

(p) New 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 Previous Actions

    This paragraph provides credit for the inspections at WS 51.00 
required by paragraphs (n) and (o) of this AD, if those inspections 
were performed within the last 550 flight hours or 1,850 water drops 
before the effective date of this AD using Bombardier Alert Service 
Bulletin 215-A454, Revision 3, dated March 13, 2001.

(r) New Reporting Requirements

    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 inspections 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 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.

(u) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the following service 
information under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use the following service information to do the 
actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
July 9, 2012.
    (i) Bombardier Alert Service Bulletin 215-A454, Revision 4, 
dated November 18, 2009.
    (4) The following service information was approved for IBR on 
October 6, 2005 (70 FR 52009, September 1, 2005).
    (i) Bombardier Alert Service Bulletin 215-A454, Revision 2, 
dated January 27, 1999.
    (ii) Bombardier Alert Service Bulletin 215-A454, Revision 3, 
dated March 13, 2001.
    (iii) Bombardier Alert Service Bulletin 215-A463, Revision 2, 
dated March 13, 2001.
    (5) The following service information was approved for IBR on 
March 4, 1998 (63 FR 7640, February 17, 1998).
    (i) Canadair Alert Service Bulletin 215-A454, Revision 1, dated 
May 25, 1995.
    (ii) Canadair Alert Service Bulletin 215-A463, Revision 1, dated 
May 25, 1995.
    (6) For Bombardier, Inc. service information identified in this 
AD, contact Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, 
Dorval, Qu[eacute]bec H4S 1Y9, Canada; phone: 514-855-5000; fax: 
514-855-7401; email: [email protected]; Internet: http://www.bombardier.com.
    (7) You may review copies of the 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.
    (8) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at an NARA facility, call 202-741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on May 18, 2012.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-12911 Filed 6-1-12; 8:45 am]
BILLING CODE 4910-13-P