32892 Federal Register / Vol. 77, No. 107 / Monday, June 4, 2012 / Rules and Regulations 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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 the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle ACO 

to make those findings. For a repair method 

to be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(i) Related Information 

For more information about this AD, 

contact James Sutherland, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425–917– 

6533; fax: 425–917–6590; email: 

James.Sutherland@faa.gov. 

(j) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. 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: 

(i) Boeing Alert Service Bulletin 777– 

57A0090, dated August 24, 2011. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; phone: 

206–544–5000, extension 1; fax: 206–766– 

5680; email: me.boecom@boeing.com; 

Internet: https://www.myboeingfleet.com. 

(3) 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. 

(4) 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 NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal-register/ 

cfr/ibr-locations.html. 

Issued in Renton, Washington, on May 18, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–12910 Filed 6–1–12; 8:45 am] 

BILLING CODE 4910–13–P 

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. 

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. 


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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 workhours 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 workhour. 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 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 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 


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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 

Coˆte-Vertu Road West, Dorval, Que ́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., 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 


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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 Coˆte-Vertu Road West, 

Dorval, Que ́bec H4S 1Y9, Canada; phone: 

514–855–5000; fax: 514–855–7401; email: 

thd.crj@aero.bombardier.com; 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 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2011–0363; Airspace 

Docket No. 11–ANM–8] 

Modification of Class D and Class E 

Airspace and Revocation of Class E 

Airspace; Bellingham, WA 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action modifies Class D 

and Class E airspace at Bellingham, WA, 

to accommodate aircraft departing and 

arriving under Instrument Flight Rules 

(IFR) at Bellingham International 

Airport. This action, initiated by the 

biennial review of the Bellingham 

airspace area, enhances the safety and 

management of aircraft operations at the 

airport. 

DATES: Effective date, 0901 UTC, 

September 20, 2012. The Director of the 

Federal Register approves this 

incorporation by reference action under 

1 CFR Part 51, subject to the annual 

revision of FAA Order 7400.9 and 

publication of conforming amendments. 


pmangrum on DSK3VPTVN1PROD with RULES