Federal Register / Vol. 77, No. 54 / Tuesday, March 20, 2012 / Rules and Regulations 16151 

(j) Exception to Service Bulletin 

Specifications 

Where Boeing Service Bulletin 767– 

56A0010, Revision 3, dated March 3, 2011, 

specifies a compliance time ‘‘after the 

Revision 1 date of the service bulletin,’’ this 

AD requires compliance within the specified 

time after the effective date of this AD. 

(k) 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. 

(l) Related Information 

For more information about this AD, 

contact Emerson Hevia, Aerospace Engineer, 

Cabin Safety and Environmental Systems 

Branch, ANM–150S, FAA, 1601 Lind Avenue 

SW., Renton, Washington 98057–3356; 

phone: 425–917–6414; fax: 425–917–6590; 

email: emerson.hevia@faa.gov. 

(m) Material Incorporated by Reference 

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) under 5 

U.S.C. 552(a) and 1 CFR part 51 of the 

following service information. 

(1) Boeing Service Bulletin 767–56A0010, 

Revision 3, dated March 3, 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; telephone 

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 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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on March 5, 

2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–6118 Filed 3–19–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0565; Directorate 

Identifier 2010–NM–280–AD; Amendment 

39–16977; AD 2012–05–05] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model CL–215–1A10, 

CL–215–6B11 (CL–215T Variant), and 

CL–215–6B11 (CL–415 Variant) 

airplanes. This AD was prompted by 

reports of cracked or broken support 

bracket assemblies of the emergency 

water dump pulley. This AD requires 

inspecting the bracket assembly of the 

emergency water dump pulley to 

determine if certain rivets are installed; 

replacing rivets and installing new 

stiffeners on the bracket assembly, if 

necessary; inspecting the stiffeners for 

the bracket assembly for cracks, 

deformation, or corrosion, and 

replacement if necessary; and reinstalling the bracket assembly with 

radius packers. We are issuing this AD 

to detect and correct failure of the 

support bracket assembly of the 

emergency water dump pulley, and in 

combination with other system failures, 

such as an engine failure during take off 

or a pitch control system jam, may 

result in loss of controllability of the 

airplane. 

DATES: This AD becomes effective April 

24, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 24, 2012. 

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: 

Andreas Rambalakos, 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– 

7345; 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 June 10, 2011 (76 FR 34014). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The MCAI states: 

The emergency water dump pulley support 

bracket assembly, Part Number (P/N) 215– 

94711–2, has been found cracked or broken 

on a number of aeroplanes. Failure of the 

emergency water dump pulley support 

bracket assembly in combination with other 

system failures such as an engine failure 

during take off or pitch control system jam, 

may result in a loss of control of the 

aeroplane. 

Revision 2 of this [Transport Canada Civil 

Aviation (TCCA)] AD is issued to ensure that 

terminating action for this [TCCA] AD is 

carried out prior to the 2011 fire season. 

The required actions include a general 

visual inspection to determine if either 

universal solid (round head) rivets or 

flush rivets of the bracket assembly of 

the emergency water dump pulley are 

installed; replacing the solid rivets with 

flush rivets and installing new stiffeners 

on the bracket assembly of the 

emergency water dump pulley, if 

necessary; a detailed inspection and a 

liquid penetrant inspection of the 

stiffeners for cracks, deformations, or 

signs of corrosion, and replacing the 

stiffeners with new stiffeners if 

necessary; and re-installing the bracket 

assembly of the emergency water dump 

pulley using radius packers. You may 

obtain further information by examining 

the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request To Extend Proposed 

Compliance Time for Replacing 

Damaged Stiffeners for Airplanes Used 

in Utility-Category Flight Operations 

Aero-Flite, Inc. stated that it does not 

find that a reduction in operational 

safety exists for utility-category flight 

operations where the water tanks 


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remain empty and the emergency water 

dump system becomes inoperative. 

Aero-Flite, Inc. stated that its review of 

the airplane flight manual emergency 

and abnormal procedures for Model CL– 

215 airplanes conducting restricted 

category operations revealed that the 

emergency water dump system is 

required as a back up in the event of 

failure of the electro-hydraulic water 

door system. Aero-Flite, Inc. also stated 

that prohibiting all flight operations if 

cracks, signs of corrosion, or 

deformation of the stiffeners is found 

during inspection creates an 

unnecessary burden for the operator, 

affecting mission availability and 

increasing the cost of compliance 

without providing a meaningful 

improvement in safety. Aero-Flite, Inc. 

stated the changes will allow the 

operator to plan for utility-category 

flight mission requirements. 

Aero-Flite, Inc. recommended that all 

flight limitations contained in the 

NPRM (76 FR 34014, June 10, 2011) be 

changed to consider that water or fire 

retardant must be in the tanks for the 

unsafe condition to exist. Therefore, 

Aero-Flite, Inc. suggested that all 

occurrences of ‘‘before further flight’’ 

(specified in paragraphs (i) and (j) of the 

NPRM) be changed to ‘‘before further 

approved restricted category operations 

with water or fire retardant in the tanks 

including scooping operations.’’ 

We do not agree. Per the type 

certificate data sheet for Model CL–215– 

1A10, CL–215–6B11 (CL–215T Variant), 

and CL–215–6B11 (CL–415 Variant) 

airplanes, these airplanes are 

certificated in the restricted category 

only and therefore no reference can be 

made to utility-category operations. In 

addition, because of the safety 

implications and consequences 

associated with cracking, our policy 

requires repair of known cracks, 

deformation, and signs of corrosion, 

before further flight. This policy is 

based on the fact that such damaged 

airplanes do not conform to the FAAcertificated type design and, therefore, 

are not airworthy until a properly 

approved repair is made. While we 

recognize that repair deferrals might be 

necessary in certain cases of unusual 

need, routinely deferring repairs could 

reduce the safety of the type certificated 

design if such repair deferrals are 

practiced routinely. We have not 

changed the AD regarding this issue. 

Request To Extend the Compliance 

Time for the Liquid Penetrant 

Inspection and Re-Installing the 

Bracket Assembly of the Emergency 

Water Dump Pulley 

Aero-Flite, Inc. requested that we 

change the compliance time in 

paragraph (j) of the NPRM (76 FR 34014, 

June 10, 2011) to ‘‘Within 100 flight 

cycles or 120 days after the effective 

date of this AD or as of November 1, 

2011, whichever occurs later.’’ AeroFlite, Inc. stated that it finds that the 

compliance time specified in paragraph 

(j) of this NPRM may provide an 

unnecessary burden for the operator, 

resulting in airplanes becoming 

unavailable, and risking substantial loss 

of property and life from wild fires 

without providing a meaningful 

improvement in airplane operational 

safety. 

We disagree with extending the 

compliance time for the liquid penetrant 

inspection and re-installing the bracket 

assembly of the emergency water dump 

pulley. In developing an appropriate 

compliance time for the actions 

specified in paragraph (j) of this AD, we 

considered the safety implications, parts 

availability, and normal maintenance 

schedules for the timely 

accomplishment of the specified 

actions. We have determined that the 

proposed compliance time will ensure 

an acceptable level of safety and allow 

the actions to be done during scheduled 

maintenance intervals for most affected 

operators. In addition, investigations by 

Bombardier have revealed that the 

cracked support bracket assemblies did 

not pass limit and ultimate load 

conditions. Because this is a strength 

issue, Bombardier recommends 

replacement of affected parts followed 

by installation of radius packers to 

strengthen the support bracket 

assembly, which would terminate the 

need for repetitive inspections. Affected 

operators, however, may request an 

alternative method of compliance 

(AMOC) under the provisions of 

paragraph (1)(1) of this AD by 

submitting data substantiating that the 

change would provide an acceptable 

level of safety. We have not changed 

this AD in this regard. 

Request To Use an Optional Service 

Inspection 

Aero-Flite, Inc. requested that we 

revise paragraph (l) of the NPRM (76 FR 

34014, June 10, 2011) to add an optional 

visual inspection for the exposed areas 

of the stiffeners, paying special attention 

to the identified critical locations 

(removing the bolt from the critical bolt 

hole and inspect the hole). 

Aero-Flite, Inc. stated that 

accomplishing the repetitive inspections 

in accordance with Bombardier Service 

Bulletin 215–A543, Revision 1, dated 

June 23, 2010, requires removal of the 

bracket assembly from the airplane. 

Aero-Flite, Inc. stated that it finds that 

the repetitive visual inspections of the 

critical locations on the stiffeners can be 

accomplished without removing the 

bracket assembly and without 

substantial systems disassembly by 

removing the fastener common to the 

triangular flange. Aero-Flite, Inc. also 

stated that mandating removal of the 

bracket assembly to conduct visual 

inspections creates a burden on the 

operator, which may affect fire fighting 

mission availability, and increase the 

cost of compliance without providing a 

meaningful improvement in safety. 

We disagree with the request to use an 

optional visual inspection. Bombardier 

has only validated the required 

inspections in Bombardier Service 

Bulletin 215–A543, Revision 1, dated 

June 23, 2010. We have not received 

sufficient technical information from 

Bombardier validating that a visual 

inspection without removing the bracket 

assembly would identify the unsafe 

condition. Affected operators, however, 

may request an AMOC under the 

provisions of paragraph (l)(1) of this AD 

by submitting data substantiating that 

the change would provide an acceptable 

level of safety. We have not changed 

this AD in this regard. 

Request To Use Optional Surface Eddy 

Current Inspection 

Aero-Flite, Inc. recommends that we 

revise paragraph (j)(1) of the NPRM (76 

FR 34014, June 10, 2011) to include an 

optional surface eddy current inspection 

for detecting cracks, corrosion, and 

deformation of the stiffeners. 

Aero-Flite, Inc. stated that the liquid 

penetrant inspection specified in the 

NPRM (76 FR 34014, June 10, 2011) 

seems to eliminate an equivalent 

inspection, such as a surface eddy 

current inspection for detecting cracks, 

and a visual inspection for corrosion 

and deformation. Aero-Flite, Inc. also 

stated that general surface eddy current 

inspection procedures are published in 

the Bombardier CL–215 nondestructive 

testing manual, and that the procedures 

can be used to detect cracks in the 

stiffeners with an accuracy that is at 

least equivalent to liquid penetrant 

inspection procedure. Aero-Flite, Inc. 

stated that using a visual inspection for 

signs of corrosion allows the inspector 

to look for loose paint, discoloration of 

the surface, or variations in surface 

roughness, and that a visual inspection 

provides detection that is equivalent to 


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the liquid penetrant inspection. AeroFlite, Inc. stated that requiring the 

operator to inspect the stiffeners only 

using liquid penetrant may create a 

burden on the operator that may affect 

fire fighting mission availability and 

increase the cost of compliance without 

providing an improvement in safety. 

We disagree with the request to use an 

optional surface eddy current 

inspection. Bombardier has only 

validated the required inspections in 

Bombardier Service Bulletin 215–A543, 

Revision 1, dated June 23, 2010. We 

have not received sufficient technical 

information from Bombardier validating 

that an inspection other than visual 

would identify the unsafe condition. 

Affected operators, however, may 

request an optional inspection under the 

provisions of paragraph (l)(1) of this AD 

by submitting data substantiating that 

the change would provide an acceptable 

level of safety. We have not changed 

this AD in this regard. 

Requests To Allow Use of Locally or 

Operator Fabricated Parts 

Aero-Flite, Inc. requested that we 

revise paragraph (j)(2) of the NPRM (76 

FR 34014, June 10, 2011) to allow 

operators to install owner/operator 

fabricated replacement parts. 

Aero-Flite, Inc. stated that the 

requirement for replacing defective 

stiffeners with new stiffeners, and using 

original equipment manufacturer radius 

packers appears to eliminate the 

possibility of using engineering 

dispositions for serviceable stiffeners or 

fabricated radius packers. Aero-Flite, 

Inc. also stated that it finds that 

installing locally fabricated stiffeners 

and radius packers will not reduce the 

level of safety achieved, and that 

requiring the operator to install only 

new parts and radius packers purchased 

from the OEM may create a burden on 

the operator that may affect fire fighting 

mission availability and increase the 

cost of compliance without providing an 

improvement in safety. 

We disagree with the request to use 

locally or operator fabricated parts. The 

requested list of non-OEM substitute 

parts and materials is extensive and 

uncontrolled—and, in many cases, not 

FAA-approved. An operator may 

request approval of an AMOC in 

accordance with the provisions of 

paragraph (l)(1) of this AD. We have not 

changed this AD regarding this issue. 

Explanation of Change Made to This 

AD 

We have revised the heading for and 

the wording in paragraph (k) of this AD; 

this change has not changed the intent 

of that paragraph. 

Conclusion 

We reviewed the available data, 

including the comments received, 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 (76 FR 

34014, June 10, 2011) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (76 FR 34014, 

June 10, 2011). 

Differences Between This AD and the 

MCAI or Service Information 

This AD differs from the MCAI and/ 

or service information as follows: 

Although Canadian Airworthiness 

Directive CF–2010–38R2, dated March 

17, 2011, has a compliance time of ‘‘No 

later than 01 June 2011,’’ for Part II— 

Terminating Action, this AD has a 

compliance time for a terminating 

action of ‘‘Within 100 flight cycles or 60 

days after the effective date of this AD, 

whichever occurs first.’’ We have 

coordinated this difference with 

Transport Canada Civil Aviation 

(TCCA). 

Although Canadian Airworthiness 

Directive CF–2010–38R2, dated March 

17, 2011, has an initial compliance time 

of ‘‘within 50 flight cycles after the 

effective date of this AD’’ for identifying 

the type of rivet installed, this AD has 

a compliance time of ‘‘within 50 flight 

cycles or 30 days after the effective date 

of this AD, whichever occurs first.’’ In 

addition, the follow-on inspections in 

paragraph (i) of this AD for airplanes on 

which flush rivets are determined to be 

installed, is ‘‘within 100 flight cycles or 

60 days after the effective date of this 

AD, whichever occurs first.’’ We have 

coordinated this difference with TCCA. 

Costs of Compliance 

We estimate that this AD will affect 6 

products of U.S. registry. We also 

estimate that it will take about 40 workhours per product to comply with the 

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 $20,400, or $3,400 per product. 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions 

specified in this 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 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, 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. 


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16154 Federal Register / Vol. 77, No. 54 / Tuesday, March 20, 2012 / Rules and Regulations 

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 adding 

the following new AD: 

2012–05–05 Bombardier, Inc.: Amendment 

39–16977. Docket No. FAA–2011–0565; 

Directorate Identifier 2010–NM–280–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective April 24, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

CL–215–1A10 airplanes, serial numbers 1051 

through 1125 inclusive; Model CL–215–6B11 

(CL–215T Variant) airplanes, serial numbers 

1056 through 1125 inclusive; and Model CL– 

215–6B11 (CL–415 Variant) airplanes; serial 

numbers 2001 through 2085 inclusive; 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 25: Equipment/Furnishings. 

(e) Reason 

This AD was prompted by reports of 

cracked or broken support bracket assemblies 

of the emergency water dump pulley. We are 

issuing this AD to detect and correct failure 

of the support bracket assembly of the 

emergency water dump pulley, and in 

combination with other system failures, such 

as an engine failure during take off or a pitch 

control system jam, may result in loss of 

controllability 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) Inspections 

Within 50 flight cycles or 30 days after the 

effective date of this AD, whichever occurs 

first, do a general visual inspection to 

determine if either universal solid (round 

head) rivets or flush rivets of the bracket 

assembly of the emergency water dump 

pulley are installed, in accordance with the 

Accomplishment Instruction of Bombardier 

Alert Service Bulletin 215–A543, Revision 1, 

dated June 23, 2010 (for Model CL–215–1A10 

and CL–215–6B11 (CL–215T Variant) 

airplanes); or Bombardier Alert Service 

Bulletin 215–A4424, Revision 2, dated June 

23, 2010 (for Model CL–215–6B11 (CL–415 

Variant) airplanes). 

(h) Corrective Action if Universal Solid 

Rivets are Installed 

If, during the inspection required by 

paragraph (g) of this AD, universal solid 

rivets are determined to be installed: Within 

50 flight cycles or 30 days after the effective 

date of this AD, whichever occurs first, 

replace the solid rivets with flush rivets, and 

install new stiffeners on the bracket assembly 

of the emergency water dump pulley, in 

accordance with the Accomplishment 

Instructions of Bombardier Alert Service 

Bulletin 215–A543, Revision 1, dated June 

23, 2010 (for Model CL–215–1A10 and CL– 

215–6B11 (CL–215T Variant) airplanes); or 

Bombardier Alert Service Bulletin 215– 

A4424, Revision 2, dated June 23, 2010 (for 

Model CL–215–6B11 (CL–415 Variant) 

airplanes). 

(i) Corrective Action if Flush Rivets are 

Installed 

If, during the inspection required by 

paragraph (g) of this AD, flush rivets are 

determined to be installed; and for airplanes 

on which flush rivets are installed in 

accordance with paragraph (h) of this AD: 

Within 100 flight cycles or 60 days after the 

effective date of this AD, whichever occurs 

first, do a detailed inspection of the stiffeners 

for cracks, deformation, and signs of 

corrosion, in accordance with the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin 215–A543, Revision 1, 

dated June 23, 2010 (for Model CL–215–1A10 

and CL–215–6B11 (CL–215T Variant) 

airplanes); or Bombardier Alert Service 

Bulletin 215–A4424, Revision 2, dated June 

23, 2010 (for Model CL–215–6B11 (CL–415 

Variant) airplanes). Thereafter, at intervals 

not to exceed 100 flight cycles, repeat the 

detailed inspections of the stiffeners. If any 

crack, deformation, or signs of corrosion are 

found, before further flight, replace the 

stiffeners with new stiffeners, in accordance 

with the Accomplishment Instructions of 

Bombardier Alert Service Bulletin 215–A543, 

Revision 1, dated June 23, 2010 (for Model 

CL–215–1A10 and CL–215–6B11 (CL–215T 

Variant) airplanes); or Bombardier Alert 

Service Bulletin 215–A4424, Revision 2, 

dated June 23, 2010 (for Model CL–215–6B11 

(CL–415 Variant) airplanes). 

(j) Terminating Action 

Within 100 flight cycles or 60 days after 

the effective date of this AD, whichever 

occurs first, do the actions specified in 

paragraphs (j)(1) and (j)(2) of this AD. 

Installation of the radius packers terminates 

the repetitive detailed inspections of the 

support bracket assembly of the emergency 

water dump pulley required by paragraph (i) 

of this AD. 

(1) Do a liquid penetrant inspection of the 

stiffeners having P/N 215–94711–6 and P/N 

215–94711–8 for cracks, deformation, or 

signs of corrosion, in accordance with the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin 215–A543, Revision 1, 

dated June 23, 2010 (for Model CL–215–1A10 

and CL–215–6B11 (CL–215T Variant) 

airplanes); or Bombardier Alert Service 

Bulletin 215–A4424, Revision 2, dated June 

23, 2010 (for Model CL–215–6B11 (CL–415 

Variant) airplanes). If any crack, deformation, 

or sign of corrosion is found, before further 

flight, replace damaged stiffeners with new 

stiffeners, in accordance with the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin 215–A543, Revision 1, 

dated June 23, 2010 (for Model CL–215–1A10 

and CL–215–6B11 (CL–215T Variant) 

airplanes); or Bombardier Alert Service 

Bulletin 215–A4424, Revision 2, dated June 

23, 2010 (for Model CL–215–6B11 (CL–415 

Variant) airplanes). 

(2) Re-install the bracket assembly of the 

emergency water dump pulley using radius 

packers, in accordance with the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin 215–A543, Revision 1, 

dated June 23, 2010 (for Model CL–215–1A10 

and CL–215–6B11 (CL–215T Variant) 

airplanes); or Bombardier Alert Service 

Bulletin 215–A4424, Revision 2, dated June 

23, 2010 (for Model CL–215–6B11 (CL–415 

Variant) airplanes). 

(k) Credit Previous Actions 

This paragraph provides credit for the 

actions required by paragraphs (g), (h), (i), 

and (j) of this AD, if the actions were 

performed before the effective date of this AD 

using the service information specified in 

paragraphs (k)(1), (k)(2), and (k)(3) of this AD. 

(1) Bombardier Service Bulletin 215–4424, 

dated January 25, 2010. 

(2) Bombardier Alert Service Bulletin 215– 

A4424, Revision 1, dated May 18, 2010. 

(3) Bombardier Alert Service Bulletin 215– 

A543, dated May 19, 2010. 

(l) 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, 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. 


wreier-aviles on DSK5TPTVN1PROD with RULES
Federal Register / Vol. 77, No. 54 / Tuesday, March 20, 2012 / Rules and Regulations 16155 

(m) Related Information 

Refer to MCAI Canadian Airworthiness 

Directive CF–2010–38R2, dated March 17, 

2011, and the service information specified 

in paragraphs (m)(1) and (m)(2) of this AD; 

for related information. 

(1) Bombardier Alert Service Bulletin 215– 

A543, Revision 1, dated June 23, 2010. 

(2) Bombardier Alert Service Bulletin 215– 

A4424, Revision 2, dated June 23, 2010. 

(n) 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) Bombardier Alert Service Bulletin 215– 

A543, Revision 1, dated June 23, 2010. 

(ii) Bombardier Alert Service Bulletin 215– 

A4424, Revision 2, dated June 23, 2010. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu 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. 

(3) 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. 

(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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on March 1, 

2012. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–6117 Filed 3–19–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0191; Directorate 

Identifier 2012–NM–035–AD; Amendment 

39–16980; AD 2012–05–08] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Empresa Brasileira de Aeronautica S.A. 

(EMBRAER) Model ERJ 170 airplanes. 

This AD requires repetitive inspections 

for fuel leakage and cracks on the wing 

spar II, close to the rib 10 area, and 

repair if necessary. This AD was 

prompted by reports of fuel seepage at 

the left-hand wing, close to the rib 10 

area in two airplanes. We are issuing 

this AD to detect and correct cracking 

on the wing spar II, which could result 

in a fuel leak, consequent reduced 

structural integrity of the airplane, and 

possible fire. 

DATES: This AD becomes effective April 

4, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of April 4, 2012. 

We must receive comments on this 

AD by May 4, 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. 

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 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: 

Cindy Ashforth, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

425–227–2768; fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The Ageˆncia Nacional de Aviac ̧a ̃o 

Civil (ANAC), which is the aviation 

authority for Brazil, has issued Brazilian 

Airworthiness Directive 2012–02–01, 

dated February 22, 2012 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

It has been found cases of fuel seepage at 

the Left Hand (LH) wing and close to the Rib 

10 area in two different airplanes. Further 

investigation revealed that the seepage was 

caused by a crack at the LH wing spar II close 

to the Rib 10. The ANAC is issuing this AD 

to detect and correct cracking in the wing 

spar II, which could result in a fuel leak and 

reduced structural integrity of the airplane. 

* * * * * 

This AD requires repetitive general 

visual inspections for fuel leakage on 

the wing spar II, close to the rib 10 area; 

repetitive detailed inspections for cracks 

on the wing spar II, spar cap third, and 

main box lower skins of the wings, close 

to the rib 10 area; an eddy current 

inspection for cracks on the wing spar 

II if necessary; and repair if necessary. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

EMBRAER has issued Alert Service 

Bulletin 170–57–A053, dated February 

13, 2012. 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 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 issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Interim Action 

This AD is considered interim action 

to address the unsafe condition. If final 

action is later identified, we might 

consider further rulemaking then. 

Differences Between the AD and the 

MCAI or Service Information 

The MCAI requires actions only for 

airplanes that have exceeded 12,000 

total flight cycles, but the requirements 

of this (FAA) AD apply to all Model 170 

airplanes. 


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