Federal Register / Vol. 77, No. 76 / Thursday, April 19, 2012 / Rules and Regulations 23385 

Corporation, Attn: Manager, Commercial 

Technical Support, Mailstop s581a, 6900 

Main Street, Stratford, CT 06614; telephone 

(800) 562–4409; email 

tsslibrary@sikorsky.com; or at http:// 

www.sikorsky.com. You may review a copy 

of this service information at the FAA, Office 

of the Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 7200, Engine (Turbine/Turboprop). 

Issued in Fort Worth, Texas, on April 9, 

2012. 

Lance T. Gant, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–9298 Filed 4–18–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1226; Directorate 

Identifier 2011–NM–006–AD; Amendment 

39–17001; AD 2012–06–20] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Fokker Services B.V. Model F.28 Mark 

0070 and 0100 airplanes. This AD was 

prompted by a report that the fuel 

crossfeed valves cannot be controlled 

when only emergency electrical power 

is available, that an unwanted 

configuration of the indication logic for 

the fuel fire shutoff valve was 

introduced during production, and that 

current fuel crossfeed indications are 

based on selection by the flightcrew 

instead of actual position of the 

crossfeed valve actuators. This AD 

requires modifying the crossfeed valve 

control and power supply, the crossfeed 

indication logic and power supply, and 

the indication logic for the fuel fire 

shutoff valve; modifying the overhead 

panel; and for certain airplanes, 

modifying the transfer logic of the 

center wing fuel tank. We are issuing 

this AD to prevent failure of an in-flight 

engine re-light following a double 

engine flame-out event, which could 

result in loss of the airplane. 

DATES: This AD becomes effective May 

24, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of May 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: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1137; fax (425) 227–1149. 

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 November 8, 2011 (76 FR 

69163). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

A recent safety review revealed that the 

fuel crossfeed valves cannot be controlled 

when only emergency electrical power is 

available. 

This condition, if not corrected, could (in 

combination with other factors) prevent an 

in-flight engine re-light following a double 

engine flame-out event, possibly resulting in 

loss of the aeroplane. 

Another review revealed that an unwanted 

configuration of the fuel fire shut-off valve 

indication logic had been introduced during 

production on a limited number of F28 Mark 

0100 aeroplanes. 

Furthermore, most of the current fuel 

crossfeed indications are based on the 

crossfeed selection made by the flight crew 

and not on the actual positions of the 

crossfeed valve actuators. In combination 

with other factors, the current crossfeed 

indications may mislead flight crews, 

possibly resulting in single engine in-flight 

shutdowns and/or unnecessary precautionary 

landings. 

For the reasons described above, this 

[EASA] AD requires modifications of the 

crossfeed valve control and power supply, of 

the crossfeed indication logic and power 

supply and of the fuel fire shut-off valve 

indication logic. 

* * * * * 

Required actions also include modifying 

the overhead panel (introducing 

provisions for a modified crossfeed 

indication), and, for certain airplanes, 

modifying the transfer logic of the 

center wing fuel tank. 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 

received no comments on the NPRM (76 

FR 69163, November 8, 2011) or on the 

determination of the cost to the public. 

Explanation of Changes Made to This 

AD 

We have revised the heading for and 

the wording in paragraph (i) of this AD; 

this change has not changed the intent 

of that paragraph. We have also revised 

the document citations throughout this 

AD to more clearly identify the 

documents and their attachments. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously— 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (76 FR 

69163, November 8, 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 69163, 

November 8, 2011). 

Costs of Compliance 

We estimate that this AD will affect 6 

products of U.S. registry. We also 

estimate that it will take about 86 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $4,180 

per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these parts. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of 

this AD to the U.S. operators to be 

$68,940, or $11,490 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 


srobinson on DSK4SPTVN1PROD with RULES
23386 Federal Register / Vol. 77, No. 76 / Thursday, April 19, 2012 / Rules and 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 this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. We prepared a 

regulatory evaluation of the estimated 

costs to comply with this 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 (76 FR 69163, 

November 8, 2011), 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 adding 

the following new AD: 

2012–06–20 Fokker Services B.V.: 

Amendment 39–17001. Docket No. 

FAA–2011–1226; Directorate Identifier 

2011–NM–006–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective May 24, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Fokker Services B.V. 

Model F.28 Mark 0070 and 0100 airplanes, 

certificated in any category, serial numbers 

11244 through 11585 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28: Fuel. 

(e) Reason 

This AD was prompted by a report that the 

fuel crossfeed valves cannot be controlled 

when only emergency electrical power is 

available, that an unwanted configuration of 

the indication logic for the fuel fire shutoff 

valve was introduced during production, and 

that current fuel crossfeed indications are 

based on selection by the flightcrew instead 

of actual position of the crossfeed valve 

actuators. We are issuing this AD to prevent 

failure of an in-flight engine re-light 

following a double engine flame-out event, 

which could result in loss 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) Modifications 

Within 24 months after the effective date 

of this AD, modify the crossfeed valve 

control and power supply, the crossfeed 

indication logic and power supply, and the 

indication logic for the fuel fire shutoff valve, 

in accordance with the Accomplishment 

Instructions of Fokker Service Bulletin 

SBF100–28–047, Revision 3, dated May 2, 

2011, including the attachments specified in 

paragraphs (g)(1) through (g)(39) of this AD 

(*the issue date is not specified on the 

drawing). 

(1) Fokker Manual Change Notification— 

Operational Documentation MCNO–F100– 

060, dated June 10, 2011. 

(2) Fokker Manual Change Notification— 

Operational Document MCNO–F100–049, 

Revision 1, dated May 30, 2011. 

(3) Fokker Drawing D42770, Sheet 6, Issue 

U*. 

(4) Fokker Drawing D42780, Sheet 6, Issue 

T*. 

(5) Fokker Drawing W41074, Sheet 100, 

Issue GB*. 

(6) Fokker Drawing W41074, Sheet 101, 

Issue FW*. 

(7) Fokker Drawing W41194, Sheet 010, 

Issue J*. 

(8) Fokker Drawing W41194, Sheet 011, 

Issue U*. 

(9) Fokker Drawing W41194, Sheet 012, 

Issue J*. 

(10) Fokker Drawing W41194, Sheet 013, 

Issue U*. 

(11) Fokker Drawing W41194, Sheet 014, 

Issue S*. 

(12) Fokker Drawing W41194, Sheet 015, 

Issue U*. 

(13) Fokker Drawing W41194, Sheet 017, 

Issue Q*. 

(14) Fokker Drawing W41194, Sheet 019, 

Issue S*. 

(15) Fokker Drawing W41194, Sheet 020, 

Issue S*. 

(16) Fokker Drawing W41319, Sheet 063, 

Issue DY*. 

(17) Fokker Drawing W41319, Sheet 064, 

Issue DY*. 

(18) Fokker Drawing W41319, Sheet 065, 

Issue DY*. 

(19) Fokker Drawing W41319, Sheet 066, 

Issue DY*. 

(20) Fokker Drawing W41319, Sheet 067, 

Issue DW*. 

(21) Fokker Drawing W41319, Sheet 068, 

Issue DW*. 

(22) Fokker Drawing W41319, Sheet 069, 

Issue DY*. 

(23) Fokker Drawing W41319, Sheet 070, 

Issue DW*. 

(24) Fokker Drawing W41319, Sheet 071, 

Issue DY*. 

(25) Fokker Drawing W41319, Sheet 072, 

Issue DW*. 

(26) Fokker Drawing W41319, Sheet 073, 

Issue DW*. 

(27) Fokker Drawing W41319, Sheet 074, 

Issue DY*. 

(28) Fokker Drawing W46211, Sheet 71, 

Issue DL, dated April 21, 2009. 

(29) Fokker Drawing W46211, Sheet 74, 

Issue DN, dated July 16, 2010. 

(30) Fokker Drawing W46254, Sheet 30, 

Issue BL, dated March 30, 2009. 

(31) Fokker Drawing W46254, Sheet 31, 

Issue BL, dated March 30, 2009. 

(32) Fokker Drawing W46254, Sheet 32, 

Issue BL, dated March 30, 2009. 

(33) Fokker Drawing W46254, Sheet 33, 

Issue BL, dated March 30, 2009. 

(34) Fokker Drawing W46254, Sheet 34, 

Issue BL, dated March 30, 2009. 

(35) Fokker Drawing W46254, Sheet 35, 

Issue BL, dated March 30, 2009. 

(36) Fokker Drawing W46254, Sheet 36, 

Issue BL, dated March 30, 2009. 

(37) Fokker Drawing W46254, Sheet 37, 

Issue BP, dated March 30, 2009. 

(38) Fokker Drawing W59221, Sheet 161, 

Issue FC, July 9, 2010. 

(39) Fokker Drawing W59221, Sheet 162, 

Issue FC, July 9, 2010. 

(h) Concurrent Modifications 

Before or concurrent with the modification 

specified in paragraph (g) of this AD, do the 

applicable actions specified in paragraphs 

(h)(1) and (h)(2) of this AD: 

(1) For all airplanes: Modify the overhead 

panel (introduce provisions for a modified 

crossfeed indication) in accordance with the 

Accomplishment Instructions of Fokker 

Proforma Service Bulletin SBF100–28–043, 

Revision 1, dated March 31, 2009, including 


srobinson on DSK4SPTVN1PROD with RULES
Federal Register / Vol. 77, No. 76 / Thursday, April 19, 2012 / Rules and Regulations 23387 

Appendix II, Revision 2, dated July 22, 2010, 

including the drawings specified in 

paragraphs (h)(i) through (h)(iv) of this AD, 

which are attached to Appendix II, Revision 

2, dated July 22, 2010 (*the issue date is not 

specified on the drawing). 

(i) Fokker Drawing W41194, Sheet 009, 

Issue F*. 

(ii) Fokker Drawing W41194, Sheet 016, 

Issue N*. 

(iii) Fokker Drawing W41194, Sheet 018, 

Issue S*. 

(iv) Fokker Drawing W59221, Sheet 159, 

Issue ED, dated October 2, 2009. 

(2) For airplanes with serial numbers 

11442 through 11585, equipped with the 

automatic fuel transfer system: Modify the 

transfer logic of the center wing fuel tank, in 

accordance with the Accomplishment 

Instructions of Fokker Service Bulletin 

SBF100–28–052, dated June 15, 2009, 

including the attachments specified in 

paragraphs (h)(2)(i) through (h)(2)(vii) of this 

AD. 

(i) Fokker Manual Change Notification— 

Operational Documentation MCNO–F100– 

052, dated June 15, 2009. 

(ii) Fokker Manual Change Notification— 

Maintenance Documentation MCNM–F100– 

126, dated June 15, 2009. 

(iii) Fokker Drawing D42126, Sheet 38, 

Issue AR, dated October 6, 1993. 

(iv) Fokker Drawing D42213, Sheet 2, Issue 

H, dated May 23, 1990. 

(v) Fokker Drawing D42220, Sheet 60, Issue 

V, dated September 1, 1991. 

(vi) Fokker Drawing D42220, Sheet 71, 

Issue AQ, dated June 7, 1993. 

(vii) Fokker Drawing D42250, Sheet 23, 

Issue U, dated April 1993. 

(i) Credit for Previous Actions 

This paragraph provides credit for 

modifications required by paragraphs (g) and 

(h) of this AD, if the modifications were 

performed before the effective date of this 

AD, using the applicable service bulletins 

specified in paragraphs (i)(1), (i)(2), (i)(3), 

and (i)(4) of this AD. 

(1) Fokker Service Bulletin SBF100–28– 

043, including Appendix II, dated March 31, 

2009. 

(2) Fokker Service Bulletin SBF100–28– 

047, Revision 2, dated August 4, 2010. 

(3) Fokker Service Bulletin SBF100–28– 

047, Revision 1, dated July 22, 2010. 

(4) Fokker Service Bulletin SBF100–28– 

047, dated May 10, 2010. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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 International Branch, send it to ATTN: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1137; fax (425) 

227–1149. Information may be emailed to: 

9-ANM-116-AMOC-REQUESTS@faa.gov. 

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. 

(k) Related Information 

Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2010– 

0158R1, dated November 8, 2010, and the 

service bulletins specified in paragraphs (g) 

and (h) of this AD, for related information. 

(l) 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) Fokker Proforma Service Bulletin 

SBF100–28–043, Revision 1, dated March 31, 

2009, including Appendix II, Revision 2, 

dated July 22, 2010, and including the 

following drawings which are attached to 

Appendix II, Revision 2, dated July 22, 2010 

(*the issue date is not specified on the 

drawing): 

(A) Fokker Drawing W41194, Sheet 009, 

Issue F*. 

(B) Fokker Drawing W41194, Sheet 016, 

Issue N*. 

(C) Fokker Drawing W41194, Sheet 018, 

Issue S*. 

(D) Fokker Drawing W59221, Sheet 159, 

Issue ED, dated October 2, 2009. 

(ii) Fokker Service Bulletin SBF100–28– 

047, Revision 3, dated May 2, 2011, 

including the following attachments (*the 

issue date is not specified on the drawing): 

(A) Fokker Manual Change Notification— 

Operational Documentation MCNO–F100– 

060, dated June 10, 2011. 

(B) Fokker Manual Change Notification— 

Operational Document MCNO–F100–049, 

Revision 1, dated May 30, 2011. 

(C) Fokker Drawing D42770, Sheet 6, Issue 

U*. 

(D) Fokker Drawing D42780, Sheet 6, Issue 

T*. 

(E) Fokker Drawing W41074, Sheet 100, 

Issue GB*. 

(F) Fokker Drawing W41074, Sheet 101, 

Issue FW*. 

(G) Fokker Drawing W41194, Sheet 010, 

Issue J*. 

(H) Fokker Drawing W41194, Sheet 011, 

Issue U*. 

(I) Fokker Drawing W41194, Sheet 012, 

Issue J*. 

(J) Fokker Drawing W41194, Sheet 013, 

Issue U*. 

(K) Fokker Drawing W41194, Sheet 014, 

Issue S*. 

(L) Fokker Drawing W41194, Sheet 015, 

Issue U*. 

(M) Fokker Drawing W41194, Sheet 017, 

Issue Q*. 

(N) Fokker Drawing W41194, Sheet 019, 

Issue S*. 

(O) Fokker Drawing W41194, Sheet 020, 

Issue S*. 

(P) Fokker Drawing W41319, Sheet 063, 

Issue DY*. 

(Q) Fokker Drawing W41319, Sheet 064, 

Issue DY*. 

(R) Fokker Drawing W41319, Sheet 065, 

Issue DY*. 

(S) Fokker Drawing W41319, Sheet 066, 

Issue DY*. 

(T) Fokker Drawing W41319, Sheet 067, 

Issue DW*. 

(U) Fokker Drawing W41319, Sheet 068, 

Issue DW*. 

(V) Fokker Drawing W41319, Sheet 069, 

Issue DY*. 

(W) Fokker Drawing W41319, Sheet 070, 

Issue DW*. 

(X) Fokker Drawing W41319, Sheet 071, 

Issue DY*. 

(Y) Fokker Drawing W41319, Sheet 072, 

Issue DW*. 

(Z) Fokker Drawing W41319, Sheet 073, 

Issue DW*. 

(AA) Fokker Drawing W41319, Sheet 074, 

Issue DY*. 

(BB) Fokker Drawing W46211, Sheet 71, 

Issue DL, dated April 21, 2009. 

(CC) Fokker Drawing W46211, Sheet 74, 

Issue DN, dated July 16, 2010. 

(DD) Fokker Drawing W46254, Sheet 30, 

Issue BL, dated March 30, 2009. 

(EE) Fokker Drawing W46254, Sheet 31, 

Issue BL, dated March 30, 2009. 

(FF) Fokker Drawing W46254, Sheet 32, 

Issue BL, dated March 30, 2009. 

(GG) Fokker Drawing W46254, Sheet 33, 

Issue BL, dated March 30, 2009. 

(HH) Fokker Drawing W46254, Sheet 34, 

Issue BL, dated March 30, 2009. 

(II) Fokker Drawing W46254, Sheet 35, 

Issue BL, dated March 30, 2009. 

(JJ) Fokker Drawing W46254, Sheet 36, 

Issue BL, dated March 30, 2009. 

(KK) Fokker Drawing W46254, Sheet 37, 

Issue BP, dated March 30, 2009. 

(LL) Fokker Drawing W59221, Sheet 161, 

Issue FC, July 9, 2010. 

(MM) Fokker Drawing W59221, Sheet 162, 

Issue FC, July 9, 2010. 

(iii) Fokker Service Bulletin SBF100–28– 

052, dated June 15, 2009, including the 

following attachments: 

(A) Fokker Manual Change Notification— 

Operational Documentation MCNO–F100– 

052, dated June 15, 2009. 

(B) Fokker Manual Change Notification— 

Maintenance Documentation MCNM–F100– 

126, dated June 15, 2009. 

(C) Fokker Drawing D42126, Sheet 38, 

Issue AR, dated October 6, 1993. 

(D) Fokker Drawing D42213, Sheet 2, Issue 

H, dated May 23, 1990. 

(E) Fokker Drawing D42220, Sheet 60, 

Issue V, dated September 1, 1991. 

(F) Fokker Drawing D42220, Sheet 71, 

Issue AQ, dated June 7, 1993. 

(G) Fokker Drawing D42250, Sheet 23, 

Issue U, dated April 1993. 


srobinson on DSK4SPTVN1PROD with RULES
23388 Federal Register / Vol. 77, No. 76 / Thursday, April 19, 2012 / Rules and Regulations 

(2) For Fokker Services B.V. service 

information identified in this AD, contact 

Fokker Services B.V., Technical Services 

Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, 

the Netherlands; telephone +31 (0)252–627– 

350; fax +31 (0)252–627–211; email 

technicalservices.fokkerservices@stork.com; 

Internet http://www.myfokkerfleet.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 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 March 

19, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–9294 Filed 4–18–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0395; Directorate 

Identifier 2012–SW–007–AD; Amendment 

39–17016; AD 2012–02–51] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Limited 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are publishing a new 

airworthiness directive (AD) for Bell 

Helicopter Textron Canada Limited 

(Bell) Model 206L, 206L–1, 206L–3, and 

206L–4 helicopters with certain main 

rotor blades installed to reduce the life 

limit of those blades. This AD is 

prompted by two accidents and the 

subsequent investigations that revealed 

that, in each accident, a main rotor 

blade failed because of fatigue cracking. 

These actions are intended to prevent 

failure of the main rotor blade and 

subsequent loss of control of the 

helicopter. 

DATES: This AD becomes effective May 

4, 2012 to all persons except those 

persons to whom it was made 

immediately effective by Emergency AD 

No. 2012–02–51, issued on February 1, 

2012, which contained the requirements 

of this AD. 

We must receive comments on this 

AD by June 18, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address 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 

economic evaluation, 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 service information identified in 

this AD, contact Bell Helicopter Textron 

Canada Limited, 12,800 Rue de l’Avenir, 

Mirabel, Quebec J7J1R4, telephone (450) 

437–2862 or (800) 363–8023, fax (450) 

433–0272, or at http:// 

www.bellcustomer.com/files/. You may 

review a copy of the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

FOR FURTHER INFORMATION CONTACT: 

Sharon Miles, Aerospace Engineer, 

FAA, Rotorcraft Directorate, Regulations 

and Policy Group, 2601 Meacham Blvd., 

Fort Worth, Texas 76137, telephone 

(817) 222–5110, email 

sharon.y.miles@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments prior to it becoming effective. 

However, we invite you to participate in 

this rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that resulted from 

adopting this AD. The most helpful 

comments reference a specific portion of 

the AD, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit them only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this rulemaking during the 

comment period. We will consider all 

the comments we receive and may 

conduct additional rulemaking based on 

those comments. 

Discussion 

Transport Canada Civil Aviation 

(TCCA) issued TCCA AD No. CF–2011– 

44R1, on February 1, 2012, to correct 

this same unsafe condition on the Bell 

Model 206 L, L–1, L–3, and L–4 

helicopters. TCCA advises that there is 

no reliable inspection method to detect 

the cracks on these blades before blade 

failure and has reduced the life limit on 

all affected blades from 3,600 hours 

time-in-service (TIS) to 1,400 hours TIS 

and mandated removal from service of 

those blades that exceed the new life 

limit. Bell has determined that the 

fatigue cracks occurred as a result of the 

use by a Bell supplier of unapproved 

manufacturing processes, which have 

since been corrected, and are limited to 

a specific range of part numbers and 

serial numbers. 

We issued EAD 2012–02–51 also on 

February 1, 2012, for Bell Model 206L, 

206L–1, 206L–3, and 206L–4 helicopters 

with certain main rotor blades installed 

and reduced the life limit on these 

blades to correct the unsafe condition 

caused by this fatigue cracking. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Canada and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with Canada, TCCA, its 

technical representative, has notified us 

of the unsafe condition described in the 

TCCA AD. We are issuing this AD 

because we evaluated all information 

provided by the TCCA and determined 

the unsafe condition exists and is likely 

to exist or develop on other helicopters 

of these same type designs. 

Related Service Information 

Bell Helicopter Alert Service Bulletin 

No. 206L–09–159 Revision A, dated 

November 13, 2009, describes 


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