37788 Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Rules and Regulations 

2011; or having P/N 85714232–001 and a job 

detail number listed in table 1 of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–57–23, Revision B, dated 

February 16, 2011; on any airplane. 

(j) Credit for Previous Actions 

This paragraph provides credit for 

inspections and fuel access panel 

replacements required by this AD, if those 

actions were performed before the effective 

date of this AD using Bombardier Service 

Bulletin 84–57–22, Revision A, dated 

December 9, 2010; or Bombardier Service 

Bulletin 84–57–23, Revision A, dated 

December 9, 2010; as applicable. 

(k) 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 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. 

(l) 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. 

(i) Bombardier Service Bulletin 84–57–22, 

Revision B, dated February 16, 2011. 

(ii) Bombardier Service Bulletin 84–57–23, 

Revision B, dated February 16, 2011. 

(3) For Bombardier, Inc. service 

information identified in this AD, contact 

Bombardier, Inc., Q–Series Technical Help 

Desk, 123 Garratt Boulevard, Toronto, 

Ontario M3K 1Y5, Canada; telephone 416– 

375–4000; fax 416–375–4539; email 

thd.qseries@aero.bombardier.com; Internet 

http://www.bombardier.com. 

(4) 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. 

(5) 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 June 11, 

2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–14916 Filed 6–22–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0039; Directorate 

Identifier 2011–NM–144–AD; Amendment 

39–17087; AD 2012–12–07] 

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 reports of cracks 

underneath the passenger door in a buttjoint on the forward fuselage of a Model 

F.28 Mark 0100 airplane. This AD 

requires repetitive low frequency eddy 

current inspections of the forward 

fuselage butt-joints for cracks, and if 

necessary, a temporary repair followed 

by a permanent repair. We are issuing 

this AD to detect and correct cracking of 

the butt-joint on the forward fuselage, 

which could result in explosive 

decompression and consequent loss of 

control of the airplane. 

DATES: This AD becomes effective July 

30, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 30, 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 February 6, 2012 (77 FR 

5724). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

A report has been received of a crack, 

detected in a butt-joint on the forward 

fuselage of an F28 Mark 0100 aeroplane, 

underneath the passenger door. 

Investigations revealed that, depending on 

the configuration of the aeroplane, one or two 

butt-joints in the forward fuselage can be 

affected. 

This condition, if not detected and 

corrected, could lead to explosive 

decompression and consequent loss of the 

aeroplane. 

For the reasons described above, this 

[EASA] AD requires repetitive [low 

frequency eddy current] inspections of the 

forward fuselage butt joints for cracks and, 

when a crack is detected, accomplishment of 

a temporary repair. This [EASA] AD also 

requires reporting any cracks found to Fokker 

Services to enable the development of a 

modification and the determination of an 

interval for a repetitive inspection task, to be 

incorporated in the ALI [airworthiness 

limitations instructions] section of the MRB 

[maintenance review board] document. This 

[EASA] AD is considered to be an interim 

measure and further AD action is likely. 

Required actions include a permanent 

repair of the forward fuselage buttjoints. 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 (77 

FR 5724, February 6, 2012) or on the 

determination of the cost to the public. 

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 5724, 

February 6, 2012) for correcting the 

unsafe condition; and 


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Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Rules and Regulations 37789 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 5724, 

February 6, 2012). 

Costs of Compliance 

We estimate that this AD will affect 4 

products of U.S. registry. We also 

estimate that it will take about 3 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 $1,020, or $255 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 40 work-hours and require parts 

costing $0, for a cost of $3,400 per 

product. 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 (77 FR 5724, 

February 6, 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 adding 

the following new AD: 

2012–12–07 Fokker Services B.V.: 

Amendment 39–17087. Docket No. 

FAA–2012–0039; Directorate Identifier 

2011–NM–144–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective July 30, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Fokker Services B.V. 

Model F.28 Mark 0070 and 0100 airplanes, as 

identified in Fokker Service Bulletin 

SBF100–53–115, dated June 16, 2011. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53: Fuselage. 

(e) Reason 

This AD was prompted by reports of cracks 

underneath the passenger door in a butt-joint 

on the forward fuselage of a Model F.28 Mark 

0100 airplane. We are issuing this AD to 

detect and correct cracking of the butt-joint 

on the forward fuselage, which could result 

in explosive decompression and consequent 

loss of control 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) Inspection 

Before the accumulation of 20,000 total 

flight cycles, or within 180 flight cycles after 

the effective date of this AD, whichever 

occurs later, do a low frequency eddy current 

inspection of the forward fuselage butt-joints 

for cracks, in accordance with the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–53–115, dated June 

16, 2011. Repeat the inspection thereafter at 

intervals not to exceed 1,000 flight cycles. 

Doing the temporary repair in paragraph (h) 

of this AD is terminating action for the 

repetitive inspections required by this 

paragraph. The temporary repair can also be 

accomplished if no cracking is found. 

(h) Temporary Repair 

If any cracking is found during any 

inspection required by paragraph (g) of this 

AD, before further flight, do a temporary 

repair, in accordance with the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–53–115, dated June 

16, 2011. Doing the temporary repair is 

terminating action for the repetitive 

inspections required by paragraph (g) of this 

AD. 

(i) Permanent Repair 

Within 10,000 flight cycles after installing 

the temporary repair, as required by 

paragraph (h) of this AD, install a permanent 

repair using a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA. 

(j) Reporting 

Submit a report of the findings (both 

positive and negative), to Fokker Services 

B.V., Technical Services Dept., P.O. Box 231, 

2150 AE Nieuw-Vennep, the Netherlands, 

using the reports form of Fokker Service 

Bulletin SBF100–53–115, dated June 16, 

2011, of the inspection required by paragraph 

(g) of this AD, at the applicable time 

specified in paragraph (j)(1) or (j)(2) of this 

AD. 

(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. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 


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37790 Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Rules and Regulations 

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. 

(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. 

(l) Related Information 

Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2011–0115, 

dated June 17, 2011; and Fokker Service 

Bulletin SBF100–53–115, dated June 16, 

2011; for related information. 

(m) 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. 

(i) Fokker Service Bulletin SBF100–53– 

115, dated June 16, 2011. 

(3) For Fokker 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 

(4) 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. 

(5) 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 June 7, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–14546 Filed 6–22–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0566; Directorate 

Identifier 2011–SW–008–AD; Amendment 

39–17065; AD 2012–11–02] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

Deutschland GmbH Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) that 

supersedes an existing Emergency 

Airworthiness Directive (EAD) for 

certain Eurocopter Deutschland GmbH 

(ECD) Model EC135 helicopters. The 

existing EAD, which was previously 

sent to all known U.S. owners and 

operators of ECD Model EC135 

helicopters and not made generally 

effective by publication in the Federal 

Register, currently requires inspecting 

the ring frame between the rear 

structure tube (tailboom) and the tail 

rotor fenestron housing (fenestron 

housing) for a crack before the first 

flight of each day and replacing any 

cracked ring frame with an airworthy 

ring frame. Since we issued that EAD, 

we have determined that a pre-flight 

pilot check in conjunction with a 

recurring 25-hour inspection is 

sufficient for determining the 

airworthiness of the ring frame. 

Additionally, ECD has developed a 

modification that is terminating action 

for the requirements of that EAD. This 

superseding AD revises the inspection 

requirements of the EAD to allow an 

owner/operator to perform the pre-flight 

pilot check, adds a recurring inspection 

of the ring frame, and allows for 

installation of a ring frame 

reinforcement as an optional 

terminating action for the AD 

requirements. The actions are intended 

to detect a crack in the ring frame which 

could result in loss of the fenestron 

structure and subsequent loss of control 

of the helicopter. 

DATES: This AD becomes effective July 

10, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of July 10, 2012. 

We must receive comments on this 

AD by August 24, 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, 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 service information identified in 

this AD, contact American Eurocopter 

Corporation, 2701 N. Forum Drive, 

Grand Prairie, TX 75052, telephone 

(972) 641–0000 or (800) 232–0323, fax 

(972) 641–3775, or at http://www.

eurocopter.com/techpub. 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; phone (817) 

222–5110; email: sharon.y.miles@faa.

gov. 


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