37786 Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Rules and Regulations 

Issued in Renton, Washington, on June 7, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–14547 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–2012–0298; Directorate 

Identifier 2011–NM–072–AD; Amendment 

39–17096; AD 2012–12–16] 

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 DHC–8–400 

series airplanes. This AD was prompted 

by reports of cracking of certain fuel 

access panels of the outer wing. This AD 

requires an external inspection, and if 

necessary an internal inspection, to 

determine if certain fuel access panels 

are installed, and replacement if 

necessary; optional repetitive 

inspections for cracking of the fuel 

access panels, and replacement if 

necessary, would defer the internal 

inspection; and eventual replacement of 

affected fuel access panels with new 

panels. We are issuing this AD to 

prevent cracking of fuel access panels, 

which could result in arcing and 

ignition of fuel vapor in the outer wing 

fuel tank during a lightning strike. 

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: Aziz 

Ahmed, Aerospace Engineer, Airframe 

and Mechanical Systems Branch, ANE– 

171, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 40, Westbury, New York 

11590; telephone (516) 228–7329; 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 March 27, 2012 (77 FR 

18135). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

[Canadian] Airworthiness Directive (AD) 

CF–2005–37 was issued on 11 October 2005 

to address cracking of the outer wing fuel 

access panel, Part Number (P/N) 85714230– 

001. Similar cracking on an outer wing fuel 

access panel, P/N 85714231–001, has been 

reported. Further investigation revealed that 

certain fuel access panels may have seal 

grooves manufactured with non-conforming 

fillet radii which could lead to cracking. 

Cracking of the fuel access panel, if not 

corrected, could result in arcing and ignition 

of fuel vapor in the outer wing fuel tank 

during a lightning strike. 

This [TCCA] directive mandates the 

inspection and replacement of the affected 

fuel access panels. 

Required actions include an external 

detailed inspection of the outer wing 

access panels for rivets of the 

identification plate, and an internal 

inspection of panels without rivets to 

determine if the identification plate is 

installed, and replacing the fuel access 

panel if necessary. As an option, this 

AD allows repetitive external detailed 

inspections for cracking of the fuel 

access panels and, replacing if 

necessary, until the internal inspection 

is done. This AD also requires 

eventually replacing the affected fuel 

access panels with new fuel access 

panels. 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 18135, March 27, 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. 

Costs of Compliance 

We estimate that this AD will affect 

74 products of U.S. registry. We also 

estimate that it will take about 36 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 $33,632 

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 

$2,715,208, or $36,692 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:// 


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Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Rules and Regulations 37787 

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 18135, 

March 27, 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: 

2012–12–16 Bombardier, Inc.: Amendment 

39–17096. Docket No. FAA–2012–0298; 

Directorate Identifier 2011–NM–072–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective July 30, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

DHC–8–400, –401, and –402 airplanes; 

certificated in any category; serial numbers 

4001 and 4003 through 4106 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by reports of 

cracking of certain fuel access panels of the 

outer wing. We are issuing this AD to prevent 

cracking of fuel access panels, which could 

result in arcing and ignition of fuel vapor in 

the outer wing fuel tank during a lightning 

strike. 

(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 and Replacement of Part 

Number (P/N) 85714231–001 

Within 600 flight hours after the effective 

date of this AD, do an external detailed 

inspection of the outer wing access panels 

having P/N 85714231–001 to locate the rivets 

of the identification plates, in accordance 

with the Accomplishment Instructions of 

Bombardier Service Bulletin 84–57–22, 

Revision B, dated February 16, 2011. If the 

rivets of the identification plate are found, no 

further action is required by this paragraph 

for that fuel access panel. If the rivets of the 

identification plate cannot be found: Before 

further flight, do the actions specified in 

paragraph (g)(1) or (g)(2) of this AD. 

(1) Remove fuel access panels having P/N 

85714231–001 and inspect the panels to 

determine if the identification plate is 

installed, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–57–22, Revision B, dated 

February 16, 2011. If the identification plate 

is found: No further action is required by 

paragraph (g) of this AD for that fuel access 

panel. 

(i) If the identification plate cannot be 

found, and the job detail number stamped on 

the underside of the access panel does not 

match any of those listed in table 1 of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–57–22, Revision B, dated 

February 16, 2011: No further action is 

required by paragraph (g) of this AD for that 

fuel access panel. 

(ii) If the identification plate cannot be 

found, and the job detail number stamped on 

the underside of the fuel access panel does 

match any of those specified in table 1 of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–57–22, Revision B, dated 

February 16, 2011: Before further flight, 

replace the fuel access panel with a new fuel 

access panel having P/N 85714231–003, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–57–22, Revision B, dated February 16, 

2011. 

(2) Do an external detailed inspection on 

fuel access panels having P/N 85714231–001 

for cracking, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–57–22, Revision B, dated 

February 16, 2011. If no cracking is found: 

Repeat the inspection thereafter at intervals 

not to exceed 600 flight hours until the 

replacement specified in paragraph (g)(2)(i) 

of this AD, or the inspection specified in 

paragraph (g)(1) of this AD, is done. 

(i) If the fuel access panel is found cracked 

during any inspection required by this AD: 

Before further flight, replace the fuel access 

panel with a new fuel access panel having 

P/N 85714231–003, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 84–57–22, Revision B, dated 

February 16, 2011. 

(ii) Within 6,000 flight hours after the 

initial inspection required by paragraph (g)(2) 

of this AD, do the actions specified by 

paragraph (g)(1) of this AD, unless the 

replacement required by paragraph (g)(2)(i) of 

this AD is done. 

(h) Inspection and Replacement of P/N 

85714232–001 

Within 1,200 flight hours after the effective 

date of this AD, do an external detailed 

inspection of the outer wing access panels 

having P/N 85714232–001 to locate the rivets 

of the identification plates, in accordance 

with the Accomplishment Instructions of 

Bombardier Service Bulletin 84–57–23, 

Revision B, dated February 16, 2011. If the 

rivets of the identification plate are found: 

No further action is required by this 

paragraph for that fuel access panel. If the 

rivets of the identification plate cannot be 

found: Before further flight, do the actions 

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

AD. 

(1) Remove fuel access panels having P/N 

85714232–001 and inspect the panels to 

determine if the identification plate is 

installed, in accordance with the 

Accomplishment Instructions of Bombardier 

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

February 16, 2011. If the identification plate 

is found: No further action is required by 

paragraph (h) of this AD for that fuel access 

panel. 

(i) If the identification plate cannot be 

found, and the job detail number stamped on 

the underside of the access panel does not 

match any of those specified in table 1 of the 

Accomplishment Instructions of Bombardier 

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

February 16, 2011: No further action is 

required by paragraph (h) of this AD for that 

fuel access panel. 

(ii) If the identification plate cannot be 

found, and the job detail number stamped on 

the underside of the fuel access panel does 

match any of those specified in table 1 of the 

Accomplishment Instructions of Bombardier 

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

February 16, 2011: Before further flight, 

replace the fuel access panel with a new fuel 

access panel having P/N 85714232–003, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–57–23, Revision B, dated February 16, 

2011. 

(2) Do an external detailed inspection on 

fuel access panels having P/N 85714232–001 

for cracking, in accordance with the 

Accomplishment Instructions of Bombardier 

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

February 16, 2011. If no cracking is found: 

Repeat the inspection thereafter at intervals 

not to exceed 1,200 flight hours until the 

replacement specified in paragraph (h)(2)(i) 

of this AD, or the inspection specified in 

paragraph (h)(1) of this AD, is done. 

(i) If the fuel access panel is found cracked 

during any inspection required by this AD: 

Before further flight, replace the fuel access 

panel with a new fuel access panel having 

P/N 85714232–003, in accordance with the 

Accomplishment Instructions of Bombardier 

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

February 16, 2011. 

(ii) Within 12,000 flight hours after the 

initial inspection required by paragraph 

(h)(2) of this AD, do the actions specified in 

paragraph (h)(1) of this AD, unless the 

replacement required by paragraph (h)(2)(i) 

of this AD is done. 

(i) Parts Installation 

As of the effective date of this AD, no 

person may install a fuel access panel having 

P/N 85714231–001 and a job detail number 

listed in table 1 of the Accomplishment 

Instructions of Bombardier Service Bulletin 

84–57–22, Revision B, dated February 16, 


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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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