## 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://


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

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,


## 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 cracksunderneath 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 permanentrepair 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