## 24833 Federal Register / Vol. 77, No. 81 / Thursday, April 26, 2012 / Rules and Regulations

time specified in Goodrich Principal Instructions for Continued Airworthiness Manual for the Analog Transient Suppression Device Installation Applicable to Boeing 737–100 through -500 Airplanes Supplemental Type Certificate—ST00146BO, Document T3044–0010–0101, Revision D, dated September 26, 2011, or within 18 months after the effective date of this AD, whichever occurs later.

Note 1 to paragraph (g) of this AD: Components that have been identified as airworthy or installed on the affected airplanes before the revision of the maintenance program, as required by paragraph (g) of this AD, do not need to be reworked in accordance with the CDCCLs. However, once the maintenance program has been revised, paragraph (g) of this AD requires that future maintenance actions on these components must follow the CDCCLs.

(h) No Alternative Actions Intervals, and/or Critical Design Configuration Control Limitations

After accomplishing the revision required by paragraph (g) of this AD, no alternative actions (e.g., inspections), intervals, and/or CDCCLs may be used other than those specified in Goodrich Principal Instructions for Continued Airworthiness Manual for the Analog Transient Suppression Device Installation Applicable to Boeing 737–100 through -500 Airplanes Supplemental Type Certificate—ST00146BO, Document

T3044–0010–0101, Revision D, dated September 26, 2011, unless the actions, intervals, and/or CDCCLs are approved as an AMOC in accordance with the procedures specified in paragraph (i) of this AD.
(i) Alternative Methods of Compliance

(1) The Manager, Boston Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD.

(2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office.
(j) Related Information

For more information about this AD, contact Marc Ronell, Aerospace Engineer, Engine and Propeller Directorate, ANE–150, FAA, New England Aircraft Certification Office, 12 New England Executive Park, Burlington, Massachusetts 01803; phone: 781–238–7776; fax: 781–238–7170; email: marc.ronell@faa.gov

. (k) 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) Goodrich Principal Instructions for Continued Airworthiness Manual for the Analog Transient Suppression Device Installation Applicable to Boeing 737–100 through -500 Airplanes Supplemental Type Certificate—ST00146BO, Document T3044– 0010–0101, Revision D, dated September 26,

2011.

(2) For service information identified in this AD, Goodrich Corporation, Sensors and Integrated Systems, 100 Panton Road, Vergennes, Vermont 05491; phone: 802–877– 4580; fax: 802–877–4444; email: les.blades@goodrich.com; Internet: http:// www.goodrich.com/TechPubs.

(3) You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221.

(4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go

to: http://www.archives.gov/federal-register/ cfr/ibr-locations.html.

Issued in Renton, Washington, on April 13,

2012. John P. Piccola, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2012–9713 Filed 4–25–12; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–0033; Directorate Identifier 2011–NM–086–AD; Amendment**  **39–17029; AD 2012–08–12]**

**RIN 2120–AA64**



### Airworthiness Directives; Airbus **Airplanes**

**AGENCY** 

### : Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are adopting a new airworthiness directive (AD) for all Airbus Model A310 series airplanes. This AD was prompted by a report of an electrical arc and hydraulic haze in the wheel bay of the left-hand main landing gear (MLG) possibly resulting from chafing between the hydraulic high pressure hose and electrical wiring of the green electrical motor pump (EMP). This AD requires temporarily prohibiting in-flight use of the green EMPs; temporarily revising the airplane flight manual (AFM) limitations section; temporarily installing a placard in the cockpit overhead panel; doing a onetime general visual inspection for correct condition and installation of hydraulic pressure hoses, electrical conduits, feeder cables, and associated clamping devices; and corrective action if necessary. We are issuing this AD to detect and correct chafing of hydraulic pressure hoses and electrical wiring of the green EMPs, which in combination with a system failure, could cause an uncontrolled and undetected fire in the MLG bay.

**DATES** 

### : This AD becomes effective May 31, 2012.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of May 31, 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** 

### : Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–2125; 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 January 20, 2012 (77 FR 2928). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states:

An operator reported an electrical arc and a large hydraulic haze in the left hand Main Landing Gear (LH MLG) wheel bay that occurred during ground operation. The analysis revealed that this occurrence is likely the result of chafing between hydraulic high pressure hose and electrical wiring of the Green Electrical Motor Pump (EMP).

This condition, if not detected and corrected, and in combination with a system failure leading to the use of the Green EMPs in flight, could lead to an uncontrolled and undetected fire in the MLG bay.

For the reasons explained above, this AD temporarily prohibits the in-flight use of green EMPs, by mandating an update of the Aeroplane Flight Manual (AFM) limitations section and installation of a placard in the cockpit overhead panel. This [EASA] AD requires also a one-time [general] visual inspection of hydraulic pressure hoses and electrical wiring of Green EMPs and corrective action(s), depending on findings.


## 24834 Federal Register / Vol. 77, No. 81 / Thursday, April 26, 2012 / Rules and Regulations

Corrective actions include repairing or replacing the hydraulic pressure hoses and electrical wiring. 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 have considered the comment received.
Request To Add Word to Summary Paragraph

Airbus requested the word ‘‘temporarily’’ be added before the phrases in the Summary section of the NPRM (77 FR 2928, January 20, 2012): ‘‘prohibiting in-flight use of the green EMPs,’’ ‘‘revising the airplane flight manual (AFM) limitations section,’’ and ‘‘installing a placard in the cockpit overhead panel.’’ Airbus explained that after the one-time visual inspection of the hydraulic pressure hoses and electrical wiring of the green EMPs and accomplishing the corrective actions, if needed, these limitations must be removed.

We concur. We have added the word ‘‘temporarily’’ before those phrases in the Summary section of this AD.

Conclusion

We reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD as proposed except for minor editorial changes. We have determined that these minor changes:

• Are consistent with the intent that was proposed in the NPRM (77 FR 2928, January 20, 2012) for correcting the unsafe condition; and

• Do not add any additional burden upon the public than was already proposed in the NPRM (77 FR 2928, January 20, 2012).
Costs of Compliance

We estimate that this AD will affect 58 products of U.S. registry. We alsoestimate that it will take about 2 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 $200 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 $21,460, or $370 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:// 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 2928, January 20, 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:

2012–08–12 Airbus: Amendment 39–17029. Docket No. FAA–2012–0033; Directorate Identifier 2011–NM–086–AD.

(a) Effective Date

This airworthiness directive (AD) becomes effective May 31, 2012.

(b) Affected ADs

None.
(c) Applicability

This AD applies to Airbus Model A310– 203, –204, –221, –222, –304, –322, –324, and –325 airplanes, certificated in any category, all serial numbers.
(d) Subject

Air Transport Association (ATA) of America Code 29: Hydraulic Power.

(e) Reason

This AD was prompted by a report of an electrical arc and hydraulic haze in the wheel bay of the left-hand main landing gear (MLG) possibly resulting from chafing between the hydraulic high pressure hose and electrical wiring of the green electrical motor pump (EMP). We are issuing this AD to detect and correct chafing of hydraulic pressure hoses and electrical wiring of the green EMP, which in combination with a system failure, could cause an uncontrolled and undetected fire in the MLG bay.
(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) Installing Placard and Revising Airplane Flight Manual (AFM)

For all airplanes, as of the effective date of this AD, the in-flight use of green EMPs is prohibited. Before the next flight, do the actions specified in paragraphs (g)(1) and (g)(2) of this AD.

(1) Install in the cockpit on the hydraulic power overhead panel 427VU, a locally manufactured self-adhesive placard temporarily prohibiting the in-flight use of the green EMPs, in accordance with the


## 24835 Federal Register / Vol. 77, No. 81 / Thursday, April 26, 2012 / Rules and Regulations

instructions in Airbus All Operators Telex A310–29A2101, Revision 01, dated April 12, 2011 (for airplanes equipped with EATON (formerly VICKERS) hydraulic EMPs); or Airbus All Operators Telex A310–29A2102, dated April 12, 2011 (for airplanes equipped with PARKER (formerly ABEX) hydraulic EMPs).

(2) Revise the Limitations section of the applicable AFM to prohibit the in-flight use of the green EMPs. This may be accomplished by inserting a copy of this AD into the Limitations section of the AFM.
(h) Inspecting for Damage and Chafing

Within 500 flight hours or 4 months after the effective date of this AD, whichever occurs first, do a one-time general visual inspection for correct condition (i.e., no damage and no chafing) and correct installation of the hydraulic pressure hoses, electrical conduits, feeder cables, and associated clamping devices at frame 54, as well as the electrical conduits and feeder cables underneath the clamps (including removal of the concerned clamps), in accordance with the instructions in Airbus All Operators Telex A310–29A2101, Revision 01, dated April 12, 2011 (for airplanes equipped with EATON (formerly VICKERS) hydraulic EMPs); or Airbus All Operators Telex A310–29A2102, dated April 12, 2011 (for airplanes equipped with PARKER (formerly ABEX) hydraulic EMPs). If any incorrect installation is found, before further flight, install the affected parts correctly, in accordance with Airbus All Operators Telex A310–29A2101, Revision 01, dated April 12, 2011 (for airplanes equipped with EATON (formerly VICKERS) hydraulic EMPs); or Airbus All Operators Telex A310–29A2102, dated April 12, 2011 (for airplanes equipped with PARKER (formerly ABEX) hydraulic EMPs).

(1) If any damage or chafing marks are found during the inspection required by paragraph (h) of this AD, before further flight, replace or repair the affected parts (hydraulic pressure hoses, electrical conduits, feeder cables, clamps, and spacer, if installed), in accordance with the instructions in Airbus All Operators Telex A310–29A2101, Revision 01, dated April 12, 2011 (for airplanes equipped with EATON (formerly VICKERS) hydraulic EMPs); or Airbus All Operators Telex A310–29A2102, dated April 12, 2011 (for airplanes equipped with PARKER (formerly ABEX) hydraulic EMPs).

(2) Before further flight after compliance with the requirements of paragraph (h) of this AD, as applicable, remove the placard required by paragraph (g)(1) of this AD; and remove the revision of the Limitations section of the AFM, as required by paragraph (g)(2) of this AD; from the airplane and the AFM, respectively.

(i) 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: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; telephone (425) 227–2125; 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.
(j) Related Information

Refer to MCAI EASA Airworthiness Directive 2011–0071, dated April 18, 2011; Airbus All Operators Telex A310–29A2101, Revision 01, dated April 12, 2011; and Airbus All Operators Telex A310–29A2102, dated April 12, 2011; for related information.
(k) 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) Airbus All Operators Telex A310– 29A2101, Revision 01, dated April 12, 2011. The document number, revision level, and issue date of this document is specified only on the first page of the document.

(ii) Airbus All Operators Telex A310– 29A2102, dated April 12, 2011. The document number, revision level, and issue date of this document is specified only on the first page of the document.

(2) For service information identified in this AD, contact Airbus SAS—EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email: account.airwortheas@airbus.com; Internet http:// www.airbus.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 April 12,

2012. John P. Piccola, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2012–9475 Filed 4–25–12; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0277; Directorate Identifier 2009–NM–217–AD; Amendment**  **39–17031; AD 2012–08–14]**

**RIN 2120–AA64**



### Airworthiness Directives; The Boeing **Company Airplanes**

**AGENCY** 

### : Federal Aviation Administration (FAA), DOT.

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767 airplanes. This AD was prompted by reports of cracking in the upper wing skin at the fastener holes common to the pitch load fittings of the inboard and outboard front spar, which could result in the loss of the strut-to-wing upper link load path and possible separation of a strut and engine from the airplane during flight. This AD requires repetitive inspections to detect fatigue cracking in the wing skin, and corrective actions if necessary. We are issuing this AD to correct the unsafe condition on these products.

**DATES** 

### : This AD is effective May 31,

2012.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of May 31, 2012.

**ADDRESSES** 

### : For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124– 2207; telephone 206–544–5000, extension 1; fax 206–766–5680; email me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may review copies of the referenced 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. Examining the AD Docket

You may examine the AD docket on the Internet at http://