### 15802 Federal Register / Vol. 76, No. 55 / Tuesday, March 22, 2011 / Rules and Regulations

**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 airworthiness directive (AD):
2011–06–12 The Boeing Company: Amendment 39–16637; Docket No. FAA–2010–1202; Directorate Identifier 2010–NM–167–AD.

Effective Date

(a) This AD is effective April 26, 2011.

Affected ADs

(b) None.
Applicability

(c) This AD applies to all The Boeing Company Model MD–90–30 airplanes, certificated in any category.
Subject

(d) Joint Aircraft System Component (JASC)/Air Transport Association (ATA) of America Code 55, Stabilizers.

Unsafe Condition

(e) This AD was prompted by a report of a crack found in the upper center skin panel at the aft inboard corner of a right horizontal stabilizer. We are issuing this AD to detect and correct cracks in the upper center skin panel of the horizontal stabilizer. Uncorrected cracks might ultimately lead to the loss of overall structural integrity of the horizontal stabilizer.
Compliance

(f) Comply with this AD within the compliance times specified, unless already done.
Inspections

(g) Before the accumulation of 20,000 total flight cycles, or within 3,778 flight cycles after the effective date of this AD, whichever occurs later, do eddy current inspections to detect cracking of the left and right upper center skin panels of the horizontal stabilizer, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD90–55A015, dated July 16, 2010.

(1) If no crack is found during any inspection required by paragraph (g) of this AD, repeat the applicable inspections thereafter at the applicable times specified in paragraph 1.E., ‘‘ Compliance, ’’ of Boeing Alert Service Bulletin MD90–55A015, dated July 16, 2010.

(2) If any crack is found during any inspection required by paragraph (g) of this AD, before further flight, replace the skin panel with a serviceable skin panel, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD90–55A015, dated July 16, 2010. Within 20,000 flight cycles after the replacement, do eddy current inspections as required by paragraph (g) of this AD. Alternative Methods of Compliance (AMOCs)

(h)(1) The Manager, Los Angeles 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.

(3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and 14 CFR 25.571, Amendment 45, and the approval must specifically refer to this AD.

Related Information

(i) For more information about this AD, contact Roger Durbin, Aerospace Engineer, Los Angeles ACO, Airframe Branch, ANM– 120L, FAA, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627– 5233; fax: 562–627–5210; e-mail: Roger.Durbin@faa.gov.
Material Incorporated by Reference

(j) You must use Boeing Alert Service Bulletin MD90–55A015, dated July 16, 2010, to do the actions required by this AD, unless the AD specifies otherwise.

(1) The Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin MD90–55A015, dated July 16, 2010, under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, California 90846– 0001; phone: 206–544–5000, extension 2; fax: 206–766–5683; e-mail: dse.boecom@boeing.com; Internet: https:// www.myboeingfleet.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 9,
2011. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011–6249 Filed 3–21–11; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–0212; Directorate Identifier 2010–SW–055–AD; Amendment**  **39–16632; AD 2011–06–07]**

**RIN 2120–AA64**

**Airworthiness Directives; Eurocopter France (Eurocopter) Model EC130 B4**  **Helicopters**

**AGENCY :**  Federal Aviation Administration, DOT.

**ACTION :**  Final rule; request for
comments.

**SUMMARY :**  This amendment adopts a new airworthiness directive (AD) for Eurocopter Model EC130 B4 helicopters. This action requires identifying and inspecting a certain emergency flotation gear unit ‘‘ 1G’’ (1G unit). This action also requires modification of certain affected 1G units. This amendment is prompted by an uncommanded in-flight deployment of the emergency flotation gear when it was not armed by the crew. The actions specified in this AD are intended to prevent an uncommanded in-flight deployment of the emergency flotation gear, unexpected deceleration and pitch down movement of the helicopter, and subsequent loss of control of the helicopter.

**DATES :**  Effective April 6, 2011.

The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of April 6,
2011.

Comments for inclusion in the Rules Docket must be received on or before May 23, 2011.

**ADDRESSES :**  Use one of the following addresses to submit comments on this AD:

• Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.

• Fax: 202–493–2251.

• Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590.

• Hand Delivery: U.S. Department of Transportation, Docket Operations, M–


### 15803 Federal Register / Vol. 76, No. 55 / Tuesday, March 22, 2011 / Rules and Regulations

30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

You may get the service information identified in this AD from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, TX 75053–4005, telephone (800) 232–0323, fax (972) 641–3710, or at http:// www.eurocopter.com. Examining the Docket

You may examine the docket that contains the AD, any comments, and other information 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 Docket Operations office (telephone (800) 647–5527) is located in Room W12–140 on the ground floor of the West Building at the street address stated in the **ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  George Schwab, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Safety Management Group, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222–5114, fax (817) 222–5961.

**SUPPLEMENTARY INFORMATION :** 

Discussion

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA AD No. 2010–0088–E, dated May 6, 2010, to correct an unsafe condition for the Model EC130 B4 helicopters. EASA advises that an uncontrolled in-flight deployment of the emergency flotation gear (not armed) on an EC130 B4 helicopter has been reported. The flight crew heard a detonation followed by heavy vibrations and noticed the emergency flotation gear floats were inflating. Investigations on the emergency flotation gear control system revealed that a wire was damaged inside the 1G unit. This wire was damaged, due to interference with the screw securing cable 1GR19E lug to the bus bar, causing a short circuit in the emergency flotation gear deployment activation circuit and the consequent deployment of the emergency flotation gear. EASA further states the possibility of interference of the 1G unit’s internal wire harnesses with a fuselage metal structure member (stringer) has been identified, which could have the same
consequences. Related Service Information Eurocopter has issued Emergency Alert Service Bulletin No. 25A037, dated April 27, 2010, for the Model EC130 B4 helicopters, which specifies inspecting 1G units without an ‘‘ * ’’ displayed on the 1G unit panel after the part number (P/N) and taking various corrective actions at various times pending installation of a conforming 1G unit. EASA classified this EASB as mandatory and issued AD No. 2010– 0088–E, dated May 6, 2010, to ensure the continued airworthiness of these helicopters.

FAA’s Evaluation and Unsafe Condition Determination

This helicopter has been approved by the aviation authority of France and is approved for operation in the United States. Pursuant to our bilateral agreement with France, EASA, their technical representative, has notified us of the unsafe condition described in the MCAI AD. We are issuing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other helicopters of this same type design.

Differences Between This AD and the EASA AD

This AD does not require the actions to be completed at the compliance times of 3 months and 8 months, nor does it require the repetitive actions specified in the EASA AD. This AD requires theactions to be done within 15 hours timein-service (TIS). Also, this AD refers to flight hours as hours TIS. FAA’s Determination and Requirements of This AD

This unsafe condition is likely to exist or develop on other helicopters of the same type design. Therefore, this AD is being issued to prevent an uncommanded in-flight deployment of the emergency flotation gear, unexpected deceleration and pitch down movement of the helicopter, and subsequent loss of control of the helicopter.

This AD requires determining if the 1G unit has an asterisk after the P/N displayed on the 1G unit panel. If an asterisk follows the P/N, the AD requires inspecting for a rubber extrusion installed on the stringer. If no rubber extrusion is installed on the stringer, the AD requires removing the 1G unit, bonding a rubber extrusion on the stringer, reinstalling the 1G unit, and functionally testing the emergency flotation gear control system. If no asterisk follows the P/N, the AD requires removing the 1G unit and inspecting the 1G unit for interference between the harness wires and the stringer and between internal parts. Also, the AD requires if no rubber extrusion is installed on the stringer, protecting the stringer by bonding a rubber extrusion on the stringer. The AD also requires inspecting for interference between the attachment screw and the wires of the nearby harness and for damage to the wires of the harness. The AD also requires modifying the 1G unit as necessary to protect the 1G unit from interference. Also, the AD requires identifying the modified 1G unit by marking an asterisk after the P/N. The AD also requires reinstalling and functionally testing the 1G unit. Installing a conforming 1G unit is terminating action for the requirements of this AD. Do the actions by following specified portions of the service bulletin described previously.

The short compliance time involved is required because the previously described critical unsafe condition can adversely affect the controllability of the helicopter. This AD requires, within 15 hours TIS, determining whether a conforming 1G unit is installed, and if not, modifying the 1G unit within 15 hours TIS. Fifteen hours TIS is a very short compliance time; therefore, this AD must be issued immediately.

Since a situation exists that requires the immediate adoption of this regulation, it is found that notice and opportunity for prior public comment hereon are impracticable, and that good cause exists for making this amendment effective in less than 30 days. Costs of Compliance

We estimate that this AD will affect about 119 helicopters of U.S. registry. Determining whether an asterisk is present on the 1G unit panel will require a minimal amount of time. Weestimate that it will take about 8 workhours per helicopter to remove, modify, and replace a 1G unit. The average labor rate is $85 per work-hour. Required parts will cost about $25 per helicopter. Based on these figures, we estimate the cost of this AD on U.S. operators is $8,460, assuming 12 helicopters will require modification of the 1G unit per this AD.

Comments Invited

This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the **ADDRESSES** . Include

‘‘ Docket No. FAA–2011–0212;


### 15804 Federal Register / Vol. 76, No. 55 / Tuesday, March 22, 2011 / Rules and Regulations

Directorate Identifier 2010–SW–055– AD ’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those
comments.

We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this AD. Using the search function of the docket Web site, you can find and read the comments to any of our dockets, including the name of the individual who sent the comment. You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78). Regulatory Findings

We have 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 the 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); and

3. 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 an economic evaluation of the estimated costs to comply with this AD. See the AD docket to examine the economic evaluation. 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. 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. Section 39.13 is amended by adding a new airworthiness directive to read as follows:
2011–06–07 Eurocopter France: Amendment 39–16632; Docket No. FAA–2011–0212; Directorate Identifier 2010–SW–055–AD. Applicability: Model EC130 B4 helicopters with a flotation gear unit ‘‘ 1G’’ (1G unit), part number (P/N) 350A63256300, installed, certificated in any category.

Compliance: Within 15 hours time-inservice, unless accomplished previously.

To prevent an uncommanded in-flight deployment of the emergency flotation gear, unexpected deceleration and pitch down movement of the helicopter, and subsequent loss of control of the helicopter, do the following:

(a) Determine whether the 1G unit has an asterisk (*) after the P/N displayed on the 1G unit panel as shown in Figure 4 of Eurocopter Emergency Alert Service Bulletin No. 25A037, dated April 27, 2010 (EASB).

(b) If there is an asterisk after the P/N displayed on the 1G unit panel, determine if there is a rubber extrusion installed on the stringer as shown in Figure 6 of the EASB.

(1) If no rubber extrusion is installed on the stringer, remove the 1G unit by following the Accomplishment Instructions, paragraph 2.B.2.a. of the EASB.

(2) Bond a rubber extrusion onto the stringer using Bostik 1400 or an equivalent adhesive. Bostik 1400 is ready for use; if using an equivalent adhesive, follow the manufacturer’s directions for preparation and application.

(i) Thoroughly clean the bonding surfaces of the stringer; remove all traces of grease.

(ii) Apply a uniform adhesive film on the bonding surfaces.

(A) For Bostik 1400, allow to dry until tack free (about 15 minutes).

(B) For equivalent adhesive, follow the manufacturer’s procedures. (iii) After adhesive application, assemble the bonding faces and press firmly to eliminate air bubbles. Maintain the pressure throughout the hardening period as described for the adhesive being used. For Bostik 1400, the adhesive hardens in about 48 hours at room temperature.

(3) Reinstall the 1G unit by following the Accomplishment Instructions, paragraph 2.B.2.b., of the EASB. Functionally test the emergency flotation gear control system.

(c) If there is no asterisk displayed after the P/N on the 1G unit panel, remove the 1G unit by following the Accomplishment Instructions, paragraph 2.B.2.a., of the EASB.

(1) Inspect the 1G unit for interference: (i) If you find interference between the harness wires and the stringer, install a sheath, P/N EN6049–006–08–5, on all the harnesses in the area of the interference, and secure the sheath with cable ties as depicted in Figure 5 of the EASB.

(ii) If you find interference between the harness wires and the inside surface of the 1G unit or with any of the 1G unit’s internal components, remove the installed cable ties, P/N E0043–1A0P, and spacer(s), P/N E0688– 01, as required, to allow repositioning or routing of the harness to eliminate interference. Secure repositioned harnesses using new cable ties, P/N E0043–1A0P, and new spacers, P/N E0688–01.

(iii) If you find interference between the harness and the helicopter structural stringer, install a sheath, P/N EN6049–006–08–5, on all the harnesses located at the stringer as depicted in Figures 5 and 6 of the EASB. Secure the sheath with cable ties, P/N E0043–1A0P, so that no interference between the sheathed harness and the structural stringer exists.

(iv) Bond a black rubber extrusion, P/N BT4, on the stringer as shown in Figure 6 by following the requirements of paragraph (b)(2) of this AD.

(2) Inspect the attachment screw of cable 1GR19E for orientation and arrangement that matches the Post EASB detail, as shown in insert D of Figure 5 of the EASB, and determine if it is covered with heat shrink, P/N VG95343T05E004A, or equivalent. If orientation and arrangement of the attachment screw cable 1GR19E are not as shown in insert D of Figure 5 or the attachment screw is not covered with heat shrink, modify the attachment screw by following the Accomplishment Instructions, paragraph 2.B.5.b., of the EASB.

Note 1. Figure 5 of the EASB does not show the heat shrink installed for clarity of screw head and lug detail.

(3) Inspect for damage to a wire of the harness inside the 1G unit as depicted in Figure 7 of the EASB. Replace any damaged wire using the correct wire and contact information listed in the Appendix, paragraph 4, of the EASB.

(4) Mark an asterisk ‘‘ * ’’ after P/N 350A63256300 on the 1G unit panel using indelible ink to indicate compliance with this AD.

(5) Reinstall the 1G unit by following the Accomplishment Instructions, paragraph 2.B.2.b., of the EASB, and functionally test the emergency flotation gear control system.

(d) Installing an airworthy 1G unit that has been modified and identified as required by


### 15805 Federal Register / Vol. 76, No. 55 / Tuesday, March 22, 2011 / Rules and Regulations

this AD is terminating action for the requirements of this AD.

(e) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Safety Management Group, FAA, Attn: George Schwab, Aviation Safety Engineer, Rotorcraft Directorate, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222– 5114, fax (817) 222–5961, for information about previously approved alternative methods of compliance.

(f) The Joint Aircraft System/Component (JASC) Code is 2497: Electrical Power System Wiring.

(g) Remove and install the 1G unit, determine the correct wire and contact information, and do the inspections by following the specified portions of Eurocopter Emergency Alert Service Bulletin No. 25A037, dated April 27, 2010. The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, TX 75053–4005, telephone (800) 232–0323, fax (972) 641–3710, or at http://www.eurocopter.com. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas, or 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/code

_ of

_ federal

_regulations/ibr

_locations.html. (h) This amendment becomes effective on April 6, 2011.

Note 2: The subject of this AD is addressed in European Aviation Safety Agency No. 2010–0088–E, dated May 6, 2010.

Issued in Fort Worth, Texas, March 7,
2011. Lance T. Gant, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2011–6212 Filed 3–21–11; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–1162; Directorate Identifier 2010–NM–099–AD; Amendment**  **39–16634; AD 2011–06–09]**

**RIN 2120–AA64**

**Airworthiness Directives; Airbus Model A310 Series Airplanes, and Airbus**  **Model A300 B4–600, B4–600R, and F4– 600R Series Airplanes, and Model C4–**  **605R Variant F Airplanes (Collectively Called A300–600 Series Airplanes)** 

**AGENCY :**  Federal Aviation Administration (FAA), Department of Transportation (DOT). **ACTION :**  Final rule.

**SUMMARY :**  We are superseding an existing airworthiness directive (AD) that applies to the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:

Prompted by a reported in-service event, EASA issued AD 2009–0084 to prevent unwanted movement of pilot- or co-pilot seat in the horizontal direction which is considered as potentially unsafe, especially during the takeoff phase when the speed of the aeroplane is greater than 100 knots and until landing gear retraction.

* * * * * Uncommanded movement of the pilot and co-pilot seats during takeoff or landing could interfere with the operation of the airplane and, as a result, could cause loss of control of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.

**DATES :**  This AD becomes effective April 26, 2011.

The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of April 26, 2011.

The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of June 12, 2009 (74 FR 25399, May 28, 2009).

**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; phone: 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 December 1, 2010 (75 FR 74665), and proposed to supersede AD 2009–11–09, Amendment 39–15919 (74 FR 25399, May 28, 2009). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI
states:

Prompted by a reported in-service event, EASA issued AD 2009–0084 [which corresponds to FAA AD 2009–11–09] toprevent unwanted movement of pilot- or copilot seat in the horizontal direction which is considered as potentially unsafe, especially during the takeoff phase when the speed of the aeroplane is greater than 100 knots and until landing gear retraction.

AD 2009–0084 required the deactivation of the electrical power of SOGERMA pilot seats P/N 2510112 series and co-pilot seats P/N 2510113 series. Optional intermediate actions were also provided by AD 2009–0084 to allow partial or full restoration of seat adjustment functionality.

Since AD 2009–0084 was issued, a permanent solution has been developed that terminates the de-activation requirement and invalidates the intermediate actions.

Consequently, this AD retains requirements of EASA AD 2009–0084, which is superseded, and requires implementing the terminating action. In addition, this AD prohibits the (re)installation of unmodified pilot- and co-pilot seats on any aeroplane that has been modified in accordance with the requirements of this AD. Uncommanded movement of the pilot and co-pilot seats during takeoff or landing could interfere with the operation of the airplane and, as a result, could cause loss of control of the airplane. You may obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

Since issuance of the NPRM, Airbus has issued Mandatory Service Bulletin A310–25–2205, Revision 01, dated November 19, 2010. This revision does not require any additional work. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. We have updated this final rule to refer to Airbus Mandatory Service Bulletin A310–25–2205, Revision 01, dated November 19, 2010. We added a new paragraph (n) of this AD to provide credit for doing actions before the effective date of this AD in accordance with Airbus Mandatory Service Bulletin A310–25–2205, dated August 31, 2009, for Airbus Model A310 series airplanes.

Comments

We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM 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 with the changes described previously.