Daily Rules, Proposed Rules, and Notices of the Federal Government
For service information identified in this proposed AD, contact Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email
You may examine the AD docket on the Internet at
We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the
We will post all comments we receive, without change, to
The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2012-0009, dated January 13, 2012 (referred to after this as “the MCAI”), to correct an unsafe condition for the specified products. The MCAI states:
Two operators have reported that several spoilers did not remain locked in the retracted position (lifted up without order) after manual depressurization of the corresponding hydraulic circuit during flight test.
Subsequent checks on ground confirmed that, for each affected spoiler surface, the spoiler was fitted with one MZ-type Spoiler Servo Control (SSC) (Part Number (P/N) MZ4339390-12 or P/N MZ4306000-12).
The results of the investigations on the affected SSCs, done by the supplier, revealed that the loss of the hydraulic locking function—which is ensured by a blocking valve—was due to an internal leakage caused by a sheared seal. This seal is installed at the left end of the blocking valve.
During the on-wing modification of the maintenance cover, blocking valve movement may have damaged the seal on the outer diameter of the blocking valve assembly, causing the loss of the hydraulic locking function.
This condition, if not detected and corrected, if occurring during take-off and go-around phases in combination with one engine inoperative, could jeopardize the aeroplane safe flight.
For the reasons described above, this [EASA] AD requires the identification of the installed SSCs, to perform an operational test of the hydraulic locking function of the affected SSCs and to accomplish the applicable corrective actions if any discrepancy is detected during the operational test. This [EASA] AD also requires reporting operational test results to Airbus.
On August 26, 2009, the FAA issued AD 2009-18-20, Amendment 39-16017 (74 FR 46313, September 9, 2009), applicable to certain Airbus Model A330-300, A340-200, and A340-300 series airplanes. That AD requires identifying the part number of spoiler servo-controls installed on the airplane at all positions to determine the number of affected hydraulic circuits, and modifying affected spoiler servo-controls. The actions required by that AD are intended to prevent loss of the three hydraulic systems, which could result in reduced controllability of the airplane.
Airbus has issued All Operators Telex (AOT) A330-27A3185 and AOT A340-27A4181, both dated January 4, 2012. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI.
This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design.
Unlike the procedures recommended in Airbus AOTs A330-27A3185 and A340-27A4181, both dated January 4, 2012, this proposed AD would not permit further flight after a faulty SSC is detected on the green or yellow hydraulic line. Instead, this proposed AD would require replacing the SSC with a new or serviceable SSC before further flight. We find that, to achieve an adequate level of safety for the affected fleet, damaged SSCs must be replaced before further flight.
Although the MCAI mandates performing the operational test within 90 days after the effective date of the AD, we have determined that the operational test should be performed within 90 days after identification of the part.
These differences have been coordinated with EASA.
Based on the service information, we estimate that this proposed AD would affect about 61 products of U.S. registry. We also estimate that it would take up to 7 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $36,295, or $595 per product.
In addition, we estimate that any necessary follow-on actions would take about 36 work-hours and require parts costing $34,928, for a cost of $37,988 per affected SSC. We have no way of determining the number of products that may need these actions.
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.
We determined this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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.
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 proposed AD and placed it in the AD docket.
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
1. The authority citation for part 39 continues to read as follows:
49 U.S.C. 106(g), 40113, 44701.
2. The FAA amends § 39.13 by adding the following new AD:
We must receive comments by November 5, 2012.
This AD applies to all Airbus Model A330-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes; and Model A340-211, -212, -213, -311, -312, and -313 airplanes; certificated in any category; all manufacturer serial numbers.
Air Transport Association (ATA) of America Code 27: Flight controls.
This AD was prompted by reports that, during flight test, several spoiler servo-controls (SSCs) did not remain locked in the retracted position (hydraulic locking function) after manual depressurization of the corresponding hydraulic circuit. Loss of that locking function—which is ensured by a blocking valve—was caused by an internal leak from a sheared seal on the blocking valve. We are issuing this AD to prevent loss of the hydraulic locking function during take-off and go-around phases, which, in combination with malfunction of one engine, could result in reduced controllability of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Within 90 days after the effective date of this AD: Inspect to determine the part number (P/N) of all SSCs installed, in accordance with Airbus All Operators Telex (AOT) A330-27A3185 (for Model A330-300 series airplanes) or A340-27A4181 (for Model A340-200 and -300 series airplanes), both dated January 4, 2012. A review of airplane maintenance records is acceptable in lieu of the inspection to identify the part number of the SSC installed, provided that part number can be conclusively determined from that review.
(1) For any SSC having P/N MZ4339390-12 or P/N MZ4306000-12 (MZ-type): Within 90 days after identification of the part, perform an operational test of the hydraulic locking function at each position fitted with an MZ-type SSC, in accordance with the Accomplishment Instructions of Airbus AOT A330-27A3185 (for Model A330-300 series airplanes) or A340-27A4181 (for Model A340-200 and -300 series airplanes), both dated January 4, 2012.
(2) If any discrepancy is detected during the operational test specified in paragraph (g)(1) of this AD, or if the test fails, before further flight, replace the affected SSC with a new or serviceable SSC, in accordance with Airbus AOT A330-27A3185 (for Model A330-300 series airplanes) or A340-27A4181 (for Model A340-200 and -300 series airplanes), both dated January 4, 2012.
Submit a report of the findings of the operational test required by paragraph (g)(1) of this AD (both positive and negative) to Airbus, Customer Services, Engineering and Technical Support, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex France, Attn: Daniel Lopez-Fernandez, SEEL6; fax: (+33) 5 61 93 04 52; email:
(1) If the test was done on or after the effective date of this AD: Submit the report within 30 days after the test.
(2) If the test was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD.
The following provisions also apply to this AD:
(1) Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2012-0009, dated January 13, 2012, and the service information specified in paragraph (j)(1)(i) or (j)(1)(ii) of this AD, for related information.
(i) Airbus AOT A330-27A3185, dated January 4, 2012.
(ii) Airbus AOT A340-27A4181, dated January 4, 2012.
(2) For service information identified in this AD, contact Airbus SAS—Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email