1 [Federal Register: December 14, 2005 (Volume 70, Number 239)] [Rules and Regulations] [Page 73919-73921] From the Federal Register Onlin e via GPO Access [wais.access.gpo.gov] [DOCID:fr14de05-2]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-23252; Directorate Iden tifier 2004-NM-146-AD; Amendment 39-14414; AD 2005-25-21]

RIN 2120-AA64

Airworthiness Directives; Ai rbus Model A330-243, -341, -342, and -343 Airplanes Equipped with Rolls-Royce RB211 TRENT 700 Engines

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

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A330-243, -341, -342, and -343 airplanes equipped with Rolls-Royce RB211 TRENT 700 engines. This AD requires modifying the cowl assemblies of th e left- and right-hand thrust reversers. This AD

results from a review of certificati on tests of the thrust reverser, whic h revealed that certain structural components within the C-duct need strengthening to meet high fatigue loads and maintain structural integrity. We are issuing this AD to prevent fati gue cracking of the hinges integrated into the 12 o'clock beam of the thrust reversers, which could re sult in separation of a thrust reverser from the airplane, and consequent reduced controllability of the airplane.

DATES: This AD becomes effective December 29, 2005.

The Director of the Federal Register approved the incorpora tion by reference of a certain publication listed in the AD as of December 29, 2005. We must receive comments on this AD by February 13, 2006.

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

• DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically.

• Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically.

• Mail: Docket Management Facility; U.S. De partment of Transporta tion, 400 Seventh Street, SW., Nassif Building, room PL-401, Washington, DC 20590.

• Fax: (202) 493-2251. • Hand Delivery: Room PL-401 on the plaza leve l of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.2 Contact Airbus, 1 Rond Point Maurice Bellont e, 31707 Blagnac Cedex, France, for the service

information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-2797; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

The Direction Générale de l'Aviation Civile (D GAC), which is the airworthiness authority for France, notified us that an unsafe condition may exist on certain Airbus Model A330-243, -341, -342, and -343 airplanes equipped with Rolls-Royce RB211 TRENT 700 engines. The DGAC advises that

a review of certification tests of th e thrust reverser revealed that cer tain structural components within the C-duct need strengthening to meet high fatig ue loads and maintain structural integrity. Unexpected high loads were measured on the hinges in tegrated into the 12 o'clock beam of the thrust reverser; the 12 o'clock beam forms the upper edge of the C-duct of the thrust reverser on RollsRoyce engines. This condition, if not corrected, could result in fatigue cracking of the hinges integrated into the 12 o'clock beam of the thrust reversers, separati on of a thrust reverser from the airplane, and consequent reduced controllability of the airplane.

Relevant Service Information

Airbus has issued Service Bulletin A 330-78-3010, Revision 03, dated April 28, 2004. The service bulletin describes procedur es for modifying the cowl assemb lies of the left- and right-hand thrust reversers. Accomplishing th e actions specified in the service information is intended to adequately address the unsafe condition. The DGAC mandated the service information and issued

French airworthiness directiv e F-2001-528 R2, dated June 23, 2004, to ensure the continued airworthiness of these airplanes in France. The service bulletin refers to Rolls-Royce Service Bulletin RB.211-78-C899, Revision 3, dated May 7, 2004, as an additional source of service info rmation for modifying the cowl assemblies of the left- and right-hand thrust revers ers. The modification includes re lated investigative actions, and repair if necessary. The related i nvestigative actions include certain inspections for discrepancies of the bores, bushings, plug holes, and cav ity webs of the thrust reversers.

FAA's Determination and Requirements of This AD

These airplane models are manufactured in Fran ce and are type certificated for operation in the United States under the provisions of section 21. 29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral ai rworthiness agreement. Pursuant to this bilateral airworthiness agreement, the DGAC has kept the FAA informed of the situation described above. We have examined the DGAC's findings, evaluated all pertinen t information, and determined that we need to issue an AD for products of this type design that are certificated for operation in the United States. Therefore, we are issuing this AD to prevent fati gue cracking of the hinges integrated into the 12 o'clock beam of the thrust reversers, which could re sult in separation of a thrust reverser from the airplane, and consequent reduced controllability of the airplane. This AD requires accomplishing the actions specified in the Airbus service information described prev iously except as discussed under ''Difference Among the AD, French Airworthiness Directive, and Airbus Service Information.''3 Difference Among the AD, French Airworthine ss Directive, and Airbus Service Information

The French airworthiness dire ctive and the service information specify a modification that involves replacement of certain thru st reverser C-ducts with new ducts at or before specific total flight cycle thresholds. This AD requires you to repl ace the affected parts befo re the accumulation of

those thresholds or within 6 months after the effective date of the AD, whichever is later. A table containing those flight cycle threshol ds is specified in paragraph (f) of this AD. We have included a 6-month grace period to ensure that a ny airplane that is close to or ha s passed its applicable threshold (if imported and placed on the U.S. Register) is not grounded as of the effective date of the AD.

Costs of Compliance

None of the airplanes affected by this action ar e on the U.S. Register. All airplanes affected by this AD are currently operated by non-U.S. operators under foreign re gistry; therefore, they are not directly affected by this AD action. However, we consider this AD necessary to ensure that the unsafe condition is addressed if any affected airplane is imported a nd placed on the U.S. Register in

the future. If an affected airplane is imported and placed on the U.S. Register in the future, the required

modification would take about 1 wo rk hour per airplane, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the modification would be $65 per airplane.

FAA's Determination of the Effective Date

No airplane affected by this AD is currently on the U.S. Register. Therefore, providing notice and opportunity for public comment is unnecessary be fore this AD is issued, and this AD may be made effective in less than 30 days afte r it is published in the Federal Register.

Comments Invited

This AD is a final rule that involves requirement s that affect flight sa fety and was not preceded by notice and an opportunity for public comment; how ever, we invite you to submit any relevant written data, views, or arguments regarding this AD. Send your comments to an address listed in the

ADDRESSES section. Include ''Docket No. FAA-2005-23252; Directorate Identifier 2004-NM-146- AD'' at the beginning of your comments. We speci fically invite comments on the overall regulatory, economic, environmental, and energy aspects of th e AD that might suggest a need to modify it. We will post all comments we receive, without change, to http://dms.dot.gov , including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this AD. Usi ng the search function of that Web site, anyone can find and read the comments in any of our dockets , including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT's complete Privacy Act Statem ent in the Federal Register published on April 11, 2000 (65 FR 19477-78), or you may visit http://dms.dot.gov

.

Examining the Docket

You may examine the AD docket on the Internet at http://dms.dot.gov , or in person at the Docket Management Facility office between 9 a.m. a nd 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility offi ce (telephone (800) 647-5227) is located on the plaza level of the Nassif Building at the DOT street ad dress stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them.4 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 und er the authority described in Sub title VII, Part A, Subpart III, Section 44701, ''General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in ai r 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 be cause it addresses an unsafe condition that is likely to exist or develop on products iden tified in this rulemaking action.

Regulatory Findings

We have determined that this AD will not ha ve federalism implications under Executive Order

13132. This AD will not have a substantial direct eff ect on the States, on the relationship between the national government and the States, or on the dist ribution 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 regulator y action'' under Executive Order 12866; 2. Is not a ''significant rule'' under the DOT Re gulatory 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 a regulatory evaluation of the estim ated costs to comply with this AD and placed it

in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safe ty, 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 Federal Aviation Admini stration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD):5 

## AIRWORTHINESS DIRECTIVE

Aircraft Certification Service Washington, DC U.S. Department of Transportation Federal Aviation
Administration We post ADs on the internet at www.faa.gov/aircraf t/safety/alerts/

The following Airworthiness Directive issued by the Federal Aviation Administration in accordance with the provisions of Title 14 of the Code of Federal Regulations (14 CFR) part 39, applies to an aircraft model of which our records indicate you may be the registered owner. Airworthiness Directives affect avi ation safety and are regulations which require immediate attention. You are cautioned that no person may operate an aircraft to which an Airworthiness Directive applies, except in acco rdance with the requirements of the Airworthiness Directive (reference 14 CFR part 39, subpart 39.3).

2005-25-21 Airbus: Amendment 39-14414. Docket No. F AA-2005-23252; Directorate Identifier

2004-NM-146-AD.

Effective Date

(a) This AD becomes effective December 29, 2005.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Airbus Model A330-243, -341, -342, and -343 airplane s, certificated in any category; equipped with Ro lls-Royce RB211 TRENT 700 engines.

Unsafe Condition

(d) This AD results from a review of certification tests of the thrust revers er, which revealed that certain structural components within the C-duct need strengthening to meet high fatigue loads and maintain structural integrity. The FAA is issuing this AD to prevent fatigue cracking of the hinges integrated into the 12 o'clock beam of the thrust reversers, which coul d result in separation of a thrust reverser from the airplane, and consequent reduced controllability of the airplane.

Compliance

(e) You are responsible for having the actio ns required by this AD performed within the compliance times specified, unless th e actions have already been done.

Modification

(f) At the applicable compliance time specified in Table 1 of this AD: Modify the cowl assemblies of the left- and right-hand thrust reve rsers in accordance with Airbus Service Bulletin A330-78-3010, Revision 03, dated April 28, 2004.6 TABLE 1.—MODIFICATION (PART REPLACEMENT) THRESHOLDS
Replace part

number— At the later of the times specified—

(1) 3410L, 3410R, 3411L, 3411R, 3412R, 3413R. (i) Before the accumulation of 10,000 total flight cycles

since the C-duct was new. (ii) Within 6 months

after the effective

date of this AD. (i) For airplanes modified according to Airbus Service Bulletin A330–78–3010 with more than 7,200 total flight cycles since the C-duct was new: Before the accumulation of 10,000 total flight cycles since the C-duct was new. (2) 3414L, 3416R,

3417R

(ii) For airplanes modified according to Airbus Service Bulletin A330–78–3010 with less than or equal to 7,200 total flight cycles since the C-duct was new: Before theaccumulation of 25,000 total flight cycles since the Cduct was new. (iii) Within 6

months after the

effective date of this

AD.

(3) 3414L, 3416R,

3417R (i) For airplanes modified in production by Airbus Modification 47316: Before the accumulation of 25,000 total flight cycles since the C-duct was new. (ii) Within 6 months

after the effective

date of this AD. (4) 3412L, 3414R (i) Fo r airplanes modified in production by Airbus Modification 46879: Before the accumulation of 25,000 total flight cycles since the C-duct was new. (ii) Within 6 months

after the effective

date of this AD. (5) 3413L, 3415R (i) Before the accumu lation of 40,000 tota l flight cycles

since the C-duct was new. (ii) Within 6 months

after the effective

date of this AD.

Note 1: Airbus Service Bulletin A330-78-3010, Revi sion 03, dated April 28, 2004, refers to Rolls-Royce Service Bulletin RB.211-78-C899, Re vision 3, dated May 7, 2004, as an additional source of service information for modifying the co wl assemblies of the left- and right-hand thrust

reversers.

Parts Installation

(g) As of the effective date of this AD, no pe rson may install, on any airplane, a cowl assembly of the left- or right-hand thrust reverser if the airpla ne has exceeded the applicable flight cycle threshold specified in Table 1 of this AD.

Alternative Methods of Compliance (AMOCs)

(h) The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if request ed in accordance with the procedures found in 14

CFR 39.19.

Related Information

(i) French airworthiness dire ctive F-2001-528 R2, dated June 23, 2004, also addresses the subject

of this AD.7 Material Incorporated by Reference

(j) You must use Airbus Service Bulletin A330-78-3010, Revision 03, dated April 28, 2004, to perform the actions that are requir ed by this AD, unless the AD specifi es otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Airbus , 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for a copy of this service info rmation. You may review copies at the Docket Management Facility, U.S. Department of Tran sportation, 400 Seventh Street SW., room PL-401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov ; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, 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 December 2, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Direct orate, Aircraft Certification Service. [FR Doc. 05-23902 Filed 12-13-05; 8:45 am]

BILLING CODE 4910-13-P