This section of the FEDERAL REGISTER

contains regulatory documents having general

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are keyed to and codified in the Code of

Federal Regulations, which is published under

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Rules and Regulations Federal Register

46979

Vol. 69, No. 149

Wednesday, August 4, 2004

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA–2004–18669; Directorate 

Identifier 2004–NM–83–AD; Amendment 39–

13757; AD 2004–16–01] 

RIN 2120–AA64

Airworthiness Directives; Airbus Model 

A330, A340–200, and A340–300 Series 

Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A330, A340–200, and 

A340–300 series airplanes. This AD 

requires repetitive inspections for 

cracking of the chromed area of the left 

and right piston rods for the main 

landing gear (MLG) retraction actuators, 

and related investigative and corrective 

actions if necessary. This AD is 

prompted by reports of the piston rods 

for the MLG retraction actuators 

rupturing during flight. We are issuing 

this AD to detect and correct corrosion 

pitting and cracking of the piston rods 

for the MLG retraction actuators, which 

could result in rupture of a piston rod, 

non-damped extension of the MLG, high 

loads on the fully extended MLG, and 

consequent reduced structural integrity 

of the MLG.

DATES: Effective August 19, 2004. 

The incorporation by reference of 

certain publications listed in the AD is 

approved by the Director of the Federal 

Register as of August 19, 2004. 

We must receive comments on this 

AD by October 4, 2004.

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. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

For service information identified in 

this AD, contact Airbus, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France. You can examine this 

information 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. 

You can examine the contents of this 

AD docket on the Internet at http://

dms.dot.gov, or at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., room PL–401, on the plaza level of 

the Nassif Building, Washington, DC. 

Docket Management System (DMS) 

The FAA has implemented new 

procedures for maintaining AD dockets 

electronically. As of May 17, 2004, new 

AD actions are posted on DMS and 

assigned a docket number. We track 

each action and assign a corresponding 

directorate identifier. The DMS AD 

docket number is in the form ‘‘Docket 

No. FAA–2004–99999.’’ The Transport 

Airplane Directorate identifier is in the 

form ‘‘Directorate Identifier 2004-NM–

999-AD.’’ Each DMS AD docket also 

lists the directorate identifier (‘‘Old 

Docket Number’’) as a cross-reference 

for searching purposes. 

Examining the Dockets 

You can 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. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket 

Management Facility office (telephone 

(800) 647–5227) is located on the plaza 

level of the Nassif Building at the DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the DMS 

receives them.

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: The 

Direction Ge ́ne ́rale de l’Aviation Civile 

(DGAC), which is the airworthiness 

authority for France, notified the FAA 

that an unsafe condition may exist on 

certain Airbus Model A330, A340–200, 

and A340–300 series airplanes. The 

DGAC advises that it has received a 

report of the flightcrew on a Model 

A330 series airplane doing a free-fall 

extension of the main landing gear 

(MLG) during approach. Investigation 

revealed a rupture of the piston rod for 

the left MLG retraction actuator. It was 

determined that corrosion and cracking 

caused the rupture. Additional reports 

indicate that cracking was found on the 

chromed area of several piston rods; the 

cracking started from a line of corrosion 

pitting in the rod bores. These 

conditions, if not corrected, could result 

in rupture of a piston rod, non-damped 

extension of the MLG, and high loads on 

the fully extended MLG, which could 

result in reduced structural integrity of 

the MLG. 

The MLG system on Model A340–200 

and A340–300 series airplanes is 

identical to the MLG system on the 

affected Model A330 series airplanes. 

Therefore, Model A340–200 and A340–

300 series airplanes may be subject to 

the same unsafe condition identified on 

the Model A330 series airplanes. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A330–32–3173, Revision 01 (for Model 

A330 series airplanes); and A340–32–

4212, Revision 01 (for Model A340–200 

and -300 series airplanes); both dated 

June 16, 2004. The service bulletins 

describe procedures for repetitive 

detailed visual inspections for cracking 

of the chromed area of the left and right 

piston rods for the MLG retraction 

actuators. If any cracking is found, the 

corrective actions include replacing the 

46980 Federal Register / Vol. 69, No. 149 / Wednesday, August 4, 2004 / Rules and Regulations 

affected MLG retraction actuator with a 

new actuator before the next flight. 

The service bulletins also describe 

procedures for related investigative 

actions. Those procedures include 

repetitive ultrasonic inspections for 

corrosion pitting and cracking of the 

inner surface of the piston rods for the 

MLG retraction actuators. If any 

corrosion pitting or cracking is found, 

the corrective actions include replacing 

the affected MLG retraction actuator 

with a new actuator. The compliance 

time for the corrective action depends 

on the results of the ultrasonic 

inspection, and is either before the next 

flight, or within the next 10 landings. 

The service bulletins also include 

procedures for reporting the results of 

both the detailed visual and ultrasonic 

inspections to Airbus. 

The DGAC mandated these service 

bulletins and issued French 

airworthiness directives F–2004–086 

and F–2004–087, both dated June 23, 

2004, to ensure the continued 

airworthiness of these airplanes in 

France.

Both of the Airbus service bulletins 

reference Messier-Dowty Service 

Bulletin A33/34–32–222, including 

Appendices A and B, dated December 6, 

2003, as an additional source of service 

information for the detailed visual and 

ultrasonic inspections. 

FAA’s Determination and Requirements 

of This AD 

These airplane models are 

manufactured in France 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 airworthiness 

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 pertinent 

information, and determined that AD 

action is necessary for products of this 

type design that are certificated for 

operation in the United States. 

Therefore, we are issuing this AD to 

detect and correct corrosion pitting and 

cracking of the piston rods for the MLG 

retraction actuators, which could result 

in rupture of the piston rods, nondamped extension of the MLG, high 

loads on the fully extended MLG, and 

consequent reduced structural integrity 

of the MLG. 

This AD requires doing the actions 

specified in the Airbus service 

information described previously, 

except as discussed under ‘‘Differences 

Between the AD and French 

Airworthiness Directives.’’ This AD also 

requires sending certain inspection 

results to the manufacturer. 

Interim Action 

We consider this AD to be interim 

action. The inspection reports that are 

required by this AD will enable the 

manufacturer to obtain better insight 

into the nature, cause, and extent of the 

corrosion/cracking, and eventually to 

develop final action to address the 

unsafe condition. Once final action has 

been identified, we may consider 

further rulemaking. 

Differences Between the AD and French 

Airworthiness Directives 

The French airworthiness directives 

do not include compliance times for 

airplanes equipped with piston rods 

that have been in service less than 36 

months, as of the effective date of the 

French airworthiness directives. 

However, the FAA AD includes 

compliance times for these airplanes. 

Because this AD is an interim action, we 

have determined that it is necessary to 

address airplanes equipped with piston 

rods that are close to having 36 months 

in service, as of the effective date of the 

AD. This difference has been 

coordinated with the DGAC. 

Clarification of Inspection Terminology 

The Airbus service bulletins specify 

to do a ‘‘detailed visual inspection’’ of 

the chromed area of the piston rods for 

the MLG retraction actuators. This AD 

instead requires a ‘‘detailed inspection,’’

which is defined in Note 1 of this AD. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD; therefore, providing notice and 

opportunity for public comment before 

the AD is issued is impracticable, and 

good cause exists to make this AD 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

written relevant data, views, or 

arguments regarding this AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–

2004–18669; Directorate Identifier 

2004–NM–83–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the AD. We will consider all 

comments received by the closing date 

and may amend the AD in light of those 

comments. 

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. Using the 

search function of our docket 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 can review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78), or you can visit 

http://dms.dot.gov. 

We are reviewing the writing style we 

currently use in regulatory documents. 

We are interested in your comments on 

whether the style of this document is 

clear, and your suggestions to improve 

the clarity of our communications with 

you. You can get more information 

about plain language at http://www/

faa.gov/language and http://

www.plainlanguage.gov. 

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 a regulatory evaluation 

of the estimated costs to comply with 

this AD. See the ADDRESSES section for 

a location to examine the regulatory 

evaluation.

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:

Federal Register / Vol. 69, No. 149 / Wednesday, August 4, 2004 / Rules and Regulations 46981

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):

2004–16–01 Airbus: Amendment 39–13757. 

Docket No. FAA–2004–18669; 

Directorate Identifier 2004–NM–83–AD.

Effective Date 

(a) This AD becomes effective August 19, 

2004. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A330, 

A340–200, and A340–300 series airplanes; 

certificated in any category; equipped with a 

piston rod, part number (P/N) 114256309 or 

114256321, for the main landing gear (MLG) 

retraction actuators. 

Unsafe Condition 

(d) This AD was prompted by reports of the 

piston rods for the MLG retraction actuators 

rupturing during flight. We are issuing this 

AD to detect and correct corrosion pitting 

and cracking of the piston rods for the MLG 

retraction actuators, which could result in 

rupture of a piston rod, non-damped 

extension of the MLG, high loads on the fully 

extended MLG, and consequent reduced 

structural integrity of the MLG. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Repetitive Detailed Inspections and 

Corrective Actions 

(f) Before each MLG retraction actuator has 

been in service 36 months, or within 14 days 

after the effective date of this AD, whichever 

is later: Do a detailed inspection for cracking 

of the chromed area of the left and right 

piston rod of the MLG retraction actuators. 

Do the inspection in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–32–3173, Revision 01 

(for Model A330 series airplanes); or A340–

32–4212, Revision 01 (for Model A340–200 

and –300 series airplanes); both dated June 

16, 2004; as applicable. Repeat the inspection 

thereafter at intervals not to exceed 7 days.

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

(g) If any cracking is found during any 

inspection required by paragraph (f) of this 

AD: Before further flight, replace the MLG 

retraction actuator with a new or serviceable 

part in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330–

32–3173, Revision 01 (for Model A330 series 

airplanes); or A340–32–4212, Revision 01 

(for Model A340–200 and –300 series 

airplanes); both dated June 16, 2004; as 

applicable. 

Related Investigative and Corrective Actions 

(h) If no cracking is found during the initial 

detailed inspection required by paragraph (f) 

of this AD: At the later of the times specified 

in paragraphs (h)(1) and (h)(2) of this AD, do 

an ultrasonic inspection for corrosion pitting 

or cracking of the inner surface of the piston 

rods for the MLG retraction actuators. Do the 

ultrasonic inspection in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–32–3173, Revision 01 

(for Model A330 series airplanes); or A340–

32–4212, Revision 01 (for Model A340–200 

and -300 series airplanes); both dated June 

16, 2004; as applicable. Any corrective action 

must be done at the times specified in Figure 

2 of the applicable service bulletin. 

(1) Before each MLG retraction actuator has 

been in service 36 months. 

(2) Within 1,400 flight hours, 250 flight 

cycles, or 4 months after the effective date of 

this AD, whichever is first.

Note 2: Airbus Service Bulletins A330–32–

3173, Revision 01; and A340–32–4212, 

Revision 01; reference Messier-Dowty Service 

Bulletin A33/34–32–222, including 

Appendices A and B, dated December 6, 

2003, as an additional source of service 

information for doing the detailed and 

ultrasonic inspections.

(i) Repeat the ultrasonic inspection 

thereafter at intervals not to exceed 1,400 

flight hours, 250 flight cycles, or 4 months 

after the most recent ultrasonic inspection, 

whichever is first. 

Reporting Requirement 

(j) Submit a report of the results (both 

positive and negative) for any ultrasonic 

inspection required by paragraph (h) of this 

AD, and only negative findings for any 

detailed inspection required by paragraph (f) 

of this AD. Submit the report to Airbus 

Customer Services Directorate, Attention: 

SDC32 Technical Data and Documentation 

Services, fax +33+ 5 61 93 28 06, or via your 

resident customer support office. Submit the 

report at the applicable time specified in 

paragraph (j)(1) or (j)(2) of this AD. The 

report must include the inspection results, a 

description of any discrepancies found, the 

airplane serial number, and the period of 

time the affected piston rod has been in 

service. Under the provisions of the 

Paperwork Reduction Act of 1980 (44 U.S.C. 

3501 et seq.), the Office of Management and 

Budget (OMB) has approved the information 

collection requirements contained in this AD 

and has assigned OMB Control Number 

2120–0056. 

(1) If the inspection is done after the 

effective date of this AD: Submit the report 

within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

Parts Installation 

(k) As of the effective date of this AD, no 

person may install a piston rod, part number 

(P/N) 114256309 or 114256321, for the main 

landing gear (MLG) retraction actuators, on 

any airplane, unless the part has been 

inspected in accordance with paragraphs (f) 

and (h) of this AD and found free of cracking. 

Ultrasonic Inspections Done Per Airbus All 

Operator’s Telex (AOT) 

(l) Ultrasonic inspections done in 

accordance with Airbus AOT A330–32A3172 

(for Model A330 series airplanes); or A340–

32A4211 (for Model A340–200 and -300 

series airplanes); both dated May 22, 2003; 

are acceptable for compliance with the initial 

ultrasonic inspection required by paragraph 

(h) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(m) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

Related Information 

(n) French airworthiness directives F–

2004–086 and F–2004–087, both dated June 

23, 2004, also address the subject of this AD. 

Material Incorporated by Reference 

(o) You must use Airbus Service Bulletin 

A330–32–3173, Revision 01, dated June 16, 

2004; or Airbus Service Bulletin A340–32–

4212, Revision 01, dated June 16, 2004; as 

applicable; to perform the actions that are 

required by this AD, unless the AD specifies 

otherwise. The Director of the Federal 

Register approves the incorporation by 

reference of these documents in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. For 

copies of the documents contact Airbus, 1 

Rond Point Maurice Bellonte, 31707 Blagnac 

Cedex, France. You can review copies at the 

Docket Management Facility, U.S. 

Department of Transportation, 400 Seventh 

Street, SW., room PL–401, Nassif Building, 

Washington, DC; 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.

Issued in Renton, Washington, on July 23, 

2004. 

Kevin M. Mullin, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–17623 Filed 8–3–04; 8:45 am] 

BILLING CODE 4910–13–P