16104 Federal Register / Vol. 70, No. 60 / Wednesday, March 30, 2005 / Rules and Regulations 

(1) If the inspection was done after the 

effective date of this AD: Submit the report 

within 10 days after the inspection. 

(2) If the inspection was accomplished 

prior to the effective date of this AD: Submit 

the report within 10 days after the effective 

date of this AD. 

Parts Installation 

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

person may install an outer cylinder having 

a S/N listed in paragraph 1.D., ‘‘Description,’’

of the service bulletin on any airplane unless 

it has been inspected and all specified and 

corrective actions are accomplished in 

accordance with paragraph (h)(2) of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(1) The Manager, Seattle ACO, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 

(2) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by an 

Authorized Representative for the Boeing 

Delegation Option Authorization 

Organization who has been authorized by the 

Manager, Seattle ACO, to make those 

findings. 

Material Incorporated by Reference 

(l) You must use Boeing Alert Service 

Bulletin 777–32A0038, Revision 1, dated 

February 19, 2004, 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 this document in accordance 

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

copies of the service information, contact 

Boeing Commercial Airplanes, P.O. Box 

3707, Seattle, Washington 98124–2207. For 

information on the availability of this 

material at the National Archives and 

Records Administration (NARA), call (202) 

741–6030, or go to http://www.archives.gov/

federal_register/code_of_federal_regulations/

ibr_locations.html. You may view the AD 

docket at the Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street SW., room PL–401, Nassif 

Building, Washington, DC.

Issued in Renton, Washington, on March 

21, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 05–6110 Filed 3–29–05; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2001–NM–243–AD; Amendment 

39–14028; AD 2005–07–04] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330, A340–200, and A340–300 Series 

Airplanes

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT).

ACTION: Final rule.

SUMMARY: This amendment supersedes 

an existing airworthiness directive (AD), 

applicable to the airplane models listed 

above. That AD currently requires 

repetitive inspections to detect 

discrepancies of the transfer tubes and 

the collar of the ball nut of the 

trimmable horizontal stabilizer actuator 

(THSA), and corrective action if 

necessary. This amendment expands the 

applicability of the existing AD; and 

requires new repetitive inspections for 

discrepancies of the ball screw 

assembly; corrective action if necessary; 

repetitive greasing of the THSA ball nut, 

and replacement of the THSA if 

necessary; and a modification or 

replacement (as applicable) of the ball 

nut assembly, which would end certain 

repetitive inspections. The actions 

specified by this AD are intended to 

prevent degraded operation of the THSA 

due to the entrance of water into the ball 

nut. Degraded operation could lead to 

reduced controllability of the airplane. 

This action is intended to address the 

identified unsafe condition.

DATES: Effective May 4, 2005. 

The incorporation by reference of 

certain publications, as listed in the 

regulations, is approved by the Director 

of the Federal Register as of May 4, 

2005. 

The incorporation by reference of 

certain other publications, as listed in 

the regulations, was approved 

previously by the Director of the Federal 

Register as of June 26, 2001 (66 FR 

31143, June 11, 2001).

ADDRESSES: The service information 

referenced in this AD may be obtained 

from Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France. 

This information may be examined at 

the Federal Aviation Administration 

(FAA), Transport Airplane Directorate, 

Rules Docket, 1601 Lind Avenue, SW., 

Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98055–4056; telephone (425) 227–2125; 

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) 

by superseding AD 2001–11–09, 

amendment 39–12252 (66 FR 31143, 

June 11, 2001), which is applicable to 

certain Airbus Model A330 and A340 

series airplanes, was published as a 

supplemental notice of proposed 

rulemaking (NPRM) in the Federal 

Register on August 31, 2004 (69 FR 

53016). That action proposed to expand 

the applicability of the existing AD; and 

require new repetitive inspections for 

discrepancies of the ball screw 

assembly; corrective action if necessary; 

repetitive greasing of the trimmable 

horizontal stabilizer actuator (THSA) 

ball nut, and replacement of the THSA 

if necessary; and a modification or 

replacement (as applicable) of the ball 

nut assembly, which would end certain 

repetitive inspections. 

Explanation of New Relevant Service 

Information 

Since the preparation of the 

supplemental NPRM, Airbus has issued 

Service Bulletin A330–27–3102, 

Revision 05, dated July 7, 2004. (The 

supplemental NPRM refers to Airbus 

Service Bulletin A330–27–3102, 

Revision 04, dated December 8, 2003, as 

the acceptable source of service 

information for accomplishing certain 

inspections and corrective actions.) 

Airbus issued Revision 05 to expand the 

effectivity to include Models A330–302 

and –303 airplanes, and to list 

additional manufacturer’s serial 

numbers in the service bulletin. 

Revision 05 does not contain any new 

procedures. Accordingly, we have 

revised paragraph (e) of this AD to refer 

to Revision 05 as the acceptable source 

of service information for the actions 

required by that paragraph. We have 

also revised paragraph (i)(2) of this AD 

to state that inspections and corrective 

actions accomplished previously in 

accordance with Airbus Service Bulletin 

A330–27–3102, Revision 04, are 

acceptable for compliance with 

paragraph (e). We find that referring to 

Revision 05 does not result in an 

expansion of the applicability of this AD 

because the applicability of the 

supplemental NPRM includes all Airbus 

Model A330, A340–200, and A340–300 

series airplanes. 

The Direction Ge ́ne ́rale de l’Aviation 

Civile (DGAC), which is the 

airworthiness authority for France, 

Federal Register / Vol. 70, No. 60 / Wednesday, March 30, 2005 / Rules and Regulations 16105

classified Airbus Service Bulletin A330–

27–3102, Revision 05, as mandatory and 

issued French airworthiness directive 

F–2002–414 R3, dated July 7, 2004, to 

ensure the continued airworthiness of 

these airplanes in France. We have 

revised Note 8 of this AD to refer to this 

latest revision of the French 

airworthiness directive. 

Explanation of Editorial Change 

We have revised paragraphs (c)(3) and 

(f) of this AD to more accurately state 

the warning messages that may be 

displayed on the electronic centralized 

aircraft monitor (ECAM) associated with 

the ‘‘PITCH TRIM ACTR (1CS)’’

maintenance message. 

Comments 

Interested persons have been afforded 

an opportunity to participate in the 

making of this amendment. Due 

consideration has been given to the 

comments received. 

Request To Remove Paragraph (f)

One commenter requests that we 

revise the supplemental NPRM to 

remove paragraph (f), which requires 

inspecting in accordance with 

paragraph (e) of the supplemental 

NPRM before further flight if a ‘‘F/CTL 

PRIM X PITCH FAULT’’ or ‘‘F/CTL 

STAB CTL FAULT’’ warning message is 

displayed on the ECAM associated with 

the ‘‘PITCH TRIM ACTR (1CS).’’ The 

commenter states that it has no 

mechanism to document compliance 

with this requirement because, if the 

ECAM warning is displayed in flight, 

there is no process to ensure that the 

pilot will record the warning in the 

airplane logbook, though this is the 

general practice. 

The commenter further states that the 

normal procedures if the subject ECAM 

message appears would lead a mechanic 

to the Airbus A330/A340 

Troubleshooting Manual (TSM), most 

likely to TSM Task 27–90–00–810–847, 

‘‘Failure of the Pitch Trim Actuator 

Detected by the FCPC1 or FCPC2.’’ The 

commenter explains that the first step of 

this task would be to perform an 

operational test of the servo loops of the 

trimmable horizontal stabilizer. If this 

operational test shows no discrepancy, 

no further action would be necessary. If 

the test confirms a discrepancy, the 

TSM specifies a detailed visual 

inspection of the ball screw assembly in 

accordance with Task 27–44–51–210–

805 of the Airbus A330/A340 Airplane 

Maintenance Manual (AMM). The 

commenter feels that the TSM is the 

primary source of guidance for 

diagnosing system problems and that 

the procedures in the TSM would 

provide adequate guidance should a 

subject ECAM message appear. Thus, 

the commenter states that the 

requirements of paragraph (f) of the 

supplemental NPRM are not warranted. 

The commenter does note that there is 

no mechanism for it ‘‘to generate the 

requirement to refer to the specific TSM 

task and document its compliance in 

every instance.’’

We do not concur that paragraph (f) 

of this AD is unnecessary. Section 

121.563 (‘‘Reporting mechanical 

irregularities’’) of the Federal Aviation 

Regulations (FARs) (14 CFR 121.563) 

requires that the pilot ensure that all 

mechanical irregularities that occur 

during flight are entered into the 

maintenance log at the end of the flight. 

That section also requires that, before 

each flight, the pilot must determine the 

status of any irregularity entered in the 

maintenance log at the end of the 

preceding flight. A ‘‘F/CTL PRIM X 

PITCH FAULT’’ message is 

informational only and will remain 

displayed on ECAM through landing 

because there is no action that the crew 

can take that will correct the failure. 

Crew procedures for the ‘‘F/CTL STAB 

CTL FAULT’’ will also not correct the 

failure; therefore that ECAM message 

will remain displayed through landing. 

ECAM messages remaining after the 

flight are considered mechanical 

irregularities that must be entered in the 

maintenance log in accordance with 14 

CFR 121.563. We have not changed the 

AD in this regard. 

However, we do concur that 

performing an operational test in 

accordance with TSM Task 27–90–00–

810–847 would be an acceptable means 

of complying with paragraph (e) of this 

AD, provided that, if the operational test 

confirms a discrepancy, the detailed 

inspection required by paragraph (e) of 

this AD, and any necessary corrective 

actions, are done before further flight. 

We have revised paragraph (e) of this 

AD accordingly. 

Request To Allow Alternative Method 

for Repetitive Inspections 

The first commenter requests that, if 

we decide that it is necessary to retain 

paragraph (f) of the supplemental 

NPRM, we refer to AMM Task 27–44–

51–210–805 as an alternative method for 

doing the repetitive inspections. A 

second commenter makes the same 

request. The commenters note that the 

procedures in this AMM task are 

equivalent to those in Airbus Service 

Bulletin A330–27–3102, Revision 04, 

which is referenced in the supplemental 

NPRM as the appropriate source of 

service information for the necessary 

inspection. 

We concur. We have revised 

paragraph (e) of this AD to state that an 

inspection done according to Task 27–

44–51–210–805 of the AMM is 

acceptable for compliance with that 

paragraph. (Paragraph (f) of this AD 

refers to the inspection in paragraph 

(e).)

Request To Clarify Terminology 

One commenter requests that we 

revise paragraph (d) of the supplemental 

NPRM to revise the reference to grease 

being expelled through the ‘‘drain 

hole.’’ The commenter notes that the 

lubrication procedures specified in 

Chapter 12–22–27 of the Airbus A330/

A340 AMM identify this orifice as the 

‘‘vent hole.’’ The commenter requests 

that the terminology be changed for 

clarification. We concur and have 

revised paragraph (d) of this AD 

accordingly. 

Request To Revise Cost Impact Estimate 

One commenter requests that we 

revise the number of affected airplanes 

estimated in the Cost Impact section of 

the supplemental NPRM. The 

commenter notes that we estimate that 

9 Model A330 series airplanes would be 

affected. The commenter operates 10 

affected U.S.-registered Model A330 

series airplanes. 

We concur. Since the issuance of the 

original NPRM and the supplemental 

NPRM, more Model A330 series 

airplanes have been registered in the 

U.S. We have revised the estimated 

number of affected Model A330 series 

airplanes to 19. 

Conclusion 

After careful review of the available 

data, including the comments noted 

above, the FAA has determined that air 

safety and the public interest require the 

adoption of the rule with the changes 

previously described. The FAA has 

determined that these changes will 

neither increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Cost Impact 

There are approximately 19 Model 

A330 series airplanes of U.S. registry 

that are affected by this AD. Currently, 

there are no affected Model A340–200 

or –300 series airplanes on the U.S. 

Register. However, if an affected Model 

A340–200 or –300 series airplane is 

imported and placed on the U.S. 

Register in the future, the following 

costs will also apply to those airplanes. 

The inspections (in accordance with 

Airbus All Operators Telex (AOT) 

A330–27A3088 or A340–27A4093, as 

applicable) that are currently required 

16106 Federal Register / Vol. 70, No. 60 / Wednesday, March 30, 2005 / Rules and Regulations 

by AD 2001–11–09 take approximately 

1 work hour per airplane, per inspection 

cycle, at an average labor rate of $65 per 

work hour. Based on these figures, the 

cost impact of the currently required 

actions on U.S. operators is estimated to 

be $1,235, or $65 per airplane, per 

inspection cycle. 

The new inspections (in accordance 

with Airbus SBs A330–27–3088 or 

A340–27–4093, as applicable) that are 

required by this AD take approximately 

1 work hour per airplane, per inspection 

cycle, at an average labor rate of $65 per 

work hour. Based on these figures, the 

cost impact of this requirement on U.S. 

operators is estimated to be $1,235, or 

$65 per airplane, per inspection cycle. 

The new greasing action that is 

required by this AD takes approximately 

1 work hour per airplane, per 

maintenance cycle, at an average labor 

rate of $65 per work hour. Based on 

these figures, the cost impact of this 

requirement on U.S. operators is 

estimated to be $1,235, or $65 per 

airplane, per maintenance cycle. 

In addition to the actions stated 

above, certain airplanes may be subject 

to additional actions. The following 

table contains the cost impact estimate 

for each airplane affected by the SBs 

listed below, at an average labor rate of 

$65 per work hour:

For airplanes listed in Airbus SB— Estimated number of work 

hours Estimated parts cost Estimated cost per airplane 

A330–27–3085 or A340–27–4089, both Revision 02 .............. 12 ............................................ No charge ............................... $780 

A330–27–3093 or A340–27–4099, both Revision 01 .............. 6 .............................................. No charge ............................... 390 

A330–27–3052, Revision 03 .................................................... 6 .............................................. No charge ............................... 390 

A330–27–3007, Revision 01 .................................................... 1 .............................................. No charge ............................... 65 

A330–27–3015 .......................................................................... 2 .............................................. No charge ............................... 130 

A330–27–3047, Revision 01 .................................................... 2 .............................................. No charge ............................... 130 

A330–27–3050 .......................................................................... 2 .............................................. No charge ............................... 130 

A330–55–3020, Revision 01 .................................................... 2 (inspection only) .................. None ....................................... 130 

A340–27–4059, Revision 03 .................................................... 6 .............................................. No charge ............................... 390 

A340–27–4007 .......................................................................... 2 .............................................. No charge ............................... 130 

A340–27–4025 .......................................................................... 2 .............................................. No charge ............................... 130 

A340–27–4054, Revision 01 .................................................... 2 .............................................. No charge ............................... 130 

A340–27–4057 .......................................................................... 2 .............................................. No charge ............................... 130 

A340–55–4021, Revision 01 .................................................... 2 (inspection only) .................. None ....................................... 130 

The cost impact figures discussed 

above are based on assumptions that no 

operator has yet accomplished any of 

the requirements of this AD action, and 

that no operator would accomplish 

those actions in the future if this AD 

were not adopted. The cost impact 

figures discussed in AD rulemaking 

actions represent only the time 

necessary to perform the specific actions 

actually required by the AD. These 

figures typically do not include 

incidental costs, such as the time 

required to gain access and close up, 

planning time, or time necessitated by 

other administrative actions. 

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 Impact 

The regulations adopted herein 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. Therefore, it is 

determined that this final rule does not 

have federalism implications under 

Executive Order 13132. 

For the reasons discussed above, I 

certify that this action (1) is not a 

‘‘significant regulatory action’’ under 

Executive Order 12866; (2) is not a 

‘‘significant rule’’ under 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. A final evaluation has 

been prepared for this action and it is 

contained in the Rules Docket. A copy 

of it may be obtained from the Rules 

Docket at the location provided under 

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety.

Adoption of the Amendment

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (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 

removing amendment 39–12252 (66 FR 

31143, June 11, 2001), and by adding a 

new airworthiness directive (AD), 

amendment 39–14028, to read as 

follows:

2005–07–04 Airbus: Amendment 39–14028. 

Docket 2001–NM–243–AD. Supersedes 

AD 2001–11–09, Amendment 39–12252.

Applicability: All Model A330, A340–200, 

and A340–300 series airplanes; certificated in 

any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent degraded operation of the 

trimmable horizontal stabilizer actuator 

(THSA) due to the entrance of water into the 

ball nut, which could result in reduced 

controllability of the airplane, accomplish 

the following:

Federal Register / Vol. 70, No. 60 / Wednesday, March 30, 2005 / Rules and Regulations 16107

Requirements of AD 2001–11–09 

Repetitive Inspections 

(a) For Model A330, A340–200, and A340–

300 series airplanes equipped with a THSA 

part number (P/N) 47172, and on which 

Airbus Modification 45299 has been 

performed: Within 150 flight hours from June 

26, 2001 (the effective date of AD 2001–11–

09, amendment 39–12252), perform a 

detailed inspection to detect discrepancies in 

the THSA (including distortion of the 

transfer tubes, disconnection of the tubes, 

and distortion of the collar of the ball nut), 

in accordance with Airbus All Operators 

Telex (AOT) A330–27A3088 (for Model A330 

series airplanes) or A340–27A4093 (for 

Model A340 series airplanes), both dated 

April 5, 2001, as applicable. If any 

discrepancy, as defined in paragraph 4–2–2/

Rejection Criteria of the applicable AOT, is 

detected, prior to further flight, replace the 

THSA with a serviceable one, in accordance 

with the applicable AOT.

Note 1: For the purposes of this AD, a 

detailed inspection is defined as: ‘‘An 

intensive visual examination of a specific 

structural area, system, installation, or 

assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at intensity deemed appropriate by 

the inspector. Inspection aids such as mirror, 

magnifying lenses, etc., may be used. Surface 

cleaning and elaborate access procedures 

may be required.’’

(b) At intervals not to exceed 150 flight 

hours, repeat the inspection mandated in 

paragraph (a) of this AD, until paragraph (c) 

of this AD has been accomplished. 

New Requirements of This AD 

Repetitive Detailed Inspections of THSA Ball 

Nut and Corrective Action 

(c) For airplanes equipped with a THSA 

having P/N 47172 or 47147–400: At the 

applicable compliance time specified in 

paragraph (c)(1), (c)(2), or (c)(3) of this AD, 

perform a detailed inspection of the transfer 

tubes and collar on the THSA ball nut to 

detect discrepancies, including ball 

migration, distortion, or evidence of 

disconnection of the THSA ball nut; in 

accordance with Airbus Service Bulletin 

A330–27–3088 (for Model A330 series 

airplanes) or A340–27–4093 (for Model 

A340–200 and –300 series airplanes), both 

Revision 04, both dated September 5, 2002; 

as applicable. Repeat this inspection at 

intervals not to exceed 150 flight hours until 

paragraph (g) of this AD is accomplished. If 

any discrepancy is found during any 

inspection in accordance with this 

paragraph, before further flight, repair the 

THSA, in accordance with a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; or the Direction Ge ́ne ́rale 

de l’Aviation Civile (DGAC) (or its delegated 

agent). 

(1) For airplanes equipped with a THSA 

having P/N 47172 or 47147–400: Except as 

provided by paragraph (c)(3) of this AD, for 

airplanes inspected before the effective date 

of this AD in accordance with paragraph (a) 

of this AD, do the initial inspection within 

150 flight hours since the most recent 

inspection in accordance with paragraph (a) 

or (b) of this AD. Accomplishment of this 

inspection terminates the repetitive 

inspections required by paragraph (b) of this 

AD. 

(2) For airplanes equipped with a THSA 

having P/N 47172 or 47147–400: Except as 

provided by paragraph (c)(3) of this AD, for 

airplanes not inspected before the effective 

date of this AD in accordance with paragraph 

(a) of this AD, do the initial inspection 

within 150 flight hours after the effective 

date of this AD. Accomplishment of this 

inspection within the compliance time 

specified in paragraph (a) of this AD 

eliminates the need to accomplish the 

inspection in paragraph (a) of this AD and 

terminates the repetitive inspections required 

by paragraph (b) of this AD. 

(3) For airplanes equipped with a THSA 

having P/N 47172 or 47147–400: If the ‘‘F/

CTL PRIM X PITCH FAULT’’ or ‘‘F/CTL 

STAB CTL FAULT’’ message is displayed on 

the electronic centralized aircraft monitor 

(ECAM) associated with the ‘‘PITCH TRIM 

ACTR (1CS)’’ maintenance message, do the 

inspection in paragraph (c) of this AD before 

further flight after the message is displayed 

on the ECAM. 

Repetitive Greasing Procedure 

(d) For airplanes equipped with a THSA 

having P/N 47172, 47172–300, or 47147–

XXX (where ‘‘XXX’’ is any dash number): 

Within 700 flight hours after accomplishment 

of the last greasing of the ball nut of the 

THSA, grease the ball nut of the THSA in 

accordance with a method approved by the 

Manager, International Branch, ANM–116; or 

the DGAC (or its delegated agent). Doing the 

actions in Chapter 12–22–27, page block 301, 

of the Airbus A330/A340 Airplane 

Maintenance Manual (AMM) is one approved 

method. Repeat the greasing procedures at 

intervals not to exceed 700 flight hours. If, 

during any accomplishment of the greasing 

procedure, the new grease is expelled from 

the transfer tube (instead of through the vent 

hole): Before further flight, replace the THSA 

with a new or serviceable THSA in 

accordance with a method approved by 

either the Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA; or the DGAC (or its delegated agent). 

Replacement of the THSA in accordance with 

Chapter 27–44–51 of the Airbus A330/A340 

AMM is one approved method. 

Repetitive Inspections of the Ball Screw 

Assembly and Corrective Actions 

(e) For airplanes equipped with a THSA 

having P/N 47172, 47172–300, or 47147–

XXX (where ‘‘XXX’’ is any dash number): 

Except as provided by paragraph (f) of this 

AD, within 700 flight hours after the effective 

date of this AD, perform a detailed inspection 

of the ball screw assembly for discrepancies; 

including cracks, metallic debris, dents, 

corrosion, loose nuts, and damaged or 

missing lock washers and pins; and an 

inspection of the gap between the secondary 

nut tenons and the transfer plates using a 

feeler gage to ensure free movement; in 

accordance with Airbus Service Bulletins 

A330–27–3102, Revision 05, dated July 7, 

2004 (for Model A330 series airplanes); or 

A340–27–4107, Revision 04, dated June 20, 

2003 (for Model A340–200 and –300 series 

airplanes); as applicable. A detailed 

inspection done in accordance with Task 27–

44–51–210–805 of the Airbus A330/A340 

AMM is one approved method of compliance 

with the inspection requirements of this 

paragraph. An operational test in accordance 

with Task 27–90–00–810–847 is another 

approved method for compliance with the 

inspection requirements of this paragraph, 

provided that, if the operational test confirms 

a discrepancy, the detailed inspection 

required by this paragraph, and applicable 

corrective actions, are done before further 

flight. 

(1) Repeat the inspection at intervals not to 

exceed 700 flight hours, except as provided 

by paragraph (f) of this AD. 

(2) If any discrepancy is found that is 

outside the limits specified in the applicable 

service bulletin, before further flight, replace 

the THSA with a new part, in accordance 

with a method approved by either the 

Manager, International Branch, ANM–116; or 

the DGAC (or its delegated agent). 

Replacement of the THSA in accordance with 

Chapter 27–44–51 of the Airbus A330/A340 

AMM is one approved method.

Note 2: There is no terminating action at 

this time for the repetitive actions required 

by paragraphs (d) and (e) of this AD.

(f) If the ‘‘F/CTL PRIM X PITCH FAULT’’

or ‘‘F/CTL STAB CTL FAULT’’ message is 

displayed on the ECAM associated with the 

‘‘PITCH TRIM ACTR (1CS)’’ maintenance 

message, do the inspection in paragraph (e) 

of this AD before further flight after the 

message is displayed on the ECAM. 

Modification 

(g) Within 24 months after the effective 

date of this AD, modify the ball nut of each 

THSA by doing paragraph (g)(1) or (g)(2) of 

this AD, as applicable. Accomplishment of 

paragraph (g)(1) or (g)(2) of this AD 

terminates the repetitive inspections required 

by paragraph (c) of this AD.

(1) For THSAs having P/N 47172: Modify 

the ball nut of the THSA, or replace the 

existing THSA with a serviceable part having 

P/N 47172–300; in accordance with Airbus 

Service Bulletin A330–27–3085 (for Model 

A330 series airplanes) or A340–27–4089 (for 

Model A340–313 series airplanes), both 

Revision 02, both dated September 5, 2002; 

as applicable.

Note 3: Airbus Service Bulletins A330–27–

3085 and A340–27–4089 refer to TRW 

Aeronautical Systems Service Bulletin 

47172–27–03, dated October 24, 2001, as the 

appropriate source of service information for 

additional instructions for accomplishing the 

modification of the ball nut of the THSA.

(2) For THSAs having P/N 47147–2XX, 

47147–3XX, or 47147–400 (where ‘‘XX’’

represents any dash number): Modify the ball 

nut of the THSA, or replace the existing 

THSA with an improved part having P/N 

47147–500; as applicable; in accordance with 

Airbus Service Bulletin A330–27–3093 (for 

Model A330 series airplanes) or A340–27–

4099 (for Model A340–200 and –300 series 

16108 Federal Register / Vol. 70, No. 60 / Wednesday, March 30, 2005 / Rules and Regulations 

airplanes), both Revision 01, both dated 

September 5, 2002; as applicable.

Note 4: Airbus Service Bulletins A330–27–

3093 and A340–27–4099 refer to TRW 

Aeronautical Systems Service Bulletin 

47147–27–10, dated June 27, 2002, as the 

appropriate source of service information for 

additional instructions for accomplishing the 

modification of the ball nut of the THSA.

Previous/Concurrent Requirements 

(h) Prior to or concurrently with 

accomplishment of the requirements of 

paragraph (g)(2) of this AD, do all of the 

actions specified in the Accomplishment 

Instructions of the applicable Airbus service 

bulletins listed in Table 1 or 2 of this AD, as 

applicable, in accordance with those service 

bulletins.

Note 5: Airbus Service Bulletin A330–27–

3093, Revision 01, dated September 5, 2002, 

specifies that the actions in Airbus Service 

Bulletin A330–27–3052 must be 

accomplished previously or concurrently. 

Airbus Service Bulletin A330–27–3052, 

Revision 03, dated December 5, 2001, 

specifies that the actions in Airbus Service 

Bulletins A330–27–3007, A330–27–3015, 

A330–27–3047, A330–27–3050, and A330–

55–3020 must be accomplished previously or 

concurrently.

Note 6: Airbus Service Bulletin A340–27–

4099, Revision 01, dated September 5, 2002, 

specifies that the actions in Airbus Service 

Bulletin A340–27–4059 must be 

accomplished previously or concurrently. 

Airbus Service Bulletin A340–27–4059, 

Revision 03, dated December 5, 2001, 

specifies that the actions in Airbus Service 

Bulletins A340–27–4007, A340–27–4025, 

A340–27–4054, A340–27–4057, and A340–

55–4021, must be accomplished previously 

or concurrently.

TABLE 1.—PREVIOUS/CONCURRENT REQUIREMENTS FOR MODEL A330 SERIES AIRPLANES

Airbus service

bulletin Revision level Date Main action Additional source of service information 

A330–27–3007 ...... 01 ......................... September 18, 1996 .................. Replace rudder servo controls 

with modified parts.

Samm Avionique Service Bulletin SC5300–27–24–01, 

dated April 15, 1994. 

A330–27–3015 ...... Original ................. June 7, 1995 ............................. Modify the control valve detent 

and the jamming protection 

device on the THSA.

Lucas Aerospace Service Bulletin 47147–27–02, Revision 

1, dated January 31, 1996. 

A330–27–3047 ...... 01 ......................... November 26, 1997 ................... Replace hydraulic motors on the 

THSA with new parts.

Lucas Aerospace Service Bulletin 47147–27–04, Revision 

1, dated June 20, 1997. 

A330–27–3050 ...... Original ................. November 15, 1996 ................... Replace mechanical input shaft 

for THSA with modified part.

Lucas Aerospace Service Bulletin 47147–27–05, dated November 8, 1996. 

A330–27–3052 ...... 03 ......................... December 5, 2001 ..................... Replace THSA with a modified 

THSA.

Lucas Aerospace Service Bulletin 47147–27–07, dated 

May 4, 1998. 

A330–55–3020 ...... 01 ......................... October 21, 1998 ...................... Perform a general visual inspection of the THSA screw jack 

fitting assembly for correct installation of a washer; and 

correctly install washer as applicable.

None. 

TABLE 2.—PREVIOUS/CONCURRENT REQUIREMENTS FOR MODEL A340 SERIES AIRPLANES

Airbus service

bulletin Revision level Date Main action Additional source of service information 

A340–27–4007 ...... Original ................. April 7, 1994 .............................. Replace hydraulic motors on the 

THSA with new parts.

Lucas Aerospace Service Bulletin 47147–27–01, dated 

May 4, 1998. 

A340–27–4025 ...... Original ................. June 7, 1995 ............................. Modify the control valve detent 

and the jamming protection 

device on the THSA.

Lucas Aerospace Service Bulletin 47147–27–02, Revision 

1, dated January 31, 1996. 

A340–27–4054 ...... 01 ......................... November 26, 1997 ................... Replace hydraulic motors on the 

THSA with new parts.

Lucas Aerospace Service Bulletin 47147–27–04, Revision 

1, dated June 20, 1997. 

A340–27–4057 ...... Original ................. November 15, 1996 ................... Replace mechanical input shaft 

for THSA with modified part.

Lucas Aerospace Service Bulletin 47147–27–05, dated November 8, 1996. 

A340–27–4059 ...... 03 ......................... December 5, 2001 ..................... Replace THSA with a modified 

THSA.

Lucas Aerospace Service Bulletin 47147–27–07, dated 

May 4, 1998. 

A340–55–4021 ...... 01 ......................... October 21, 1998 ...................... Perform a general visual inspection of the THSA screw jack 

fitting assembly for correct installation of a washer; and 

correctly install washer as applicable.

None. 

Note 7: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

Federal Register / Vol. 70, No. 60 / Wednesday, March 30, 2005 / Rules and Regulations 16109

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’

Actions Accomplished Previously 

(i) Actions accomplished before the 

effective date of this AD in accordance with 

previous revisions of the service information 

referenced in this AD are acceptable for 

corresponding actions required by this AD as 

specified in paragraphs (i)(1), (i)(2), (i)(3), 

and (i)(4) of this AD. 

(1) Inspections and corrective actions 

accomplished in accordance with Airbus 

Service Bulletin A330–27–3088 (for Model 

A330 series airplanes) or A340–27–4093 (for 

Model A340–200 and –300 series airplanes), 

both Revision 03, both excluding Appendix 

01, both dated October 19, 2001; as 

applicable; are acceptable for compliance 

with paragraph (c) of this AD. 

(2) Inspections and corrective actions 

accomplished in accordance with Airbus 

Service Bulletin A330–27–3102, Revision 02, 

excluding Appendix 01, dated November 7, 

2002, Revision 03, excluding Appendix 01, 

dated June 20, 2003, or Revision 04, dated 

December 8, 2003 (for Model A330 series 

airplanes); or A340–27–4107, Revision 03, 

excluding Appendix 01, dated December 4, 

2002 (for Model A340–200 and –300 series 

airplanes); as applicable; are acceptable for 

compliance with paragraph (e) of this AD. 

(3) Modifications accomplished in 

accordance with Airbus Service Bulletin 

A330–27–3085 (for Model A330 series 

airplanes) or A340–27–4089 (for Model 

A340–313 series airplanes), both Revision 01, 

both dated January 23, 2002; as applicable; 

are acceptable for compliance with paragraph 

(g)(1) of this AD. 

(4) Modifications accomplished in 

accordance with Airbus Service Bulletin 

A330–27–3093 (for Model A330 series 

airplanes) or A340–27–4099 (for Model 

A340–200 and -300 series airplanes), both 

dated June 27, 2002; as applicable; are 

acceptable for compliance with paragraph 

(g)(2) of this AD. 

No Reporting Required 

(j) Where Airbus Service Bulletins A330–

27–3088, Revision 04, dated September 5, 

2002; A340–27–4093, Revision 04, dated 

September 5, 2002; A330–27–3102, Revision 

05, dated July 7, 2004; and A340–27–4107, 

Revision 04, dated June 20, 2003; describe 

procedures for completing a reporting sheet 

with inspection results, this AD does not 

require that action. 

Alternative Methods of Compliance 

(k) In accordance with 14 CFR 39.19, the 

Manager, International Branch, ANM–116, is 

authorized to approve alternative methods of 

compliance for this AD. 

Incorporation by Reference 

(l) Unless otherwise specified in this AD, 

the actions shall be done in accordance with 

Airbus All Operators Telex A330–27A3088, 

dated April 5, 2001; Airbus All Operators 

Telex A340–27A4093, dated April 5, 2001; or 

the Airbus service bulletins listed in Table 3 

of this AD; as applicable.

TABLE 3.—AIRBUS SERVICE BULLETINS INCORPORATED BY REFERENCE

Service bulletin Revision Date 

A330–27–3007 ........................................................................................................................... 01 ........................... September 18, 1996. 

A330–27–3015 ........................................................................................................................... Original .................. June 7, 1995. 

A330–27–3047 ........................................................................................................................... 01 ........................... November 26, 1997. 

A330–27–3050 ........................................................................................................................... Original .................. November 15, 1996. 

A330–27–3052 ........................................................................................................................... 03 ........................... December 5, 2001. 

A330–27–3085 ........................................................................................................................... 02 ........................... September 5, 2002. 

A330–27–3088, excluding Appendix 01 .................................................................................... 04 ........................... September 5, 2002. 

A330–27–3093 ........................................................................................................................... 01 ........................... September 5, 2002. 

A330–27–3102, excluding Appendix 01 .................................................................................... 05 ........................... July 7, 2004. 

A330–55–3020 ........................................................................................................................... 01 ........................... October 21, 1998. 

A340–27–4007 ........................................................................................................................... Original .................. April 7, 1994. 

A340–27–4025 ........................................................................................................................... Original .................. June 7, 1995. 

A340–27–4054 ........................................................................................................................... 01 ........................... November 26, 1997. 

A340–27–4057 ........................................................................................................................... Original .................. November 15, 1996. 

A340–27–4059 ........................................................................................................................... 03 ........................... December 5, 2001. 

A340–27–4089 ........................................................................................................................... 02 ........................... September 5, 2002. 

A340–27–4093, excluding Appendix 01 .................................................................................... 04 ........................... September 5, 2002. 

A340–27–4099 ........................................................................................................................... 01 ........................... September 5, 2002. 

A340–27–4107, excluding Appendix 01 .................................................................................... 04 ........................... June 20, 2003. 

A340–55–4021 ........................................................................................................................... 01 ........................... October 21, 1998. 

Airbus Service Bulletin A330–27–3007, 

Revision 01, contains the following effective 

pages:

Page No. 

Revision 

level 

shown on 

the page 

Date shown on the 

page 

1, 7 ........... 01 ............ September 18, 

1996. 

2–6 ........... Original .... October 5, 1994. 

(1) The incorporation by reference of the 

Airbus Service Bulletins in Table 3 of this 

AD is approved by the Director of the Federal 

Register in accordance with 5 U.S.C. 552(a) 

and 1 CFR part 51. 

(2) The incorporation by reference of 

Airbus All Operators Telex A330–27A3088, 

dated April 5, 2001; and Airbus All 

Operators Telex A340–27A4093, dated April 

5, 2001; was approved previously by the 

Director of the Federal Register as of June 26, 

2001 (66 FR 31143, June 11, 2001). 

(3) To get copies of this service 

information, go to Airbus, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France. To inspect copies of this service 

information, go to the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue, 

SW., Renton, Washington; or to 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.

Note 8: The subject of this AD is addressed 

in French airworthiness directives F–2002–

414 R3, dated July 7, 2004, and 2002–415(B) 

R2, dated October 30, 2002.

Effective Date 

(m) This amendment becomes effective on 

May 4, 2005.

Issued in Renton, Washington, on March 

17, 2005. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 05–6111 Filed 3–29–05; 8:45 am] 

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