Federal Register / Vol. 70, No. 165 / Friday, August 26, 2005 / Rules and Regulations 50157 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–20794; Directorate 

Identifier 2004–NM–172–AD; Amendment 

39–14235; AD 2005–17–14] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 B2 and B4 Series Airplanes; 

Model A300 B4–600, B4–600R, and F4– 

600R Series Airplanes, and Model A300 

C4–605R Variant F Airplanes 

(Collectively Called A300–600 Series 

Airplanes); and Model A310–200 and 

–300 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to all Airbus Model A300 

B2 and B4 series airplanes; Model 

A300–600 series airplanes; and Model 

A310–200 and –300 series airplanes. 

That AD currently requires, among other 

actions, repetitive tests to detect 

desynchronization of the rudder servo 

actuators, and adjustment or 

replacement of the spring rods of the 

rudder servo actuators, if necessary. 

This new AD requires new repetitive 

tests/inspections/analyses of the rudder 

servo actuators, and related 

investigative/corrective actions if 

necessary. Accomplishment of the new 

actions ends the existing repetitive 

requirements. This AD is prompted by 

new reports of desynchronization of the 

rudder servo actuators. We are issuing 

this AD to prevent desynchronization of 

one of the three rudder servo actuators, 

which, if combined with an engine 

failure, could result in the loss of the 

related hydraulic system and could 

cause the loss of one of the two 

synchronized actuators. This condition 

could create additional fatigue loading 

and possible cracking on the attachment 

fittings and could result in the inability 

of the remaining synchronized actuator 

to maintain the commanded rudder 

deflection, which could result in 

reduced controllability of the airplane. 

DATES: This AD becomes effective 

September 30, 2005. 

The incorporation by reference of 

certain publications listed in the AD is 

approved by the Director of the Federal 

Register as of September 30, 2005. 

On July 30, 1998 (63 FR 34580, June 

25, 1998), the Director of the Federal 

Register approved the incorporation by 

reference of certain other publications 

listed in the AD. 

ADDRESSES: For service information 

identified in this AD, contact Airbus, 1 

Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France. 

Docket: The AD docket contains the 

proposed AD, comments, and any final 

disposition. 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 U.S. Department of Transportation, 

400 Seventh Street, SW., room PL–401, 

Washington, DC. This docket number is 

FAA–2005–20794; the directorate 

identifier for this docket is 2004–NM– 

172–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: The FAA 

proposed to amend part 39 of the 

Federal Aviation Regulations (14 CFR 

part 39) with an AD to supersede AD 

98–13–33, amendment 39–10624 (63 FR 

34580, June 25, 1998). The existing AD 

applies to all Airbus Model A300 B2 

and B4 series airplanes; Model A300 

B4–600, B4–600R, and F4–600R series 

airplanes, and Model A300 C4–605R 

Variant F airplanes (collectively called 

A300–600 series airplanes); and Model 

A310–200 and –300 series airplanes. 

The proposed AD was published in the 

Federal Register on April 5, 2005 (70 FR 

17212), to continue to require repetitive 

tests to detect desynchronization of the 

rudder servo actuators, and adjustment 

or replacement of the spring rods of the 

rudder servo actuators, if necessary. The 

proposed AD would also require new 

repetitive tests/inspections/ analyses of 

the rudder servo actuators, and related 

investigative/corrective actions if 

necessary. The proposed AD states that 

accomplishing the new actions ends the 

existing repetitive requirements. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments that have 

been submitted on the proposed AD. 

Request To Withdraw the Proposed AD 

The commenter states that it can find 

no compelling reason for the proposed 

AD. The commenter notes that it has 

been accomplishing the requirements of 

AD 98–13–33 for several years and has 

had no significant findings. The 

commenter states that it has previously 

accomplished the actions in the parallel 

French airworthiness directive, F–2004– 

092, dated June 23, 2004, which 

introduced the inspection for dead 

travel of the input lever of the rudder 

servo control due to an isolated incident 

with a single operator. The commenter 

asserts that this incident most likely 

resulted from improper assembly and 

testing of the servo control during repair 

and overhaul of the component. 

Therefore, the commenter does not see 

the value of or need for the inspection 

for dead travel. The commenter suggests 

that resolution of the discrepancy with 

the input lever of the rudder servo 

control should be addressed by revising 

the applicable component maintenance 

manual. 

We infer that the commenter is 

requesting that we withdraw the 

proposed AD. We do not agree. The 

information that we have received from 

the manufacturer and the Direction 

Ge ́ne ́rale de l’Aviation Civile (DGAC), 

which is the airworthiness authority for 

France, does not indicate that the 

malfunction or misadjustment of the 

spring rods of the rudder servo actuator 

is an isolated incident. We find that the 

new repetitive tests, inspections, and 

analyses of the rudder servo actuators 

that will be newly required by this AD 

are necessary to ensure that all potential 

causes of desynchronization of the 

rudder servo actuators are addressed. As 

explained previously, 

desynchronization of one of the three 

rudder servo actuators, if combined 

with an engine failure, could result in 

the loss of the related hydraulic system 

and, potentially, loss of one of the two 

synchronized actuators. This condition 

could create additional fatigue loading 

and possible cracking on the attachment 

fittings and could result in the inability 

of the remaining synchronized actuator 

to maintain the commanded rudder 

deflection, which could result in 

reduced controllability of the airplane. 

The tests, inspections, and analyses, as 

well as any necessary investigative and 

corrective actions, required by this AD 

are intended to address this unsafe 

condition. We have not changed the 

final rule in this regard. 

Request To Remove Reporting 

Requirement 

The commenter declares that the 

reporting requirement included in 

paragraph (n) of the proposed AD is 

unnecessary and does not enhance the 

value of the proposed requirements. The 

50158 Federal Register / Vol. 70, No. 165 / Friday, August 26, 2005 / Rules and Regulations 

commenter states that reporting data at 

this point would not be relevant because 

there have been numerous opportunities 

to correct the unsafe condition prior to 

the proposed AD. 

We partially agree with the 

commenter’s request. Reporting any 

discrepancy will help to determine the 

extent of the unsafe condition in the 

affected fleet. Based on the results of 

these reports, we may determine that 

further investigative or corrective action 

is necessary. Reporting any discrepancy 

may also help us to determine if other 

conditions, as yet undetected, are 

present in the fleet, which could lead to 

desynchronization of the rudder servo 

actuators. For these reasons, this AD 

will continue to require reporting any 

discrepancy in accordance with the 

applicable referenced Airbus service 

bulletin. 

However, we have determined that it 

is not necessary to require reporting the 

inspection results in which there are no 

findings. Thus, we have revised 

paragraph (n) of this AD to specify that 

only positive findings must be reported. 

Explanation of Change to Applicability 

We have revised the applicability of 

this AD to identify model designations 

as published in the most recent type 

certificate data sheet for the affected 

models. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

that have been submitted, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We have determined that these changes 

will neither increase the economic 

burden on any operator nor increase the 

scope of the AD. 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD. The average labor 

rate is $65 per hour. 

ESTIMATED COSTS

Action Work hour Parts 

Cost per airplane, per 

cycle 

Number of 

U.S.-registered 

airplanes 

Fleet cost per 

cycle 

Tests (required by AD 98–13–13) ......................................... 1 None ............ $65 179 $11,635 

Tests/inspections/analyses (new requirement) ..................... 1 None ............ 65 179 11,635 

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 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 this AD: 

(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. 

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: 

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 

removing amendment 39–10624 (63 FR 

34580, June 25, 1998) and by adding the 

following new airworthiness directive 

(AD): 

2005–17–14 Airbus: Amendment 39–14235. 

Docket No. FAA–2005–20794; 

Directorate Identifier 2004–NM–172–AD. 

Effective Date 

(a) This AD becomes effective September 

30, 2005. 

Affected ADs 

(b) This AD supersedes AD 98–13–33, 

amendment 39–10624 (63 FR 34580, June 25, 

1998). 

Applicability 

(c) This AD applies to all Airbus Model 

A300 B2–1A, B2–1C, B2K–3C, and B2–203 

airplanes; Model A300 B4–2C, B4–103, and 

B4–203 airplanes; Model A300 B4–601, B4– 

603, B4–605R, B4–620, B4–622, B4–622R, 

C4–605R Variant F, F4–605R, and F4–622R 

airplanes; and Model A310–203, –204, –221, 

–222, –304, –322, –324, and –325 airplanes; 

certificated in any category. 

Unsafe Condition 

(d) This AD was prompted by new reports 

of desynchronization of the rudder servo 

actuators. We are issuing this AD to prevent 

desynchronization of one of the three rudder 

servo actuators, which, if combined with an 

engine failure, could result in the loss of the 

related hydraulic system and could cause the 

loss of one of the two synchronized actuators. 

This condition could create additional 

fatigue loading and possible cracking on the 

attachment fittings and could result in the 

inability of the remaining synchronized 

actuator to maintain the commanded rudder 

deflection, which could result in reduced 

controllability of the airplane. 

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. 

Federal Register / Vol. 70, No. 165 / Friday, August 26, 2005 / Rules and Regulations 50159 

Requirements of AD 98–13–33 

Repetitive Tests and Adjustment or 

Replacement 

(f) Prior to accumulation of 1,300 total 

flight hours, or within 500 flight hours after 

July 30, 1998 (the effective date of AD 98– 

13–33), whichever occurs later, and 

thereafter at intervals not to exceed 1,300 

flight hours: Perform a test to detect 

desynchronization of the rudder servo 

actuators in accordance with Airbus Service 

Bulletin A300–27–0188, Revision 2, dated 

October 1, 1997 (for Model A300 series 

airplanes); A300–27–6036, Revision 2, dated 

October 1, 1997 (for Model A300–600 series 

airplanes); or A310–27–2082, Revision 2, 

dated October 1, 1997 (for Model A310–200 

and –300 series airplanes); as applicable. If 

any desynchronization (rudder movement) is 

detected, prior to further flight, either adjust 

or replace, as applicable, the spring rod of the 

affected rudder servo actuator in accordance 

with the applicable service bulletin. 

Note 1: A test to detect desynchronization 

of the rudder servo actuators, if 

accomplished prior to the effective date of 

this AD in accordance with Airbus Service 

Bulletin A300–27–0188, dated October 24, 

1996, or Revision 1, dated November 5, 1996 

(for Model A300 series airplanes); A300–27– 

6036, dated October 24, 1996, or Revision 1, 

dated November 5, 1996 (for Model A300– 

600 series airplanes); or A310–27–2082, 

dated October 24, 1996, or Revision 1, dated 

November 5, 1996 (for Model A310–200 and 

–300 series airplanes); is considered 

acceptable for compliance with the initial 

test required by paragraph (f) of this AD. 

(g) Except as provided by paragraph (h) of 

this AD, if any desynchronization (rudder 

movement) greater than the limit specified in 

Paragraph B of the Accomplishment 

Instructions of the applicable service bulletin 

is detected during any test required by 

paragraph (f) of this AD, prior to further 

flight, accomplish either paragraph (g)(1) or 

(g)(2) of this AD, in accordance with Airbus 

Service Bulletin A300–55–0044, dated 

October 22, 1996 (for Model A300 series 

airplanes); A300–55–6023, dated October 22, 

1996 (for Model A300–600 series airplanes); 

or A310–55–2026, dated October 22, 1996 

(for Model A310 series airplanes); as 

applicable. 

(1) Conduct a visual inspection, high 

frequency eddy current inspection, or 

ultrasonic inspection, as applicable, to detect 

cracking of the rudder attachments; and 

repeat the inspection thereafter, as 

applicable, at the intervals specified in the 

applicable service bulletin. Or 

(2) Modify the rudder attachments to cold 

expand the rivet holes. 

(h) If any crack is found during any 

inspection or modification required by 

paragraph (g) of this AD, and the applicable 

service bulletin specifies to contact Airbus 

for an appropriate action: Prior to further 

flight, repair the affected structure in 

accordance with a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA, or in 

accordance with a method approved by the 

Direction Ge ́ne ́rale de l’Aviation Civile 

(DGAC). 

New Requirements of This AD 

Service Bulletins 

(i) The term ‘‘primary service bulletin,’’ as 

hereafter used in this AD, means the 

Accomplishment Instructions of the 

applicable primary service bulletin in Table 

1 of this AD. 

TABLE 1.—PRIMARY SERVICE BULLETINS

Airbus service bulletin— For— 

(1) A300–27–0188, including Appendix 01 and Reporting Sheet, Revision 05, dated April 16, 

2004.

Model A300 B2 and B4 series airplanes. 

(2) A300–27–6036, including Appendix 01 and Reporting Sheet, Revision 08, dated April 16, 

2004.

Model A300–600 series airplanes. 

(3) A310–27–2082, including Appendix 01 and Reporting Sheet, Revision 05, dated April 16, 

2004.

Model A310–200 and –300 series airplanes. 

(j) The primary service bulletin refers to 

the applicable secondary service bulletin in 

Table 2 of this AD as an additional source of 

service information for accomplishing the 

related investigative actions for certain 

conditions. 

TABLE 2.—SECONDARY SERVICE BULLETINS

Airbus service bulletin— For— 

(1) A300–55–0044, Revision 03, dated April 16, 2004 .................................................................. Model A300 B2 and B4 series airplanes. 

(2) A310–55–2026, Revision 02, dated April 16, 2004 .................................................................. Model A310–200 and –300 series airplanes. 

(3) A300–55–6023, Revision 05, dated April 16, 2004 .................................................................. Model A300–600 series airplanes. 

Compliance Times 

(k) Do the actions specified in paragraph (l) 

of this AD at the following times: 

(1) Within 700 flight hours after the 

effective date of this AD or within 1,300 

flight hours after the last inspection required 

by either paragraph (f) or (g) of this AD, 

whichever occurs first; and 

(2) Thereafter at intervals not to exceed 

1,300 flight hours. 

Tests/Inspections/Analyses and Related 

Investigative/Corrective Actions 

(l) Do the actions specified in paragraphs 

(l)(1) through (l)(4) of this AD and any 

applicable related investigative/corrective 

actions by doing all the actions in accordance 

with the primary service bulletin, except as 

required by paragraph (m) of this AD. Related 

investigative and corrective actions must be 

done before further flight. Accomplishing 

these actions ends the requirements of 

paragraphs (f) through (h) of this AD. 

(1) Do an operational test of the rudder 

system with each hydraulic system 

pressurized in turn. 

(2) Do a static inspection for correct 

synchronization of the rudder servo controls 

with each hydraulic system. 

(3) Inspect to find dead travel of the input 

lever of the rudder servo control for each 

hydraulic system. 

(4) Analyze the results of the static 

inspection required by paragraph (l)(2) of this 

AD and the inspection to find dead travel 

required by paragraph (l)(3) of this AD. 

(m) If the primary/secondary service 

bulletin recommends contacting Airbus for 

appropriate action: Before further flight, 

repair any discrepancy in accordance with a 

method approved by either the Manager, 

International Branch, ANM–116; or the 

DGAC (or its delegated agent). 

Reporting 

(n) At the applicable time specified in 

paragraph (n)(1) or (n)(2) of this AD, submit 

a report only of positive findings in 

accordance with the primary service bulletin. 

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 action specified in the primary 

service bulletin was done after the effective 

date of this AD: Submit the report within 30 

days after the inspection. 

(2) If the action specified in the primary 

service bulletin was accomplished before the 

50160 Federal Register / Vol. 70, No. 165 / Friday, August 26, 2005 / Rules and Regulations 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

Alternative Methods of Compliance (AMOCs) 

(o)(1) The Manager, International Branch, 

ANM–116, has the authority to approve 

AMOCs for this AD, if requested in 

accordance with the procedures found in 14 

CFR 39.19. 

(2) AMOCs approved previously according 

to AD 98–13–33 are not approved as AMOCs 

with this AD. 

Related Information 

(p) French airworthiness directive F–2004– 

092, issued June 23, 2004, also addresses the 

subject of this AD. 

Material Incorporated by Reference 

(q) You must use the service information 

listed in Table 3 of this AD to perform the 

actions that are required by this AD, unless 

the AD specifies otherwise. 

TABLE 3.—MATERIAL INCORPORATED BY REFERENCE

Airbus service bulletin Revision level Date 

A300–27–0188 ......................................................................................................................... 2 ............................................. October 1, 1997. 

A300–27–0188, including Appendix 01 and Reporting Sheet ................................................ 05 ........................................... April 16, 2004. 

A300–27–6036 ......................................................................................................................... 2 ............................................. October 1, 1997. 

A300–27–6036, including Appendix 01 and Reporting Sheet ................................................ 08 ........................................... April 16, 2004. 

A300–55–0044 ......................................................................................................................... Original ................................... October 22, 1996. 

A300–55–6023 ......................................................................................................................... Original ................................... October 22, 1996. 

A310–27–2082 ......................................................................................................................... 2 ............................................. October 1, 1997. 

A310–27–2082, including Appendix 01 and Reporting Sheet ................................................ 05 ........................................... April 16, 2004. 

A310–55–2026 ......................................................................................................................... Original ................................... October 22, 1996. 

(1) The Director of the Federal Register 

approves th incorporatin by reference of the 

service information listed in Table 4 of this 

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

1 CFR part 51. 

TABLE 4.—NEW MATERIAL INCORPORATED BY REFERENCE

Airbus service bulletin Revision level Date 

A300–27–0188, including Appendix 01 and Reporting Sheet ................................................ 05 ........................................... April 16, 2004. 

A300–27–6036, including Appendix 01 and Reporting Sheet ................................................ 08 ........................................... April 16, 2004. 

A310–27–2082, including Appendix 01 and Reporting Sheet ................................................ 05 ........................................... April 16, 2004. 

(2) On July 30, 1998 (63 FR 34580, June 25, 

1998), the Director of the Federal Register 

previously approved the incorporation by 

reference of the service information listed in 

Table 5 of this AD. 

TABLE 5.—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE

Airbus service bulletin Revision level Date 

A300–27–0188 ......................................................................................................................... 2 ............................................. October 1, 1997. 

A300–27–6036 ......................................................................................................................... 2 ............................................. October 1, 1997. 

A300–55–0044 ......................................................................................................................... Original ................................... October 22, 1996. 

A300–55–6023 ......................................................................................................................... Original ................................... October 22, 1996. 

A310–27–2082 ......................................................................................................................... 2 ............................................. October 1, 1997. 

A310–55–2026 ......................................................................................................................... Original ................................... October 22, 1996. 

(3) To get copies of the service information, 

contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France. To 

view the AD docket, go to the Docket 

Management Facility, U.S. Department of 

Transportation, 400 Seventh Street SW., 

room PL–401, Nassif Building, Washington, 

DC. To review copies of the service 

information, go 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/federalregister/cfr/ibr-locations.html. 

Issued in Renton, Washington, on August 

12, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–16749 Filed 8–25–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22168; Directorate 

Identifier 2005–NM–146–AD; Amendment 

39–14234; AD 2005–17–13] 

RIN 2120–AA64 

Airworthiness Directives; Short 

Brothers Model SD3–60 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT).