Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations 47537 

FIGURE 1 TO PARAGRAPH (c)—TGB RADIAL GEARSHAFT P/N 1995M24P02 S/N’S—Continued 

FIA0JETL FIA0K62V FIA0KH9J FIA0J7VW 

FIA0JER8 FIA0HEGY FIA0HY8G FIA0J7VY 

FIA0J7WC FIA0HWKC FIA0HY8M FIA0J7VT 

FIA0JETE FIA0K3A0 FIA0HY8A FIA0J7WF 

FIA0K3AT FIA0JVRJ FIA0H0VG FIA0J7V6 

FIA0JJ59 FIA0K8AA FIA0K3AR FIA0K89G 

FIA0K3AW FIA0KCYT FIA0JETC FIA0K89K 

FIA0JVRN FIA0KH9T FIA0KH9W FIA0K89R 

FIA0JNH8 FIA0HEG1 FIA0JNJC FIA0KCYJ 

FIA0JETN FIA0HEG3 FIA0K63L FIA0JJ6G 

FIA0HY78 FIA0J7WJ FIA0KCYN FIA0JJ6A 

FIA0HY75 FIA0JER7 FIA0JVRG FIA0HY8K 

FIA0HEG0 FIA0JVRF FIA0HY8L FIA0HLY6 

FIA0KH9E FIA0K63K FIA0HY8J FIA0HLY0 

FIA0KH9F FIA0J7WK FIA0H0VH FIA0HLY1 

FIA0H0T9 FIA0JER5 FIA0H0VF FIA0HLY4 

FIA0HLY3 FIA0JETM 

(d) Unsafe Condition 

This AD was prompted by reports of 

three failures of TGB radial gearshafts 

which resulted in in-flight shutdowns 

(IFSDs). We are issuing this AD to 

prevent failure of the TGB radial 

gearshaft, which could result in IFSD of 

one or more engines, loss of thrust 

control, and damage to the airplane. 

(e) Compliance 

(1) Comply with this AD within the 

compliance times specified, unless 

already done. 

(2) Before further flight after the 

effective date of this AD, do not operate 

the airplane if more than one installed 

engine has a TGB radial gearshaft P/N 

and S/N listed in Figure 1 to paragraph 

(c) of this AD. 

(f) Mandatory Terminating Action 

No later than 60 days after the 

effective date of this AD, as terminating 

action to the requirements of paragraph 

(e) of this AD, replace all TGB radial 

gearshafts identified in Figure 1 to 

paragraph (c) of this AD that are 

installed on an airplane with TGB radial 

gearshafts that are eligible for 

installation. 

(g) Prohibition on Operation 

Sixty days after the effective date of 

this AD, do not operate any airplane 

that has an engine installed that has a 

TGB radial gearshaft P/N and S/N listed 

in Figure 1 to paragraph (c) of this AD. 

(h) Definition 

For the purposes of this AD, a TGB 

radial gearshaft eligible for installation 

is: 

(1) A TGB radial gearshaft P/N and S/ 

N, not listed in this AD or 

(2) A TGB radial gearshaft with an S/ 

N listed in paragraph (c) of this AD with 

part number 1995M24P04, 2205M61P01 

or 2205M61P02. 

(i) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification 

Office, FAA, may approve AMOCs for 

this AD. Use the procedures in 14 CFR 

39.19 to make your request. 

(j) Related Information 

(1) For more information about this 

AD, contact Carlos Fernandes, 

Aerospace Engineer, Engine 

Certification Office, FAA, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7189; fax: 781– 

238–7199; email: 

carlos.fernandes@faa.gov. 

(2) GE GE90–100 Series Alert Service 

Bulletin No. GE90–100 S/B 72–A0568, 

Revision 0, dated July 10, 2013; GE 

GE90–100 Series Service Bulletin (SB) 

No. GE90–100 S/B 72–0569, Revision 0, 

dated July 19, 2013; GE GE90–100 

Series SB No. GE90–100 S/B 72–0563, 

Revision 0, dated June 21, 2013, and 

Revision 1, dated July 10, 2013; GE 

GE90 SB No. GE90 S/B 72–1066, 

Revision 0, dated June 21, 2013; and GE 

GE90 SB No. GE90 S/B 72–1091, 

Revision 0, dated June 11, 2013, can be 

obtained from GE using the contact 

information in paragraph (j)(3) of this 

AD. 

(3) For service information identified 

in this AD, contact General Electric 

Company, One Neumann Way, Room 

285, Cincinnati, OH; phone: 513–552– 

3272; email: geae.aoc@ge.com. 

(4) You may view this service 

information at the FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

(k) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

July 25, 2013. 

Frank P. Paskiewicz, 

Acting Director, Aircraft Certification Service. 

[FR Doc. 2013–18840 Filed 8–5–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1033; Directorate 

Identifier 2010–NM–266–AD; Amendment 

39–17504; AD 2013–13–16] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2005–07– 

04 for all Airbus Model A330–200 and 

–300 series airplanes, and Model A340– 

200 and –300 series airplanes. AD 2005– 

07–04 required 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; repetitive inspections for 

discrepancies of the ball screw 

assembly, and corrective action if 

necessary; repetitive greasing of the 

THSA ball nut, and replacement of the 

THSA if necessary; and modification or 

replacement (as applicable) of the ball 

nut assembly, which ends certain 

repetitive inspections. This new AD 

removes certain inspections, revises 

certain actions, and adds airplanes to 

the applicability. This AD was 

prompted by several reports of 


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47538 Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations 

disconnection of the transfer tube from 

the ball nut of the THSA. We are issuing 

this AD to prevent degraded operation 

of the THSA, which could result in 

reduced controllability of the airplane. 

DATES: This AD becomes effective 

September 10, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 10, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of May 4, 2005 (70 FR 16104, 

March 30, 2005). 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–1138; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. The 

NPRM was published in the Federal 

Register on October 2, 2012 (77 FR 

60075), and proposed to supersede AD 

2005–07–04, Amendment 39–14028 (70 

FR 16104, March 30, 2005). (AD 2005– 

07–04 superseded AD 2001–11–09, 

Amendment 39–12252 (66 FR 31143, 

June 11, 2001).) The NPRM proposed to 

correct an unsafe condition for the 

specified products. The European 

Aviation Safety Agency (EASA), which 

is the Technical Agent for the Member 

States of the European Community, has 

issued EASA Airworthiness Directive 

2010–0192 (corrected), dated October 

11, 2010; and EASA Airworthiness 

Directive 2010–0193 (corrected), dated 

October 11, 2010; (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

Several cases of transfer tube 

disconnection from the ball-nut of the 

trimmable horizontal stabilizer actuator 

(THSA) part number (P/N) 47172 and 47147– 

400 were detected on the ground during 

greasing and maintenance. 

This condition is caused by water ingress 

into the ball-nut resulting in the jamming of 

the ball transfer circuit when the water 

freezes. 

If the three (independent) ball circuits fail, 

then the THSA will operate on a fail-safe nut. 

This nut (which operates without balls) 

would then jam after several movements on 

the screw of the THSA. 

This degraded operation is not detectable 

in the cockpit by the crew as long as the 

THSA does not jam and could damage the 

ball screw and the fail-safe nut. 

To detect this unsafe condition, [Direccio ́n 

General de Aviacio ́n Civil] DGAC France AD 

F–2001–356 [and F–2001–357] was issued to 

require repetitive inspections of the transfer 

tubes and their collars in order to detect at 

an early stage any distortion or initiation of 

disconnection. 

Further to a new case of transfer tube 

disconnection, * * * [revised DGAC ADs] 

required an additional repetitive greasing 

task with reinforcement of the ball-nut 

maintenance greasing instructions. 

In addition, the electrical flight control 

computers monitor the operation of the 

THSA and the jamming of this actuator could 

be detected and indicated by messages on the 

maintenance system and on the ECAM 

[electronic centralized aircraft monitor]. In 

this case a mandatory inspection of the 

THSA is required before the next flight. 

DGAC France AD F–2002–038 [and F– 

2002–037] required application of a final fix 

(related to inspection and greasing task 

required by DGAC France AD F–2001–356 

[and F–2001–357]) for the THSA P/N 47172 

by application of Airbus modification 49590/ 

Service Bulletin (SB) A330–27–3085 [or SB 

A340–27–4089]. It changes the THSA P/N 

from 47172 to 47172–300. 

Later on, DGAC France AD F–2002–414R3 

replaced the DGAC AD France F–2001– 

356R2 and F–2002–038 [and DGAC France 

AD F2002–415R2 superseded DGAC France 

ADs F–2001–357R2 and F–2002–037] 

requiring: 

—the repetitive [detailed] inspection [for 

discrepancies] of all THSA P/N in service 

[for integrity of the primary and secondary 

load path and check the Checkable Shear 

Pins (CSPs)], and 

—the lubrication of some THSA P/N, and 

—the replacement of THSA P/N 47172, 

47147–400 and 47147–2XX/–3XX 

[DGAC France AD F–2002–414R3 and F– 

2002–415R2 correspond to FAA AD 2005– 

07–04, Amendment 39–14028 (70 FR 16104, 

March 30, 2005).] 

Airbus has later introduced 4 new THSA 

P/N (47172–500, 47172–510, 47172–520 and 

47172–530). 

This [EASA] AD retains the requirements 

of DGAC France AD F–2002–414R3 [and F– 

2002–415R2], which is superseded, and 

requires repetitive inspections and 

lubrications of the new THSA P/N. 

The repetitive inspection and lubrication 

requirements for THSA P/N 47172–520 and 

47172–530 shall [also] be included in the 

next Airworthiness Limitation Section (ALS) 

Part 4 revision. 

* * * * * 

Corrective actions include replacing 

the THSA with a new THSA if cracks, 

dents, or corrosion are found, or if the 

feeler gage has failed at any of the four 

gaps. Other corrective action includes 

using a method approved by the FAA or 

the EASA (or its delegated agent) for a 

finding of metallic debris, loose nut, 

damaged or missing lock washers, pins 

and parts, or incorrect installation of 

items. AD 2005–07–04, Amendment 39– 

14028 (70 FR 16104, March 30, 2005), 

required repetitive inspections for 

discrepancies. This AD requires, for 

certain airplanes, repetitive inspections 

for the integrity of the primary and 

secondary load path, and the CSPs. The 

unsafe condition is the degraded 

operation of the THSA, which could 

result in reduced controllability of the 

airplane. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request To Use Later Document 

Revision 

Delta Airlines (Delta) requested that 

paragraph (j)(2) of the NPRM (77 FR 

60075, October 2, 2012) refer to Airbus 

A330 Airworthiness Limitations Section 

(ALS) Part 4—Ageing Systems 

Maintenance, Revision 03, dated 

September 9, 2011; instead of Revision 

02, dated December 16, 2009. Delta 

stated that Revision 03 of that ALS 

specifies the 1,000 flight-hour 

lubrication threshold and repetitive 

interval that are specified in paragraph 

(j)(2) of the NPRM, whereas Revision 02 

of this ALS specifies 700 flight hours for 

the lubrication threshold and repetitive 

interval. 

We agree that Airbus A330 

Airworthiness Limitations Section 

(ALS) Part 4—Ageing Systems 

Maintenance, Revision 03, dated 

September 9, 2011, correctly specifies 

the lubrication threshold and repetitive 

interval. We have changed paragraph 

(j)(2) of this AD accordingly. In 

addition, we have changed paragraph 

(j)(2) of this AD to reference Airbus 

A340 ALS Part 4—Ageing Systems 

Maintenance, Revision 02, dated 

October 12, 2011; and Revision 03, 

dated November 15, 2012; for the same 

reason. 

Request To Change Wording 

Delta requested that we change the 

wording in paragraph (l) of the NPRM 

(77 FR 60075, October 2, 2012), which 

states ‘‘For airplanes identified in 

paragraph (k) of this AD.’’ The 

commenter asked that the wording 

‘‘identified in’’ be replaced with 


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Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations 47539 

‘‘affected by.’’ The commenter provided 

no reason for the change. 

We disagree to change the wording in 

paragraph (n) in this AD (identified as 

paragraph (l) in the NPRM (77 FR 

60075, October 2, 2012)) as requested by 

the commenter. However, we have 

moved the content of paragraphs (k)(1), 

(k)(2), and (k)(3) of the NPRM to new 

paragraph (l) in this AD to clarify the 

actions and affected airplanes. We have 

also moved the content of paragraph 

(k)(6) of the NPRM to new paragraph 

(m) of this AD, and re-identified 

succeeding paragraphs accordingly. 

Finally, in paragraph (n) of this AD, we 

revised the wording to describe the 

affected airplanes. 

Request To Include Additional Part 

Number 

Delta requested that we include THSA 

P/N 47172–520 and P/N ‘‘47127–530’’ 

in paragraph (m) of the NPRM (77 FR 

60075, October 2, 2012) as applicable 

part numbers for Model A330 series 

airplanes. 

We disagree to include THSA P/N 

47127–530 as there is no such part 

number. We infer that the commenter 

meant to specify THSA P/N 47172–530. 

THSA P/N 47172–520 and P/N 47172– 

530 are not included in the MCAI. 

However, all necessary tasks for those 

THSA part numbers are contained in 

Airbus A330 Airworthiness Limitations 

Section (ALS) Part 4—Ageing Systems 

Maintenance, Revision 03, dated 

September 9, 2011; and Airbus A340 

ALS Part 4—Ageing Systems 

Maintenance, Revision 02, dated 

October 12, 2011, and Revision 03, 

dated November 15, 2012. The FAA 

NPRMs to mandate these ALS Part 4 

documents are pending at this time. 

Therefore, we have not changed this AD 

in this regard. 

Request To Consider Another EASA AD 

Corinne Dayde stated that she 

‘‘Cannot see how EASA 2012–0061 is 

considered.’’ 

We are considering addressing EASA 

AD 2012–0061R1, dated November 30, 

2012, in a separate FAA AD. We have 

not changed this AD in this regard. 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously— 

and minor editorial changes. We have 

determined that these changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

60075, October 2, 2012) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 60075, 

October 2, 2012). 

Costs of Compliance 

We estimate that this AD will affect 

about 33 products of U.S. registry. 

The actions that are required by AD 

2005–07–04, Amendment 39–14028 (70 

FR 16104, March 30, 2005), and retained 

in this AD take up to 36 work-hours per 

product, at an average labor rate of $85 

per work-hour. Based on these figures, 

the estimated cost of the retained 

actions is up to $3,060 per product. 

We estimate that it will take about 2 

work-hours per product to comply with 

the new basic requirements of this AD. 

The average labor rate is $85 per workhour. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be $5,610, or $170 per 

product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

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 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 the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

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 airworthiness directive (AD) 

2005–07–04, Amendment 39–14028 (70 

FR 16104, March 30, 2005), and adding 

the following new AD: 

2013–13–16 Airbus: Amendment 39–17504. 

Docket No. FAA–2012–1033; Directorate 

Identifier 2010–NM–266–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective September 10, 2013. 

(b) Affected ADs 

This AD supersedes AD 2005–07–04, 

Amendment 39–14028 (70 FR 16104, March 

30, 2005). 

(c) Applicability 

This AD applies to all Airbus Model A330– 

201, –202, –203, –223, –223F, –243, –243F, 

–301, –302, –303, –321, –322, –323, –341, 

–342, and –343 airplanes; and Model A340– 


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47540 Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations 

211, –212, –213, –311, –312, and –313 

airplanes; certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27: Flight Controls. 

(e) Reason 

This AD was prompted by several reports 

of disconnection of the transfer tube from the 

ball nut of the trimmable horizontal stabilizer 

actuator (THSA). We are issuing this AD to 

prevent degraded operation of the THSA, 

which could result in reduced controllability 

of the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Retained Modification or Replacement 

This paragraph restates the requirements of 

paragraph (g) of AD 2005–07–04, 

Amendment 39–14028 (70 FR 16104, March 

30, 2005). Except for Model A330–223F and 

–243F airplanes: Within 24 months after May 

4, 2005 (the effective date of AD 2005–07– 

04), modify the ball nut of each THSA by 

doing paragraph (g)(1) or (g)(2) of this AD, as 

applicable. 

(1) For THSAs having part number (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 1 to paragraph (g)(1) of this AD: 

Airbus Service Bulletins A330–27–3085 and 

A340–27–4089, both Revision 02, both dated 

September 5, 2002, refer to TRW 

Aeronautical Systems Service Bulletin 

47172–27–03, dated October 24, 2001 (which 

is not incorporated by reference in this AD), 

as additional guidance for accomplishing the 

modification of the ball nut of the THSA. 

(2) For THSAs having P/N 47147–200, 

–210, –213, –300, –303, –350, or –400: 

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 airplanes), both 

Revision 01, both dated September 5, 2002; 

as applicable. 

Note 2 to paragraph (g)(2) of this AD: 

Airbus Service Bulletins A330–27–3093 and 

A340–27–4099, both Revision 01, both dated 

September 5, 2002, refer to TRW 

Aeronautical Systems Service Bulletin 

47147–27–10, dated June 27, 2002 (which is 

not incorporated by reference in this AD), as 

additional guidance for accomplishing the 

modification of the ball nut of the THSA. 

(h) Retained Previous/Concurrent 

Requirements 

This paragraph restates the requirements of 

paragraph (h) of AD 2005–07–04, 

Amendment 39–14028 (70 FR 16104, March 

30, 2005). 

(1) Except for Model A330–223F and 

–243F airplanes, prior to or concurrently 

with accomplishing 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 to paragraph 

(h)(1) of this AD, as applicable, in accordance 

with those service bulletins. 

Note 3 to paragraph (h)(1) of this AD: 

Airbus Service Bulletin A330–27–3093, 

Revision 01, dated September 5, 2002, 

specifies that the actions in Airbus Service 

Bulletin A330–27–3052 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 be accomplished 

previously or concurrently. 

Note 4 to paragraph (h)(1) of this AD: 

Airbus Service Bulletin A340–27–4099, 

Revision 01, dated September 5, 2002, 

specifies that the actions in Airbus Service 

Bulletin A340–27–4059 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 be accomplished 

previously or concurrently. 

TABLE 1 TO PARAGRAPH (h)(1) OF THIS AD—RETAINED PREVIOUS/CONCURRENT REQUIREMENTS FOR MODEL A330 

SERIES AIRPLANES

Airbus service 

bulletin— 

Revision 

level— Date— Main action— Additional source of guidance (not incorporated by reference in this AD)— 

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 ..... ................ 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 ..... ................ 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 TO PARAGRAPH (h)(1) OF THIS AD—RETAINED PREVIOUS/CONCURRENT REQUIREMENTS FOR MODEL A340 

SERIES AIRPLANES

Airbus service 

bulletin— 

Revision 

level— Date— Main action— Additional source of guidance (not incorporated by reference in this AD)— 

A340-27-4007 ..... ................ 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 ..... ................ 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. 


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Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations 47541 

TABLE 2 TO PARAGRAPH (h)(1) OF THIS AD—RETAINED PREVIOUS/CONCURRENT REQUIREMENTS FOR MODEL A340 

SERIES AIRPLANES—Continued 

Airbus service 

bulletin— 

Revision 

level— Date— Main action— Additional source of guidance (not incorporated by reference in this AD)— 

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 ..... ................ 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. 

(2) 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 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. 

(i) Retained Credit for Previous Actions 

(1) This paragraph provides credit for the 

requirements of paragraph (g)(1) of this AD, 

if those actions were performed before May 

4, 2005 (the effective date of AD 2005–07–04, 

Amendment 39–14028 (70 FR 16104, March 

30, 2005)), using 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 (which are not 

incorporated by reference in this AD), as 

applicable. 

(2) This paragraph provides credit for the 

requirements of paragraphs (g)(2) of this AD, 

if those actions were performed before May 

4, 2005 (the effective date of AD 2005–07–04, 

Amendment 39–14028 (70 FR 16104, March 

30, 2005)), using 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 (which are not 

incorporated by reference in this AD), as 

applicable. 

(j) New Repetitive Greasing Procedure 

(1) Within 700 flight hours after the 

effective date of this AD, or within 700 flight 

hours after the date of the last lubrication, 

whichever occurs later; and thereafter at 

intervals not to exceed 700 flight hours from 

the last lubrication of the trimmable 

horizontal stabilizer (THS) actuator ball 

screw nut: Perform Task 27.40.00/02, 

Lubrication of THS Actuator Ball Screw Nut, 

in accordance with Airbus A330 

Maintenance Review Board Report (MRBR), 

Revision 12, dated July 1, 2010 (for Model 

A330 series airplanes); or Airbus A340 

MRBR, Revision 12, dated July 1, 2010 (for 

Model A340 series airplanes); on all THSAs. 

(2) For airplanes identified in paragraphs 

(j)(2)(i), (j)(2)(ii), and (j)(2)(iii) of this AD, as 

applicable, lubrication of the THS actuator 

ball screw nut performed at a threshold of 

1,000 flight hours and a repetitive interval 

not exceeding 1,000 flight hours, in 

accordance with Task 274400–00002–1–E, 

Lubrication of the THSA Ball Nut, of Airbus 

A330 Airworthiness Limitations Section 

(ALS) Part 4—Ageing Systems Maintenance, 

Revision 03, dated September 9, 2011 (for 

Model A330 series airplanes); or Task 

274400–00002–1–E, Lubrication of the THSA 

Ball Nut, of Airbus A340 ALS Part 4—Ageing 

Systems Maintenance, Revision 02, dated 

October 12, 2011, or Revision 03, dated 

November 15, 2012 (for Model A340–200 and 

–300 series airplanes); is acceptable for 

compliance with the requirements of 

paragraph (j)(1) of this AD. 

(i) Airplanes on which Airbus 

Modifications 52269, 56056, and 55780 have 

been done in production. 

(ii) Model A330 series airplanes on which 

the actions specified in Airbus Mandatory 

Service Bulletin A330–27–3137, dated March 

20, 2007, or Revision 01, dated December 6, 

2007, or Revision 02, dated January 18, 2010; 

and Airbus Mandatory Service Bulletin 

A330–92–3046, Revision 04, dated July 16, 

2010, or Revision 05, dated November 7, 

2011; which are not incorporated by 

reference in this AD; have been done in 

service. 

(iii) Model A340–200 and –300 series 

airplanes on which the actions specified in 

Airbus Mandatory Service Bulletin A340–27– 

4136, dated March 20, 2007, Revision 01, 

dated December 6, 2007, or Revision 02, 

dated February 24, 2010; and Airbus 

Mandatory Service Bulletin A340–92–4056, 

Revision 03, dated July 16, 2010; which are 

not incorporated by reference in this AD; 

have been done in service. 

(k) New Repetitive Inspections of the Ball 

Screw Assembly and Corrective Actions 

For airplanes other than those identified in 

paragraphs (l)(1), (l)(2), and (l)(3) of this AD: 

Do the applicable actions specified in 

paragraphs (k)(1) and (k)(2) of this AD within 

700 flight hours after the effective date of this 

AD, and repeat the inspection thereafter at 

intervals not to exceed 700 flight hours. 

(1) For airplanes on which the actions 

specified in Airbus Mandatory Service 

Bulletin A330–27–3137, dated March 20, 

2007, Revision 01, dated December 6, 2007, 

or Revision 02, dated January 18, 2010 (for 

Model A330 series airplanes); or Airbus 

Mandatory Service Bulletin A340–27–4136, 

dated March 20, 2007, Revision 01, dated 

December 6, 2007, or Revision 02, dated 

February 24, 2010 (for Model A340–200 and 

–300 series airplanes); none of which are 

incorporated by reference in this AD; have 

been done: Do the applicable detailed 

inspection of the ball screw assembly for 

integrity of the primary and secondary load 

path and check the checkable shear pins 

(CSP), and do all applicable corrective 

actions, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–27–3102, 

Revision 08, dated December 6, 2007 (for 

Model A330 series airplanes); or Airbus 

Mandatory Service Bulletin A340–27–4107, 

Revision 08, dated December 6, 2007 (for 

Model A340–200 and –300 series airplanes); 

except as required by paragraph (m) of this 

AD. Do all applicable corrective actions 

before further flight. 

(2) For airplanes on which the actions 

specified in Airbus Mandatory Service 

Bulletin A330–27–3137, dated March 20, 

2007, Revision 01, dated December 6, 2007, 

or Revision 02, dated January 18, 2010 (for 

Model A330 series airplanes); or Airbus 

Mandatory Service Bulletin A340–27–4136, 

dated March 20, 2007, Revision 01, dated 

December 6, 2007, or Revision 02, dated 

February 24, 2010 (for Model A340–200 and 

–300 series airplanes); none of which are 

incorporated by reference in this AD; have 

not been done: Perform a detailed inspection 

of the ball screw assembly for integrity of the 

primary and secondary load path, and do all 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A330–27– 

3102, Revision 08, dated December 6, 2007 

(for Model A330 series airplanes); or Airbus 

Mandatory Service Bulletin A340–27–4107, 

Revision 08, dated December 6, 2007 (for 

Model A340 series airplanes); except as 

required by paragraph (m) of this AD. Do all 

applicable corrective actions before further 

flight. 


tkelley on DSK3SPTVN1PROD with RULES
47542 Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations 

(l) Certain Airplanes Excluded From 

Paragraphs (k) and (n) of This AD 

This paragraph specifies the airplanes 

excluded from the actions required by 

paragraphs (k) and (n) of this AD. 

(1) Airplanes on which the actions 

specified in Airbus Modifications 52269, 

56056, and 55780 have been done in 

production. 

(2) Model A330 series airplanes on which 

Airbus Mandatory Service Bulletin A330–27– 

3137, dated March 20, 2007, Revision 01, 

dated December 6, 2007, or Revision 02, 

dated January 18, 2010; and Airbus 

Mandatory Service Bulletin A330–92–3046, 

Revision 04, dated July 16, 2010, or Revision 

05, dated November 7, 2011; none of which 

are incorporated by reference in this AD; 

have been done in service. 

(3) Model A340–200 and –300 series 

airplanes on which the actions specified in 

Airbus Mandatory Service Bulletin A340–27– 

4136, dated March 20, 2007, Revision 01, 

dated December 6, 2007, or Revision 02, 

dated February 24, 2010; and Airbus 

Mandatory Service Bulletin A340–92–4056, 

Revision 03, dated July 16, 2010; have been 

done in service. 

(m) Service Information Exception 

Where Airbus Mandatory Service Bulletin 

A330–27–3102, Revision 08, dated December 

6, 2007 (for Model A330 series airplanes); or 

Airbus Mandatory Service Bulletin A340–27– 

4107, Revision 08, dated December 6, 2007 

(for Model A340 series airplanes); specify 

contacting Airbus for a damage assessment, 

this AD requires contacting the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA) (or its 

delegated agent); for required actions before 

further flight, and doing the specified actions 

within the times given. 

(n) New Actions for Electronic Centralized 

Aircraft Monitor (ECAM) Fault Messages 

For airplanes other than those identified in 

paragraphs (l)(1), (l)(2), and (l)(3) of this AD, 

if one of the ‘‘PRIM X PITCH FAULT’’ or 

‘‘STAB CTL FAULT’’ messages is displayed 

on the ECAM associated with the ‘‘PITCH 

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

the applicable detailed inspection and all 

applicable corrective actions specified in 

paragraph (k)(1) or (k)(2) of this AD, as 

applicable to airplane configuration, before 

further flight after the message is displayed 

on the ECAM. 

(o) New Optional Method of Compliance 

For airplanes having THSA P/N 47147– 

500, 47147–700, 47172–300, 47172–500, or 

47172–510, accomplishing the repetitive 

actions specified in paragraph (o)(1) or (o)(2) 

of this AD, as applicable, is acceptable for 

compliance with the corresponding actions 

specified in paragraph (k)(1) or (k)(2) of this 

AD, as applicable. 

(1) For Model A330 series airplanes: The 

repetitive actions specified in paragraphs 

(o)(1)(i) through (o)(1)(viii) of this AD. 

(i) Task 274400–00001–1–E of Airbus A330 

ALS Part 4—Ageing Systems Maintenance, 

Revision 02, dated December 16, 2009. 

(ii) Task 274400–00001–1–E of Airbus 

A330 ALS Part 4—Ageing Systems 

Maintenance, Revision 03, dated September 

9, 2011. 

(iii) Task 274400–00001–2–E of Airbus 

A330 ALS Part 4—Ageing Systems 

Maintenance, Revision 02, dated December 

16, 2009. 

(iv) Task 274400–00001–2–E of Airbus 

A330 ALS Part 4—Ageing Systems 

Maintenance, Revision 03, dated September 

9, 2011. 

(v) Task 274400–00001–3–E of Airbus 

A330 ALS Part 4—Ageing Systems 

Maintenance, Revision 02, dated December 

16, 2009. 

(vi) Task 274400–00001–3–E of Airbus 

A330 ALS Part 4—Ageing Systems 

Maintenance, Revision 03, dated September 

9, 2011. 

(vii) Task 274400–00001–4–E of Airbus 

A330 ALS Part 4—Ageing Systems 

Maintenance, Revision 02, dated December 

16, 2009. 

(viii) Task 274400–00001–4–E of Airbus 

A330 ALS Part 4—Ageing Systems 

Maintenance, Revision 03, dated September 

9, 2011. 

(2) For Model A340–200 and –300 series 

airplanes: The repetitive actions specified in 

paragraphs (o)(2)(i) through (o)(2)(viii) of this 

AD. 

(i) Task 274400–00001–1–E of Airbus A340 

ALS Part 4—Ageing Systems Maintenance, 

Revision 01, dated December 15, 2009. 

(ii) Task 274400–00001–1–E of Airbus 

A340 ALS Part 4—Ageing Systems 

Maintenance, Revision 02, dated October 12, 

2011. 

(iii) Task 274400–00001–2–E of Airbus 

A340 ALS Part 4—Ageing Systems 

Maintenance, Revision 01, dated December 

15, 2009. 

(iv) Task 274400–00001–2–E of Airbus 

A340 ALS Part 4—Ageing Systems 

Maintenance, Revision 02, dated October 12, 

2011. 

(v) Task 274400–00001–3–E of Airbus 

A340 ALS Part 4—Ageing Systems 

Maintenance, Revision 01, dated December 

15, 2009. 

(vi) Task 274400–00001–3–E of Airbus 

A340 ALS Part 4—Ageing Systems 

Maintenance, Revision 02, dated October 12, 

2011. 

(vii) Task 274400–00001–4–E of Airbus 

A340 ALS Part 4—Ageing Systems 

Maintenance, Revision 01, dated December 

15, 2009. 

(viii) Task 274400–00001–4–E of Airbus 

A340 ALS Part 4—Ageing Systems 

Maintenance, Revision 02, dated October 12, 

2011. 

(p) New Credit for Previous Actions 

(1) For Model A300 series airplanes: This 

paragraph provides credit for the actions 

specified in paragraph (j) of this AD, if those 

actions were performed before the effective 

date of this AD using Task 27.40.00/02, 

Lubrication of THS Actuator Ball Screw Nut, 

of Airbus A330 MRBR, Revision 11, dated 

June 18, 2008 (which is not incorporated by 

reference in this AD). 

(2) For Model A340 series airplanes: This 

paragraph provides credit for the actions 

specified in paragraph (j) of this AD, if those 

actions were performed before the effective 

date of this AD using Task 27.40.00/02, 

Lubrication of THS Actuator Ball Screw Nut, 

of Airbus A340 MRBR, Revision 11, dated 

June 18, 2008 (which is not incorporated by 

reference in this AD). 

(3) For Model A330 series airplanes: This 

paragraph provides credit for the inspections 

and corrective actions required by paragraph 

(k) of this AD, if those actions were 

performed before the effective date of this AD 

using the service information specified in 

paragraphs (p)(3)(i) through (p)(3)(vi) of this 

AD (which are not incorporated by reference 

in this AD). 

(i) Airbus Service Bulletin A330–27–3102, 

Revision 02, dated November 7, 2002. 

(ii) Airbus Service Bulletin A330–27–3102, 

Revision 03, dated June 20, 2003. 

(iii) Airbus Service Bulletin A330–27– 

3102, Revision 04, dated December 8, 2003. 

(iv) Airbus Mandatory Service Bulletin 

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

2004. 

(v) Airbus Mandatory Service Bulletin 

A330–27–3102, Revision 06, dated December 

16, 2005. 

(vi) Airbus Mandatory Service Bulletin 

A330–27–3102, Revision 07, dated March 16, 

2007. 

(4) For Model A340 series airplanes: This 

paragraph provides credit for the inspections 

and corrective actions required by paragraph 

(k) of this AD, if those actions were 

performed before the effective date of this AD 

using the service information specified in 

paragraphs (p)(4)(i) through (p)(4)(vi) of this 

AD (which are not incorporated by reference 

in this AD). 

(i) Airbus Mandatory Service Bulletin 

A340–27–4107, Revision 02, dated 

September 23, 2002. 

(ii) Airbus Service Bulletin A340–27–4107, 

Revision 03, dated December 4, 2002. 

(iii) Airbus Mandatory Service Bulletin 

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

2003. 

(iv) Airbus Mandatory Service Bulletin 

A340–27–4107, Revision 05, dated December 

8, 2003. 

(v) Airbus Mandatory Service Bulletin 

A340–27–4107, Revision 06, dated December 

16, 2005. 

(vi) Airbus Mandatory Service Bulletin 

A340–27–4107, Revision 07, dated March 16, 

2007. 

(q) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1138; fax (425) 227– 

1149. Information may be emailed to: 9- 


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Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations 47543 

ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(r) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2010–0192 

(corrected), dated October 11, 2010; and 

EASA Airworthiness Directive 2010–0193 

(corrected), dated October 11, 2010; for 

related information. This MCAI may be 

found in the AD docket on the Internet at 

http://www.regulations.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be obtained at the addresses specified in 

paragraphs (s)(5), (s)(6), and (s)(7) of this AD. 

(s) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on September 10, 2013. 

(i) Airbus Mandatory Service Bulletin 

A330–27–3102, Revision 08, dated December 

6, 2007. 

(ii) Airbus Mandatory Service Bulletin 

A340–27–4107, Revision 08, dated December 

6, 2007. 

(iii) Task 27.40.00/02, Lubrication of 

Trimmable Horizontal Stabilizer (THS) 

Actuator Ball Screw Nut, of Airbus A330 

Maintenance Review Board Report (MRBR), 

Revision 12, dated July 1, 2010. 

(iv) Task 27.40.00/02, Lubrication of THS 

Actuator Ball Screw Nut, of Airbus A340 

MRBR, Revision 12, dated July 1, 2010. 

(v) A330 Airworthiness Limitations 

Section (ALS) Part 4—Ageing Systems 

Maintenance, Revision 02, dated December 

16, 2009. Only the title page and Record of 

Revision of this document contain the 

revision level; no other page of the document 

contains this information. The title page of 

this document does not contain an issue date. 

(vi) Airbus A330 ALS Part 4—Ageing 

Systems Maintenance, Revision 03, dated 

September 9, 2011. Only the title page and 

Record of Revision of this document contain 

the revision level; no other page of the 

document contains this information. The title 

page of this document does not contain an 

issue date. 

(vii) Airbus A340 ALS Part 4—Ageing 

Systems Maintenance, Revision 01, dated 

December 15, 2009. Only the title page and 

Record of Revision of this document contains 

the revision level; no other page of this 

document contains this information. The title 

page of this document does not contain an 

issue date. 

(viii) Airbus A340 ALS Part 4—Ageing 

Systems Maintenance, Revision 02, dated 

October 12, 2011. Only the title page and 

Record of Revision of this document contain 

the revision level; no other page of the 

document contains this information. The title 

page of this document does not contain an 

issue date. 

(ix) Airbus A340 ALS Part 4—Ageing 

Systems Maintenance, Revision 03, dated 

November 15, 2012. Only the title page and 

Record of Revision of this document contain 

the revision level; no other page of the 

document contains this information. The title 

page of this document does not contain an 

issue date. 

(4) The following service information was 

approved for IBR on May 4, 2005 (60 FR 

16104, March 30, 2005). 

(i) Airbus Service Bulletin A330–27–3007, 

Revision 01, dated September 18, 1996. 

(ii) Airbus Service Bulletin A330–27–3015, 

dated June 7, 1995. 

(iii) Airbus Service Bulletin A330–27– 

3047, Revision 01, dated November 26, 1997. 

(iv) Airbus Service Bulletin A330–27– 

3050, dated November 15, 1996. 

(v) Airbus Service Bulletin A330–27–3052, 

Revision 03, dated December 5, 2001. 

(vi) Airbus Service Bulletin A330–27– 

3085, Revision 02, dated September 5, 2002. 

(vii) Airbus Service Bulletin A330–27– 

3093, Revision 01, dated September 5, 2002. 

(viii) Airbus Service Bulletin A330–55– 

3020, Revision 01, dated October 21, 1998. 

(ix) Airbus Service Bulletin A340–27– 

4007, dated April 7, 1994. 

(x) Airbus Service Bulletin A340–27–4025, 

dated June 7, 1995. 

(xi) Airbus Service Bulletin A340–27– 

4054, Revision 01, dated November 26, 1997. 

(xii) Airbus Service Bulletin A340–27– 

4057, dated November 15, 1996. 

(xiii) Airbus Service Bulletin A340–27– 

4059, Revision 03, dated December 5, 2001. 

(xiv) Airbus Service Bulletin A340–27– 

4089, Revision 02, dated September 5, 2002. 

(xv) Airbus Service Bulletin A340–27– 

4099, Revision 01, dated September 5, 2002. 

(xvi) Airbus Service Bulletin A340–55– 

4021, Revision 01, October 21, 1998. 

(5) For Airbus service information 

identified in this AD, contact Airbus SAS— 

Airworthiness Office—EAL, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France; telephone +33 5 61 93 36 96; fax +33 

5 61 93 45 80; email airworthiness.A330- 

A340@airbus.com; Internet: http:// 

www.airbus.com. 

(6) For TRW Aeronautical Systems, SAMM 

Avionique, and Lucas Aerospace service 

information identified in this AD, contact 

Goodrich Corporation, Actuation Systems, 

Stafford Road, Fordhouses, Wolverhampton 

WV10 7EH, England; telephone +44 (0) 1902 

624938; fax +44 (0) 1902 788100; email 

techpubs.wolverhampton@goodrich.com; 

Internet http://www.goodrich.com/TechPubs. 

(7) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

(8) You may view this service information 

that is incorporated by reference 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/cfr/ibrlocations.html. 

Issued in Renton, Washington, on June 21, 

2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–18774 Filed 8–5–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0209; Directorate 

Identifier 2012–NM–127–AD; Amendment 

39–17514; AD 2013–14–09] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2012–14– 

04 for certain Bombardier, Inc. Model 

DHC–8–100, –200, and –300 series 

airplanes. AD 2012–14–04 required 

replacing certain parking brake 

accumulators. This new AD retains this 

requirement. This new AD also requires 

installing restraint devices around the 

parking brake accumulator end caps. We 

are issuing this AD to prevent failure of 

a parking brake accumulator screw cap 

or end cap resulting in loss of the 

number 2 hydraulic system and damage 

to airplane structures, which could 

adversely affect the controllability of the 

airplane. 

DATES: This AD becomes effective 

September 10, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 10, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of August 27, 2012 (77 FR 

42956, July 23, 2012). 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 


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