Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations 65187 

Issued in Renton, Washington, on October 

15, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–24943 Filed 10–30–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0665; Directorate 

Identifier 2012–NM–082–AD; Amendment 

39–17634; AD 2013–22–02] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A330–300 series airplanes 

and Model A340–200 and –300 series 

airplanes. This AD was prompted by 

reports of corrosion found on certain 

trimmable horizontal stabilizer actuators 

(THSA), affecting the ballscrew lower 

splines between the tie bar and the 

screw-jack. This AD requires repetitive 

detailed inspections for corrosion of 

certain THSAs, ballscrew integrity tests 

if necessary; and replacing any affected 

THSA with a serviceable or new and 

improved THSA, if necessary. We are 

issuing this AD to detect and correct 

corrosion of the THSAs, which could 

lead, in the case of ballscrew rupture, to 

the loss of transmission of THSA torque 

loads from the ballscrew to the tie-bar, 

prompting THSA blowback, and 

possibly resulting in loss of control of 

the airplane. 

DATES: This AD becomes effective 

December 5, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 5, 2013. 

ADDRESSES: You may examine the AD 

on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0665 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 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. For 

Goodrich service information identified 

in this AD, contact Goodrich 

Corporation, Actuation Systems, 

Product Support Department 13, 

Avenue de L’Eguillette—Saint-Ouen 

L’Aumone Boite Postale 7186 95056, 

Cergy Pontoise Cedex, France; fax: 33– 

1–34326310. You may view this 

referenced 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. 

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 by adding an AD that would 

apply to the specified products. The 

NPRM published in the Federal 

Register on August 1, 2013 (78 FR 

46543). 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 2012–0061R1, 

dated November 30, 2012 (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: 

Some Trimmable Horizontal Stabilizer 

Actuators (THSA), Part Number (P/N) 47147– 

500, have been found with corrosion, 

affecting the ballscrew lower splines between 

the tie bar and the screw-jack. 

The results of the technical investigations 

have identified that the corrosion was caused 

by a combination of: 

—Contact/friction between the tie bar and the 

inner surface of the ballscrew leading to 

the removal of Molykote (corrosion 

protection) at the level of the tie bar 

splines, 

—Humidity ingress initiating surface 

oxidation starting from areas where 

Molykote is removed, and 

—Water retention in THSA lower part 

leading to corrosion spread out and to the 

creation of a brown deposit (iron oxide). 

The results of the technical investigations 

have also concluded that THSA P/N 47147– 

500 and P/N 47147–700 ballscrews might be 

affected by this corrosion issue. 

THSA P/N 47147–400 ballscrews might be 

affected as well, but should no longer be in 

service, and modified into P/N 47147–500, as 

required by EASA AD 2010–0192 and EASA 

AD 2010–0193 [and as required by FAA AD 

2005–07–04, Amendment 39–14028 (70 FR 

16104, March 30, 2005)]. 

This condition, if not detected and 

corrected, may lead, in case of ballscrew 

rupture, to loss of transmission of THSA 

torque loads from the ballscrew to the tie-bar, 

prompting THSA blowback, possibly 

resulting in loss of control of the aeroplane. 

To correct this potential unsafe condition, 

EASA issued AD 2012–0061 to require 

repetitive [detailed] visual inspections of the 

ballscrew lower splines of THSA having P/ 

N 47147–500 or P/N 47147–700 to detect 

corrosion and, depending on findings 

[ballscrew integrity tests], the 

accomplishment of applicable corrective 

actions [replacing the affected THSA with a 

serviceable or improved THSA]. 

Since that [EASA] AD [2012–0061] was 

issued, Airbus published new Service 

Bulletin (SB) A330–27–3194 or Airbus SB 

A340–27–4187 (Airbus modification 202802), 

which allow installation in service of an 

improved THSA P/N 47172–530. 

For the reasons described above, this 

[EASA] AD [2012–0061R1] is revised to 

specify that installation of THSA P/N 47172– 

530 is an alternative (optional) terminating 

action to the repetitive inspections required 

by this AD. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0665- 

0002. 

Relevant Service Information 

We have received Airbus Mandatory 

Service Bulletins A330–27–3179 and 

A340–27–4175, both Revision 01, both 

dated June 13, 2013; which specify no 

additional work. We have updated 

paragraphs (g), (i), and (n) of this final 

rule to reference this service 

information. We have also added new 

paragraph (m) to this final rule to allow 

credit for the actions specified in 

paragraphs (g), (i), and (n) of this final 

rule, if those actions were performed 

before the effective date of this AD using 

Airbus Mandatory Service Bulletins 

A330–27–3179, dated February 14, 

2012; or A340–27–4175, dated February 

14, 2012. Subsequent paragraphs have 

been re-designated accordingly. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (78 

FR 46543, August 1, 2013) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 


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65188 Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations 

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 (78 FR 

46543, August 1, 2013) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 46543, 

August 1, 2013). 

Costs of Compliance 

Based on the service information, we 

estimate that this AD affects about 30 

products of U.S. registry. We also 

estimate that it takes about 6 work-hours 

per product to comply with the basic 

requirements of this AD. The average 

labor rate is $85 per work-hour. Based 

on these figures, we estimate the cost of 

this AD on U.S. operators to be $15,300, 

or $510 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 13 work-hours and require parts 

costing up to $722,556 for a cost of up 

to $723,661 per product. We have no 

way of determining the number of 

products that may need these actions. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave. SW., Washington, 

DC 20591. ATTN: Information 

Collection Clearance Officer, AES–200. 

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 MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0665- 

0002; 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 MCAI, 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. 

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 adding 

the following new AD: 

2013–22–02 Airbus: Amendment 39–17634. 

Docket No. FAA–2013–0665; Directorate 

Identifier 2012–NM–082–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective December 5, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A330– 

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

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

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

airplanes; certificated in any category; all 

manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight controls. 

(e) Reason 

This AD was prompted by reports of 

corrosion found on certain trimmable 

horizontal stabilizer actuators (THSA), 

affecting the ballscrew lower splines between 

the tie bar and the screw-jack. We are issuing 

this AD to detect and correct corrosion of the 

THSAs, which could lead, in the case of 

ballscrew rupture, to loss of transmission of 

THSA torque loads from the ballscrew to the 

tie-bar, prompting THSA blowback, and 

possibly resulting in loss of control 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) Repetitive Inspections 

At the applicable time specified in 

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

as required by paragraphs (h)(1) and (h)(2) of 

this AD: Do a detailed inspection of the gaps 

between the screw shaft and tie rod teeth of 

any THSA having part numbers (P/N) 47147– 

500 and 47147–700, to determine if the 

corrosion condition is Type I, Type II, or 

Type III, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–27–3179, 

Revision 01, dated June 13, 2013 (for Model 

A330–301, –302, –303, –321, –322, –323, 

–341, –342, and –343 airplanes); or A340– 

27–4175, Revision 01, dated June 13, 2013 

(for Model A340–211, –212, –213, –311, 

–312, and –313 airplanes); and the 

Accomplishment Instructions and flowchart 


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Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations 65189 

following the Accomplishment Instructions 

of Goodrich Actuation Systems Service 

Bulletin 47147–27–18, dated February 17, 

2012. Repeat the inspection thereafter at 

intervals not to exceed 24 months until the 

modification specified in paragraph (k) is 

done. 

(1) For any THSA, which, as of the 

effective date of this AD, has accumulated 

less than 156 months since its first flight on 

an airplane as THSA P/N 47147–400, or since 

its first flight after the modification specified 

in the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A330–27– 

3052 or A340–27–4059 has been done: Do the 

inspection before the accumulation of 156 

months but not before the accumulation of 

132 months since first flight on an airplane 

as THSA P/N 47147–400, or since the 

THSA’s first flight after the modification 

specified in the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–27–3052 or A340–27–4059 

has been done; or within 3 months after the 

effective date of this AD; whichever occurs 

later. 

(2) For any THSA, which, as of the 

effective date of this AD, has accumulated 

156 months or more since its first flight on 

an airplane as THSA P/N 47147–400, or since 

its first flight after the modification specified 

in the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A330–27– 

3052 or A340–27–4059 has been done: Do the 

inspection within 3 months after the effective 

date of this AD. 

(h) Compliance Time Exceptions 

(1) Some THSAs having P/N 47147–500 

(and further derivative with P/N 47147–700) 

were originally THSA P/N 47147–400 and 

were subsequently modified in service. In 

this case, the time accumulated by any THSA 

must be calculated from the first installation 

on airplanes as THSA P/N 47147–400. 

(2) Some THSAs having P/N 47147–500 

(and further derivative with P/N 47147–700) 

were originally THSA P/N 47147–200, –210, 

–213, –300, –303, or –350 and were 

subsequently modified in service as specified 

in the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A330–27– 

3052 or A340–27–4059. In this case, the time 

accumulated by any THSA must be 

calculated from the first flight on an airplane 

after the THSA has been modified as 

specified in the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–27–3052 or A340–27–4059. 

(i) Ballscrew Integrity Test and Corrective 

Actions 

If, during any inspection required by 

paragraph (g) of this AD, it is determined that 

a THSA has Type II or Type III corrosion: 

Before further flight, do a ballscrew integrity 

test, in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–27–3179, Revision 01, dated 

June 13, 2013 (for Model A330–301, –302, 

–303, –321, –322, –323, –341, –342, and –343 

airplanes); or A340–27–4175, Revision 01, 

dated June 13, 2013 (for Model A340–211, 

–212, –213, –311, –312, and –313 airplanes). 

(1) For THSAs having Type II or Type III 

corrosion, and on which the results of the 

ballscrew integrity test were not correct, as 

specified in the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–27–3179, Revision 01, dated 

June 13, 2013 (for Model A330–301, –302, 

–303, –321, –322, –323, –341, –342, and –343 

airplanes); or A340–27–4175, Revision 01, 

dated June 13, 2013 (for Model A340–211, 

–212, –213, –311, –312, and –313 airplanes): 

Before further flight, replace the affected 

THSA with a new or serviceable THSA, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–27–3179, Revision 01, dated 

June 13, 2013 (for Model A330–301, –302, 

–303, –321, –322, –323, –341, –342, and –343 

airplanes); or A340–27–4175, Revision 01, 

dated June 13, 2013 (for Model A340–211, 

–212, –213, –311, –312, and –313 airplanes). 

(2) For THSAs having Type III corrosion, 

and on which the results of the ballscrew 

integrity test are correct, as specified in the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–27–3179, 

Revision 01, dated June 13, 2013 (for Model 

A330–301, –302, –303, –321, –322, –323, 

–341, –342, and –343 airplanes); or A340– 

27–4175, Revision 01, dated June 13, 2013 

(for Model A340–211, –212, –213, –311, 

–312, and –313 airplanes): Within 10 days 

after the most recent inspection, replace the 

THSA with a new or serviceable THSA, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–27–3179, Revision 01, dated 

June 13, 2013 (for Model A330–301, –302, 

–303, –321, –322, –323, –341, –342, and –343 

airplanes); or A340–27–4175, Revision 01, 

dated June 13, 2013 (for Model A340–211, 

–212, –213, –311, –312, and –313 airplanes). 

(3) For THSAs having Type II corrosion, 

and on which the results of the ballscrew 

integrity test are correct: Within 24 months 

or 4,400 flight cycles after the most recent 

inspection, whichever occurs first, replace 

the THSA with a new or serviceable THSA, 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–27–3179, Revision 01, dated 

June 13, 2013 (for Model A330–301, –302, 

–303, –321, –322, –323, –341, –342, and –343 

airplanes); or A340–27–4175, Revision 01, 

dated June 13, 2013 (for Model A340–211, 

–212, –213, –311, –312, and –313 airplanes). 

(j) Replacement of a THSA Is Not 

Terminating Action 

Replacement of a THSA with a THSA 

having P/N 47147–500 or 47147–700 does 

not constitute a terminating action for the 

repetitive inspections required by paragraph 

(g) of this AD. 

(k) Optional Terminating Modification 

(1) Replacing any THSA having P/N 

47147–500 with a new improved THSA 

having P/N 47172–300 (Airbus modification 

200238), in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–27–3182 (for Model 

A330–301, –302, –303, –321, –322, –323, 

–341, –342, and –343 airplanes); or A340– 

27–4178 (for Model A340–211, –212, –213, 

–311, –312, and –313 airplanes); both dated 

February 14, 2012; terminates the repetitive 

inspections required by paragraph (g) of this 

AD. 

(2) Replacing any THSA having P/N 

47147–700 with a new improved THSA 

having P/N 47172–530 (Airbus modification 

202802), in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–27–3194 (for Model 

A330–301, –302, –303, –321, –322, –323, 

–341, –342, and –343 airplanes); or A340– 

27–4187 (for Model A340–211, –212, –213, 

–311, –312, and –313 airplanes); both dated 

October 8, 2012; terminates the repetitive 

inspections required by paragraph (g) of this 

AD. 

(l) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install a THSA, P/N 47147–500 

or P/N 47147–700, on any airplane, unless 

the THSA is classified as Type I (no 

corrosion), in accordance with the criteria 

defined in Goodrich Actuation Systems 

Service Bulletin 47147–27–18, dated 

February 17, 2012; and thereafter inspected 

in accordance with the requirements of 

paragraph (g) of this AD and any applicable 

actions required by paragraph (i) of this AD 

are accomplished. 

(m) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions specified in paragraphs (g), (i), and 

(n) of this AD, if those actions were 

performed before the effective date of this AD 

using Airbus Mandatory Service Bulletin 

A330–27–3179, dated February 14, 2012, 

which is not incorporated by reference in this 

AD. 

(2) This paragraph provides credit for the 

actions specified in paragraphs (g), (i), and 

(n) of this AD, if those actions were 

performed before the effective date of this AD 

using Airbus Mandatory Service Bulletin 

A340–27–4175, dated February 14, 2012, 

which is not incorporated by reference in this 

AD. 

(n) Reporting 

Submit a report of the findings (both 

positive and negative) of the inspection 

required by paragraph (g) of this AD to 

Airbus, at the applicable time specified in 

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

Appendix 01 of Airbus Mandatory Service 

Bulletin A330–27–3179, Revision 01, dated 

June 13, 2013 (for Model A330–301, –302, 

–303, –321, –322, –323, –341, –342, and –343 

airplanes); or A340–27–4175, Revision 01, 

dated June 13, 2013 (for Model A340–211, 

–212, –213, –311, –312, and –313 airplanes). 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 90 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 90 days after the effective date of this 

AD. 

(o) 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 


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65190 Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations 

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-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. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(p) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2012–0061R1, dated 

November 30, 2012, for related information. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2013-0665-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be obtained at the addresses specified in 

paragraphs (q)(3) and (q)(4) of this AD. 

(q) 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 this AD specifies otherwise. 

(i) Airbus Mandatory Service Bulletin 

A330–27–3179, Including Appendix 01, 

Revision 01, dated June 13, 2013. 

(ii) Airbus Service Bulletin A330–27–3182, 

dated February 14, 2012. 

(iii) Airbus Service Bulletin A330–27– 

3194, dated October 8, 2012. 

(iv) Airbus Mandatory Service Bulletin 

A340–27–4175, including Appendix 01, 

Revision 01, dated June 13, 2013. 

(v) Airbus Service Bulletin A340–27–4178, 

dated February 14, 2012. 

(vi) Airbus Service Bulletin A340–27– 

4187, dated October 8, 2012. 

(vii) Goodrich Actuation Systems Service 

Bulletin 47147–27–18, dated February 17, 

2012. 

(3) 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. For Goodrich Actuation 

Systems service information identified in this 

AD, contact Goodrich Corporation, Actuation 

Systems, Product Support Department 13, 

Avenue de L’Eguillette—Saint-Ouen 

L’Aumone Boite Postale 7186 95056, Cergy 

Pontoise Cedex, France; fax: 33–1–34326310. 

(4) 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. 

(5) 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 October 

15, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–25130 Filed 10–30–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0332; Directorate 

Identifier 2013–NM–009–AD; Amendment 

39–17637; AD 2013–22–05] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model CL–600–2B16 

(CL–601–3A, CL–601–3R, and CL–604 

Variants) airplanes. This AD was 

prompted by reports of airspeed 

mismatch between the pilot and copilot’s airspeed indicators, which 

occurred during or after heavy rain. This 

AD requires, for certain airplanes, 

inspecting for drain bottles having 

certain part numbers, and replacing 

affected drain bottles. This AD requires, 

for certain other airplanes, replacing 

drain bottles. We are issuing this AD to 

prevent pitot static tubing from 

becoming blocked by water, which if 

not corrected, could lead to erroneous 

airspeed and altitude indications, and 

consequent loss of control of the 

airplane. 

DATES: This AD becomes effective 

December 5, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of December 5, 2013. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0332; 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 service information identified in 

this AD, contact Bombardier, Inc., 400 

Coˆte-Vertu Road West, Dorval, Que ́bec 

H4S 1Y9, Canada; telephone 514–855– 

5000; fax 514–855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.com. You may review 

copies of the referenced 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. 

FOR FURTHER INFORMATION CONTACT: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office (ACO), 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7318; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to the specified products. The 

NPRM was published in the Federal 

Register on April 17, 2013 (78 FR 

22806). The NPRM proposed to correct 

an unsafe condition for the specified 

products. 

Transport Canada Civil Aviation, 

which is the aviation authority for 

Canada, has issued Canadian 


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