Federal Register / Vol. 76, No. 25 / Monday, February 7, 2011 / Rules and Regulations 6543 

Mark 0100 airplanes, serial numbers 11244 

through 11441; certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 28: Fuel. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Prompted by an accident * * *, the FAA 

published Special Federal Aviation 

Regulation (SFAR) 88, and the Joint Aviation 

Authorities (JAA) published Interim Policy 

INT/POL/25/12. The design review 

conducted by Fokker on the F28 in response 

to these regulations revealed that, in case of 

a lightning strike, an ignition source can 

develop in the wing tank vapour space 

during fuel transfer from bag tank CWT 

[center wing tank], if the electrical power for 

refuelling is not switched off after refuelling. 

Service experience has revealed situations 

where the power switch of the Fuelling 

Control Panel (FCP) appeared to be ‘‘ON’’ 

with the access panel closed. The cam on the 

access panel that should operate the power 

switch, if forgotten by flight crew or 

maintenance staff, can pivot away during 

closing of the panel, which may result in the 

switch staying in the ‘‘ON’’ position. 

This condition, if not corrected, could 

result in a wing fuel tank explosion and 

consequent loss of the aeroplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Initial Inspection and Corrective Actions 

(g) Within 6 months after the effective date 

of this AD, inspect the FCP cam to determine 

the part number (P/N), in accordance with 

Part 1 of the Accomplishment Instructions of 

Fokker Service Bulletin SBF28–28–052, 

dated April 20, 2010 (for Model F.28 Mark 

1000, 2000, 3000, and 4000 airplanes); or 

SBF100–28–063, dated April 15, 2010 (for 

Model F.28 Mark 0100 airplanes). 

(1) If the correct part number is installed 

(P/N D48127–009 for Model F.28 Mark 0100 

airplanes and P/N A42509–089 for Model 

F.28 Mark 1000, 2000, 3000, and 4000 

airplanes), before further flight, do an 

inspection to verify that the cam operates 

correctly, in accordance with Part 1 of the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF28–28–052, dated April 

20, 2010 (for Model F.28 Mark 1000, 2000, 

3000, and 4000 airplanes); or SBF100–28– 

063, dated April 15, 2010 (for Model F.28 

Mark 0100 airplanes). 

(2) If a part number other than P/N 

D48127–009 for Model F.28 Mark 0100 

airplanes and P/N A42509–089 for Model 

F.28 Mark 1000, 2000, 3000, and 4000 

airplanes is installed, within 24 months after 

the effective date of this AD, replace the cam 

with a cam having a correct part number, and 

do an inspection to verify that the cam 

operates correctly, in accordance with Part 2 

of the Accomplishment Instructions of 

Fokker Service Bulletin SBF28–28–052, 

dated April 20, 2010 (for Model F.28 Mark 

1000, 2000, 3000, and 4000 airplanes); or 

SBF100–28–063, dated April 15, 2010 (for 

Model F.28 Mark 0100 airplanes). 

(3) If, during any inspection required by 

paragraphs (g)(1) and (g)(2) of this AD, the 

cam does not operate correctly, before further 

flight, adjust the cam until it operates 

correctly, in accordance with Part 2 of the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF28–28–052, dated April 

20, 2010 (for Model F.28 Mark 1000, 2000, 

3000, and 4000 airplanes); or SBF100–28– 

063, dated April 15, 2010 (for Model F.28 

Mark 0100 airplanes). 

Repetitive Inspections 

(h) Within 1,200 flight hours after verifying 

that the cam operates correctly, as required 

by paragraphs (g)(1) and (g)(2) of this AD, as 

applicable: Do an inspection to verify that the 

cam operates correctly and, before further 

flight, do all applicable corrective actions, in 

accordance with Part 2 of the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF28–28–052, dated April 

20, 2010 (for Model F.28 Mark 1000, 2000, 

3000, and 4000 airplanes); or SBF100–28– 

063, dated April 15, 2010 (for Model F.28 

Mark 0100 airplanes). Thereafter, repeat the 

inspection of the cam at intervals not to 

exceed 1,200 flight hours. 

Parts Installation 

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

person may install an FCP access door, cam, 

or fueling panel on any airplane, unless the 

requirements of this AD have been 

accomplished on the cam. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: 

Although paragraph (6) of the MCAI provides 

an option to incorporate the repetitive 

functional inspection into the maintenance 

program and then use the maintenance 

program as a method of complying with the 

repetitive inspection requirement, this AD 

does not include that provision. 

Other FAA AD Provisions 

(j) 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. 

Send information to ATTN: Tom Rodriguez, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1137; fax (425) 227–1149. 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. 

Related Information 

(k) Refer to MCAI European Aviation 

Safety Agency (EASA) Airworthiness 

Directive 2010–0139, dated July 1, 2010; 

Fokker Service Bulletin SBF28–28–052, 

dated April 20, 2010; and Fokker Service 

Bulletin SBF100–28–063, dated April 15, 

2010; for related information. 

Material Incorporated by Reference 

(l) You must use Fokker Service Bulletin 

SBF28–28–052, dated April 20, 2010; or 

Fokker Service Bulletin SBF100–28–063, 

dated April 15, 2010; as applicable; to do the 

actions required by this AD, unless the AD 

specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Fokker Services B.V., 

Technical Services Dept., P.O. Box 231, 2150 

AE Nieuw-Vennep, the Netherlands; 

telephone +31 (0)252–627–350; fax +31 

(0)252–627–211; e-mail 

technicalservices.fokkerservices@stork.com; 

Internet http://www.myfokkerfleet.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on January 

25, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–2162 Filed 2–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0852; Directorate 

Identifier 2010–NM–005–AD; Amendment 

39–16594; AD 2011–03–10] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–200 and –300 and A340–200 and 

–300 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
6544 Federal Register / Vol. 76, No. 25 / Monday, February 7, 2011 / Rules and Regulations 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) 

that applies to the products listed above. 

This AD results from mandatory 

continuing airworthiness information 

(MCAI) originated by an aviation 

authority of another country to identify 

and correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as: 

A debonding area was detected on the RH 

[right-hand] elevator of an A340 in-service 

aeroplane during a scheduled maintenance 

task inspection. 

Investigation has revealed that this 

debonding may have been caused by water 

ingress and, if not detected and corrected, 

might compromise the structural integrity of 

the elevators [and could result in reduced 

controllability of the airplane]. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

March 14, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 14, 2011. 

On November 16, 2005 (70 FR 59263, 

October 12, 2005), the Director of the 

Federal Register approved the 

incorporation by reference of certain 

other publications listed in this AD. 

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, 

Washington 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. That 

NPRM was published in the Federal 

Register on September 8, 2010 (75 FR 

54536), and proposed to supersede AD 

2005–20–32, Amendment 39–14329 (70 

FR 59263, October 12, 2005). That 

NPRM proposed to correct an unsafe 

condition for the specified products. 

The MCAI states: 

A debonding area was detected on the RH 

[right-hand] elevator of an A340 in-service 

aeroplane during a scheduled maintenance 

task inspection. 

Investigation has revealed that this 

debonding may have been caused by water 

ingress and, if not detected and corrected, 

might compromise the structural integrity of 

the elevators [and could result in reduced 

controllability of the airplane]. 

DGAC [Direction Ge ́ne ́rale de l’Aviation 

Civile] France AD F–2004–118 R1 (EASA 

approval N. 2004–10125) required a one-time 

inspection of elevators skin panels installed 

on MSN up to 091, to detect potential liquid 

ingress and repair as necessary, in 

accordance with Airbus inspection service 

bulletins (ISB) A330–55–3032 and A340–55– 

4029. 

Following the AD issuance, further inservice experience has shown that in order to 

ensure the structural integrity of all A330/ 

A340 elevators skin panels with sandwich 

construction (excluding A340–500/–600), it 

is necessary to perform the same elevators 

panels inspection and to repair as necessary, 

but in a repetitive manner. 

The aim of this AD, which supersedes 

DGAC France AD F–2004–118 R1, is to 

require this additional inspection program in 

order to maintain the structural integrity of 

the elevators. 

The required actions include repetitive 

special detailed inspections and 

repetitive re-protection of the elevator 

assembly. The special detailed 

inspections consist of the following 

actions: 

• Repetitive endoscopic inspections 

for damage (such as a scratch, 

disbonding, or a tear) of the inner skin 

of the upper and lower elevator panels 

on both sides of the airplane, and if any 

damage is found, contacting Airbus for 

instructions and doing the instructions. 

• Repetitive tap tests for debonding in 

the inner side of the upper and lower 

elevator panels on both sides, and if any 

debonding is found, contacting Airbus 

for instructions and doing the 

instructions. 

• Repetitive thermographic 

inspections for indications of trapped 

water in the upper and lower elevator 

panels on both sides of the airplane, and 

if any indications of trapped water are 

found, doing applicable corrective 

actions (including, but not limited to, 

repeating the thermographic inspection 

to determine the size of the damaged 

area, doing a general visual inspection 

to determine if there is an existing 

repair, contacting Airbus for 

instructions and doing the instructions, 

re-protecting the affected surfaces, and 

repairing holes). 

• Repetitively re-protect the elevator 

assembly (including doing a general 

visual inspection to determine damage 

and repair if necessary, a general visual 

inspection to determine if the drainage 

holes are clean and not obstructed and 

cleaning the drainage holes if necessary, 

a general visual inspection to determine 

the status of the static discharges 

contour and sealing the static discharges 

contour if necessary, and installing front 

spar access hole covers). 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

New Service Information 

The NPRM referred to Airbus Service 

Bulletin A330–55–3032 and Airbus 

Service Bulletin A340–55–4029, both 

dated December 22, 2003, as appropriate 

sources of service information for 

certain actions. Airbus has revised this 

service information. Airbus has issued 

Mandatory Service Bulletins A330–55– 

3032, Revision 01 including Appendix 

01, dated March 29, 2005; and A340– 

55–4029, Revision 01, dated March 29, 

2005; which among minor changes, 

change the classification of these service 

bulletins from recommended to 

mandatory. We have revised this final 

rule to also refer to Revision 01 of these 

service bulletins as appropriate sources 

of service information for certain 

actions. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. 

Request for a New AD Instead of a 

Superseding AD 

Delta Air Lines, Inc. (Delta) requested 

that we mandate a new AD instead of 

superseding AD 2005–20–32, to 

eliminate possible confusion for 

operators in complying with the 

requirements of the NPRM and the AD 

being superseded. Delta explained that 

AD 2005–20–32 applied to a specific 

range of elevator parts and serial 

numbers that required inspection, 

repair, and re-protection, as required by 

Airbus Service Bulletin A330–55–3032, 

dated December 22, 2003. Delta 

reasoned that paragraph (h) of AD 2005– 

20–32, states that installation of an 

affected elevator after the AD effective 

date, November 16, 2005, was not 

approved unless the subject elevator 

complied with paragraph (h) of AD 

2005–20–32. Delta reasoned further that 

the NPRM applies to a larger population 

of elevators and has inspections, repairs 

(if required), and re-protection, as 

specified in Airbus Mandatory Service 

Bulletin A330–55–3039, dated August 7, 

2009. Delta stated that the thresholds in 

the NPRM are based on previous 

inspections required by Airbus Service 

Bulletin A330–55–3032, dated 

December 22, 2003. 

We assume that Delta intended to 

refer to paragraph (i) instead of (h) of 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
Federal Register / Vol. 76, No. 25 / Monday, February 7, 2011 / Rules and Regulations 6545 

AD 2005–20–32, which states that 

installation of an affected elevator after 

the AD effective date, November 16, 

2005, is not approved unless the subject 

elevator complies with paragraph (h) of 

AD 2005–20–32. We disagree with 

mandating a new AD instead of this 

final rule, which supersedes AD 2005– 

20–32. Operators that comply with the 

new requirements of this final rule 

terminate the restated requirements of 

AD 2005–20–32. Restating the 

requirements of AD 2005–20–32 is 

necessary because some of the new 

required inspection thresholds in this 

final rule are calculated from the date 

the inspection was performed, as 

specified in AD 2005–20–32. We have 

not changed this final rule in this 

regard. 

Request for Removal of Reporting 

Requirements 

Delta requested that we remove the 

reporting requirements of paragraph (n) 

of the NPRM. Delta explained that 

requiring operators to report their 

findings (both positive and negative) to 

Airbus does not affect safety of flight, 

but instead puts operators at risk of noncompliance for failure to report findings 

within the required timeline, and is a 

duplication of records that is a burden 

to operators. Delta indicated that they 

maintain records of accomplishment of 

mandated work. Delta argued further, 

that removal of the reporting 

requirement would be consistent with 

the FAA’s ruling per AD 2005–20–32, 

which notes: 

‘‘We require operators to submit 

information relevant to AD actions only 

when our analyses indicate that such 

information is needed to ensure safety or to 

document compliance. We cannot require 

operators to submit information to improve 

processes. We have not changed the AD in 

this regard.’’ 

We disagree to remove the reporting 

requirements of this final rule. We 

mandate reporting to Airbus in support 

of collecting the inspection results, 

which are helpful to Airbus in 

developing a final fix to the problem, a 

potential change in the design of the 

affected part, or the manufacturing 

process. We have not changed this final 

rule in this regard. 

Request for Reference to Paragraph (k) 

Delta requested that we revise 

paragraph (o) to include a reference to 

paragraph (k) instead of paragraph (l) in 

the NPRM. Delta explained that the 

following sentence in paragraph (o) of 

the NPRM, which states: 

‘‘do not install any elevator identified in 

Table 1 of this AD on any airplane, unless 

the elevator has been inspected in 

accordance with paragraph (l) of this AD and 

all applicable corrective actions have been 

done.’’ 

contains a typographical error and 

should include a reference to paragraph 

(k) for inspections and paragraph (l) for 

corrective actions. 

We agree to include a reference to 

paragraph (k) instead of paragraph (l), in 

paragraph (o) of the final rule. We have 

revised the final rule accordingly. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a Note within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

about 56 products of U.S. registry. 

The actions that are required by AD 

2005–20–32 and retained in this AD 

take about 1 work-hour per product, at 

an average labor rate of $85 per workhour. Based on these figures, the 

estimated cost of the currently required 

actions is $85 per product. 

We estimate that it will take about 14 

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 to the U.S. 

operators to be $66,640, or $1,190 per 

product. 

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 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); 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 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 the NPRM, 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: 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
6546 Federal Register / Vol. 76, No. 25 / Monday, February 7, 2011 / Rules and Regulations 

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 39–14329 (70 FR 

59263, October 12, 2005) and adding the 

following new AD: 

2011–03–10 Airbus: Amendment 39–16594. 

Docket No. FAA–2010–0852; Directorate 

Identifier 2010–NM–005–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective March 14, 2011. 

Affected ADs 

(b) This AD supersedes AD 2005–20–32, 

Amendment 39–14329. 

Applicability 

(c) This AD applies to Airbus Model A330– 

201, –202, –203, –223, –243, –301, –302, 

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

airplanes, and A340–211, –212, –213, –311, 

–312, and –313 airplanes; certificated in any 

category; all manufacturer serial numbers, if 

equipped with any of the elevator part 

numbers (P/N) identified in Table 1 of this 

AD (‘‘ZZ’’ indicates a number from 00 up to 

99 inclusive). 

TABLE 1—ELEVATOR PART NUMBERS

For the left-hand 

elevator 

For the right-hand 

elevator 

P/N F55280000000ZZ P/N F55280000001ZZ 

P/N F55280000002ZZ P/N F55280000003ZZ 

P/N F55280000004ZZ P/N F55280000005ZZ 

P/N F55280000006ZZ P/N F55280000007ZZ 

P/N F55280000008ZZ P/N F55280000009ZZ 

P/N F55280000012ZZ P/N F55280000013ZZ 

P/N F55280002000ZZ P/N F55280002001ZZ 

TABLE 1—ELEVATOR PART

NUMBERS—Continued 

For the left-hand 

elevator 

For the right-hand 

elevator 

P/N F55280005000ZZ P/N F55280005001ZZ 

P/N F55280005002ZZ P/N F55280005003ZZ 

P/N F55280005004ZZ P/N F55280005005ZZ 

Subject 

(d) Air Transport Association (ATA) of 

America Code 55: Stabilizers. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

A debonding area was detected on the RH 

[right-hand] elevator of an A340 in-service 

aeroplane during a scheduled maintenance 

task inspection. 

Investigation has revealed that this 

debonding may have been caused by water 

ingress and, if not detected and corrected, 

might compromise the structural integrity of 

the elevators [and could result in reduced 

controllability of the airplane]. 

* * * * * 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Restatement of Requirements of AD 2005– 

20–32 

Service Bulletin Exceptions for Airbus 

Service Bulletin A330–55–3032 and Airbus 

Service Bulletin A340–55–4029 

(g) Where Airbus Service Bulletins A330– 

55–3032 and Airbus Service Bulletin A340– 

55–4029, both dated December 22, 2003; and 

Airbus Mandatory Service Bulletin A330–55– 

3032 and Airbus Mandatory Service Bulletin 

A340–55–4029, both Revision 1, both dated 

March 29, 2005; recommend contacting 

Airbus for appropriate action: Before further 

flight, repair the condition according to a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; the Direction 

Ge ́ne ́rale de l’Aviation Civile (or its delegated 

agent); or EASA (or its delegated agent). 

(h) Although Airbus Service Bulletin 

A330–55–3032 and Airbus Service Bulletin 

A340–55–4029, both dated December 22, 

2003; and Airbus Mandatory Service Bulletin 

A330–55–3032 and Airbus Mandatory 

Service Bulletin A340–55–4029, both 

Revision 1, both dated March 29, 2005; 

specify to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

Determining Part Number, Serial Number 

(i) For Model A330–201, –202, –203, –223, 

–243, –301, –321, –322, –323, –341, –342, 

and –343 airplanes; and Model A340–211, 

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

At the later of the times specified in 

paragraphs (i)(1) and (i)(2) of this AD, 

perform an inspection to determine the part 

number and serial number of the left- and 

right-hand elevator assemblies. A review of 

airplane maintenance records is acceptable in 

lieu of this inspection if the part number and 

serial number of each elevator assembly can 

be conclusively determined from that review. 

If neither elevator assembly has a part 

number and serial number combination 

identified in Table 2 of this AD, no further 

action is required by this paragraph. If either 

elevator assembly has a part number and 

serial number combination identified in 

Table 2 of this AD, do paragraph (j) of this 

AD. Doing the actions in paragraph (k) of this 

AD terminates the requirements of paragraph 

(i) of this AD. 

(1) Within 10 years after the date of the 

first flight of the airplane, or before the 

accumulation of 12,000 total flight cycles, 

whichever is first. 

(2) Within 18 months after November 16, 

2005 (the effective date of AD 2005–20–32). 

TABLE 2—AFFECTED ELEVATOR PART NUMBERS AND SERIAL NUMBERS IN AD 2005–20–32 

Part Affected part Nos. Affected serial Nos. 

Left-hand elevator assembly ........................................ F55280000000, F55280000004 .. CG1002 through CG1091 inclusive, CG1093, 

CG1094, CG2001. 

Right-hand elevator assembly ...................................... F55280000001, F55280000005 .. CG1002 through CG1094 inclusive, CG2001. 

Inspections 

(j) For Model A330–201, –202, –203, –223, 

–243, –301, –321, –322, –323, –341, –342, 

and –343 airplanes; and Model A340–211, 

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

If the left- or right-hand elevator assembly 

has a part number and serial number 

combination identified in Table 2 of this AD, 

before further flight after accomplishing 

paragraph (i) of this AD, do the actions in 

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

as applicable. Doing the actions in paragraph 

(k) of this AD terminates the requirements of 

paragraph (j) of this AD. 

(1) Perform an endoscopic inspection to 

detect damage (such as a scratch, disbonding, 

or a tear), and a tap test and a thermographic 

inspection to detect signs of moisture 

penetration, to the upper and lower elevator 

panels on both sides of the airplane, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330– 

55–3032 (for Model A330–201, –202, –203, 

–223, –243, –301, –321, –322, –323, –341, 

–342, and –343 airplanes) or Airbus Service 

Bulletin A340–55–4029 (for Model A340– 

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

airplanes), both dated December 22, 2003, as 

applicable; or Airbus Mandatory Service 

Bulletin A330–55–3032 (for Model A330– 

201, –202, –203, –223, –243, –301, –321, 

–322, –323, –341, –342, and –343 airplanes) 

or Airbus Mandatory Service Bulletin A340– 

55–4029 (for Model A340–211, –212, –213, 

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

Revision 1, both dated March 29, 2005, as 

applicable; except as provided by paragraphs 

(g) and (h) of this AD. 

(2) If any damage is found, before further 

flight, do all applicable corrective actions 

(including, but not limited to, repeating the 

thermographic inspection to determine the 

size of the damaged area, and performing a 

tap test around the areas where moisture is 

indicated), in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–55–3032 (for Model 

A330–201, –202, –203, –223, –243, –301, 

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

airplanes) or Airbus Service Bulletin A340– 

55–4029 (for Model A340–211, –212, –213, 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
Federal Register / Vol. 76, No. 25 / Monday, February 7, 2011 / Rules and Regulations 6547 

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

December 22, 2003, as applicable; or Airbus 

Mandatory Service Bulletin A330–55–3032 

(for Model A330–201, –202, –203, –223, 

–243, –301, –321, –322, –323, –341, –342, 

and –343 airplanes) or Airbus Mandatory 

Service Bulletin A340–55–4029 (for Model 

A340–211, –212, –213, –311, –312, and –313 

airplanes), both Revision 1, both dated March 

29, 2005, as applicable; except as provided 

by paragraphs (g) and (h) of this AD. 

(3) Re–protect the elevator assembly 

(including performing a general visual 

inspection to determine if the drainage holes 

are clean, a general visual inspection to 

determine the condition of the sealant 

covering the static discharges contour, and 

applicable corrective actions), in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A330–55–3032 (for 

Model A330–201, –202, –203, –223, –243, 

–301, –321, –322, –323, –341, –342, and –343 

airplanes) or Airbus Service Bulletin A340– 

55–4029 (for Model A340–211, –212, –213, 

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

December 22, 2003, as applicable; or Airbus 

Mandatory Service Bulletin A330–55–3032 

(for Model A330–201, –202, –203, –223, 

–243, –301, –321, –322, –323, –341, –342, 

and –343 airplanes) or Airbus Mandatory 

Service Bulletin A340–55–4029 (for Model 

A340–211, –212, –213, –311, –312, and –313 

airplanes), both Revision 1, both dated March 

29, 2005, as applicable; except as provided 

by paragraphs (g) and (h) of this AD. 

Note 1: 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.’’ 

New Requirements of This AD 

Repetitive Inspection 

(k) Within the applicable time in paragraph 

(k)(1) or (k)(2) of this AD, do a special 

detailed inspection for discrepancies 

(scratches, debonding, tears, and indications 

of trapped water), on the elevator upper and 

lower skin panels, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–55–3039 

(for Model A330–201, –202, –203, –223, 

–243, –301, –302, –303, –321, –322, –323, 

–341, –342, and –343 airplanes) or A340–55– 

4035 (for Model A340–211, –212, –213, –311, 

–312, and –313 airplanes), both dated August 

7, 2009. Repeat the inspections thereafter at 

intervals not to exceed 72 months from the 

date of the elevator’s first flight after the last 

inspection. Doing the special detailed 

inspection specified in this paragraph 

terminates the requirements of paragraphs (i) 

and (j) of this AD. 

(1) For elevators identified in Table 1 of 

this AD that have not been inspected in 

accordance with Airbus Service Bulletin 

A330–55–3032 (for Model A330–201, –202, 

–203, –223, –243, –301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes) 

or Airbus Service Bulletin A340–55–4029 

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

–312, and –313 airplanes) both dated 

December 22, 2003; and Airbus Mandatory 

Service Bulletin A330–55–3032 (for Model 

A330–201, –202, –203, –223, –243, –301, 

–302, –303, –321, –322, –323, –341, –342, 

and –343 airplanes) or Airbus Mandatory 

Service Bulletin A340–55–4029 (for Model 

A340–211, –212, –213, –311, –312, and –313 

airplanes), both Revision 1, both dated March 

29, 2005: Within 144 months since the date 

of the elevator’s first flight on any airplane, 

or within 24 months after the effective date 

of this AD, whichever occurs later. 

(2) For elevators identified in Table 1 of 

this AD that have been inspected in 

accordance with Airbus Service Bulletin 

A330–55–3032 (for Model A330–201, –202, 

–203, –223, –243, –301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes) 

or Airbus Service Bulletin A340–55–4029 

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

–312, and –313 airplanes) both dated 

December 22, 2003; or Airbus Mandatory 

Service Bulletin A330–55–3032 (for Model 

A330–201, –202, –203, –223, –243, –301, 

–302, –303, –321, –322, –323, –341, –342, 

and –343 airplanes) or Airbus Mandatory 

Service Bulletin A340–55–4029 (for Model 

A340–211, –212, –213, –311, –312, and –313 

airplanes), both Revision 1, both dated March 

29, 2005: Within 72 months since the date of 

the elevator’s first flight on any airplane after 

accomplishing Airbus Service Bulletin 

A330–55–3032 (for Model A330–201, –202, 

–203, –223, –243, –301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes) 

or Airbus Service Bulletin A340–55–4029, 

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

–312, and –313 airplanes) both dated 

December 22, 2003; or Airbus Mandatory 

Service Bulletin A330–55–3032 (for Model 

A330–201, –202, –203, –223, –243, –301, 

–302, –303, –321, –322, –323, –341, –342, 

and –343 airplanes) or Airbus Mandatory 

Service Bulletin A340–55–4029, (for Model 

A340–211, –212, –213, –311, –312, and –313 

airplanes) both Revision 1, both dated March 

29, 2005; as applicable; or within 24 months 

after the effective date of this AD, whichever 

occurs later. 

Corrective Action 

(l) If any discrepancy is found during any 

inspection required by paragraph (k) of this 

AD, before further flight, do all applicable 

corrective actions (including applicable 

inspections and repair), in accordance with 

the Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–55–3039 

(for Model A330–201, –202, –203, –223, 

–243, –301, –302, –303, –321, –322, –323, 

–341, –342, and –343 airplanes) or A340–55– 

4035 (for Model A340–211, –212, –213, –311, 

–312, and –313 airplanes), both dated August 

7, 2009; or contact Airbus for instructions 

and follow their corrective actions. 

Re-protection 

(m) For elevators on which any action 

required by paragraph (k) or (l) of this AD is 

done: Before the elevator’s next flight, do a 

re–protection (including all applicable 

inspections and corrective actions), in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–55–3039 (for Model A330– 

201, –202, –203, –223, –243, –301, –302, 

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

airplanes); or A340–55–4035 (for Model 

A340–211, –212, –213, –311, –312, and –313 

airplanes), both dated August 7, 2009. 

Reporting 

(n) Submit a report of the findings (both 

positive and negative) of the inspection 

required by paragraph (k) of this AD to 

Airbus, as specified in Appendix 1 of Airbus 

Mandatory Service Bulletin A330–55–3039, 

dated August 7, 2009; or Airbus Mandatory 

Service Bulletin A340–55–4035, dated 

August 7, 2009; as applicable; at the 

applicable time specified in paragraph (n)(1) 

or (n)(2) of this AD. The report must include 

the information identified in Appendix 1 of 

Airbus Mandatory Service Bulletin A330–55– 

3039, dated August 7, 2009; or Airbus 

Mandatory Service Bulletin A340–55–4035, 

dated August 7, 2009; as applicable. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

Parts Installation 

(o) As of the effective date of this AD, do 

not install any elevator identified in Table 1 

of this AD on any airplane, unless the 

elevator has been inspected in accordance 

with paragraph (k) of this AD and all 

applicable corrective actions have been done. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(p) 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. 

Send information to ATTN: Vladimir 

Ulyanov, Aerospace Engineer, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. 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 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
6548 Federal Register / Vol. 76, No. 25 / Monday, February 7, 2011 / Rules and Regulations 

(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. 

Related Information 

(q) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2009– 

0255, dated December 1, 2009, and the 

service bulletins listed in Table 3 of this AD, 

for related information. 

TABLE 3—SERVICE BULLETINS

Document Revision Date 

Airbus Service Bulletin A330–55–3032 ........................................................................................... Original ...................... December 22, 2003. 

Airbus Mandatory Service Bulletin A330–55–3032 ......................................................................... 1 ................................ March 29, 2005. 

Airbus Service Bulletin A340–55–4029 ........................................................................................... Original ...................... December 22, 2003. 

Airbus Mandatory Service Bulletin A340–55–4029 ......................................................................... 1 ................................ March 29, 2005. 

Airbus Mandatory Service Bulletin A330–55–3039 ......................................................................... Original ...................... August 7, 2009. 

Airbus Mandatory Service Bulletin A340–55–4035 ......................................................................... Original ...................... August 7, 2009. 

Material Incorporated by Reference 

(r) You must use the service information 

contained in Table 4 of this AD, as 

applicable, to do the actions required by this 

AD, unless the AD specifies otherwise. 

TABLE 4—ALL MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Airbus Service Bulletin A330–55–3032, excluding Appendix 01 .................................................... Original ...................... December 22, 2003. 

Airbus Mandatory Service Bulletin A330–55–3032, excluding Appendix 01 .................................. 1 ................................ March 29, 2005. 

Airbus Service Bulletin A340–55–4029, excluding Appendix 01 .................................................... Original ...................... December 22, 2003. 

Airbus Mandatory Service Bulletin A340–55–4029, excluding Appendix 01 .................................. 1 ................................ March 29, 2005. 

Airbus Mandatory Service Bulletin A330–55–3039, including Appendix 01 ................................... Original ...................... August 7, 2009. 

Airbus Mandatory Service Bulletin A340–55–4035, including Appendix 01 ................................... Original ...................... August 7, 2009. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information contained in Table 5 

of this AD under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

TABLE 5—NEW MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Airbus Mandatory Service Bulletin A330–55–3032, excluding Appendix 01 .................................. 1 ................................ March 29, 2005. 

Airbus Mandatory Service Bulletin A340–55–4029, excluding Appendix 01 .................................. 1 ................................ March 29, 2005. 

Airbus Mandatory Service Bulletin A330–55–3039, including Appendix 1 ..................................... Original ...................... August 7, 2009. 

Airbus Mandatory Service Bulletin A340–55–4035, including Appendix 1 ..................................... Original ...................... August 7, 2009. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of Airbus Service Bulletin A330– 

55–3032, excluding Appendix 01, dated 

December 22, 2003; and Airbus Service 

Bulletin A340–55–4029, excluding Appendix 

01, dated December 22, 2003; on November 

16, 2005 (70 FR 59263, October 12, 2005). 

(3) For 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; e-mail 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. 

(4) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(5) You may also review copies of the 

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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on January 

26, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–2430 Filed 2–4–11; 8:45 am] 

BILLING CODE 4910–13–P 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1