39790 Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0790; Directorate 

Identifier 2008–NM–177–AD; Amendment 

39–16285; AD 2010–10–06] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–200 and –300 Airplanes and 

Model A340–200, –300, –500, and –600 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

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: 

Uncontained APU [auxiliary power unit] 

generator failures on ground have occurred 

on Airbus A330 aircraft in service. APU 

generator design is common to all A330 and 

A340 aircraft. 

Preliminary investigations confirmed that 

these failures have resulted in structural 

damage to the APU compartment and, in one 

case, to the stabiliser compartment. Loose 

APU generator parts can lead to damage to 

the APU firewall, reducing its fire 

extinguishing capability and potentially 

leading to a temporary uncontrolled fire. 

Although the root cause has not yet been 

determined, the investigation showed a 

sequence of events where a collapse of the 

Drive End Bearing (DEB) leads to an 

uncontained failure. Evidence has also 

shown that the DEB failures are not 

instantaneous, and therefore, the detection of 

small debris could indicate early stage of a 

DEB failure. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

August 17, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 17, 2010. 

On June 26, 2007 (72 FR 31973, June 

11, 2007), 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 25, 2009 (74 FR 

48872), and proposed to supersede AD 

2007–18–04, Amendment 39–15184 (72 

FR 50042, August 30, 2007). That NPRM 

proposed to correct an unsafe condition 

for the specified products. The MCAI 

states: 

Uncontained APU [auxiliary power unit] 

generator failures on ground have occurred 

on Airbus A330 aircraft in service. APU 

generator design is common to all A330 and 

A340 aircraft. 

Preliminary investigations confirmed that 

these failures have resulted in structural 

damage to the APU compartment and, in one 

case, to the stabiliser compartment. Loose 

APU generator parts can lead to damage to 

the APU firewall, reducing its fire 

extinguishing capability and potentially 

leading to a temporary uncontrolled fire. 

Although the root cause has not yet been 

determined, the investigation showed a 

sequence of events where a collapse of the 

Drive End Bearing (DEB) leads to an 

uncontained failure. Evidence has also 

shown that the DEB failures are not 

instantaneous, and therefore, the detection of 

small debris could indicate early stage of a 

DEB failure. 

To address this subject, EASA issued 

Emergency AD 2007–0188–E, requiring 

repetitive inspections of the APU generator 

Scavenge filter element and filter housing 

and of the APU generator Drain plug for signs 

of small debris coming from the APU 

generator, allowing detection of the early 

stage of APU generator failure. That AD was 

later revised to extend the compliance time 

and to provide another option for the 

repetitive inspection. 

Subsequently, another uncontained APU 

generator failure occurred on ground on an 

A330 aircraft, operated within the provisions 

of MMEL [master minimum equipment list] 

item 36–11–01, with similar structural 

damages as the previous APU generator burst 

events. The investigation of this event 

revealed that the inspection required by 

paragraph 4 of AD 2007–0188R1 before the 

first flight under the MMEL rectification 

interval had not been performed and that the 

APU generator had not been properly 

installed (two seal plates instead of one). 

Consequently, EASA issued AD 2008– 

0017, superseding AD 2007–0188R1 and 

requiring the following additional actions: 

—a visual inspection of the APU generator 

seal plate fitting, 

—an inspection following MMEL item 36– 

11–01 or 24–22–01 rectification and 

—an inspection each time a new or 

serviceable APU generator or APU is 

installed on an aircraft. 

EASA issued AD 2008–0017R1 to cancel 

the inspection of paragraph 4 for A330 

aircraft, when operated within the provisions 

of MMEL item 36–11–01 further to ETOPS 

[Extended-Range Twin-Engine Operations 

Performance Standards] certification of A330 

APU. 

Finally, Airbus has developed a secondary 

housing for the APU generator that is 

designed to contain APU generator parts in 

the event of an APU generator burst. 

For the above described reasons, this AD 

retains the requirements of EASA AD 2008– 

0017R1, which is superseded, and adds the 

requirement to install a secondary housing 

on the APU generator. After installation of 

the secondary APU generator housing on an 

aircraft, the repetitive inspections of this AD 

are no longer required for that aircraft. 

This AD retains the requirements of AD 

2007–18–04. The new requirements 

include inspecting the APU generator 

scavenge oil filter element for 

contamination, the APU generator drain 

plug for contamination, and the APU 

generator scavenge filter housing for 

contamination, and a terminating action 

(installing a secondary housing line 

replaceable unit). Applicable corrective 

actions include, depending on the 

findings, replacing or reinstalling the 

APU generator scavenge oil filter and 

packing, replacing or reinstalling the 

APU generator drain plug, and replacing 

or reinstalling the APU generator 

scavenge filter housing. You may obtain 

further information by examining the 

MCAI in the AD docket. 

Relevant Service Information 

The NPRM cited Airbus Service 

Bulletins A330–24–3045, dated June 13, 

2008; A340–24–4058, dated June 13, 

2008; and A340–24–5022, dated June 

23, 2008. Airbus has released the 

following new service bulletins: 


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TABLE—NEW SERVICE INFORMATION

Airbus— Revision— Dated— 

Mandatory Service Bulletin A330–24–3045 .................................................................................................... 01 October 1, 2008. 

Mandatory Service Bulletin A340–24–4058 .................................................................................................... 01 October 1, 2008. 

Mandatory Service Bulletin A340–24–5022 .................................................................................................... 01 November 27, 2008. 

The latest revisions of the service 

information make minor updates and 

specify that no additional work is 

necessary on airplanes modified in 

accordance with the original 

documents. We have revised this final 

rule to incorporate the latest revisions of 

the service information. We have also 

added paragraph (h)(6) and Table 5 to 

this AD to give credit for actions done 

in accordance with the original service 

information. We have reidentified 

subsequent tables accordingly. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. 

Request To Include a Terminating 

Modification for Actions Required by 

Paragraphs (h)(3) and (h)(4) of the 

NPRM 

EVA Airways Corporation (EVA) 

requests that we revise the NPRM to 

include a terminating modification for 

actions required by paragraphs (h)(3) 

and (h)(4) of the NPRM. Accomplishing 

the actions specified in paragraph (h)(5) 

of the NPRM would terminate the 

actions required by paragraphs (g)(2), 

(g)(3), and (h)(2) of the NPRM. EVA 

refers to a message it received from 

Airbus and states that installing the 

APU generator secondary housing 

terminates the repetitive inspections 

specified in paragraphs (g)(2), (g)(3), 

(h)(2), (h)(3), and (h)(4) of the NPRM. 

We agree with the commenter’s 

request. The EASA AD specifies that 

installing the secondary housing line 

replacement unit terminates repetitive 

inspections. We have also received 

information from Airbus indicating that 

installing the APU generator secondary 

housing terminates the repetitive 

inspections required by paragraphs 

(h)(3) and (h)(4) of the NPRM. We have 

revised paragraph (h)(5) of this final rule 

to specify that installing the APU 

generator secondary housing terminates 

the repetitive inspections specified in 

paragraphs (g)(2) and (g)(3) of this AD 

and the inspections specified in 

paragraphs (h)(2), (h)(3), and (h)(4) of 

this AD. We have also revised 

paragraphs (g)(2) and (g)(3) of this final 

rule to clarify that doing the installation 

required by paragraph (h)(5) of this AD 

terminates the repetitive inspections. 

We have also revised paragraphs (h)(2), 

(h)(3), and (h)(4) of this AD to clarify 

that doing the installation terminates 

the inspection requirements of those 

paragraphs. 

Explanation of Changes Made to This 

AD 

In paragraphs (g)(1), (g)(2), and (g)(3) 

of this AD, we have clarified that the 

service information specified in Table 2 

or Table 3 of this AD is acceptable for 

compliance with the applicable actions. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We also 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. 

Explanation of Change to Costs of 

Compliance 

Since issuance of the NPRM, we have 

increased the labor rate used in the 

Costs of Compliance from $80 per workhour to $85 per work-hour. The Costs of 

Compliance information, below, reflects 

this increase in the specified hourly 

labor rate. 

Costs of Compliance 

We estimate that this AD will affect 

about 41 products of U.S. registry. 

The actions that are required by AD 

2007–18–04 and retained in this AD 

take about 11 work-hours per product, 

at an average labor rate of $85 per work 

hour. Required parts cost $0 per 

product. Based on these figures, the 

estimated cost of the currently required 

actions is $935 per product. 

We estimate that it will take about 10 

work-hours per product to comply with 

the new basic requirements of this AD. 

The average labor rate is $85 per workhour. Required parts will cost about $0 

per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these costs. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of 

this AD to the U.S. operators to be 

$34,850, or $850 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: 


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39792 Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations 

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: 

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 39–15184 (72 FR 

50042, August 30, 2007) and adding the 

following new AD: 

2010–10–06 Airbus: Amendment 39–16285. 

Docket No. FAA–2009–0790; Directorate 

Identifier 2008–NM–177–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective August 17, 2010. 

Affected ADs 

(b) This AD supersedes AD 2007–18–04, 

Amendment 39–15184. 

Applicability 

(c) This AD applies to the airplanes 

certificated in any category, identified in 

paragraphs (c)(1) and (c)(2) of this AD. 

(1) Airbus Model A330–201, –202, –203, 

–223, –243, –301, –302, –303, –321, –322, 

–323, –341, –342, and –343 series airplanes, 

all serial numbers, except those on which 

Airbus modification 56985 has been 

embodied in production. 

(2) Airbus Model A340–211, –212, –213, 

–311, –312, and –313 series airplanes; and 

Model A340–541 and A340–642 airplanes; 

all serial numbers, except those on which 

Airbus modification 56985 has been 

embodied in production. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 24: Electrical power. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Uncontained APU [auxiliary power unit] 

generator failures on ground have occurred 

on Airbus A330 aircraft in service. APU 

generator design is common to all A330 and 

A340 aircraft. 

Preliminary investigations confirmed that 

these failures have resulted in structural 

damage to the APU compartment and, in one 

case, to the stabiliser compartment. Loose 

APU generator parts can lead to damage to 

the APU firewall, reducing its fire 

extinguishing capability and potentially 

leading to a temporary uncontrolled fire. 

Although the root cause has not yet been 

determined, the investigation showed a 

sequence of events where a collapse of the 

Drive End Bearing (DEB) leads to an 

uncontained failure. Evidence has also 

shown that the DEB failures are not 

instantaneous, and therefore, the detection of 

small debris could indicate early stage of a 

DEB failure. 

To address this subject, EASA issued 

Emergency AD 2007–0188–E, requiring 

repetitive inspections of the APU generator 

Scavenge filter element and filter housing 

and of the APU generator Drain plug for signs 

of small debris coming from the APU 

generator, allowing detection of the early 

stage of APU generator failure. That AD was 

later revised to extend the compliance time 

and to provide another option for the 

repetitive inspection. 

Subsequently, another uncontained APU 

generator failure occurred on ground on an 

A330 aircraft, operated within the provisions 

of MMEL [master minimum equipment list] 

item 36–11–01, with similar structural 

damages as the previous APU generator burst 

events. The investigation of this event 

revealed that the inspection required by 

paragraph 4 of AD 2007–0188R1 before the 

first flight under the MMEL rectification 

interval had not been performed and that the 

APU generator had not been properly 

installed (two seal plates instead of one). 

Consequently, EASA issued AD 2008– 

0017, superseding AD 2007–0188R1 and 

requiring the following additional actions: 

—a visual inspection of the APU generator 

seal plate fitting, 

—an inspection following MMEL item 36– 

11–01 or 24–22–01 rectification and 

—an inspection each time a new or 

serviceable APU generator or APU is 

installed on an aircraft. 

EASA issued AD 2008–0017R1 to cancel 

the inspection of paragraph 4 for A330 

aircraft, when operated within the provisions 

of MMEL item 36–11–01 further to ETOPS 

[Extended-Range Twin-Engine Operations 

Performance Standards] certification of A330 

APU. 

Finally, Airbus has developed a secondary 

housing for the APU generator that is 

designed to contain APU generator parts in 

the event of an APU generator burst. 

For the above described reasons, this AD 

retains the requirements of EASA AD 2008– 

0017R1, which is superseded, and adds the 

requirement to install a secondary housing 

on the APU generator. After installation of 

the secondary APU generator housing on an 

aircraft, the repetitive inspections of this AD 

are no longer required for that aircraft. 

This AD retains the requirements of AD 

2007–18–04, which superseded AD 2007–12– 

10, Amendment 39–15088. The new 

requirements include inspecting the APU 

generator scavenge oil filter element for 

contamination, the APU generator drain plug 

for contamination, and the APU generator 

scavenge filter housing for contamination, 

and a terminating action (installing a 

secondary housing line replaceable unit). 

Applicable corrective actions include, 

depending on the findings, replacing or 

reinstalling the APU generator scavenge oil 

filter and packing, replacing or reinstalling 

the APU generator drain plug, and replacing 

or reinstalling the APU generator scavenge 

filter housing. 

RESTATEMENT OF REQUIREMENTS OF 

AD 2007–12–10, WITH NO CHANGES 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) For airplanes on which the date of 

issuance of the original French airworthiness 

certificate or the date of issuance of the 

original French or EASA export certificate of 

airworthiness is before March 1, 2007: 

Within 63 days after June 26, 2007 (the 

effective date of AD 2007–12–10), in 

accordance with the instructions of Airbus 

All Operators Telex (AOT) A330–24A3042, 

A340–24A4056, or A340–24A5020, all 

Revision 02, all dated April 12, 2007; as 

applicable, inspect the inlet screen (last 

chance filter) for the generator scavenge-oil 

pump for signs of debris and, as applicable, 

apply all associated corrective actions before 

further flight. 

(2) For Model A330 aircraft operating 

under MMEL (master minimum equipment 

list) Item 24–22–01 ‘AC Main Generation’ or 

MMEL Item 36–11–01 ‘Bleed Air Supply 

System Failure’ and on which the date of 

issuance of the original French airworthiness 

certificate or the date of issuance of the 

original French or EASA export certificate of 

airworthiness is before March 1, 2007: As of 

June 26, 2007, before each flight, perform a 

check of the differential pressure indicator 

button on the lube filter and the generator 

scavenge filter in accordance with the 

instructions of Airbus AOT A330–24A3042, 

Revision 02, dated April 12, 2007, until 

accomplishment of paragraph (g)(5) of this 

AD. 

Note 1: The repetitive checks before each 

flight specified in paragraph (f)(2) of this AD 

are not required for airplanes operated under 


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MMEL Item 36–11–01, provided the APU 

generator has been removed or deactivated in 

accordance with the instructions of Airbus 

AOT A330–24A3042, Revision 02, dated 

April 12, 2007. 

(3) Actions done before June 26, 2007, in 

accordance with the applicable Airbus 

service information in Table 1 of this AD are 

acceptable for compliance with the 

corresponding provisions of paragraph (f) of 

this AD. 

TABLE 1—ACCEPTABLE EARLIER REVISIONS OF SERVICE INFORMATION

Airbus all operators telex— Revision— Dated— 

A330–24A3042 .................................................................................................................... Original ........................................... March 22, 2007. 

A330–24A3042 .................................................................................................................... 01 ................................................... March 29, 2007. 

A340–24A4056 .................................................................................................................... Original ........................................... March 22, 2007. 

A340–24A4056 .................................................................................................................... 01 ................................................... March 29, 2007. 

A340–24A5020 .................................................................................................................... Original ........................................... March 22, 2007. 

A340–24A5020 .................................................................................................................... 01 ................................................... March 29, 2007. 

RESTATEMENT OF REQUIREMENTS OF 

AD 2007–18–04, WITH REVISED SERVICE 

INFORMATION 

Actions and Compliance 

(g) Unless already done, do the following 

actions. 

(1) For airplanes on which the date of 

issuance of the original French airworthiness 

certificate or the date of issuance of the 

original French or EASA export certificate of 

airworthiness is on or before July 1, 2007: 

Within 30 days after September 14, 2007 (the 

effective date of AD 2007–18–04), in 

accordance with the instructions of 

paragraph 4.2.1 of the applicable Airbus 

service information specified in Table 2 or 3 

of this AD, clean and inspect the APU 

generator scavenge oil filter element and 

housing and inspect the APU generator drain 

plug to detect metallic debris, and apply all 

applicable associated corrective actions 

before further flight. After the effective date 

of this AD, use only the service information 

specified in Table 3 of this AD. 

TABLE 2—SERVICE INFORMATION

Airbus all operators telex— Revision— Dated— 

A330–24A3044 .................................................................................................................................................... 01 July 20, 2007. 

A330–24A3044 .................................................................................................................................................... 02 December 20, 

2007. 

A340-24A4057 ..................................................................................................................................................... 02 August 14, 2007. 

A340–24A5021 .................................................................................................................................................... 01 July 20, 2007. 

TABLE 3—NEW SERVICE INFORMATION

Airbus all operators telex— Revision— Dated— 

A330–24A3044 .................................................................................................................................................... 03 May 26, 2008. 

A340–24A4057 .................................................................................................................................................... 03 December 20, 

2007. 

A340–24A5021 .................................................................................................................................................... 02 December 20, 

2007. 

(2) Within 450 aircraft flight hours or 200 

APU operating hours, whichever occurs later, 

after accomplishing the inspection required 

by paragraph (g)(1) of this AD, in accordance 

with the instructions of paragraph 4.2.2 of 

the applicable Airbus information specified 

in Table 2 or Table 3 of this AD: Inspect the 

APU generator scavenge oil filter element 

and housing and the APU generator drain 

plug to detect metallic debris; and apply all 

applicable associated corrective actions 

before further flight. Repeat the inspections 

thereafter at intervals not to exceed 450 

aircraft flight hours or 200 APU operating 

hours, whichever occurs later until the 

installation required by paragraph (h)(5) of 

this AD is done. After the effective date of 

this AD, use only the service information 

specified in Table 3 of this AD. 

(3) For airplanes on which the date of 

issuance of the original French airworthiness 

certificate or the date of issuance of the 

original French or EASA export certificate of 

airworthiness is after July 1, 2007: Within 

450 aircraft flight hours or 200 APU 

operating hours after September 14, 2007, 

whichever occurs later, in accordance with 

the instructions of paragraph 4.2.2 of the 

applicable Airbus service information 

specified in Table 2 or Table 3 of this AD: 

Inspect the APU generator scavenge oil filter 

element and housing and the APU generator 

drain plug to detect metallic debris; and 

apply all applicable associated corrective 

actions before further flight. Repeat the 

inspections thereafter at intervals not to 

exceed 450 aircraft flight hours or 200 APU 

operating hours, whichever occurs later until 

the installation required by paragraph (h)(5) 

of this AD is done. After the effective date 

of this AD, use only the service information 

specified in Table 3 of this AD. 

(4) Actions done before September 14, 

2007, in accordance with the applicable 

Airbus service information in Table 4 of this 

AD are acceptable for compliance with the 

corresponding provisions of paragraph (g) of 

this AD. 

TABLE 4—ACCEPTABLE EARLIER REVISIONS OF SERVICE INFORMATION

Airbus all operators telex— Revision— Dated— 

A330–24A3044 ....................................................................................................................... Original ............................................ July 5, 2007. 

A340-24A4057 ........................................................................................................................ Original ............................................ July 5, 2007. 

A340-24A4057 ........................................................................................................................ 01 .................................................... July 20, 2007. 

A340–24A5021 ....................................................................................................................... Original ............................................ July 5, 2007. 


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(5) For Model A330 aircraft operating 

under MMEL Item 24–22–01, ‘‘AC Main 

Generation,’’ or MMEL Item 36–11–01, ‘‘Bleed 

Air Supply System Failure’’: Unless the APU 

generator has been deferred in accordance 

with the MMEL by deactivation (quill shaft 

removed) or removal, the inspection required 

by paragraph (g)(2) or (g)(3), as applicable, of 

this AD must be performed prior to the first 

flight of the specified MMEL repair time 

interval. Accomplishing the actions in this 

paragraph terminates the actions required by 

paragraph (f)(2) of this AD. 

Note 2: For A330 aircraft, MMEL Item 24– 

22–01 (AC Main Generation) and/or MMEL 

Item 36–11–01 (Bleed Air Supply System 

Failure) require that the APU be used during 

the entire flight. 

NEW REQUIREMENTS OF THIS AD 

Actions and Compliance 

(h) Unless already done, do the following 

actions. 

(1) As of the effective date of this AD, 

before further flight after an APU generator 

or an APU is installed on the airplane: 

Inspect the APU generator scavenge oil filter 

element for contamination (including 

metallic particles), the APU generator drain 

plug for contamination (including metallic 

particles), and the APU generator scavenge 

filter housing for contamination (including 

metallic particles), in accordance with 

paragraph 4.2 of the applicable service 

information specified in Table 3 of this AD. 

Do all applicable corrective actions before 

further flight in accordance with paragraph 

4.2 of the applicable service information 

specified in Table 3 of this AD. 

(2) Within 450 aircraft flight hours or 200 

APU operating hours, whichever occurs later, 

after accomplishing the inspection required 

by paragraph (h)(1) of this AD, do the 

inspection as required by paragraph (g)(2) of 

this AD. Doing the installation required by 

paragraph (h)(5) of this AD terminates the 

requirements of this paragraph. 

(3) For Model A330 airplanes operated 

within the provisions of MMEL Item 24–22– 

01, ‘‘AC Main Generation,’’ that are 

dispatched with the APU operating during 

the entire flight in accordance with the 

provisions of MMEL Item 24–22–01: Perform 

the inspection required by paragraph (g)(2) of 

this AD at the applicable time in paragraph 

(h)(3)(i) or (h)(3)(ii) of this AD, unless the 

APU generator is removed or deactivated 

(quill shaft removed as described in the 

MMEL item). Doing the installation required 

by paragraph (h)(5) of this AD terminates the 

requirements of this paragraph. 

(i) Before the first flight of the MMEL 

rectification interval. 

(ii) Before the first flight following MMEL 

rectification. 

(4) Removing or deactivating the APU 

generator, or rendering the APU inoperative, 

in accordance with paragraph 4.3 of the 

applicable service information specified in 

Table 3 of this AD, defers the inspection 

required by paragraph (g)(2) of this AD. The 

deferred inspection must be performed before 

further flight after the system is reactivated. 

Doing the installation required by paragraph 

(h)(5) of this AD terminates the requirements 

of this paragraph. 

(5) Within 6 months after the effective date 

of this AD, install a secondary housing line 

replaceable unit (LRU) over the end of the 

APU generator, in accordance with the 

Accomplishment Instructions of the 

applicable service information specified in 

Table 6 of this AD. Performing this 

modification terminates the repetitive 

inspections required by paragraphs (g)(2) and 

(g)(3) of this AD, and the inspections 

required by paragraphs (h)(2), (h)(3), and 

(h)(4) of this AD. 

(6) Actions accomplished before the 

effective date of this AD in accordance with 

service information in Table 5 of this AD are 

acceptable for compliance with the 

corresponding actions specified in this AD. 

TABLE 5—SERVICE INFORMATION ACCEPTABLE FOR PREVIOUS COMPLIANCE

Airbus service bulletin— Dated— 

A330–20–3045 .................... June 13, 2008. 

A340–24–4058 .................... June 13, 2008. 

A340–24–5022 .................... June 23, 2008. 

FAA AD Differences 

Note 3: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(i) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, 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 on any airplane to 

which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

(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: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(j) Refer to MCAI EASA Airworthiness 

Directive 2008–0173, dated September 15, 

2008, and the service information identified 

in Table 6 of this AD for related information. 

TABLE 6—SERVICE INFORMATION REQUIRED BY THIS AD 

Airbus— Revision— Dated— 

AOT A330–24A3042 ........................................................................................................................................... 02 April 12, 2007. 

AOT A330–24A3044 ........................................................................................................................................... 03 May 26, 2008. 

AOT A340–24A4056 ........................................................................................................................................... 02 April 12, 2007. 

AOT A340–24A4057 ........................................................................................................................................... 03 December 20, 

2007. 

AOT A340–24A5020 ........................................................................................................................................... 02 April 12, 2007. 

AOT A340–24A5021 ........................................................................................................................................... 02 December 20, 

2007. 

Mandatory Service Bulletin A330–24–3045 ........................................................................................................ 01 October 1, 2008. 

Mandatory Service Bulletin A340–24–4058 ........................................................................................................ 01 October 1, 2008. 

Mandatory Service Bulletin A340–24–5022 ........................................................................................................ 01 November 27, 

2008. 

Material Incorporated by Reference 

(k) You must use the service information 

contained in Table 7 of this AD, as 

applicable, to do the actions required by this 

AD, unless the AD specifies otherwise. 


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Federal Register / Vol. 75, No. 133 / Tuesday, July 13, 2010 / Rules and Regulations 39795 

TABLE 7—ALL MATERIAL INCORPORATED BY REFERENCE

Airbus— Revision— Dated— 

AOT A330–24A3042 ........................................................................................................................................... 02 April 12, 2007. 

AOT A330–24A3044 ........................................................................................................................................... 03 May 26, 2008. 

AOT A340–24A4056 ........................................................................................................................................... 02 April 12, 2007. 

AOT A340–24A4057 ........................................................................................................................................... 03 December 20, 

2007. 

AOT A340–24–A5020 ......................................................................................................................................... 02 April 12, 2007. 

AOT A340–24A5021 ........................................................................................................................................... 02 December 20, 

2007. 

Mandatory Service Bulletin A330–24–3045 ........................................................................................................ 01 October 1, 2008. 

Mandatory Service Bulletin A340–24–4058 ........................................................................................................ 01 October 1, 2008. 

Mandatory Service Bulletin A340–24–5022 ........................................................................................................ 01 November 27, 

2008. 

(The AOT document number, revision level, and date are indicated on only page 1 of these documents.) 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information contained in Table 8 

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

part 51. 

TABLE 8—NEW MATERIAL INCORPORATED BY REFERENCE

Airbus— Revision— Dated— 

AOT A330–24A3044 ........................................................................................................................................... 03 May 26, 2008. 

AOT A340–24A4057 ........................................................................................................................................... 03 December 20, 

2007. 

AOT A340–24A5021 ........................................................................................................................................... 02 December 20, 

2007. 

Mandatory Service Bulletin A330–24–3045 ........................................................................................................ 01 October 1, 2008. 

Mandatory Service Bulletin A340–24–4058 ........................................................................................................ 01 October 1, 2008. 

Mandatory Service Bulletin A340–24–5022 ........................................................................................................ 01 November 27, 

2008. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of the service information 

contained in Table 9 of this AD on June 26, 

2007 (72 FR 31973, June 11, 2007). 

TABLE 9—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE

Airbus all operators telex— Revision 

level— Dated— 

A330–24A3042 ......................................................................................................................................................... 02 April 12, 2007. 

A340–24A4056 ......................................................................................................................................................... 02 April 12, 2007. 

A340–24A5020 ......................................................................................................................................................... 02 April 12, 2007. 

(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, June 23, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–16181 Filed 7–12–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0684; Directorate 

Identifier 2010–CE–031–AD; Amendment 

39–16360; AD 2010–14–15] 

RIN 2120–AA64 

Airworthiness Directives; Aircraft 

Industries a.s. (Type Certificate G60EU 

Previously Held by LETECKE ́ ZA ́ VODY 

a.s. and LET Aeronautical Works) 

Model L–13 Blanik Gliders 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 


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