48872 Federal Register / Vol. 74, No. 185 / Friday, September 25, 2009 / Proposed Rules 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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: 

Dowty Propellers (formerly Dowty 

Aerospace; Dowty Rotol Limited; and 

Dowty Rotol): Docket No. FAA–2009– 

0776; Directorate Identifier 2009–NE– 

32–AD. 

Comments Due Date 

(a) We must receive comments by October 

26, 2009. 

Affected Airworthiness Directives (ADs) 

(b) None. 

Applicability 

(c) This AD applies to Dowty Propellers 

R408/6–123–F/17 model propellers. These 

propellers are installed on, but not limited to, 

Bombardier, Inc. (formerly de Havilland 

Canada) models DHC–8–400, DHC–8–401, 

and DHC–8–402 series airplanes. 

Reason 

(d) This AD results from mandatory 

continuing airworthiness information (MCAI) 

issued by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. We are 

issuing this AD to prevent an in-flight double 

generator failure, which could result in 

reduced controllability of the airplane. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

(1) For R408/6–123–F/17 model propellers 

with a hub, actuator, and backplate assembly 

line-replaceable unit (LRU) SNs below 

DAP0347, do the following initial sealant 

application within 5,000 flight hours (FH) 

after the effective date of this AD: 

(i) Apply sealant between the bus bar 

assemblies and the backplate assembly. 

(ii) Use paragraph 3 of the 

Accomplishment Instructions of Dowty 

Propellers Service Bulletin No. D8400–61– 

66, Revision 1, dated May 4, 2007, to do the 

sealant application. 

(2) Thereafter, for all R408/6–123–F/17 

model propellers, re-apply sealant as 

specified in paragraphs (e)(1)(i) through 

(e)(1)(ii) within every additional 10,000 FH. 

Installation Prohibition 

(3) After modification of all propellers on 

an airplane as required by paragraph (e)(1) of 

this AD, do not install any Dowty R408/6– 

123–F/17 propeller on that airplane unless 

sealant has been applied between the bus bar 

assemblies and the backplate assembly of 

that propeller using the requirements of this 

AD. 

FAA AD Differences 

(f) Dowty Propellers Service Bulletin No. 

D8400–61–66, Revision 1, dated May 4, 2007, 

requires a one-time application of sealant for 

R408/6–123–F/17 model propellers with a 

hub, actuator, and backplate assembly LRU 

SNs below DAP0347. However, this AD and 

the MCAI require repetitive applications of 

sealant for all R408/6–123–F/17 model 

propellers. 

Alternative Methods of Compliance 

(AMOCs) 

(g) The Manager, Boston Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Related Information 

(h) Refer to EASA AD 2009–0114, dated 

May 28, 2009, and Dowty Propellers Service 

Bulletin No. D8400–61–66, Revision 1, dated 

May 4, 2007, for related information. Contact 

Dowty Propellers, Anson Business Park, 

Cheltenham Road East, Gloucester GL 29QN, 

UK; telephone: 44 (0) 1452 716000; fax: 44 

(0) 1452 716001, for a copy of this service 

information. 

(i) Contact Terry Fahr, Aerospace Engineer, 

Boston Aircraft Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: terry.fahr@faa.gov; telephone 

(781) 238–7155; fax (781) 238–7170, for more 

information about this AD. 

Issued in Burlington, MA, on September 

21, 2009. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–23209 Filed 9–24–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0790; Directorate 

Identifier 2008–NM–177–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330 and A340 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above that would 

supersede an existing AD. This 

proposed 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. 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by November 9, 2009. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–40, 1200 New Jersey Avenue, SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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. You 

may review copies of the referenced 

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 or 425–227–1152. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 


jlentini on DSKJ8SOYB1PROD with PROPOSALS
Federal Register / Vol. 74, No. 185 / Friday, September 25, 2009 / Proposed Rules 48873 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2009–0790; Directorate Identifier 

2008–NM–177–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We have lengthened the 30-day 

comment period for proposed ADs that 

address MCAI originated by aviation 

authorities of other countries to provide 

adequate time for interested parties to 

submit comments. The comment period 

for these proposed ADs is now typically 

45 days, which is consistent with the 

comment period for domestic transport 

ADs. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On August 21, 2007, we issued AD 

2007–18–04, Amendment 39–15184 (72 

FR 50042, August 30, 2007). That AD 

required actions intended to address an 

unsafe condition on the products listed 

above. 

Since we issued AD 2007–18–04, a 

terminating modification has been 

developed. The European Aviation 

Safety Agency (EASA), which is the 

Technical Agent for the Member States 

of the European Community, has issued 

EASA Airworthiness Directive 2008– 

0173, dated September 15, 2008 

(referred to after this as ‘‘the MCAI’’), 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) 

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 

Airbus has issued the service 

information in the following table. 

Document Revision Date 

Airbus Service Bulletin A330–24–3045 ............................ Original ............................................................................ June 13, 2008. 

Airbus Service Bulletin A340–24–4058 ............................ Original ............................................................................ June 13, 2008. 

Airbus Service Bulletin A340–24–5022 ............................ Original ............................................................................ June 23, 2008. 

Airbus All Operators Telex (AOT) A330–24A3044 .......... 03 ..................................................................................... May 26, 2008. 

Airbus AOT A340–24A4057 ............................................. 03 ..................................................................................... December 20, 2007. 

Airbus AOT A340–24A5021 ............................................. 02 ..................................................................................... December 20, 2007. 


jlentini on DSKJ8SOYB1PROD with PROPOSALS
48874 Federal Register / Vol. 74, No. 185 / Friday, September 25, 2009 / Proposed Rules 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

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 proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a NOTE within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 41 products of U.S. registry. 

The actions that are required by AD 

2007–18–04 and retained in this 

proposed AD take about 11 work-hours 

per product, at an average labor rate of 

$80 per work hour. Required parts cost 

about $0 per product. Based on these 

figures, the estimated cost of the 

currently required actions is $880 per 

product. 

We estimate that it would take about 

10 work-hours per product to comply 

with the new basic requirements of this 

proposed AD. The average labor rate is 

$80 per work-hour. Required parts 

would 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 

the proposed AD on U.S. operators to be 

$32,800, or $800 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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 proposed regulation: 

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 proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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: 

Airbus: Docket No. FAA–2009–0790; 

Directorate Identifier 2008–NM–177–AD. 

Comments Due Date 

(a) We must receive comments by 

November 9, 2009. 

Affected ADs 

(b) The proposed 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, 


jlentini on DSKJ8SOYB1PROD with PROPOSALS
Federal Register / Vol. 74, No. 185 / Friday, September 25, 2009 / Proposed Rules 48875 

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 Operational 

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 

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 level Date 

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 

(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 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 

level Date 

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

A330–24A3044 ....................................................................................................................................... 02 December 20, 2007. 

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

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

A340–24A4057 ....................................................................................................................................... 03 December 20, 2007. 

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

A340–24A5021 ....................................................................................................................................... 02 December 20, 2007. 


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TABLE 3—SERVICE INFORMATION

Airbus all operators telex Revision 

level Date 

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 service information 

specified in Table 2 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. 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 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. 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 level Date 

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

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

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

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

(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. 

(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). 

(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. 

(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 5 of this AD. Performing this 

modification terminates the repetitive 

inspections required by paragraphs (g)(2), 

(g)(3), and (h)(2) of this AD. 

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. 


jlentini on DSKJ8SOYB1PROD with PROPOSALS
Federal Register / Vol. 74, No. 185 / Friday, September 25, 2009 / Proposed Rules 48877 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act, 

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 5 of this AD for related information. 

TABLE 5—SERVICE INFORMATION REQUIRED BY THIS AD 

Airbus service information Revision level Date 

AOT A340–24A5021 ........................................................ 02 ..................................................................................... December 20, 2007. 

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. 

Service Bulletin A330–24–3045 ....................................... Original ............................................................................ June 13, 2008. 

Service Bulletin A340–24–4058 ....................................... Original ............................................................................ June 13, 2008. 

Service Bulletin A340–24–5022 ....................................... Original ............................................................................ June 23, 2008. 

Issued in Renton, Washington, on 

September 16, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–23189 Filed 9–24–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–0083; Directorate 

Identifier 2006–NM–266–AD] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) Model EMB–135BJ, 

–135ER, –135KE, –135KL, –135LR, 

–145, –145ER, –145MR, –145LR, 

–145XR, –145MP, and –145EP 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

supplemental NPRM for the products 

listed above. This action revises the 

earlier supplemental NPRM by 

expanding the scope. This proposed 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: It has been found the 

occurrence of engine anti-ice system 

valve failure, where the valve spring 

seat has broken and obstructed the antiice system venturi tube. Therefore, 

should the aircraft encounter icing 

conditions, ice may accrete in the 

engine inlet lip and be ingested through 

the air inlet, resulting in possible engine 

damage and flame-out. The proposed 

AD would require actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by October 15, 2009. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–40, 1200 New Jersey Avenue, SE., 

Washington, DC, between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER), Technical Publications 

Section (PC 060), Av. Brigadeiro Faria 

Lima, 2170—Putim—12227–901 Sa ̃o 

Jose dos Campos—SP—BRASIL; 

telephone: +55 12 3927–5852 or +55 12 

3309–0732; fax: +55 12 3927–7546; 

e-mail: distrib@embraer.com.br; 

Internet: http://www.flyembraer.com. 

You may review copies of the 

referenced 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 or 425–227–1152. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527)) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1405; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2007–0083; Directorate Identifier 

2006–NM–266–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We proposed to amend 14 CFR part 

39 with an earlier supplemental NPRM 

for the specified products, which was 

published in the Federal Register on 


jlentini on DSKJ8SOYB1PROD with PROPOSALS