35780 Federal Register / Vol. 74, No. 138 / Tuesday, July 21, 2009 / Rules and Regulations 

Bellonte, 31707 Blagnac Cedex, France; 

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

93 44 51; e-mail: account.airwortheas@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 or 425–227–1152. 

(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 July 2, 

2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–17122 Filed 7–20–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0644; Directorate 

Identifier 2009–NM–059–AD; Amendment 

39–15972; AD 2009–15–09] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A380–841, –842, and –861 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

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: 

During inspections in production and on 

in-service aircraft, a number of Overheat 

Detection System (OHDS) installation nonconformities have been identified along the 

bleed air ducting. 

Some installation issues which may lead to 

a degraded leak detection capability have 

been reported. In case of hot air leakage, the 

potential degradation of the OHDS would not 

allow preventing damages to structure or 

components * * *. 

* * * * * 

Nonconforming installation or a 

failure of the OHDS could allow 

undetected leakage of bleed air from the 

hot engine/auxiliary power unit causing 

damage to the airplane structure and 

various airplane components and 

systems. This AD requires actions that 

are intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective 

August 5, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication, listed in the AD 

as of August 5, 2009. 

We must receive comments on this 

AD by August 20, 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1175; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2009–0066, 

dated March 19, 2009 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

During inspections in production and on 

in-service aircraft, a number of Overheat 

Detection System (OHDS) installation nonconformities have been identified along the 

bleed air ducting. 

Some installation issues which may lead to 

a degraded leak detection capability have 

been reported. In case of hot air leakage, the 

potential degradation of the OHDS would not 

allow preventing damages to structure or 

components, and therefore could lead to an 

unsafe condition. 

To ensure that in-service aircraft are free of 

such non-conformities, this AD requires an 

inspection of the OHDS installation along the 

bleed air ducting and, in case of findings [any 

sensing element or insulation muff installed 

incorrectly], to bring back the installation 

into the compliant configuration. 

Nonconforming installation or a failure 

of the OHDS could allow undetected 

leakage of bleed air from the hot engine/ 

auxiliary power unit causing damage to 

the airplane structure and various 

airplane components and systems. The 

inspection of the OHDS installation, for 

certain airplanes, consists of inspecting 

the APU overheat sensing elements APU 

1 Loop A and B, the APU overheat 

sensing elements APU 2 Loop A and B, 

the crossbleed overheat sensing 

element, the forward cargo compartment 

heating element, and the sensing 

element of the overheat detection unit of 

the wing. For certain other airplanes, 

inspecting the OHDS installation 

consists of inspecting the forward cargo 

compartment heating element. You may 

obtain further information by examining 

the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A380–36–8004, dated February 13, 

2009. 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 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 issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

There are no products of this type 

currently registered in the United States. 

However, this rule is necessary to 

ensure that the described unsafe 

condition is addressed if any of these 


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Federal Register / Vol. 74, No. 138 / Tuesday, July 21, 2009 / Rules and Regulations 35781 

products are placed on the U.S. Register 

in the future. 

Differences Between the 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 FAA policies. 

Any such differences are highlighted in 

a Note within the AD. 

FAA’s Determination of the Effective 

Date 

Since there are currently no domestic 

operators of this product, notice and 

opportunity for public comment before 

issuing this AD are unnecessary. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2009–0644; 

Directorate Identifier 2009–NM–059– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of 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 AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify 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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2009–15–09 Airbus: Amendment 39–15972. 

Docket No. FAA–2009–0644; Directorate 

Identifier 2009–NM–059–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective August 5, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A380– 

841, –842, and –861 airplanes, certificated in 

any category, serial numbers 3, 5, 6, 8, 10, 11, 

12, 13, 14, 15, 16, 20, and 22. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 36: Pneumatic. 

Reason 

(e) The mandatory continued airworthiness 

information (MCAI) states: 

During inspections in production and on 

in-service aircraft, a number of Overheat 

Detection System (OHDS) installation nonconformities have been identified along the 

bleed air ducting. 

Some installation issues which may lead to 

a degraded leak detection capability have 

been reported. In case of hot air leakage, the 

potential degradation of the OHDS would not 

allow preventing damages to structure or 

components, and therefore could lead to an 

unsafe condition. 

To ensure that in-service aircraft are free of 

such non-conformities, this AD requires an 

inspection of the OHDS installation along the 

bleed air ducting and, in case of findings [any 

sensing element or insulation muff installed 

incorrectly], to bring back the installation 

into the compliant configuration. 

Nonconforming installation or a failure of 

the OHDS could allow undetected leakage of 

bleed air from the hot engine/auxiliary power 

unit causing damage to the airplane structure 

and various airplane components and 

systems. The inspection of the OHDS 

installation, for certain airplanes, consists of 

inspecting the APU overheat sensing 

elements APU 1 Loop A and B, the APU 

overheat sensing elements APU 2 Loop A and 

B, the crossbleed overheat sensing element, 

the forward cargo compartment heating 

element, and the sensing element of the 

overheat detection unit of the wing. For 

certain other airplanes, inspecting the OHDS 

installation consists of inspecting the forward 

cargo compartment heating element. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Within 90 days after the effective date 

of this AD, do a one-time detailed visual 

inspection to determine whether the OHDS 

sensing elements and insulation muffs have 

been correctly installed, in accordance with 

Airbus Service Bulletin A380–36–8004, 

dated February 13, 2009. 

(2) If, during any inspection required by 

paragraph (f)(1) of this AD, any sensing 

element or insulation muff is found to have 

been installed incorrectly, before further 

flight, bring the installation into compliant 

configuration, in accordance with Airbus 

Service Bulletin A380–36–8004, dated 

February 13, 2009. 

(3) Submit a report of the findings (both 

positive and negative) of the inspection 

required by paragraph (f)(1) of this AD to 

Airbus, Customer Services Directorate, 1 

Rond Point Maurice Bellonte, 31707 Blagnac 

Cedex France, as specified in Figures A– 

GBCAA and A–GBDAA of Airbus Service 

Bulletin A380–36–8004, dated February 13, 


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35782 Federal Register / Vol. 74, No. 138 / Tuesday, July 21, 2009 / Rules and Regulations 

2009, at the applicable time specified in 

paragraph (f)(3)(i) or (f)(3)(ii) of this AD. 

(i) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(ii) If the inspection was accomplished 

prior to the effective date of this AD: Submit 

the report within 30 days after the effective 

date of this AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) 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: Todd Thompson, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1175; 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. 

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 FAAapproved 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, 

the Office of Management and Budget (OMB) 

has approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency (EASA) 

Airworthiness Directive 2009–0066, dated 

March 19, 2009; and Airbus Service Bulletin 

A380–36–8004, dated February 13, 2009; for 

related information. 

Material Incorporated by Reference 

(i) You must use Airbus Service Bulletin 

A380–36–8004, dated February 13, 2009, 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 Airbus SAS—EANA 

(Airworthiness Office); 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 562 110 253; Fax +33 562 110 

307; e-mail account.airworthA380@airbus.com; Internet http:// 

www.airbus.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 or 425–227–1152. 

(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 July 6, 

2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–16763 Filed 7–20–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–1311; Directorate 

Identifier 2007–NE–48–AD; Amendment 39– 

15976; AD 2009–15–13] 

RIN 2120–AA64 

Airworthiness Directives; Honeywell 

International Inc., T5313 and T5317 

Series Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for 

Honeywell International Inc., T5313 and 

T5317 series turboshaft engines. This 

AD requires initial and repetitive visual 

inspections and initial and repetitive 

ultrasonic inspections of combustion 

chamber housings (CCHs) for cracks. 

This AD results from eight instances of 

cracks in CCHs. Two of the instances 

resulted in an engine shutdown during 

flight. We are issuing this AD to detect 

cracks in the CCH, which could result 

in rupture of the CCH, leading to loss of 

engine power and damage to the 

helicopter. 

DATES: This AD becomes effective 

August 25, 2009. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulations as 

of August 25, 2009. 

ADDRESSES: You can get the service 

information identified in this AD from 

Honeywell International Inc., P.O. Box 

52181, Phoenix, AZ 85072–2181, 

U.S.A.; telephone (800) 601–3099 

(U.S.A.) or (602) 365–3099 

(International), Web site: http:// 

portal.honeywell.com/wps/portal/aero. 

The Docket Operations office is 

located at Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue, SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

FOR FURTHER INFORMATION CONTACT: 

Robert Baitoo, Aerospace Engineer, Los 

Angeles Aircraft Certification Office, 

FAA, Transport Airplane Directorate, 

3960 Paramount Blvd., Lakewood, CA 

90712–4137; e-mail: 

robert.baitoo@faa.gov; telephone (562) 

627–5245; fax (562) 627–5210. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed AD. The proposed AD 

applies to Honeywell International Inc., 

T5313 and T5317 series turboshaft 

engines. We published the proposed AD 

in the Federal Register on December 16, 

2008 (73 FR 76291). That action 

proposed to require initial and 

repetitive visual inspections and initial 

and repetitive ultrasonic inspections of 

CCHs for cracks. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is provided in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We received no 

comments on the proposal or on the 

determination of the cost to the public. 

Change to Optional Terminating Action 

Paragraph 

We changed optional terminating 

action paragraph (k) to state that 

installation of a CCH P/N 1–130–610–19 

or 1–130–610R16 terminates the 

inspection requirements of this AD. 

These CCHs eliminate the failure mode 

that cause cracking. 


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