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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Federal Register / Vol. 74, No. 138 / Tuesday, July 21, 2009 / Rules and Regulations 35783 

Incorporation by Reference of Service 

Bulletin Appendix 

Since we issued the proposed AD, we 

realized that we need to add the 

incorporation by reference of the 

Appendix of Honeywell International 

Inc. Service Bulletin No. T53–0144, 

Revision 4, dated March 31, 2008 for 

operators to perform the ultrasonic 

inspections. We added that reference to 

inspection paragraphs (i) and (j) of this 

AD. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD with the changes 

described previously. 

Costs of Compliance 

We estimate that this AD will affect 

100 engines installed on helicopters of 

U.S. registry. We also estimate that it 

will take about 3 work-hours per engine 

to perform the actions, and that the 

average labor rate is $80 per work-hour. 

No parts are required. Based on these 

figures, we estimate the total cost of the 

AD to U.S. operators to be $24,000. 

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 have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

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 summary of the costs 

to comply with this AD and placed it in 

the AD Docket. You may get a copy of 

this summary at the address listed 

under ADDRESSES. 

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 Federal Aviation Administration 

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 airworthiness 

directive: 

2009–15–13 Honeywell International Inc. 

(Formerly AlliedSignal and TextronLycoming): Amendment 39–15976. 

Docket No. FAA–2008–1311; Directorate 

Identifier 2007–NE–48–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective August 25, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Honeywell 

International Inc. T5313B, T5317A, T5317A– 

1, T5317B, and T5317BCV turboshaft engines 

with combustion chamber housing (CCH), 

part numbers (P/Ns) 1–130–610–05, 1–130– 

610–12, and 1–130–610–17, installed. These 

engines are installed on, but not limited to, 

Bell 205 and 210 Series and Kaman K–1200 

helicopters. 

Unsafe Condition 

(d) 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. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 

Initial Visual Inspection 

(f) For CCH, P/N 1–130–610–05 and 1– 

130–610–12, within 50 hours time-in-service 

(TIS) after the effective date of this AD, 

inspect the area between points A and B 

around the entire housing circumference in 

Figure 1 of this AD for weld repairs and 

cracks. 

(1) If you find any cracks, replace the CCH 

before further flight. Honeywell International 

Inc. Alert Service Bulletin (ASB) T53–A0142, 

Revision 1, dated September 14, 2006, 

contains additional guidance on replacing 

the CCH. 

(2) If you find any weld repairs, replace the 

CCH within 100 hours TIS after the visual 

inspection. Honeywell International Inc. ASB 

T53–A0142, Revision 1, dated September 14, 

2006, contains additional guidance on 

replacing the CCH. 

Repetitive Visual Inspections 

(g) For CCH, P/N 1–130–610–05 and 1– 

130–610–12, inspect the area between points 

A and B around the entire housing 

circumference in Figure 1 of this AD for 

cracks within every 50 hours time-since-last 

inspection. Honeywell International Inc. 

Standard Practices Manual 70–20–02, SP 

1302, contains additional guidance on visual 

inspection. 

(h) If you find any cracks, replace the CCH 

before further flight. Honeywell International 

Inc. ASB T53–A0142, Revision 1, dated 

September 14, 2006, contains additional 

guidance on replacing the CCH. 


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35784 Federal Register / Vol. 74, No. 138 / Tuesday, July 21, 2009 / Rules and Regulations 

Initial Ultrasonic Inspection 

(i) Perform an ultrasonic inspection on the 

CCH. Use Honeywell International Inc. 

Service Bulletin (SB) No. T53–0144, Revision 

4, dated March 31, 2008, section 3. 

Accomplishment Instructions and the SB 

Appendix to perform the ultrasonic 

inspection at the following compliance times. 

(1) For CCH, P/N 1–130–610–05 and 1– 

130–610–12, within 500 hours TIS or next 

hot section inspection, whichever occurs first 

after the effective date of this AD, but not to 

exceed 6 months after the effective date of 

this AD. 

(2) For CCH, P/N 1–130–610–17, perform 

at the first overhaul, but do not exceed 5,000 

hours or 11,000 cycles, after the effective date 

of this AD, whichever occurs first. 

Repetitive Ultrasonic Inspections 

(j) Repeat the ultrasonic inspection on the 

CCH using Honeywell International Inc. SB 

No. T53–0144, Revision 4, dated March 31, 

2008, section 3. Accomplishment 

Instructions and the SB Appendix at the 

following compliance times: 

(1) Within every 1,200 flights, defined as 

the cumulative number of landings, since the 

last inspection; or 

(2) Within every 200 flights, if the last 

inspection had ultrasonic findings as defined 

in paragraph 3.A.(2) or paragraph 3.A.(3) of 

Honeywell International Inc. SB No. T53– 

0144, Revision 4, dated March 31, 2008. 

Optional Terminating Action 

(k) Installation of a CCH P/N 1–130–610– 

19 or 1–130–610R16, or an FAA approved 

equivalent part, terminates the inspection 

requirements of this AD. 

Alternative Methods of Compliance 

(l) The Manager, Los Angeles Aircraft 

Certification Office, has the authority to 

approve alternative methods of compliance 

for this AD if requested using the procedures 

found in 14 CFR 39.19. 

Related Information 

(m) Honeywell International Inc. ASB T53– 

A0142, Revision 1, dated September 14, 

2006, and Standard Practices Manual 70–20– 

02, SP 1302, pertain to the subject of this AD. 

Contact Honeywell International Inc., P.O. 

Box 52181, Phoenix, AZ 85072–2181; 

telephone (800) 601–3099, Web site: http:// 

portal.honeywell.com/wps/portal/aero, for a 

copy of this service information. 

(n) 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, for more information about this AD. 

Material Incorporated by Reference 

(o) You must use the service information 

specified in the following Table 1 to perform 

the ultrasonic inspections required by this 

AD. The Director of the Federal Register 

approved the incorporation by reference of 

the documents listed in the following Table 

1 in accordance with 5 U.S.C. 552(a) and 1 

CFR part 51. Contact Honeywell International 

Inc., P.O. Box 52181, Phoenix, AZ 85072– 

2181; telephone (800) 601–3099, Web site: 

http://portal.honeywell.com/wps/portal/aero, 

for a copy of this service information. You 

may review copies at the FAA, New England 

Region, 12 New England Executive Park, 

Burlington, MA; or at the National Archives 

and Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal-register/ 

cfr/ibr-locations.html. 


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Federal Register / Vol. 74, No. 138 / Tuesday, July 21, 2009 / Rules and Regulations 35785 

TABLE 1—INCORPORATION BY REFERENCE

Honeywell International Inc. Service Bulletin No. Page Revision Date 

T53–0144, Total Pages: 10 .................................................................................................... ALL ....................... 4 March 31, 2008. 

T53–0144, Appendix, Total Pages: 13 .................................................................................. ALL ....................... C January 25, 2008. 

Issued in Burlington, Massachusetts, on 

July 14, 2009. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–17146 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–2009–0645; Directorate 

Identifier 2009–NM–034–AD; Amendment 

39–15973; AD 2009–15–10] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–301, –321, –322, –341, and –342 

Series Airplanes, and Airbus Model 

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

–313 Series 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 accomplishment of A330–300 

Airworthiness Limitation Item (ALI) task 

57.11.04–01–02 of a fastener hole between 

stringer 38 and 39 at FR40 rear fitting web, 

a crack was found on an adjacent hole at 

vertical post Y1959 lower attachment on both 

sides. 

Other crack findings on this adjacent hole 

have been reported on A330–300 and A340– 

200/–300 aircraft as a result of sampling 

inspections. 

If not corrected, crack propagation could 

result in loss of the fuselage structural 

integrity. 

* * * * * 

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 certain publications 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: 

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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2009–0001, 

dated January 8, 2009 (referred to after 

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

condition for the specified products. 

The MCAI states: 

During accomplishment of A330–300 

Airworthiness Limitation Item (ALI) task 

57.11.04–01–02 of a fastener hole between 

stringer 38 and 39 at FR40 rear fitting web, 

a crack was found on an adjacent hole at 

vertical post Y1959 lower attachment on both 

sides. 

Other crack findings on this adjacent hole 

have been reported on A330–300 and A340– 

200/–300 aircraft as a result of sampling 

inspections. 

If not corrected, crack propagation could 

result in loss of the fuselage structural 

integrity. 

In order to fulfil[l] the certification 

requirements and following a fatigue analysis 

based on reported findings, a repetitive High 

Frequency Eddy Current (HFEC) Rototest 

inspection on the affected adjacent holes on 

both left hand (LH) and right hand (RH) sides 

between stringer 38 and 39 at FR40 rear 

fitting web is required by this AD and, in 

case of crack finding, the associated 

corrective actions have to be applied. 

The associated corrective actions are 

oversizing the holes and performing an 

additional rototest inspection for 

cracking. If the cracking is within 

certain limits, the corrective action is to 

install oversize fasteners. If the cracking 

exceeds certain limits defined in the 

service bulletin, the corrective action is 

contacting Airbus for repair instructions 

and doing the repair. You may obtain 

further information by examining the 

MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A330–57–3107, including 

Appendices 01 and 02, dated October 7, 

2008; and Mandatory Service Bulletin 

A340–57–4117, including Appendices 

01 and 02, dated October 7, 2008. 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. 


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