Federal Register / Vol. 74, No. 117 / Friday, June 19, 2009 / Rules and Regulations 29123 

Subject 

(d) Air Transport Association (ATA) of 

America Code 26: Fire protection. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

During receipt of spare parts at the final 

assembly line, it was discovered that lugs of 

the assembly nut, part number (P/N) 

A2621005000200, had been inverted (wrong 

orientation of the braking pin) during 

manufacturing process at the supplier. 

The assembly nut P/N A2621005000200 is 

part of the engine fire-extinguishing piping 

assembly. It connects the extinguisher 

discharge head with the piping. The lugs 

function is to prevent the connection 

untwisting once it has been hand-tightened 

with the correct torque. This lug inversion 

could give the illusion of correct torque 

whereas the affected parts are not properly 

connected. 

Loose connection could lead to loss of the 

fire extinguishing system integrity and 

therefore inability to ensure the adequate 

agent concentration. In combination with an 

engine fire event, it could result in a 

temporary uncontrolled engine fire, which 

constitutes an unsafe condition. 

To restore connection integrity, this 

Airworthiness Directive (AD) requires a onetime general visual inspection of the affected 

nut assembly to detect and correct any wrong 

orientation of lugs. 

The corrective actions include a temporary 

repair (restoration) and replacing the fire 

extinguisher bottle nut assembly with the 

braking pin in the inverted position, if 

necessary. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) Within 900 flight hours after the 

effective date of this AD, perform a general 

visual inspection to detect any wrong 

orientation of the lugs of the fire extinguisher 

bottle nut assembly of both engines, and do 

all applicable corrective actions specified in 

paragraphs (f)(1)(i) and (f)(1)(ii) of this AD, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–26–3043, dated October 7, 

2008. 

(i) Before further flight, if the correct nut 

assembly is available, replace the fire 

extinguisher bottle nut assembly. 

(ii) Before further flight, if the correct nut 

assembly is not available, do the temporary 

repair; and within 900 flight hours after 

doing the repair, replace the fire extinguisher 

bottle nut assembly with the correct one. 

(2) Submit a report of the findings of the 

inspection required by paragraph (f)(1) of this 

AD using Appendix 01 of Airbus Mandatory 

Service Bulletin A330–26–3043, dated 

October 7, 2008, at the applicable time 

specified in paragraph (f)(2)(i) or (f)(2)(ii) of 

this AD. Send the report to Airbus 

Department SEEE6, Airbus Customer 

Services Directorate, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex France, Attn: 

SDC32 Technical Data and Documentation 

Services; fax 33 5 61 93 28 06; e-mail 

sb.reporting@airbus.com. 

(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: 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, 

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 MCAI European Aviation 

Safety Agency Airworthiness Directive 2008– 

0196, dated October 27, 2008; and Airbus 

Mandatory Service Bulletin A330–26–3043, 

including Appendices 01, 2, and 3, dated 

October 7, 2008; for related information. 

Material Incorporated by Reference 

(i) You must use Airbus Mandatory Service 

Bulletin A330–26–3043, including 

Appendices 01, 2, and 3, dated October 7, 

2008, 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—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. 

(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 June 11, 

2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–14308 Filed 6–18–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0133; Directorate 

Identifier 2008–NM–107–AD; Amendment 

39–15933; AD 2009–12–10] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

Systems (Operations) Limited Model 

BAe 146 and Avro 146–RJ Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to all BAE Systems 

(Operations) Limited Model BAe 146 

and Avro 146–RJ airplanes. That AD 

currently requires repetitive inspections 

for corrosion of frames 15, 18, 41, and 

43 and applicable related investigative 

and corrective actions. The existing AD 

also provides an optional action that 

would extend the repetitive inspection 

interval. This new AD also requires a 

high frequency eddy current inspection 

for corrosion of the outer frame flanges 

and door hinge bosses of frames 15, 18, 

41, and 43. This AD results from a 

report indicating that corrosion has been 

detected in the outer frame flanges and 

door hinge bosses during scheduled 

maintenance. We are issuing this AD to 

prevent reduced structural integrity of 

the airplane. 

DATES: This AD becomes effective July 

24, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 


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29124 Federal Register / Vol. 74, No. 117 / Friday, June 19, 2009 / Rules and Regulations 

of a certain publication listed in the AD 

as of July 24, 2009. 

ADDRESSES: For service information 

identified in this AD, contact BAE 

Systems Regional Aircraft, 13850 

McLearen Road, Herndon, Virginia 

20171; telephone 703–736–1080; e-mail 

raebusiness@baesystems.com; Internet 

http://www.baesystems.com/Businesses/ 

RegionalAircraft/index.htm. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility 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 address for the 

Docket Office (telephone 800–647–5527) 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

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 FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2006–12–09, amendment 

39–14634 (71 FR 33602, June 12, 2006). 

The existing AD applies to all BAE 

Systems (Operations) Limited Model 

BAe 146 and Avro 146–RJ airplanes. 

That NPRM was published in the 

Federal Register on February 18, 2009 

(74 FR 7565). That NPRM proposed to 

continue to require repetitive 

inspections for corrosion of frames 15, 

18, 41, and 43 and applicable related 

investigative and corrective actions. The 

NPRM also proposed to continue to 

provide an optional action that would 

extend the repetitive inspection 

interval. In addition, the NPRM 

proposed to require a high frequency 

eddy current (HFEC) inspection for 

corrosion of the outer frame flanges and 

door hinge bosses of frames 15, 18, 41, 

and 43. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. No comments 

have been received on the NPRM or on 

the determination of the cost to the 

public. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD as proposed. 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD. 

ESTIMATED COSTS

Action Work hours Average labor 

rate per hour 

Cost per 

airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

HFEC inspection, per inspection cycle (required by AD 

2006–12–09) .................................................................... 5 $80 $400 1 $400 

Detailed Inspection, per inspection cycle (required by AD 

2006–12–09) .................................................................... 3 80 240 1 240 

HFEC inspection, per inspection cycle (new action) ........... 5 80 400 1 400 

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 regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

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 Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–14634 (71 

FR 33602, June 12, 2006) and by adding 

the following new airworthiness 

directive (AD): 

2009–12–10 BAE Systems (Operations) 

Limited (Formerly British Aerospace 


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Federal Register / Vol. 74, No. 117 / Friday, June 19, 2009 / Rules and Regulations 29125 

Regional Aircraft): Amendment 39– 

15933. Docket No. FAA–2009–0133; 

Directorate Identifier 2008–NM–107–AD. 

Effective Date 

(a) This AD becomes effective July 24, 

2009. 

Affected ADs 

(b) This AD supersedes AD 2006–12–09. 

Applicability 

(c) This AD applies to all BAE Systems 

(Operations) Limited Model BAe 146–100A, 

–200A, and –300A series airplanes; and 

Model Avro 146–RJ70A, 146–RJ85A, and 

146–RJ100A airplanes; certificated in any 

category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Unsafe Condition 

(e) This AD results from a report indicating 

that corrosion has been detected in the outer 

frame flanges and door hinge bosses during 

scheduled maintenance. We are issuing this 

AD to prevent reduced structural integrity of 

the airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Restatement of Requirements of AD 2006– 

12–09 

Repetitive Inspections 

(g) Use high-frequency eddy current 

(HFEC) and detailed methods to inspect for 

signs of corrosion (including cracks, 

blistering, or flaking paint) of frames 15, 18, 

41, and 43, in accordance with the 

Accomplishment Instructions of BAE 

Systems (Operations) Limited Inspection 

Service Bulletin ISB.53–182, dated March 16, 

2005, except as required by paragraph (k) of 

this AD. Inspect at the applicable time 

specified in 1.D. ‘‘Compliance’’ of BAE 

Systems (Operations) Limited Inspection 

Service Bulletin ISB.53–182, dated March 16, 

2005. Application of corrosion-preventive 

treatment, in accordance with BAE Systems 

(Operations) Limited Inspection Service 

Bulletin ISB.53–182, dated March 16, 2005; 

or Revision 1, dated August 6, 2007; extends 

the repetitive inspection interval, as specified 

in Table 2 in 1.D. ‘‘Compliance’’ of BAE 

Systems (Operations) Limited Inspection 

Service Bulletin ISB.53–182, dated March 16, 

2005. 

Note 1: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’ 

Corrective Action 

(h) If any discrepancy is found during any 

inspection required by paragraph (g) of this 

AD: Before further flight, perform applicable 

related investigative/corrective actions in 

accordance with the Accomplishment 

Instructions of BAE Systems (Operations) 

Limited Inspection Service Bulletin ISB.53– 

182, dated March 16, 2005, except as 

required by paragraphs (i) and (k) of this AD. 

Exceptions to Service Bulletin Specifications 

(i) If BAE Systems (Operations) Limited 

Inspection Service Bulletin ISB.53–182, 

dated March 16, 2005, specifies to contact the 

manufacturer for appropriate action, before 

further flight, repair per a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the Civil Aviation Authority (or its delegated 

agent); or European Aviation Safety Agency 

(EASA) (or its delegated agent). 

(j) Where BAE Systems (Operations) 

Limited Inspection Service Bulletin ISB.53– 

182, dated March 16, 2005, specifies a 

compliance time after the issuance of the 

service bulletin, this AD requires compliance 

within the specified compliance time after 

July 17, 2006 (the effective date of AD 2006– 

12–09). Where BAE Systems (Operations) 

Limited Inspection Service Bulletin ISB.53– 

182, dated March 16, 2005, specifies a 

compliance time ‘‘since date of construction’’ 

of the airplane, this AD requires compliance 

since the date of issuance of the original 

standard airworthiness certificate or the date 

of issuance of the original export certificate 

of airworthiness. 

New Requirements of This AD 

New Service Bulletin 

(k) As of the effective date of this AD: Do 

the actions required by paragraphs (g) and (h) 

of this AD in accordance with the 

Accomplishment Instructions of BAE 

Systems (Operations) Limited Inspection 

Service Bulletin ISB.53–182, Revision 1, 

dated August 6, 2007, except as required by 

paragraph (n) of this AD. 

Additional Inspection Areas 

(l) At the applicable compliance time 

specified in paragraph (g) of this AD, except 

as provided by paragraph (o) of this AD; or 

within six months after the effective date of 

this AD; whichever occurs later: Do an HFEC 

inspection for corrosion of the outer frame 

flanges and door hinge bosses of frames 15, 

18, 41, and 43, in accordance with the 

Accomplishment Instructions of BAE 

Systems (Operations) Limited Inspection 

Service Bulletin ISB.53–182, Revision 1, 

dated August 6, 2007 (‘‘the service bulletin’’). 

Repeat the inspection thereafter at the 

applicable time specified in paragraph 1.D., 

‘‘Compliance,’’ of the service bulletin. 

Application of corrosion-preventive 

treatment, in accordance with the 

Accomplishment Instructions of the service 

bulletin, extends the repetitive inspection 

interval, as specified in Table 2 in paragraph 

1.D., ‘‘Compliance,’’ of the service bulletin. 

Corrective Action for Additional Inspection 

(m) If any discrepancy is found during any 

inspection required by paragraph (l) of this 

AD: Before further flight, perform applicable 

related investigative/corrective actions in 

accordance with the Accomplishment 

Instructions of BAE Systems (Operations) 

Limited Inspection Service Bulletin ISB.53– 

182, Revision 1, dated August 6, 2007, except 

as required by paragraph (n) of this AD. 

Exceptions to BAE Systems (Operations) 

Limited Inspection Service Bulletin ISB.53– 

182, Revision 1 

(n) If BAE Systems (Operations) Limited 

Inspection Service Bulletin ISB.53–182, 

Revision 1, dated August 6, 2007, specifies to 

contact the manufacturer for appropriate 

action, before further flight, repair per a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA (or its 

delegated agent). 

(o) Where BAE Systems (Operations) 

Limited Inspection Service Bulletin ISB.53– 

182, Revision 1, dated August 6, 2007, 

specifies a compliance time after the issuance 

of the service bulletin, this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. Where 

BAE Systems (Operations) Limited 

Inspection Service Bulletin ISB.53–182, 

Revision 1, dated August 6, 2007, specifies a 

compliance time ‘‘since date of construction’’ 

of the airplane, this AD requires compliance 

since the date of issuance of the original 

airworthiness certificate or the date of 

issuance of the original export certificate of 

airworthiness. 

No Reporting 

(p) Although BAE Systems (Operations) 

Limited Inspection Service Bulletin ISB.53– 

182, dated March 16, 2005; and Revision 1, 

dated August 6, 2007; specify to submit 

information to the manufacturer, this AD 

does not include such a requirement. 

Alternative Methods of Compliance 

(AMOCs) 

(q) The Manager, International Branch, 

ANM–116, 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. 

Related Information 

(r) European Aviation Safety Agency 

Airworthiness Directive 2008–0092 R1, dated 

May 15, 2008, also addresses the subject of 

this AD. 

Material Incorporated by Reference 

(s) You must BAE Systems (Operations) 

Limited Inspection Service Bulletin ISB.53– 

182, Revision 1, dated August 6, 2007; as 


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29126 Federal Register / Vol. 74, No. 117 / Friday, June 19, 2009 / Rules and Regulations 

applicable; to do the actions required by this 

AD, unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact BAE Systems Regional 

Aircraft, 13850 McLearen Road, Herndon, 

Virginia 20171; telephone 703–736–1080; email raebusiness@baesystems.com; Internet 

http://www.baesystems.com/Businesses/ 

RegionalAircraft/index.htm. 

(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 June 2, 

2009. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–13567 Filed 6–18–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0557; Directorate 

Identifier 2009–CE–031–AD; Amendment 

39–15944; AD 2009–13–05] 

RIN 2120–AA64 

Airworthiness Directives; SOCATA 

Model TBM 700 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), 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) 

issued by the aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

During a SOCATA flight test, it has been 

noted some difficulties for the pilot to release 

oxygen. 

After investigation it has been found that, 

due to the design of the oxygen generator 

release pin, one of the mask’s lanyard linked 

to the pin can be jammed when it is pulled 

by a pilot or a passenger. 

This condition, if not corrected, would 

lead, in case of an emergency procedure due 

to decompression to a risk of generator fault 

with subsequent lack of oxygen on crew and/ 

or passenger. 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective July 

9, 2009. 

On July 9, 2009, the Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

We must receive comments on this 

AD by July 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 

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

Washington, DC 20590, 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 Management Facility 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 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: 

Albert Mercado, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4119; fax: (816) 329–4090. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued Emergency AD 

No. 2009–0096–E, dated April 21, 2009, 

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

correct an unsafe condition for the 

specified products. The MCAI states: 

During a SOCATA flight test, it has been 

noted some difficulties for the pilot to release 

oxygen. 

After investigation it has been found that, 

due to the design of the oxygen generator 

release pin, one of the mask’s lanyard linked 

to the pin can be jammed when it is pulled 

by a pilot or a passenger. 

This condition, if not corrected, would 

lead, in case of an emergency procedure due 

to decompression to a risk of generator fault 

with subsequent lack of oxygen on crew and/ 

or passenger. 

For the reason described above, SOCATA 

has released Pilot Operating Handbook (POH) 

Temporary Revision (TR) 03 which asks, in 

case of failure to release oxygen, to pull on 

the other mask lanyard in order to activate 

the oxygen generator. 

A SOCATA modification enabling to solve 

this issue is under preparation. Once this 

modification release, this AD is expected to 

be revised to confirm the acceptability of that 

modification. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

SOCATA has issued SOCATA TBM 

700 A & B Pilot Operating Handbook 

(POH), Temporary Revision No. 3, dated 

March 2009. The actions described in 

page 3.13.5 of this service information 

are intended to correct the unsafe 

condition identified in the MCAI. 

FAA’s Determination and Requirements 

of the 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 this State of 

Design Authority, they have notified us 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all 

information provided by the State of 

Design Authority and determined the 

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 have also required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 

Any such differences are described in a 


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