Federal Register / Vol. 71, No. 202 / Thursday, October 19, 2006 / Rules and Regulations 61639 

Actions Compliance Procedures 

(5) For Model N24A airplanes: 

(i) Fabricate a placard that incorporates the 

following words (using at least 1⁄8-inch 

letters) and install this placard on the instrument panel within the pilot’s clear 

view: ‘‘USE 10° FLAP FOR TAKE-OFF 

AND LANDING—WARNING—DO NOT 

EXCEED 10° FLAP EXTENSION DURING FLIGHT, LANDING GEAR UP 

WARNING WILL INITIATE FOR A 

TORQUE PRESSURE OF LESS THAN 

30 PSI’’; and 

(ii) Incorporate the following information 

into the Limitations section of the AFM: 

(A) Limit the maximum flap extension 

to 10 degrees; and 

(B) Limit flaps down operations for 

landing to 10° flap. 

Within the next 50 hours TIS after December 

23, 2003 (the effective date of AD 2003–

22–13), unless already done following 

Nomad Alert Service Bulletin ANMD–57–18, 

dated December 19, 2002.

Following Nomad Alert Service Bulletin 

ANMD–57–18, Rev 1, dated August 14, 

2006. To show compliance with paragraphs 

(e)(5)(ii)(A) and (e)(5)(ii)(B) of this AD, a 

copy of this AD may be inserted into the 

Limitations section of the AFM. The owner/ 

operator holding at least a private pilot certificate as authorized by section 43.7 of the 

Federal Aviation Regulations (14 CFR 43.7) 

may do the AFM insertion and the placard 

requirement of paragraph (e)(5)(i) of this 

AD. Make an entry into the aircraft records 

showing compliance with these portions of 

the AD following section 43.9 of the Federal 

Aviation Regulations (14 CFR 43.9). 

Alternative Methods of Compliance 

(AMOCs) 

(f) The Manager, Standards Staff, FAA, 

ATTN: Doug Rudolph, Aerospace Engineer, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4059; fax: (816) 329–

4090, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. 

(g) AMOCs approved for AD 2003–22–13 

are not approved for this AD. 

Related Information 

(h) This AD relates to Australian AD/GAF–

N22/69, Amendment 5, dated September 14, 

2006, which references Nomad Alert Service 

Bulletin ANMD–57–18, Rev 1, dated August 

14, 2006. 

Material Incorporated by Reference 

(i) You must use Nomad Alert Service 

Bulletin ANMD–57–18, Rev 1, dated August 

14, 2006, 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 Nomad Operations, 

Aerospace Support Division, Boeing 

Australia, PO Box 767, Brisbane, QLD 4000 

Australia; telephone 61 7 3306 3366; fax 61 

7 3306 3111. 

(3) You may review copies at the FAA, 

Central Region, Office of the Regional 

Counsel, 901 Locust, Kansas City, Missouri 

64106; 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/

code_of_federal_regulations/

ibr_locations.html. 

Issued in Kansas City, Missouri, on 

October 13, 2006. 

James E. Jackson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E6–17425 Filed 10–18–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26083; Directorate 

Identifier 2006–NM–185–AD; Amendment 

39–14793; AD 2006–21–08] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–200, A340–200, and A340–300 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A330–200, A340–200, 

and A340–300 airplanes. This AD 

requires the installation of heatshields 

in the belly fairing of the center 

fuselage. This AD results from fuel 

system reviews conducted by the 

manufacturer. We are issuing this AD to 

prevent exposing any fuel leaked from 

the center fuel tank to the hot 

temperature areas of the air 

conditioning packs, which could result 

in a fire and consequent fuel tank 

explosion. 

DATES: This AD becomes effective 

November 3, 2006. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of November 3, 2006. 

We must receive comments on this 

AD by December 18, 2006. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD. 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street SW., Nassif Building, 

Room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

Contact Airbus, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France, 

for service information identified in this 

AD. 

FOR FURTHER INFORMATION CONTACT: Tim 

Backman, Aerospace Engineer, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 227–2797; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA has examined the 

underlying safety issues involved in fuel 

tank explosions on several large 

transport airplanes, including the 

adequacy of existing regulations, the 

service history of airplanes subject to 

those regulations, and existing 

maintenance practices for fuel tank 

systems. As a result of those findings, 

we issued a regulation titled ‘‘Transport 

Airplane Fuel Tank System Design 

Review, Flammability Reduction and 

Maintenance and Inspection 

Requirements’’ (66 FR 23086, May 7, 

2001). In addition to new airworthiness 

standards for transport airplanes and 

new maintenance requirements, this 

rule included Special Federal Aviation 


PWALKER on PRODPC60 with RULES
61640 Federal Register / Vol. 71, No. 202 / Thursday, October 19, 2006 / Rules and Regulations 

Regulation No. 88 (‘‘SFAR 88,’’

Amendment 21–78, and subsequent 

Amendments 21–82 and 21–83). 

Among other actions, SFAR 88 

requires certain type design (i.e., type 

certificate (TC) and supplemental type 

certificate (STC)) holders to substantiate 

that their fuel tank systems can prevent 

ignition sources in the fuel tanks. This 

requirement applies to type design 

holders for large turbine-powered 

transport airplanes and for subsequent 

modifications to those airplanes. It 

requires them to perform design reviews 

and to develop design changes and 

maintenance procedures if their designs 

do not meet the new fuel tank safety 

standards. As explained in the preamble 

to the rule, we intended to adopt 

airworthiness directives to mandate any 

changes found necessary to address 

unsafe conditions identified as a result 

of these reviews. 

In evaluating these design reviews, we 

have established four criteria intended 

to define the unsafe conditions 

associated with fuel tank systems that 

require corrective actions. The 

percentage of operating time during 

which fuel tanks are exposed to 

flammable conditions is one of these 

criteria. The other three criteria address 

the failure types under evaluation: 

Single failures, single failures in 

combination with a latent condition(s), 

and in-service failure experience. For all 

four criteria, the evaluations included 

consideration of previous actions taken 

that may mitigate the need for further 

action. 

The Joint Aviation Authorities (JAA) 

has issued a regulation that is similar to 

SFAR 88. (The JAA is an associated 

body of the European Civil Aviation 

Conference (ECAC) representing the 

civil aviation regulatory authorities of a 

number of European States who have 

agreed to co-operate in developing and 

implementing common safety regulatory 

standards and procedures.) Under this 

regulation, the JAA stated that all 

members of the ECAC that hold type 

certificates for transport category 

airplanes are required to conduct a 

design review against explosion risks. 

We have determined that the actions 

identified in this AD are necessary to 

reduce the potential of ignition sources 

inside fuel tanks, which, in combination 

with flammable fuel vapors, could result 

in fuel tank explosions and consequent 

loss of the airplane. 

The European Aviation Safety Agency 

(EASA), which is the airworthiness 

authority for the European Union, 

notified us that an unsafe condition may 

exist on certain Airbus Model A330–

200, A340–200, and A340–300 

airplanes. The EASA advises that there 

could be temperatures in excess of 200 

degrees Celsius on surfaces in the belly 

fairing of the center fuselage. Therefore, 

any fuel leaked from the center fuel tank 

would be exposed to the hot 

temperature areas of the air 

conditioning packs. This condition, if 

not corrected, could result in a fire and 

consequent fuel tank explosion. 

Relevant Service Information 

Airbus has issued Service Bulletins 

A330–21–3096 and A340–21–4107, both 

Revision 01, both dated October 10, 

2005. The service bulletins describe 

procedures for the installation of 

heatshields in the belly fairing of the 

center fuselage. The installation 

includes the following actions: 

• Replacing existing heatshields with 

new heatshields fitted with edges and 

draining tapping. 

• Adding draining systems. 

• Adding two heatshields. 

• Adding two tight insulation sleeves 

on the ozone reducer and on the trim 

pipe. 

• Replacing and adding brackets. 

• Modifying a heatshield panel. 

The EASA mandated the service 

information and issued airworthiness 

directive 2006–0191, dated July 10, 

2006, to ensure the continued 

airworthiness of these airplanes in the 

European Union. 

FAA’s Determination and Requirements 

of this AD 

These airplane models are 

manufactured in France and are type 

certificated for operation in the United 

States under the provisions of section 

21.29 of the Federal Aviation 

Regulations (14 CFR 21.29) and the 

applicable bilateral airworthiness 

agreement. As described in FAA Order 

8100.14A, ‘‘Interim Procedures for 

Working with the European Community 

on Airworthiness Certification and 

Continued Airworthiness,’’ dated 

August 12, 2005, the EASA has kept the 

FAA informed of the situation described 

above. We have examined the EASA’s 

findings, evaluated all pertinent 

information, and determined that we 

need to issue an AD for products of this 

type design that are certificated for 

operation in the United States. 

Therefore, we are issuing this AD to 

prevent exposing any fuel leaked from 

the center fuel tank to the hot 

temperature areas of the air 

conditioning packs, which could result 

in a fire and consequent fuel tank 

explosion. This AD requires 

accomplishing the actions specified in 

the service information described 

previously, except as discussed in 

‘‘Difference Between EASA 

Airworthiness Directive and This AD.’’

Difference Between EASA 

Airworthiness Directive and This AD 

The applicability of EASA 

airworthiness directive 2006–0191 

excludes airplanes on which Airbus 

Service Bulletin A330–21–3096, 

Revision 01; or Airbus Service Bulletin 

A340–21–4107, Revision 01; have been 

accomplished in service. However, we 

have not excluded those airplanes in the 

applicability of this AD; rather, this AD 

includes a requirement to accomplish 

the actions specified in Revision 01 of 

those service bulletins, as applicable. 

This requirement would ensure that the 

actions specified in the service bulletins 

and required by this AD are 

accomplished on all affected airplanes. 

Operators must continue to operate the 

airplane in the configuration required 

by this AD unless an alternative method 

of compliance is approved. 

Costs of Compliance 

None of the airplanes affected by this 

action are on the U.S. Register. All 

airplanes affected by this AD are 

currently operated by non-U.S. 

operators under foreign registry; 

therefore, they are not directly affected 

by this AD action. However, we 

consider this AD necessary to ensure 

that the unsafe condition is addressed if 

any affected airplane is imported and 

placed on the U.S. Register in the future. 

The following table provides the 

estimated costs to comply with this AD 

for any affected airplane that might be 

imported and placed on the U.S. 

Register in the future. 

ESTIMATED COSTS

Action Work hours Average labor 

rate per hour Parts cost Cost per airplane 

Installation ........................................................................................................ 65 $80 $17,290 $22,490 


PWALKER on PRODPC60 with RULES
Federal Register / Vol. 71, No. 202 / Thursday, October 19, 2006 / Rules and Regulations 61641 

FAA’s Determination of the Effective 

Date 

No airplane affected by this AD is 

currently on the U.S. Register. 

Therefore, providing notice and 

opportunity for public comment is 

unnecessary before this AD is issued, 

and this AD may be made effective in 

less than 30 days after it is published in 

the Federal Register. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

relevant written data, views, or 

arguments regarding this AD. Send your 

comments to an address listed in the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2006–26083; Directorate Identifier 

2006–NM–185–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the AD that might suggest a 

need to modify it. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of that Web site, anyone 

can find and read the comments in any 

of our dockets, including the name of 

the individual who sent the comment 

(or signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78), or you may visit 

http://dms.dot.gov. 

Examining the Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.gov, or in 

person at the Docket Management 

Facility office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket 

Management Facility office (telephone 

(800) 647–5227) is located on the plaza 

level of the Nassif Building at the DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the Docket 

Management System receives them. 

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 the 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 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 adding the following new 

airworthiness directive (AD): 

2006–21–08 Airbus: Amendment 39–14793. 

Docket No. FAA–2006–26083; 

Directorate Identifier 2006–NM–185–AD. 

Effective Date 

(a) This AD becomes effective November 3, 

2006. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A330–

200, A340–200, and A340–300 airplanes, 

certificated in any category; except airplanes 

on which Airbus Modification 49520 has 

been done in production. 

Unsafe Condition 

(d) This AD results from fuel system 

reviews conducted by the manufacturer. We 

are issuing this AD to prevent exposing any 

fuel leaked from the center fuel tank to the 

hot temperature areas of the air conditioning 

packs, which could result in a fire and 

consequent fuel tank explosion. 

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. 

Installation of Heatshields 

(f) Within 27 months after the effective 

date of this AD, install heatshields in the 

belly fairing of the center fuselage in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A330–

21–3096, Revision 01, dated October 10, 2005 

(for Model A330–200 airplanes); or Airbus 

Service Bulletin A340–21–4107, Revision 01, 

dated October 10, 2005 (for Model A340–200 

and A340–300 airplanes); as applicable. 

Alternative Methods of Compliance 

(AMOCs) 

(g)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

Related Information 

(h) European Aviation Safety Agency 

(EASA) airworthiness directive 2006–0191, 

dated July 10, 2006, also addresses the 

subject of this AD. 

Material Incorporated by Reference 

(i) You must use Airbus Service Bulletin 

A330–21–3096, Revision 01, dated October 

10, 2005; or Airbus Service Bulletin A340–

21–4107, Revision 01, dated October 10, 

2005; as applicable, to perform the actions 

that are required by this AD, unless the AD 

specifies otherwise. The Director of the 

Federal Register approved the incorporation 

by reference of these documents in 

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

part 51. Contact Airbus, 1 Rond Point 


PWALKER on PRODPC60 with RULES
61642 Federal Register / Vol. 71, No. 202 / Thursday, October 19, 2006 / Rules and Regulations 

Maurice Bellonte, 31707 Blagnac Cedex, 

France, for a copy of this service information. 

You may review copies at the Docket 

Management Facility, U.S. Department of 

Transportation, 400 Seventh Street, SW., 

Room PL–401, Nassif Building, Washington, 

DC; on the Internet at http://dms.dot.gov; or 

at the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at the 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 October 

10, 2006. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E6–17426 Filed 10–18–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–25730; Directorate 

Identifier 2006–NE–31–AD; Amendment 39–

14796; AD 2006–21–11] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

Turmo IV A and IV C Series Turboshaft 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for 

Turbomeca Turmo IV A and IV C series 

turboshaft engines. This AD requires 

identifying, inspecting and replacing 

flexible lubrication pipes manufactured 

after April 1, 2003. If both engines on 

the same helicopter each have an 

affected pipe, then this AD requires 

replacing one of the affected pipes 

before further flight. This AD also 

requires initial and repetitive borescope 

inspections of affected pipes, visual 

inspections for oil leakage, and visual 

inspections of the oil filter, on engines 

that are not required to have an affected 

pipe replaced before further flight by 

this AD. This AD results from 7 reports 

of oil leakage due to the deterioration of 

flexible lubrication pipes manufactured 

after April 1, 2003. We are issuing this 

AD to prevent dual-engine failure on a 

twin-engine helicopter. 

DATES: Effective November 3, 2006. 

We must receive any comments on 

this AD by December 18, 2006. 

ADDRESSES: Use one of the following 

addresses to comment on this AD: 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

0001. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

Contact Turbomeca, 40220 Tarnos, 

France; telephone 33 05 59 74 40 00, fax 

33 05 59 74 45 15 for the service 

information identified in this AD. 

FOR FURTHER INFORMATION CONTACT: 

Christopher Spinney, Aerospace 

Engineer, Engine Certification Office, 

FAA, Engine and Propeller Directorate, 

12 New England Executive Park, 

Burlington, MA 01803; telephone (781) 

238–7175; fax (781) 238–7199. 

SUPPLEMENTARY INFORMATION: The 

European Aviation Safety Agency 

(EASA), which is the airworthiness 

authority for the European Community, 

recently notified us that an unsafe 

condition may exist on certain 

Turbomeca Turmo IV A and IV C series 

turboshaft engines. EASA advises that 7 

reports were received of oil leakage due 

to the deterioration of flexible 

lubrication pipes, part number (P/N) 0 

249 92 813 0, installed on Turbomeca 

Turmo III C4 (military version) 

turboshaft engines. Turbomeca is still 

investigating the cause of the 

deterioration, but links a manufacturing 

process change, applied by the pipe 

manufacturer, in 2003. The same 

process was used to manufacture 

flexible lubrication pipes, P/N 0 249 92 

916 0. Either P/N pipe could be 

installed on Turmo IV A and IV C series 

turboshaft engines. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of Turbomeca Alert 

Mandatory Service Bulletin (MSB) No. 

A249 72 0802, Update No. 1, dated 

August 3, 2006. That Alert MSB 

describes procedures for identifying 

affected flexible lubrication pipes by 

their curing batch number, and 

replacing one of the affected pipes on a 

twin-engine helicopter to prevent dualengine failure. That Alert MSB also 

describes procedures for performing 

repetitive borescope inspections of all 

other affected pipes and visual 

inspections of the oil filter. EASA 

classified this service bulletin as 

mandatory and issued AD 2006–0240–E 

in order to ensure the airworthiness of 

these Turbomeca Turmo IV A and IV C 

series turboshaft engines in Europe. 

Bilateral Airworthiness Agreement 

These Turbomeca Turmo IV A and IV 

C series turboshaft engines are 

manufactured in France and are type 

certificated for operation in the United 

States under the provisions of section 

21.29 of the Federal Aviation 

Regulations (14 CFR 21.29) and the 

applicable bilateral airworthiness 

agreement. Under this bilateral 

airworthiness agreement, EASA kept the 

FAA informed of the situation described 

above. We have examined the findings 

of EASA, reviewed all available 

information, and determined that AD 

action is necessary for products of this 

type design that are certificated for 

operation in the United States. 

FAA’s Determination and Requirements 

of This AD 

The unsafe condition described 

previously is likely to exist or develop 

on other Turbomeca Turmo IV A and IV 

C series turboshaft engines of the same 

type design. We are issuing this AD to 

prevent dual-engine failure on a twinengine helicopter. This AD requires 

identifying affected flexible lubrication 

pipes by their curing batch number, and 

replacing the affected pipe before 

further flight, on one engine if both 

engines on the same helicopter each 

have an affected pipe. This AD also 

requires initial and repetitive borescope 

inspections of flexible lubrication pipes 

and visual inspections of the oil filter, 

on engines that do not have the affected 

pipe replaced before further flight. 

FAA’s Determination of the Effective 

Date 

Since an unsafe condition exists that 

requires the immediate adoption of this 

AD, we have found that notice and 

opportunity for public comment before 

issuing this AD are impracticable, and 

that good cause exists for making this 

amendment effective in less than 30 

days. 

Interim Action 

These actions are interim actions and 

we may take further rulemaking actions 

in the future. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 


PWALKER on PRODPC60 with RULES