28480 Federal Register / Vol. 75, No. 98 / Friday, May 21, 2010 / Rules and Regulations 

Reason 

(d) The mandatory continuing 

airworthiness information (MCAI) AD states 

that with certain pilot and copilot seats in the 

rear high position and seat backrest fully 

tilted the seat shoulder harness could become 

jammed between the seat and bulkhead 

X1715 adversely affecting the strap tension 

and potentially disabling the proper function 

of the inertial reel. This condition, if not 

corrected could result in the shoulder 

harness no longer retaining the flight crew 

member in the seat in the event of an 

emergency or hard landing. 

Actions and Compliance 

(e) Within 15 hours time-in-service (TIS), 

modify the pilot and copilot seats by 

relocating the rail rear stops to the position 

depicted in Figure 2, ‘‘without the ‘rail with 

the rear stop moved aft’ customization’’ or 

‘‘Post-Mod 332V080210.00.’’ Do the 

modification by following the Operational 

Procedure, of the Accomplishment 

Instructions, paragraph 2.B.1., of Eurocopter 

Emergency Alert Service Bulletin (EASB) No. 

25.02.20, dated October 19, 2009. After 

modifying the position of the rear stop, 

identify the modification (MOD) using 

indelible ink and marking 

‘‘MOD332V080210.00’’ on the left rail at the 

rear stop. 

Note: The one Eurocopter EASB contains 

two different service bulletin numbers (Nos. 

25.02.20 and 25.01.35) applicable to two 

different Eurocopter model helicopters. 

EASB No. 25.02.20 relates to Eurocopter 

Model AS332L1 and L2 helicopters. EASB 

No. 25.01.35 relates to Eurocopter Model 

AS532U2 military helicopters that are not 

type certificated in the United States. 

(f) After the effective date of this AD, do 

not install a pilot or copilot left seat rail, P/ 

N 332P76–9012–02 or P/N 332P76–9012–03, 

on a helicopter unless it has been modified 

and reidentified by following paragraph (e) of 

this AD. 

Differences Between This AD and the MCAI 

AD 

(g) We refer to flight hours as hours TIS. 

Other Information 

(h) Alternative Methods of Compliance 

(AMOCs): The Manager, Safety Management 

Group, ATTN: DOT/FAA Southwest Region, 

Gary Roach, ASW–111, Aviation Safety 

Engineer, Rotorcraft Directorate, Regulations 

and Guidance Group, 2601 Meacham Blvd., 

Fort Worth, Texas 76137, telephone (817) 

222–5130, fax (817) 222–5961, has the 

authority to approve AMOCs for this AD, if 

requested, using the procedures found in 14 

CFR 39.19. 

Related Information 

(i) The European Aviation Safety Agency 

MCAI AD No. 2009–0227–E, dated October 

22, 2009, contains related information. 

Joint Aircraft System/Component (JASC) 

Code 

(j) The JASC Code is 5347: Seat/Cargo 

Attach Fittings. 

Material Incorporated by Reference 

(k) You must use the specified portions of 

Eurocopter Emergency Alert Service Bulletin 

No. 25.02.20, dated October 19, 2009, to do 

the actions required. 

(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 American Eurocopter 

Corporation, 2701 Forum Drive, Grand 

Prairie, TX 75053–4005, telephone (800) 

232–0323, fax (972) 641–3710, or at http:// 

www.eurocopter.com. 

(3) You may review copies at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd, Fort Worth, TX 

76137; 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. 

Issued in Fort Worth, Texas, on April 29, 

2010. 

Mark R. Schilling, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–11420 Filed 5–20–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0172; Directorate 

Identifier 2009–NM–189–AD; Amendment 

39–16308; AD 2010–11–03] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A300 Series Airplanes; Model A300 

B4–600, B4–600R, F4–600R Series 

Airplanes, and Model A300 C4–605R 

Variant F Airplanes (Collectively Called 

A300–600 Series Airplanes); and A310 

Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

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: 

In the past, some operators have reported 

difficulties to pressurise the hydraulic 

reservoirs, due to leakage of the Crissair 

reservoir air pressurisation check valves. 

* * * The leakage of the check valves was 

caused by an incorrect spring material. The 

affected Crissair check valves * * * were 

then replaced with improved check valves P/ 

N [part number] 2S2794–1 * * *. 

More recently, similar issues were again 

reported on aeroplanes with Crissair check 

valves P/N 2S2794–1 installed. The 

investigations * * * have shown that a 

spring, mounted inside the valve, does not 

meet the Airbus type design specifications. 

This situation, if not corrected, can cause 

hydraulic system functional degradation, 

possibly resulting in reduced control of the 

aeroplane when combined with an air duct 

leak, air conditioning system contamination 

or, if installed, malfunction of the fire 

extinguishing system in the Class ‘C’ cargo 

compartment. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective June 

25, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 25, 2010. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2125; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on February 25, 2010 (75 FR 

8551). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

In the past, some operators have reported 

difficulties to pressurise the hydraulic 

reservoirs, due to leakage of the Crissair 

reservoir air pressurisation check valves. In 

some cases, the air conditioning system was 

contaminated with hydraulic mist. The 

leakage of the check valves was caused by an 

incorrect spring material. The affected 

Crissair check valves Part Number (P/N) 

2S2794 were then replaced with improved 

check valves P/N 2S2794–1 in accordance 

with Airbus Service Information Letter 

29–020. 

More recently, similar issues were again 

reported on aeroplanes with Crissair check 


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Federal Register / Vol. 75, No. 98 / Friday, May 21, 2010 / Rules and Regulations 28481 

valves P/N 2S2794–1 installed. The 

investigations carried out on those check 

valves have shown that a spring, mounted 

inside the valve, does not meet the Airbus 

type design specifications. 

This situation, if not corrected, can cause 

hydraulic system functional degradation, 

possibly resulting in reduced control of the 

aeroplane when combined with an air duct 

leak, air conditioning system contamination 

or, if installed, malfunction of the fire 

extinguishing system in the Class ‘C’ cargo 

compartment. 

For the reasons described above, EASA 

[European Aviation Safety Agency] AD 2008– 

0166 was issued to require the inspection of 

the Crissair check valves P/N 2S2794–1, to 

identify serial numbers (s/n) and the 

replacement of the affected ones with 

serviceable units. 

Later on, further investigation by the 

vendor Crissair revealed more suspect check 

valves P/N 2S2794–1. Based on this, it was 

concluded that EASA AD 2008–0166 did not 

adequately address the unsafe condition and 

also did not correctly identify the Functional 

Item Numbers (FIN) of the various aeroplane 

installations of the affected valves. 

Consequently, EASA AD Cancellation Notice 

No.: 2008–0166–CN was issued on 29 

October 2008 to cancel EASA AD 2008–0166. 

An updated list of suspect check valves 

with P/N 2S2794–1 has now been issued by 

Crissair Inc., the manufacturer. 

Consequently, this EASA AD requires the 

identification of the check valves by s/n and 

the replacement of the affected ones with 

serviceable units. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

206 products of U.S. registry. We also 

estimate that it will take about 12 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD to the U.S. operators to 

be $210,120, or $1,020 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this 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. 

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 the NPRM, 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. 

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: 

2010–11–03 Airbus: Amendment 39–16308. 

Docket No. FAA–2010–0172; Directorate 

Identifier 2009–NM–189–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective June 25, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A300 

B2–1A, B2–1C, B2K–3C, B2–203, B4–2C, B4– 

103, B4–203, B4–601, B4–603, B4–620, B4– 

622, B4–605R, B4–622R, F4–605R, F4–622R, 

and C4–605R Variant F airplanes; and Model 

A310–203, –204, –221, –222, –304, –322, 

–324, and –325 airplanes; certificated in any 

category, all certified models and all serial 

numbers on which any Crissair check valve 

part number 2S2794–1 is installed. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 29: Hydraulic Power; and 26: 

Fire Protection. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

In the past, some operators have reported 

difficulties to pressurise the hydraulic 

reservoirs, due to leakage of the Crissair 

reservoir air pressurization check valves. In 

some cases, the air conditioning system was 

contaminated with hydraulic mist. The 

leakage of the check valves was caused by an 

incorrect spring material. The affected 

Crissair check valves Part Number (P/N) 

2S2794 were then replaced with improved 

check valves P/N 2S2794–1 in accordance 

with Airbus Service Information Letter 29– 

020. 


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28482 Federal Register / Vol. 75, No. 98 / Friday, May 21, 2010 / Rules and Regulations 

More recently, similar issues were again 

reported on aeroplanes with Crissair check 

valves P/N 2S2794–1 installed. The 

investigations carried out on those check 

valves have shown that a spring, mounted 

inside the valve, does not meet the Airbus 

type design specifications. 

This situation, if not corrected, can cause 

hydraulic system functional degradation, 

possibly resulting in reduced control of the 

aeroplane when combined with an air duct 

leak, air conditioning system contamination 

or, if installed, malfunction of the fire 

extinguishing system in the Class ‘C’ cargo 

compartment. 

For the reasons described above, EASA 

[European Aviation Safety Agency] AD 2008– 

0166 was issued to require the inspection of 

the Crissair check valves P/N 2S2794–1, to 

identify serial numbers (s/n) and the 

replacement of the affected ones with 

serviceable units. 

Later on, further investigation by the 

vendor Crissair revealed more suspect check 

valves P/N 2S2794–1. Based on this, it was 

concluded that EASA AD 2008–0166 did not 

adequately address the unsafe condition and 

also did not correctly identify the Functional 

Item Numbers (FIN) of the various aeroplane 

installations of the affected valves. 

Consequently, EASA AD Cancellation Notice 

No.: 2008–0166–CN was issued on 29 

October 2008 to cancel EASA AD 2008–0166. 

An updated list of suspect check valves 

with P/N 2S2794–1 has now been issued by 

Crissair Inc., the manufacturer. 

Consequently, this EASA AD requires the 

identification of the check valves by s/n and 

the replacement of the affected ones with 

serviceable units. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) At the applicable compliance time 

specified in Table 1 of this AD: For Crissair 

check valves, P/N 2S2794–1, identify the 

serial number using Appendix 1 of the 

applicable service bulletin identified in Table 

2 of this AD, in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin identified in Table 

2 of this AD. Except as provided by 

paragraph (f)(2) of this AD, for any valve 

having a serial number listed in Appendix 1 

of the applicable service bulletin identified 

in Table 2 of this AD, before further flight, 

install a new or modified check valve in 

accordance with the applicable service 

bulletin identified in Table 2 of this AD. 

TABLE 1—AFFECTED CHECK VALVE INSTALLATION

Affected check valve installation, identified by FIN (Functional Item Number) Compliance time 

(i) Airplanes having Hydraulic System with FIN 29/1388, FIN 29/2388 and FIN 29/ 

3388.

Within 4 months after the effective date of this AD. 

(ii) Cargo Compartment Fire Extinguishing System, equipped with Flow Metering 

System (A310 and A300–600 airplanes having ‘‘post-Airbus modification 

06403’’ only) FIN 26/0203.

Within 4 months after the effective date of this AD. 

(iii) Airplanes having Hydraulic System with FIN 29/1378, FIN 29/1382 and FIN 

29/1394.

Within 30 months after the effective date of this AD. 

(iv) Hydraulic System (A300 airplanes having configuration 01 ‘‘pre-Airbus modification 03079’’ only) FIN 29/1381.Within 30 months after the effective date of this AD. 

(2) Check valves P/N 2S2794–1 marked 

with an ‘‘R’’ have already been modified in 

accordance with Crissair Service Bulletin 

20070407–29–1 and do not need to be 

replaced. Check valves with P/N 2S2794 are 

not affected and do not need to be replaced. 

(3) As of the effective date of this AD, no 

person may install any Crissair check valve, 

P/N 2S2794–1, on any airplane unless it has 

a serial number other than those listed in 

Appendix 1 of the applicable service bulletin 

identified in Table 2 of this AD, or unless 

check valve P/N 2S2794–1 is marked with an 

‘‘R.’’ 

TABLE 2—SERVICE INFORMATION

For Airbus Model— Use Airbus Mandatory Service Bulletin— Revision— Dated— 

A300 airplanes ................................ A300–29–0124, including Appendices 1, 2, and 3 ............................... 02 March 10, 2009. 

A300–600 airplanes ........................ A300–29–6060, including Appendices 1, 2, and 3 ............................... 01 March 10, 2009. 

A310 airplanes ................................ A310–29–2097, including Appendices 1, 2, and 3 ............................... 01 March 19, 2009. 

(4) Submit an inspection report 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; telephone +33 5 61 

93 33 33; fax +33 5 61 93 42 51; e-mail: 

sb.reporting@airbus.com; at the applicable 

time specified in paragraph (f)(4)(i) or 

(f)(4)(ii) of this AD. The report must include 

the information specified on the inspection 

report sheet provided in the applicable 

service bulletin identified in Table 2 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 done before 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: 

Although the MCAI states not to install the 

part identified in paragraph (f)(3) of this AD 

after accomplishing the actions specified in 

paragraph (f)(1) of this AD, this AD prohibits 

installation of the part as of the effective date 

of this AD. 

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: Dan Rodina, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–2125; 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 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 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the Information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 


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Related Information 

(h) Refer to MCAI EASA Airworthiness 

Directive 2009–0171, dated August 5, 2009; 

and the service bulletins identified in Table 

2 of this AD; for related information. 

Material Incorporated by Reference 

(i) You must use the service information 

contained in Table 3 of this AD 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–EAW 

(Airworthiness Office), 1 Rond Point Maurice 

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. 

(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. 

(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. 

TABLE 3—MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Airbus Mandatory Service Bulletin A300–29–0124, including Appendices 1, 2, and 3 ..................................... 02 March 10, 2009. 

Airbus Mandatory Service Bulletin A300–29–6060, including Appendices 1, 2, and 3 ..................................... 01 March 10, 2009. 

Airbus Mandatory Service Bulletin A310–29–2097, including Appendices 1, 2, and 3 ..................................... 01 March 19, 2009. 

Issued in Renton, Washington, on May 11, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–11757 Filed 5–20–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0750; Directorate 

Identifier 2008–NE–21–AD; Amendment 39– 

16302; AD 2010–10–23] 

RIN 2120–AA64 

Airworthiness Directives; Dowty 

Propellers R175/4–30–4/13; R175/4–30– 

4/13e; R184/4–30–4/50; R193/4–30– 

4/50; R193/4–30–4/61; R193/4–30–4/64; 

R193/4–30–4/65; R193/4–30–4/66; 

R.209/4–40–4.5/2; R212/4–30–4/22; 

R.245/4–40–4.5/13; R257/4–30–4/60; 

and R.259/4–40–4.5/17 Model 

Propellers 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) for 

the Dowty Propellers, propeller models 

listed above. That AD currently 

requires, for all Dowty Rotol propellers, 

visual inspections for seizure and for 

cadmium plating of the blade pitch 

change operating links and eyebolt fork 

assemblies. That AD also requires 

replacement or heat-treatment of the 

blade pitch change operating links and 

eyebolt fork assemblies, if necessary. 

This AD requires the same actions, but 

only for certain propeller models. This 

AD results from the FAA determining 

that AD 70–16–02 does not apply to all 

propellers, since current Dowty 

propellers are differently designed. We 

are issuing this AD supersedure to 

specify the affected propeller models, 

and to prevent seizure or embrittlement 

and cracking of the blade pitch change 

operating links and eyebolt fork 

assemblies, which could result in 

reduced controllability of the airplane. 

DATES: This AD becomes effective June 

25, 2010. The Director of the Federal 

Register approved the incorporation by 

reference of certain publications listed 

in the regulations as of June 25, 2010. 

ADDRESSES: You can get the service 

information identified in this AD from 

Dowty Propellers, Anson Business Park, 

Cheltenham Road East, Gloucester GL2 

9QN, UK; Telephone 44 (0) 1452 

716000; fax 44 (0) 1452 716001. 

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: 

Terry Fahr, Aerospace Engineer, Boston 

Aircraft Certification Office, FAA, 

Engine and Propeller Directorate, 12 

New England Executive Park, 

Burlington, MA 01803; e-mail: 

terry.fahr@faa.gov; telephone (781) 238– 

7155; fax (781) 238–7170. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 by 

superseding AD 70–16–02, Amendment 

39–1503 (37 FR 16535, August 16, 

1972), with a proposed AD. The 

proposed AD applies to certain Dowty 

Propellers, propeller models. We 

published the proposed AD in the 

Federal Register on August 29, 2008 (74 

FR 50892). That action proposed to 

require visual inspections before further 

flight of the blade pitch change 

operating links and eyebolt fork 

assemblies and replacement or heattreatment of them, if necessary, for 

certain Dowty Propellers, propeller 

models. 

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 have 

considered the comment received. 

Request To Revise the Proposed 

Applicability 

One commenter, a private citizen, 

states that there were no Dowty Rotol 

propellers installed on Convair 240, 

340, and 440 airplanes. However, the 

commenter also states that Convair 240, 

340, and 440 airplanes modified by 

supplemental type certificates (STC) 

SA1054WE and SA1096SW, do have 

Dowty Rotol propellers installed. The 

propeller R.245/4–40–4.5 is used on a 

Convair model 240, redesignated as 

Convair model 600 on supplemental 

type certificate (STC) SA1054WE, and 

the propellers R.245/4–40–4.5 and 


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