Federal Register / Vol. 75, No. 98 / Friday, May 21, 2010 / Rules and Regulations 28483 

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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28484 Federal Register / Vol. 75, No. 98 / Friday, May 21, 2010 / Rules and Regulations 

R.259/4–40–4.5 are used on Convair 

models 340 and 440, redesignated 

Convair model 640 on STC SA1096SW. 

We partially agree. We reviewed these 

STCs, and the aircraft type certificate 

data sheets A–793 and 6A6, and 

determined there are no official Convair 

model designations of 600 or 640 for 

these airplanes. We agree that Convair 

airplanes models 240, 340, and 440 if 

modified by these STCs have Dowty 

propellers installed and are affected by 

this proposed AD. We changed the AD 

applicability to call out the STCs, to 

remove the reference to Convair 600, 

and to list the complete part numbers of 

the affected propellers, instead of the 

basic part numbers. We also deleted 

propeller part number R251/4–30–4 

from the applicability, as it was 

inadvertently listed. 

Conclusion 

We have carefully reviewed the 

available data, including the comment 

received, and determined that air safety 

and the public interest require adopting 

the AD with the changes described 

previously. 

Costs of Compliance 

We anticipate that this AD will affect 

no propellers installed on airplanes of 

U.S. registry, as the affected propellers 

should already be in compliance with 

AD 70–16–02 since it became effective, 

on August 21, 1972. Based on this 

information, we estimate the total cost 

of the AD to U.S. operators to be $0. 

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 

removing Amendment 39–1503 (37 FR 

16535, August 16, 1972), and by adding 

a new airworthiness directive, 

Amendment 39–16302, to read as 

follows: 

2010–10–23 Dowty Propellers (Formerly 

Dowty Aerospace; Dowty Rotol Limited; 

and Dowty Rotol): Amendment 39– 

16302. Docket No. FAA–2008–0750; 

Directorate Identifier 2008–NE–21–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective June 25, 2010. 

Affected ADs 

(b) This AD supersedes AD 70–16–02, 

Amendment 39–1503. 

Applicability 

(c) This AD applies to 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. These 

propellers are installed on, but not limited to, 

Fairchild F–27, Fairchild-Hiller FH–227, 

Grumman G–159, Nihon YS–11, and BAe HS 

748 Series 2 airplanes, Convair 240 airplanes 

modified per supplemental type certificate 

(STC) SA1054WE, and Convair 340 and 440 

airplanes modified per STC SA1096SW. 

Unsafe Condition 

(d) This AD results from the FAA 

determining that AD 70–16–02 does not 

apply to all propellers, since current Dowty 

Rotol 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. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed before 

further flight after the effective date of this 

AD, unless the actions have already been 

done. 

(f) Inspect the blade pitch change operating 

link and eyebolt fork assembly for: 

(1) Seizure (the link and eyebolt are seized 

if the torque required to move the link is 300 

inch pounds or more); and 

(2) Cadmium plating on the mating 

surfaces between the operating link and 

eyebolt fork and the holes through the 

eyebolt fork and the operating link. 

(g) If the link and eyebolt fork are not 

seized and have not been cadmium plated, 

they may remain in service. 

(h) If the link and eyebolt fork are not 

seized but cadmium plating is found in the 

prohibited areas, remove the plating by 

means of wet or dry silicon carbide paper, 

fine or medium grade, and conduct a 

magnetic crack test. If no cracks are found, 

the assembly may remain in service until the 

next propeller overhaul for air carrier 

airplanes and airplanes under a continuous 

maintenance program or for 3,300 hours 

time-in-service after the effective date of this 

AD for all other airplanes. At the next 

propeller overhaul for air carrier airplanes 

and airplanes under a continuous 

maintenance program, or within 3,300 hours 

time-in-service after the effective date of this 

AD for all other airplanes, heat treat the links 

and eyebolt forks found to have been 

cadmium plated, to remove embrittlement. 

Use Dowty Rotol Service Bulletin No. 61– 

754, dated June 12, 1970 to perform the heat 

treatment. 

(i) If the link and eyebolt fork are seized, 

remove the link and eyebolt fork from service 

and replace them with an assembly having a 

part number approved for that model 

propeller that has not been cadmium plated 

in the prohibited areas. 

(j) If the link or eyebolt fork are found to 

be cracked during the inspection in 

paragraph (h) of this AD, remove the cracked 

part from service and replace it with a part 

having a part number approved for that 

model propeller that has not been cadmium 

plated. 

(k) The inspection required by paragraph 

(f) of this AD need not be performed and the 

propeller may remain in service if: 


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Federal Register / Vol. 75, No. 98 / Friday, May 21, 2010 / Rules and Regulations 28485 

(1) The operator can show that no 

cadmium plating exists in the prohibited 

areas of that propeller; or 

(2) It is a new propeller that has never been 

overhauled. 

Alternative Methods of Compliance 

(l) The Manager, Boston Aircraft 

Certification Office, FAA, 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) 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, for more information about this AD. 

Material Incorporated by Reference 

(n) You must use Dowty Rotol Service 

Bulletin No. 61–754, dated June 12, 1970 to 

perform the heat treatment required by this 

AD. The Director of the Federal Register 

approved the incorporation by reference of 

this service bulletin in accordance with 5 

U.S.C. 552(a) and 1 CFR part 51. Contact 

Dowty Propellers, Anson Business Park, 

Cheltenham Road East, Gloucester GL2 9QN, 

UK; Telephone 44 (0) 1452 716000; fax 44 (0) 

1452 716001 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/ibrlocations.html. 

Issued in Burlington, Massachusetts on 

May 5, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–11764 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–2010–0034; Directorate 

Identifier 2009–NM–120–AD; Amendment 

39–16307; AD 2010–11–02] 

RIN 2120–AA64 

Airworthiness Directives; Gulfstream 

Aerospace LP (Type Certificate 

Previously Held by Israel Aircraft 

Industries, Ltd.) Model Gulfstream 100 

Airplanes, and Model Astra SPX and 

1125 Westwind Astra Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing 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: 

* * * * * 

Incomplete closure of the MED [main entry 

door] may be followed by in-flight opening 

of the door. As a result, the MED and the 

adjacent fuselage structure may be damaged 

during opening and landing impact. Damage 

to the left engine by flying debris and objects 

may also occur. 

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: 

Mike Borfitz, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2677; 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 8, 2010 (75 FR 

6157), and proposed to supersede AD 

2007–03–05, Amendment 39–14916 (72 

FR 4414, January 31, 2007). That NPRM 

proposed to correct an unsafe condition 

for the specified products. The MCAI 

states: 

To increase pilots’ awareness to the 

possibility of incomplete closure of the Main 

Entry Door (MED) by the following means: 

1. Splitting the common caution light 

CABIN DOOR signaling both MED Improper 

Closure and MED Inflatable Seal Failure into 

two separate lights: CABIN DOOR and 

CABIN DOOR SEAL. 

2. Converting the separated CABIN DOOR 

Caution light into a Warning light by 

changing its color to red. 

Note: Aircraft Flight Manuals (AFM’S) 

refer to these changes as MOD G1–20052. 

Incomplete closure of the MED may be 

followed by in-flight opening of the door. As 

a result, the MED and the adjacent fuselage 

structure may be damaged during opening 

and landing impact. Damage to the left 

engine by flying debris and objects may also 

occur. 

Required actions include modifying the 

warning and caution lights panel 

(WACLP), changing the WACLP and 

MED wiring, changing the wiring 

harness connecting the MED to the 

WACLP, and ensuring the Log of 

Modification of the AFM includes 

reference to MOD G1–20052. 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. 

Explanation of Change to Applicability 

We have revised the applicability of 

the existing AD to identify model 

designations as published in the most 

recent type certificate data sheet for the 

affected models. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

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. 

Explanation of Change to Costs of 

Compliance 

Since issuance of the NPRM, we have 

increased the labor rate used in the 

Costs of Compliance from $80 per workhour to $85 per work-hour. The Costs of 

Compliance information, below, reflects 


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