23622 Federal Register / Vol. 74, No. 96 / Wednesday, May 20, 2009 / Rules and Regulations 

Parts Installation for RG162 

(n) For Model 747SP airplane with the 

variable number RG162: As of the effective 

date of this AD, unless the regulator assembly 

of the inflation system has been modified in 

accordance with paragraph (k) of this AD, no 

person may install on that airplane a 

regulator assembly with any of the following 

part numbers (P/Ns): P/N 4A3047, –2, –3, –4, 

–5, –8, –9, or –10; P/N 4A3194–1, –2, –3, or 

–4; or P/N 4A3474–3. 

Alternative Methods of Compliance 

(AMOCs) 

(o)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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: 

Andrew Guion, Aerospace Engineer, Cabin 

Safety and Environmental Systems Branch, 

ANM–150S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 917–6428; fax (425) 917–6590. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. 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. 

(3) AMOCs approved previously in 

accordance with AD 2005–16–06 are 

approved as AMOCs for the corresponding 

provisions of this AD. 

Material Incorporated by Reference 

(p) You must use the service information 

contained in Table 2 of this AD, as 

applicable, to do the actions required by this 

AD, unless the AD specifies otherwise. 

TABLE 2—ALL MATERIAL INCORPORATED BY REFERENCE

Boeing Service Bulletin— Revision— Dated— 

747–25–3232 ........................................................................ Original ................................................................................. July 6, 2000. 

747–25–3279 ........................................................................ 1 ........................................................................................... July 11, 2002. 

747–25–3279 ........................................................................ 4 ........................................................................................... December 11, 2008. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information contained in Table 3 

of this AD under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

TABLE 3—NEW MATERIAL INCORPORATED BY REFERENCE

Boeing Service Bulletin— Revision— Dated— 

747–25–3279 ........................................................................ 4 ........................................................................................... December 11, 2008. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of the service information 

contained in Table 4 of this AD on September 

13, 2005 (70 FR 46067, August 9, 2005). 

TABLE 4—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE

Boeing Service Bulletin— Revision— Dated— 

747–25–3232 ........................................................................ Original ................................................................................. July 6, 2000. 

747–25–3279 ........................................................................ 1 ........................................................................................... July 11, 2002. 

(3) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, P.O. Box 3707, MC 

2H–65, Seattle, Washington 98124–2207; 

telephone 206–544–5000, extension 1; fax 

206–766–5680; e-mail 

me.boecom@boeing.com; Internet https:// 

www.myboeingfleet.com. For Goodrich 

service information identified in this AD, 

contact Goodrich Corporation, Aircraft 

Interior Products, ATTN: Technical 

Publications, 3414 South Fifth Street, 

Phoenix, Arizona 85040; telephone 602–243– 

2270; e-mail george.yribarren@goodrich.com; 

Internet http://www.goodrich.com/TechPubs. 

(4) 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. 

(5) 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 May 6, 

2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–11284 Filed 5–19–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0449; Directorate 

Identifier 2008–NM–034–AD; Amendment 

39–15907; AD 2009–10–11] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–300, A340–200, and A340–300 

Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

Federal Register / Vol. 74, No. 96 / Wednesday, May 20, 2009 / Rules and Regulations 23623 

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: 

Based on some recent in-service findings 

for fluid ingress and/or inner skin disbond 

damage on rudders which could result in 

reduced structural integrity of the rudder, 

AIRBUS decided to introduce some further 

structural inspections to specific rudder 

areas[.] 

* * * * * 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective June 

4, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of June 4, 2009. 

We must receive comments on this 

AD by June 19, 2009. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

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

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–40, 1200 New Jersey Avenue, SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2008–0012, 

dated January 14, 2008 (referred to after 

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

condition for the specified products. 

The MCAI states: 

Based on some recent in-service findings 

for fluid ingress and/or inner skin disbond 

damage on rudders which could result in 

reduced structural integrity of the rudder, 

AIRBUS decided to introduce some further 

structural inspections to specific rudder 

areas: 

—A special detailed one time structural 

inspection to specific rudder areas to 

ensure earlier detection of damage at the 

inspected areas, 

—A repetitive specific ultrasonic inspection 

along the complete rudder panel front and 

bottom edges (complete z-profile area along 

the spar and the bottom rib) to detect any 

damage in this area. 

The aim of this Airworthiness Directive 

(AD) is to render mandatory this additional 

inspection program in order to maintain the 

structural integrity of the rudder. 

The special detailed one-time structural 

inspection consists of doing a 

thermography or x-ray inspection and 

an ultrasonic inspection to detect 

damage of the rudders at the rudder 

hoisting points and trailing edge screw 

areas. The corrective actions depend on 

the findings and the extent of the 

damage found, and include doing the 

repair or contacting Airbus and 

following their repair instructions. 

The repetitive ultrasonic inspection 

along the complete rudder panel front 

and bottom edges (complete z-profile 

area along the spar and the bottom rib) 

to detect damage also includes doing 

related investigative and corrective 

actions. The related investigative action 

is a thermography inspection for inner 

skin disbond damage and fluid ingress 

on the rudder. The corrective actions 

depend on the findings and the extent 

of the damage found, and may include 

venting the core (a temporary repair), 

and contacting Airbus and following 

their repair instructions for a permanent 

repair. 

The compliance time for the 

corrective actions for the special 

detailed one-time structural inspection 

ranges between ‘‘before further flight’’ 

and 4,500 flight cycles, depending on 

the damage finding. The compliance 

time for the corrective actions for the 

repetitive ultrasonic inspections ranges 

between ‘‘before further flight’’ and 

2,500 flight cycles, depending on the 

damage finding and whether the 

temporary repair is done. The repetitive 

interval for the ultrasonic inspections is 

5,000 flight cycles, except after doing 

the temporary repair, in which case the 

interval is 500 flight cycles until a 

permanent repair is done, after which 

time the interval is 5,000 flight cycles. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Airbus has issued the following 

service bulletins: 

• Airbus Mandatory Service Bulletin 

A330–55–3037, including Appendix 01, 

dated October 11, 2007; 

• Airbus Mandatory Service Bulletin 

A330–55–3038, dated November 7, 

2007; 

• Airbus Mandatory Service Bulletin 

A340–55–4033, including Appendix 01, 

dated October 11, 2007; and 

• Airbus Mandatory Service Bulletin 

A340–55–4034, dated November 7, 

2007. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

There are no products of this type 

currently registered in the United States. 

However, this rule is necessary to 

ensure that the described unsafe 

condition is addressed if any of these 

products are placed on the U.S. Register 

in the future. 

Differences Between the 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 

23624 Federal Register / Vol. 74, No. 96 / Wednesday, May 20, 2009 / Rules and Regulations 

MCAI in order to follow FAA policies. 

Any such differences are highlighted in 

a NOTE within the AD. 

FAA’s Determination of the Effective 

Date 

Since there are currently no domestic 

operators of this product, notice and 

opportunity for public comment before 

issuing this AD are unnecessary. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2009–0449; 

Directorate Identifier 2008–NM–034– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

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. 

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: 

2009–10–11 Airbus: Amendment 39–15907. 

Docket No. FAA–2009–0449; Directorate 

Identifier 2008–NM–034–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective June 4, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Airbus Model A330– 

300, A340–200, and A340–300 series 

airplanes, certificated in any category, all 

serial numbers, on which a carbon fiberreinforced plastic (CFRP) rudder part number 

(PN) A55471500 series is fitted. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 55: Stabilizers. 

Reason 

(e) The mandatory continued airworthiness 

information (MCAI) states: 

Based on some recent in-service findings 

for fluid ingress and/or inner skin disbond 

damage on rudders which could result in 

reduced structural integrity of the rudder, 

AIRBUS decided to introduce some further 

structural inspections to specific rudder 

areas[.] 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Within 500 flight cycles or 6 months 

after the effective date of this AD, whichever 

occurs first: Perform a special detailed onetime inspection to detect damage in the areas 

of the rudder hoisting points and trailing 

edge screw, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–55–3037, 

dated October 11, 2007; or Airbus Mandatory 

Service Bulletin A340–55–4033, dated 

October 11, 2007; as applicable. Do all 

applicable corrective actions at the times 

specified in and in accordance with Airbus 

Mandatory Service Bulletin A330–55–3037, 

dated October 11, 2007; or Airbus Mandatory 

Service Bulletin A340–55–4033, dated 

October 11, 2007; as applicable. 

(2) Submit a report of the findings of the 

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

AD to Airbus in accordance with the 

instructions of Appendix 01 of Airbus 

Mandatory Service Bulletin A330–55–3037, 

dated October 11, 2007; or Airbus Mandatory 

Service Bulletin A340–55–4033, dated 

October 11, 2007; as applicable; at the 

applicable time specified in paragraph 

(f)(2)(i) or (f)(2)(ii) of this AD. 

(i) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(ii) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(3) Within 500 flight cycles or 6 months 

after the effective date of this AD, whichever 

occurs first: Perform a special detailed 

inspection along the rudder z-profile to 

detect inner skin disbond damage, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–55–3038, dated November 7, 

2007; or Airbus Mandatory Service Bulletin 

A340–55–4034, dated November 7, 2007; as 

applicable. Do all applicable related 

investigative and corrective actions at the 

times specified in and in accordance with 

Airbus Mandatory Service Bulletin A330–55– 

3038, dated November 7, 2007; or Airbus 

Mandatory Service Bulletin A340–55–4034, 

dated November 7, 2007; as applicable. 

(4) Submit a report of the findings of the 

inspection required by paragraph (f)(3) of this 

AD to Airbus in accordance with the 

instructions of Airbus Mandatory Service 

Bulletin A330–55–3038, dated November 7, 

2007; or Airbus Mandatory Service Bulletin 

A340–55–4034, dated November 7, 2007; as 

applicable; at the applicable time specified in 

paragraph (f)(4)(i) or (f)(4)(ii) of this AD. 

(i) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(ii) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

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

person may install a part number (P/N) 

A55471500 series rudder on an aircraft as a 

Federal Register / Vol. 74, No. 96 / Wednesday, May 20, 2009 / Rules and Regulations 23625 

replacement part, unless it has been 

inspected and, as applicable, repaired in 

accordance with the instructions of Airbus 

Mandatory Service Bulletin A330–55–3037, 

dated October 11, 2007, or Airbus Mandatory 

Service Bulletin A340–55–4033, dated 

October 11, 2007; and Airbus Mandatory 

Service Bulletin A330–55–3038, dated 

November 7, 2007, or Airbus Mandatory 

Service Bulletin A340–55–4034, dated 

November 7, 2007. 

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, 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, 

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– 

0012, dated January 14, 2008; and the service 

bulletins listed in Table 1 of this AD; for 

related information. 

TABLE 1—SERVICE BULLETINS

Airbus Mandatory Service Bulletin— Dated— 

A330–55–3037 ......................................................................................................................................................................... October 11, 2007. 

A330–55–3038 ......................................................................................................................................................................... November 7, 2007. 

A340–55–4033 ......................................................................................................................................................................... October 11, 2007. 

A340–55–4034 ......................................................................................................................................................................... November 7, 2007. 

Material Incorporated by Reference 

(i) You must use the service information 

contained in Table 2 of this AD to do the 

actions required by this AD, as applicable, 

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; 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 that is incorporated by reference 

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 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 2—MATERIAL INCORPORATED BY REFERENCE

Document Date 

Airbus Mandatory Service Bulletin A330–55–3037, excluding Appendix 01 .......................................................................... October 11, 2007. 

Airbus Mandatory Service Bulletin A330–55–3038, including Appendix 01 ........................................................................... November 7, 2007. 

Airbus Mandatory Service Bulletin A340–55–4033, excluding Appendix 01 .......................................................................... October 11, 2007. 

Airbus Mandatory Service Bulletin A340–55–4034, including Appendix 01 ........................................................................... November 7, 2007. 

Issued in Renton, Washington, on May 6, 

2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–11283 Filed 5–19–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0114; Directorate 

Identifier 2009–NE–03–AD; Amendment 39– 

15910; AD 2009–10–14] 

RIN 2120–AA64 

Airworthiness Directives; Hartzell 

Propeller Inc. Steel Hub Turbine 

Propellers 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for Hartzell 

Propeller Inc. steel hub turbine 

propellers, with any counterweight slug 

attachment bolts, part number (P/N) B– 

3386–14H, LFC manufacturing lot 224, 

installed. This AD requires identifying 

and removing all counterweight slug 

attachment bolts, P/N B–3386–14H, LFC 

manufacturing lot 224, from service and 

installing serviceable bolts. This AD 

results from two reports of failure of the 

bolts that attach the propeller blade 

counterweight slug, and separation of 

the counterweight slug which led to 

propeller vibration and damage to the 

propeller spinner. We are issuing this 

AD to prevent separation of the