Federal Register / Vol. 70, No. 174 / Friday, September 9, 2005 / Rules and Regulations 53543 

done before further flight. Repeat the detailed 

inspection thereafter at intervals not to 

exceed 60 flight cycles or 3 months, 

whichever is first, until the actions required 

by paragraph (i) of this AD are accomplished. 

Note 1: When a statement identical to that 

in paragraph (f)(1) of this AD has been 

included in the general revision of the AFM, 

the general revision may be inserted into the 

AFM, and the copy of this AD may be 

removed from the AFM. 

Note 2: For the purposes of this AD, a 

detailed inspection is: ‘‘An intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. Available lighting is normally 

supplemented with a direct source of good 

lighting at an intensity deemed appropriate. 

Inspection aids such as mirror, magnifying 

lenses, etc., may be necessary. Surface 

cleaning and elaborate procedures may be 

required.’’

(g) For airplanes on which the actions 

described in paragraph (f)(1) of this AD are 

performed, doing the actions described in 

paragraph (f)(2) of this AD is terminating 

action for the requirements of paragraph (f)(1) 

of this AD. Once the initial detailed 

inspection specified in paragraph (f)(2) of 

this AD is performed, the AFM limitation 

and placard required by paragraph (f)(1) of 

this AD may be removed. 

New Requirements of This AD 

New Inspections and Intervals 

(h) For airplanes not operated under the 

limitation in paragraph (f)(1) of this AD, 

before the next 10 flight cycles in which the 

slat anti-icing system is activated after the 

effective date of this AD: Do a boroscope 

inspection of each flexible hose installed in 

the slat anti-icing system. Do all the 

inspections and any applicable corrective 

action (including replacing the hose with a 

new hose having P/N FAL1005D), by 

accomplishing all of the applicable actions 

specified in the Accomplishment 

Instructions of Dassault Alert Service 

Bulletin F10–A312, Revision 1, dated June 

27, 2005. Any corrective action must be done 

before further flight. Repeat the inspection 

thereafter at intervals not to exceed 10 flight 

cycles in which the slat anti-icing system is 

activated. Doing this inspection terminates 

the repetitive inspection requirements of 

paragraph (f)(2) of this AD. 

(i) For airplanes on which the actions 

described in paragraph (f)(1) of this AD are 

performed, doing the actions described in 

paragraph (h) of this AD is terminating action 

for the requirements of paragraph (f)(1) of 

this AD. Once the initial boroscope 

inspection specified in paragraph (h) of this 

AD is performed, the AFM limitation and 

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

AD may be removed. 

AFM Revision 

(j) For airplanes not operated under the 

limitation in paragraph (f)(1) of this AD, 

before further flight after the effective date of 

this AD: Revise the Limitations section of the 

Dassault Aviation Falcon 10 AFM, to include 

the following information. 

‘‘After each flight in which the slat anti-ice 

system is activated, inform maintenance.’’

The AFM revision may be done by 

inserting a copy of this AD into the AFM. 

Note 3: When a statement identical to that 

in paragraph (j)(1) of this AD has been 

included in the general revision of the AFM, 

the general revision may be inserted into the 

AFM, and the copy of this AD may be 

removed from the AFM. 

Optional Replacement 

(k) For airplanes not operated under the 

limitation in paragraph (f)(1) of this AD: 

Replacing the flexible hose installed in the 

slat anti-icing system with a new hose having 

P/N FAL1007, in accordance with the 

Accomplishment Instructions of Dassault 

Service Bulletin F10–313, dated August 10, 

2005, terminates the repetitive inspection 

intervals of paragraph (h) and (f)(2) of this 

AD. Repeat the replacement thereafter at 

intervals not to exceed 90 flight cycles in 

which the slat anti-icing system is activated. 

Reporting Requirement 

(l) At the applicable time specified in 

paragraph (l)(1) or (l)(2) of this AD: After 

performing any inspection required by this 

AD, submit a report of the findings (positive 

and negative) of the inspection to: Dassault 

Falcon Jet, Attn: Service Engineering/Falcon 

10, fax: (201) 541–4700. The report must 

include the airplane serial number, the 

location of the hose (inboard or outboard), 

the number of flight hours since hose 

installation, the number of cycles in icing 

conditions, and the manufacturing date and 

batch number of the hose. Submission of the 

Service Bulletins Compliance card, which is 

attached to Dassault Alert Service Bulletin 

F10–A312, is an acceptable method of 

complying with this requirement. Under the 

provisions of the Paperwork Reduction Act of 

1980 (44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements contained in this AD and has 

assigned OMB Control Number 2120–0056. 

(1) If the inspection is done after the 

effective date of this AD: Submit the report 

within 30 days after the inspection. 

(2) 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. 

Actions Accomplished in Accordance With 

Previous Issue of Service Bulletin 

(m) Actions accomplished before the 

effective date of this AD in accordance with 

the Accomplishment Instructions of Dassault 

Alert Service Bulletin F10–A312, dated 

February 25, 2005, are acceptable for 

compliance with the corresponding action in 

this AD. 

Alternative Methods of Compliance (AMOCs) 

(n) 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. 

Related Information 

(o) French emergency airworthiness 

directive EASA.A.AD.01001, dated June 29, 

2005, also addresses the subject of this AD. 

Material Incorporated by Reference 

(p) You must use Dassault Alert Service 

Bulletin F10–A312, dated February 25, 2005, 

including the Service Bulletins Compliance 

Card; and Dassault Alert Service Bulletin 

F10–A312, Revision 1, dated June 27, 2005, 

including the Service Bulletins Compliance 

Card; as applicable; to perform the actions 

that are required by this AD, unless the AD 

specifies otherwise. If accomplished, you 

must used Dassault Service Bulletin F10–

313, dated August 10, 2005, to perform the 

optional replacement specified by this AD. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Dassault Alert Service Bulletin F10-A312, 

Revision 1, dated June 27, 2005, including 

the Service Bulletins Compliance Card; and 

Dassault Service Bulletin F10–313, dated 

August 10, 2005; in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) On April 26, 2005 (70 FR 18282, April 

11, 2005), the Director of the Federal Register 

approved the incorporation by reference of 

Dassault Alert Service Bulletin F10–A312, 

dated February 25, 2005, including the 

Service Bulletins Compliance Card. 

(3) Contact Dassault Falcon Jet, P.O. Box 

2000, South Hackensack, New Jersey 07606, 

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 August 

26, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–17598 Filed 9–8–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–19955; Directorate 

Identifier 2004–NE–17–AD; Amendment 39–

14252; AD 2005–18–12] 

RIN 2120–AA64 

Airworthiness Directives; Hartzell 

Propeller Inc. Propellers 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

53544 Federal Register / Vol. 70, No. 174 / Friday, September 9, 2005 / Rules and Regulations 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Hartzell Propeller Inc. propellers. This 

AD requires inspecting the propeller 

blades and other critical propeller parts 

for corrosion and mechanical damage. 

This AD results from two events where 

a ‘‘Z-shank’’ blade failed and separated 

and the results of teardown inspections 

that detected corrosion in the blade 

bore. We are issuing this AD to detect 

corrosion and mechanical damage that 

can cause failure of a propeller, which 

could result in loss of control of the 

airplane. 

DATES: This AD becomes effective 

October 14, 2005. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulations as 

of October 14, 2005. 

ADDRESSES: You can get the service 

information identified in this AD from 

Hartzell Propeller Inc. Technical 

Publications Department, One Propeller 

Place, Piqua, OH 45356; telephone (937) 

778–4200; fax (937) 778–4391. 

You may examine the AD docket on 

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

Room PL–401 on the plaza level of the 

Nassif Building, 400 Seventh Street, 

SW., Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Tim 

Smyth, Aerospace Engineer, Chicago 

Aircraft Certification Office, FAA, Small 

Airplane Directorate, 2300 East Devon 

Avenue, Des Plaines, IL 60018–4696; 

telephone (847) 294–7132; fax (847) 

294–7834. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed airworthiness directive (AD). 

The proposed AD applies to certain 

Hartzell Propeller Inc. propellers. We 

published the proposed AD in the 

Federal Register on December 29, 2004 

(69 FR 77961). That action proposed to 

require inspecting the propeller blades 

and other critical propeller parts for 

corrosion and mechanical damage. 

Examining the AD Docket 

You may examine the docket that 

contains the AD, any comments 

received, and any final disposition in 

person at the Docket Management 

System Docket Offices between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The Docket 

Office (telephone (800) 647–5227) is 

located on the plaza level of the 

Department of Transportation Nassif 

Building at the street address stated in 

ADDRESSES. Comments will be available 

in the AD docket shortly after the DMS 

receives them. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Recommendation To Modify the AD To 

Exclude Certain Propellers 

One commenter recommends that this 

AD be modified to exclude propellers 

that have been examined in connection 

with AD 95–11–08 within the last five 

years. The commenter feels his 

propeller has been adequately inspected 

and he does not want to remove the 

propeller at this time. Doing so could 

introduce potential oil leaks that are 

difficult and expensive to seal. 

We do not agree. AD 95–11–08 

corrects an unsafe condition in blade 

clamp screws and on the outside surface 

of the blade shank. The requirements of 

that AD are not equivalent to the actions 

mandated by this AD. This AD 

mandates inspections of the entire 

propeller assembly, especially the 

inside surface area of the blade balance 

hole. 

Requests To Provide More Clarity in the 

Compliance Section 

One commenter requests that we 

clarify the compliance section. We 

agree, and reworded it. We changed the 

title for Table 1 to ‘‘List of Applicable 

Propeller Assemblies by Hub Model 

Series’’. 

The same commenter suggests we 

should be more specific in detailing the 

inspection method in Table 3 if we 

intend a more thorough inspection. We 

agree. We have changed (b) in Table 3 

to state ‘‘Perform visual and 

nondestructive inspections of propeller 

components for cracks, corrosion or 

pits, nicks, scratches, wear, blade 

minimum dimensions, and damage in 

the blade balance hole.’’

The same commenter states that if the 

FAA intends to detect small or light 

cracks in the hub or blade clamps, we 

should consider adding the following 

text to Table 3, under the ‘‘Then:’’

column, under (c): ‘‘Perform a magneticparticle-inspection of the hub and blade 

clamps for cracks’’. However, if the FAA 

intends to detect gross corrosion only, 

then the added wording in (c) is not 

needed. The commenter further states 

that although they support the need for 

a blade dimensional inspection, they 

suggest the FAA review the justification 

for this inspection. The commenter 

believes the FAA may find this 

inspection requirement not supportable 

by service events. 

We do not agree that (c) should be 

changed. Appropriate clarifying changes 

to Table 3, paragraph (b), as noted 

earlier, achieve the proper inspection. 

The same commenter suggests that the 

text to Table 3, under the ‘‘Then:’’

column, under (d) which reads ‘‘Repair 

and replace with serviceable parts, as 

necessary’’ be changed to ‘‘If any of 

these conditions are present, perform 

additional inspections, including 

magnetic particle or fluorescentpenetrant inspections as appropriate to 

determine the serviceability of the part’’. 

The commenter states that these 

inspections be specifically required 

when corrosion or other damage has 

been visually identified since cracks are 

more likely to start from these 

conditions, and the cracks are likely to 

be small and only detectable by 

magnetic particle or fluorescentpenetrant inspection. 

We do not agree that (d) should be 

changed. Appropriate clarifying changes 

to Table 3, paragraph (b), as noted 

earlier, achieve the proper inspection. 

Request for Repetitive Inspections 

One commenter, the National 

Transportation Safety Board (NTSB), 

states that it generally supports the 

proposed AD. However, the NTSB notes 

that the proposed AD only proposes a 

onetime inspection rather than a 

repetitive inspection. The commenter 

further states that although the proposed 

AD also includes a requirement to 

report inspection findings and indicates 

that we will use this information to 

determine whether repetitive 

inspections are in order, the NTSB 

continues to believe that repetitive 

inspections best reflect the 

manufacturer’s inspection 

recommendations. These 

recommendations have been established 

in consideration of product design and 

service requirements. Therefore, the 

NTSB again urges us to require that 

these propellers be subject to repetitive 

inspections. 

We do not agree. Our review of the 

service history for the specified 

propellers supports the need for a 

onetime action, especially in light of the 

aging of the specified propeller fleet. As 

stated in the proposed AD, we will 

review the need for a repetitive 

inspection only if new reports 

submitted per the AD requirements, 

document the need to mandate a 

repetitive inspection. We encourage the 

public to comply with manufacturer’s 

maintenance recommendations, but the 

public is only required to maintain their 

aircraft in accordance with 14 CFR part 

91 requirements. 

Federal Register / Vol. 70, No. 174 / Friday, September 9, 2005 / Rules and Regulations 53545 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

received, and determined that air safety 

and the public interest require adopting 

the AD with the changes described 

previously. We have determined that 

these changes will neither increase the 

economic burden on any operator nor 

increase the scope of the AD. 

Costs of Compliance 

There are about 1,700 Hartzell 

propeller assemblies of the affected 

design in the worldwide fleet. We 

estimate that 1,200 propeller assemblies 

installed on airplanes of U.S. registry 

will be affected by this AD. We also 

estimate that it will take about 20 work 

hours per propeller assembly to perform 

the actions, and that the average labor 

rate is $65 per work hour. Required 

parts will cost about $450 per propeller 

assembly. Based on these figures, we 

estimate the total cost of the AD to U.S. 

operators to be $2,100,000. 

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 adding 

the following new airworthiness 

directive: 

2005–18–12 Hartzell Propeller Inc. 

Propellers: Amendment 39–14252. 

Docket No. FAA–2004–19955; 

Directorate Identifier. 2004–NE–17–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective October 14, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Hartzell propeller 

assemblies with hub model series specified 

in Table 1 of this AD. These propellers are 

installed on, but not limited to, the aircraft 

listed in Table 2 of this AD. 

TABLE 1.—LIST OF APPLICABLE PROPELLER ASSEMBLIES BY HUB MODEL

SERIES

HC–92W Hub Model Series 

BHC–92W Hub Model Series 

HC–92Z Hub Model Series 

BHC–92Z Hub Model Series 

HC–B3P Hub Model Series 

HC–B3R Hub Model Series 

HC–B3W Hub Model Series 

BHC–B3W Hub Model Series 

HA–B3Z Hub Model Series 

HC–B3Z Hub Model Series 

TABLE 2.—LIST OF AIRPLANES THAT MIGHT USE AN AFFECTED PROPELLER ASSEMBLY

Aircraft manufacturer Aircraft model 

AERMACCHI (AERONAUTICA MACCHI) ............................................... AM–3C 

AERO COMMANDER .............................................................................. 560–F680, 680E, 680F, 680FL, 680FLP, 720 

AEROSPATIALE (MORANE SAULNIER) ................................................ 733 

AEROSTAR AIRCRAFT CORP. .............................................................. 360 

AEROTEK II, INC. (CALLAIR) ................................................................. B1A (CALLAIR) 

AIR & SPACE ........................................................................................... 18, 18A 

BEECH ..................................................................................................... 18 SERIES 

C45 

35 SERIES 

A65, 65, 65–80, 65–A80, 65–B80, 65–88 

95, B95, B95A, D95A, E95 

70 

C18S [(C–45(A, F), UC–45(B, F), AT–7 (A, B, C), JRB–(1, 2, 3, 4), 

SNB–2(C)] 

C18S, AT–11 

C–45G,C–45H; TC–45G, H, J; RC–45J 

D18S,E18S, G18S, H18; 3N, 3NM, 3TM 

E50, F50, G50, H50, J50 

BUSHMASTER AIRCRAFT CORP .......................................................... BUSHMASTER 2000 

CESSNA ................................................................................................... 172 

175, 175A 

53546 Federal Register / Vol. 70, No. 174 / Friday, September 9, 2005 / Rules and Regulations 

TABLE 2.—LIST OF AIRPLANES THAT MIGHT USE AN AFFECTED PROPELLER ASSEMBLY—Continued 

Aircraft manufacturer Aircraft model 

190, 195, A, B 

421, 421A 

A185E, A185F (SEAPLANES ONLY) 

CESSNA ................................................................................................... T50 

DE HAVILLAND CANADA ....................................................................... DHC–2 MKI 

DORNIER ................................................................................................. DO28D, DO28D–1 

FOUND BROTHERS ................................................................................ 100 

FOUND BROTHERS ................................................................................ FBA–2C 

GOODYEAR (LOCKHEED MARTIN) ....................................................... GZ20, GZ20A 

GRUMMAN (GULFSTREAM AERO.) ...................................................... G44, G44A 

GRUMMAN (MCKINNON) ........................................................................ G21A 

HELIO ....................................................................................................... H–250 

H–295, HT–295 (U–10D) 

H–395 (L–28A, U–10B) 

H–500 

ICA (ROMANIA) ....................................................................................... IAR–831 

JOBMASTER ............................................................................................

DGA–15P 

KWAD ....................................................................................................... SUPER–V 

LAKE (REVO) ........................................................................................... LA–4 

LOCKHEED .............................................................................................. 12A 

MESSERSCHMITT ................................................................................... 207 

MOONEY .................................................................................................. M20A 

NAVY ........................................................................................................ N3N–3 

NORD ....................................................................................................... 3400, 3402 

PACIFIC AEROSPACE (FLETCHER) ..................................................... FU–24, FU–24A 

PIAGGIO ................................................................................................... P–166B, C 

PILATUS ................................................................................................... PC–6/350; PC–6/350–H1, –H2 

PIPER ....................................................................................................... PA–23 

PA–24 

PA–25 

PROCAER ................................................................................................ F15/B 

REVO (COLONIAL) .................................................................................. C–2 

SAAB ........................................................................................................ 91D SAFIR 

SCHWEIZER (GRUMMAN) ...................................................................... G–164 

SIMMERING GRAZ PAUKER A.G .......................................................... SGP222 

SPARTON ................................................................................................ 7W 

UTVA ........................................................................................................ 66 

WDL AVIATION (formerly WDL FLUGDIENST) ...................................... An Airship 

WEATHERLY ........................................................................................... 201B, 201C, 620, 620A, 620C

Unsafe Condition 

(d) This AD results from two events where 

a ‘‘Z-shank’’ blade failed and separated and 

the results of teardown inspections that 

detected corrosion in the blade bore. We are 

issuing this AD to detect corrosion and 

mechanical damage that can cause failure of 

a propeller, which could result in loss of 

control of the airplane. 

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. 

Aircraft With Experimental Type Certificates 

(f) We recommend that you comply with 

the inspection requirements of this AD, if 

you have an aircraft with an experimental 

type certificate, and you have a propeller hub 

model listed in this AD installed on that 

aircraft. 

Inspection of the Propeller 

(g) If the time-since-overhaul (TSO) of the 

propeller is 10 years or fewer on the effective 

date of this AD, no further action is required. 

(h) If the propeller assembly was inspected 

using Hartzell Service Bulletin (SB) No. HC–

SB–61–136, Revision I, dated April 25, 2003; 

SB No. 136, Revision H, dated March 12, 

1993; or SB No. 136, Revision G, dated 

November 15, 1991; no further action is 

required. 

(i) If the TSO of the propeller assembly is 

more than 10 years on the effective date of 

this AD, or if the TSO is unknown, or if the 

propeller has not complied with Hartzell SB 

No. HC–SB–61–136, Revision I, dated April 

25, 2003; or SB No. 136, Revision H, dated 

March 12, 1993; or SB No. 136, Revision G, 

dated November 15, 1991; perform the 

actions specified in Table 3 of this AD. Use 

the compliance times specified in Table 3 of 

this AD. Information on inspecting the 

propeller assembly for cracks, corrosion or 

pits, nicks, scratches, wear, blade minimum 

dimensions, and damage in the blade balance 

bore can be found in the applicable Hartzell 

maintenance manuals. 

Federal Register / Vol. 70, No. 174 / Friday, September 9, 2005 / Rules and Regulations 53547 

TABLE 3.—COMPLIANCE TIMES FOR ONETIME INSPECTION

If the TSO of the propeller assembly on the effective date of this AD 

is . . . 

Then . . . Perform the the inspection . . . 

(1) More 25 years or the TSO is 

not known.

(a) Disassemble and clean the propeller assembly ..............................

(b) Perform visual and nondestructive inspections of propeller components for cracks, corrosion or pits, nicks, scratches, wear, blade 

minimum dimensions, and damage in the blade balance hole.

(c) Inspect and rework the propeller blade bore. Use 3.A. of the Accomplishment instructions of Hartzell SB No. HC–SB–61–136, Revision I, dated April 26, 2003.

(d) Repair and replace with serviceable parts, as necessary. 

(e) Reassemble and test. 

Within 12 months after the effective date of this AD. 

(2) Twenty-one to 25 years ............. (a) Disassemble and clean the propeller assembly ..............................

(b) Perform visual and nondestructive inspections of propeller components for cracks, corrosion or pits, nicks, scratches, wear, blade 

minimum dimensions, and damage in the blade balance hole.

(c) Inspect and rework the propeller blade bore. Use 3.A. of the Accomplishment instructions of Hartzell SB No. HC–SB–61–136, Revision I, dated April 26, 2003.

(d) Repair and replace with serviceable parts, as necessary. 

(e) Reassemble and test. 

Within 18 months after the effective date of this AD. 

(3) Sixteen to 20 years ................... (a) Disassemble and clean the propeller assembly ..............................

(b) Perform visual and nondestructive inspections of propeller components for cracks, corrosion or pits, nicks, scratches, wear, blade 

minimum dimensions, and damage in the blade balance hole.

(c) Inspect and rework the propeller blade bore. Use 3.A. of the Accomplishment instructions of Hartzell SB No. HC–SB–61–136, Revision I, dated April 26, 2003.

(d) Repair and replace with serviceable parts, as necessary. 

(e) Reassemble and test. 

Within 24 months after the effective date of this AD. 

(4) Eleven to 15 years .................... (a) Disassemble and clean the propeller assembly ..............................

(b) Perform visual and nondestructive inspections of propeller components for cracks, corrosion or pits, nicks, scratches, wear, blade 

minimum dimensions, and damage in the blade balance hole.

(c) Inspect and rework the propeller blade bore. Use 3.A. of the Accomplishment instructions of Hartzell SB No. HC–SB–61–136, Revision I, dated April 26, 2003.

(d) Repair and replace with serviceable parts, as necessary. 

(e) Reassemble and test. 

Within 36 months after the effective date of this AD. 

Propeller Overhaul 

(j) Performing an overhaul of the propeller 

assembly after the effective date of this AD 

constitutes compliance with the 

requirements specified in this AD. The latest 

applicable Maintenance Manuals issued by 

Hartzell Propeller Inc. contain information 

on overhauling a propeller assembly. 

(k) The time-since-overhaul only changes if 

you overhaul the propeller assembly while 

performing the requirements specified in this 

AD. 

Reporting Requirements 

(l) Report inspection results to the 

Manager, Chicago Aircraft Certification 

Office, FAA, Small Airplane Directorate, 

2300 East Devon Ave, Des Plaines, IL 60018, 

within 15 working days of the inspection. 

The Office of Management and Budget (OMB) 

approved the reporting requirements and 

assigned OMB control number 2120–0056. 

Alternative Methods of Compliance 

(m) The Manager, Chicago Aircraft 

Certification Office 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 

(n) None. 

Material Incorporated by Reference 

(o) You must use Hartzell Service Bulletin 

No. HC–SB–61–136, Revision I, dated April 

25, 2003, to perform the inspections and 

rework 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 Hartzell Propeller 

Inc. Technical Publications Department, One 

Propeller Place, Piqua, OH 45356; telephone 

(937) 778–4200; fax (937) 778–4391, 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., Nassif Building, 

Room PL–401, Washington, DC 20590–0001, 

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 NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

August 29, 2005. 

Peter A. White, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–17667 Filed 9–8–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22252; Directorate 

Identifier 2005–NM–182–AD; Amendment 

39–14260; AD 2005–18–51] 

RIN 2120–AA64 

Airworthiness Directives; Boeing 

Model 777 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments.