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. 

53548 Federal Register / Vol. 70, No. 174 / Friday, September 9, 2005 / Rules and Regulations 

SUMMARY: This document publishes in 

the Federal Register an amendment 

adopting airworthiness directive (AD) 

2005–18–51 that was sent previously to 

all known U.S. owners and operators of 

Boeing Model 777 airplanes by 

individual notices. This AD supersedes 

an existing AD that applies to certain 

Boeing Model 777–200 and ‘‘300 series 

airplanes. The existing AD currently 

requires modification of the operational 

program software (OPS) of the air data 

inertial reference unit (ADIRU). This 

new AD requires installing a certain 

OPS in the ADIRU, and revising the 

airplane flight manual to provide the 

flightcrew with operating instructions 

for possible ADIRU heading errors and 

for potential incorrect display of drift 

angle. This AD results from a recent 

report of a significant nose-up pitch 

event. We are issuing this AD to prevent 

the OPS from using data from faulted 

(failed) sensors, which could result in 

anomalies of the fly-by-wire primary 

flight control, autopilot, auto-throttle, 

pilot display, and auto-brake systems. 

These anomalies could result in high 

pilot workload, deviation from the 

intended flight path, and possible loss 

of control of the airplane. 

DATES: This AD becomes effective 

September 14, 2005 to all persons 

except those persons to whom it was 

made immediately effective by 

emergency AD 2005–18–51, issued 

August 29, 2005, which contained the 

requirements of this amendment. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of September 14, 2005. 

We must receive comments on this 

AD by November 8, 2005. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD. 

• DOT Docket Web site: Go to 

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

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

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

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street SW., Nassif Building, 

room PL–401, Washington, DC 20590. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

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

through Friday, except Federal holidays. 

Contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207, for service 

information identified in this AD. 

FOR FURTHER INFORMATION CONTACT: Paul 

Feider, Aerospace Engineer, Systems 

and Equipment Branch, ANM–130S, 

FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 917–6467; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Background 

On April 29, 2005, we issued AD 

2005–10–03, amendment 39–14080 (70 

FR 24703, May 11, 2005), for certain 

Boeing Model 777–200 and ‘‘300 series 

airplanes. That AD requires 

modification of the operational program 

software (OPS) of the air data inertial 

reference unit (ADIRU) from software 

version part number (P/N) 3470–HNC–

100–03 to software version P/N 3475–

HNC–100–06 or 3474–HNC–100–07. 

That AD resulted from a report of the 

display of erroneous heading 

information to the pilot due to a defect 

in the OPS of the ADIRU. We issued 

that AD to prevent the display of 

erroneous heading information to the 

pilot, which could result in loss of the 

main sources of attitude data, 

consequent high pilot workload, and 

subsequent deviation from the intended 

flight path. 

Actions Since Issuance of Previous AD 

On August 29, 2005, we issued 

emergency AD 2005–18–51, which 

applies to all Boeing Model 777 

airplanes. That AD resulted from a 

recent report of a significant nose-up 

pitch event on a Boeing Model 777–200 

series airplane while climbing through 

36,000 feet altitude. The flightcrew 

disconnected the autopilot and 

stabilized the airplane, during which 

time the airplane climbed above 41,000 

feet, decelerated to a minimum speed of 

158 knots, and activated the stick 

shaker. A review of the flight data 

recorder shows there were abrupt and 

persistent errors in the outputs of the 

ADIRU. These errors were caused by the 

OPS using data from faulted (failed) 

sensors. This problem exists in all 

software versions after P/N 3470–HNC–

100–03, beginning with P/N 3477–

HNC–100–04 approved in 1998 and 

including the versions mandated by AD 

2005–10–03. While these versions have 

been installed on many airplanes before 

we issued AD 2005–10–03, they had not 

caused an incident until recently, and 

the problem was therefore unknown 

until then. OPS using data from faulted 

sensors, if not corrected, could result in 

anomalies of the fly-by-wire primary 

flight control, autopilot, auto-throttle, 

pilot display, and auto-brake systems, 

which could result in high pilot 

workload, deviation from the intended 

flight path, and possible loss of control 

of the airplane. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin 777–34A0137, dated 

August 26, 2005. The service bulletin 

describes procedures for installing OPS, 

P/N 3470–HNC–100–03, in the ADIRU. 

We also have reviewed Boeing 777 

Operations Manual Bulletin (OMB) 

CS3–3093, dated August 26, 2005, 

which describes operating instructions 

to inform the flightcrew of possible 

heading errors following on-ground 

automatic realignment of the ADIRU 

with the OPS, P/N 3470–HNC–100–03, 

installed. 

In addition, we have reviewed Boeing 

777 OMB CS3–3155, dated August 26, 

2005, which describes operating 

instructions to inform the flightcrew of 

potential drift angle discrepancies on 

the primary flight display and the 

navigation display with the OPS, P/N 

3470–HNC–100–03, installed. 

FAA’s Determination and Requirements 

of This AD 

Since the unsafe conditions described 

previously are likely to exist or develop 

on other airplanes of the same type 

design, we issued emergency AD 2005–

18–51 to supersede AD 2005–10–03. 

This new AD requires accomplishing 

the actions specified in Boeing Alert 

Service Bulletin 777–34A0137, 

described previously. Because these 

actions reintroduce the unsafe condition 

identified in AD 2005–10–03, this new 

AD also requires revising the Limitation 

section of the Airplane Flight Manual by 

inserting a copy of Boeing 777 OMBs 

CS3–3093 and CS3–3155, described 

previously. 

Interim Action 

We consider this AD interim action. 

The manufacturer is currently 

developing a modification that will 

address the unsafe condition identified 

in this AD and AD 2005–10–03. Once 

this modification is developed, 

approved, and available, we may 

consider additional rulemaking 

FAA’s Determination of the Effective 

Date 

We found that immediate corrective 

action was required; therefore, notice 

and opportunity for prior public 

comment thereon were impracticable 

and contrary to the public interest, and 

good cause existed to make the AD 

effective immediately by individual 

notices issued on August 29, 2005, to all 

known U.S. owners and operators of 

Boeing Model 777 airplanes. These 

conditions still exist, and the AD is 

Federal Register / Vol. 70, No. 174 / Friday, September 9, 2005 / Rules and Regulations 53549 

hereby published in the Federal 

Register as an amendment to § 39.13 of 

the Federal Aviation Regulations (14 

CFR 39.13) to make it effective to all 

persons. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

relevant written data, views, or 

arguments regarding this AD. Send your 

comments to an address listed in the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2005–22252; Directorate Identifier 

2005–NM–182–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the AD. We will consider all 

comments received by the closing date 

and may amend the AD in light of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of our docket web site, 

anyone can find and read the comments 

in any of our dockets, including the 

name of the individual who sent the 

comment (or signed the comment on 

behalf of an association, business, labor 

union, etc.). You can review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78), or you can visit 

http://dms.dot.gov. 

Examining the Dockets 

You may examine the AD docket on 

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

person at the Docket Management 

Facility office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The Docket 

Management Facility office (telephone 

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

level of the Nassif Building at the DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the Docket 

Management System receives them. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in subtitle VII, 

part A, subpart III, section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

The FAA has determined that this 

regulation is an emergency regulation 

that must be issued immediately to 

correct an unsafe condition in aircraft, 

and that it is not a ‘‘significant 

regulatory action’’ under Executive 

Order 12866. It has been determined 

further that this action involves an 

emergency regulation under DOT 

Regulatory Policies and Procedures (44 

FR 11034, February 26, 1979). If this 

emergency regulation is later deemed 

significant under DOT Regulatory 

Policies and Procedures, we will 

prepare a final regulatory evaluation 

and place it in the AD Docket. See the 

ADDRESSES section for a location to 

examine the regulatory evaluation, if 

filed. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–14080 (70 

FR 24703, May 11, 2005) and adding the 

following new airworthiness directive 

(AD): 

AD 2005–18–51 Boeing: Amendment 39–

14260. Docket No. FAA–2005–22252; 

Directorate Identifier 2005–NM–182–AD. 

Effective Date 

(a) This AD becomes effective September 

14, 2005, to all persons except those persons 

to whom it was made immediately effective 

by emergency AD 2005–18–51, issued on 

August 29, 2005, which contained the 

requirements of this amendment. 

Affected ADs 

(b) This AD supersedes AD 2005–10–03. 

Applicability 

(c) This AD applies to all Boeing Model 

777–200, –300, and –300ER series airplanes, 

certificated in any category. 

Unsafe Condition 

(d) This AD results from a recent report of 

a significant nose-up pitch event. We are 

issuing this AD to prevent the operational 

program software (OPS) from using data from 

faulted (failed) sensors, which could result in 

anomalies of the fly-by-wire primary flight 

control, autopilot, auto-throttle, pilot display, 

and auto-brake systems. These anomalies 

could result in high pilot workload, deviation 

from the intended flight path, and possible 

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. 

Installation of OPS 

(f) Within 72 hours after the effective date 

of this AD, do the actions specified in 

paragraphs (f)(1) and (f)(2) of this AD. 

(1) Install OPS, part number (P/N) 3470–

HNC–100–03, in the air data inertial 

reference unit (ADIRU), in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 777–34A0137, dated 

August 26, 2005. 

(2) Revise the Limitations section of the 

Airplane Flight Manual (AFM) by inserting a 

copy of the Boeing operations manual 

bulletins in Table 1 of this AD. 

TABLE 1.—OPERATIONS MANUAL

BULLETINS

Boeing 777 operations 

manual bulletin Date 

(i) CS3–3093 .............. August 26, 2005. 

(ii) CS3–3155 ............. August 26, 2005. 

(g) When the information in the operations 

manual bulletins in Table 1 of this AD has 

been incorporated into the general revisions 

of the AFM, the general revisions may be 

incorporated into the AFM, and these 

operations manual bulletins may be removed 

from the AFM. 

53550 Federal Register / Vol. 70, No. 174 / Friday, September 9, 2005 / Rules and Regulations 

Parts Installation 

(h) As of the effective date of this AD, only 

OPS, P/N 3470–HNC–100–03, may be loaded 

into the ADIRU. 

Alternative Methods of Compliance 

(AMOCs) 

(i) The Manager, Seattle Aircraft 

Certification Office, 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 

(j) None. 

Material Incorporated by Reference 

(k) You must use the service information 

in Table 2 of this AD to perform the actions 

that are required by this AD, unless the AD 

specifies otherwise. The Director of the 

Federal Register approved the incorporation 

by reference of these documents in 

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

part 51. Contact Boeing Commercial 

Airplanes, P.O. Box 3707, Seattle, 

Washington 98124–2207, 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. 

TABLE 2.—MATERIAL INCORPORATED BY REFERENCE

Service information Date 

Boeing Alert Service Bulletin 777–34A0137 ............................................................................................................................. August 26, 2005. 

Boeing 777 Operations Manual Bulletin CS3–3093 ................................................................................................................. August 26, 2005. 

Boeing 777 Operations Manual Bulletin CS3–3155 ................................................................................................................. August 26, 2005. 

Issued in Renton, Washington, on 

September 1, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–17762 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–2005–20847; Directorate 

Identifier 2004–NE–35–AD; Amendment 39–

14261; AD 2005–18–20] 

RIN 2120–AA64 

Airworthiness Directives; Goodrich Deicing and Specialty Systems 

‘‘FASTprop’’ Propeller De-icers 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for 

Goodrich De-icing and Specialty 

Systems ‘‘FASTprop’’ propeller de-icers, 

part numbers P4E1188 series, P4E1601 

series, P4E2200 series, P4E2271–10, 

P4E2575–7, P4E2575–10, P4E2598–10, 

P5855BSW, P6199SW, P6592SW, 

P6662SW, and P6975–11, installed. This 

AD requires inspection, repair, or 

replacement of those ‘‘FASTprop’’

propeller de-icers that fail daily visual 

checks. This AD results from reports of 

Goodrich ‘‘FASTprop’’ propeller deicers becoming loose or debonded, and 

detaching from propeller blades during 

operation. 

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: Contact Goodrich De-icing 

and Specialty Systems, 1555 Corporate 

Woods Parkway, Uniontown, Ohio 

44685, telephone (330) 374–3743, for 

the service information referenced in 

this AD. 

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: 

Melissa T. Bradley, Aerospace Engineer, 

Chicago Aircraft Certification Office, 

FAA, 2300 East Devon Avenue, Des 

Plaines, IL 60018–4696; telephone (847) 

294–8110; 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 Goodrich 

De-icing and Specialty Systems 

‘‘FASTprop’’ propeller de-icers, part 

numbers P4E1188 series, P4E1601 

series, P4E2200 series, P4E2271–10, 

P4E2575–7, P4E2575–10, P4E2598–10, 

P5855BSW, P6199SW, P6592SW, 

P6662SW, and P6975–11. We published 

the proposed AD in the Federal Register 

on April 6, 2005 (70 FR 17361). That 

action proposed to require inspection, 

repair, or replacement of those 

‘‘FASTprop’’ propeller de-icers that fail 

visual checks before the first flight each 

day. 

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 (DMS) Docket Office 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 one comment received. 

The commenter states that we need to 

clarify the compliance section, and 

requests that any pilot be able to make 

required logbook entries after the visual 

check of propeller de-icers regardless of 

how the airplane is operated, whether 

under 14 CFR part 91, part 135, or part 

121. The commenter interprets 

Goodrich De-icing and Specialty 

Systems Alert Service Bulletin (ASB) 

No. 30–60–00–1, dated November 15, 

2004, as only allowing private pilots 

operating under 14 CFR part 91 to make 

the required logbook entries. 

We agree that we need to clarify the 

compliance section. Accordingly, we 

added the following statement to the 

compliance section of this AD: 

‘‘Properly certificated maintenance 

personnel must perform the initial 

inspection required in this AD. 

Thereafter, the pilot or properly 

certificated maintenance personnel may 

perform the repetitive visual check.’’

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. We have determined that 

these changes will neither increase the