Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Proposed Rules 21171 

2006; are considered acceptable for 

compliance with the corresponding action 

specified in this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, Los Angeles Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

Issued in Renton, Washington, on April 23, 

2007. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E7–8176 Filed 4–27–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–25927; Directorate 

Identifier 2006–CE–52–AD] 

RIN 2120–AA64 

Airworthiness Directives; M7 

Aerospace LP SA226 and SA227 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 98–19–15 

R1 and AD 2000–03–17, which apply to 

M7 Aerospace LP SA226 and SA227 

series airplanes equipped with certain 

pitch trim actuators. AD 98–19–15 R1 

currently requires you to incorporate 

changes into the Limitations Section of 

the FAA-approved Airplane Flight 

Manual (AFM) if certain part number 

(P/N) pitch trim actuators are installed. 

AD 2000–03–17 requires repetitive 

inspections and repetitive replacements 

of the pitch trim actuator. The repetitive 

inspection and repetitive replacement 

times vary depending on the 

combination of airplane model and 

pitch trim actuator P/N installed. We are 

proposing this AD because we have 

determined that reliance on critical 

repetitive inspections on aging 

commuter-class airplanes carries an 

unnecessary safety risk when a design 

change exists that could eliminate or, in 

certain instances, reduce the number of 

those critical inspections. Consequently, 

this proposed AD would retain all of the 

actions of the previously referenced 

ADs, place life limits on certain P/N 

pitch trim actuators, and require the 

replacement of certain P/N pitch trim 

actuators with one of an improved 

design. Once installed, the improved 

design pitch trim actuator would 

terminate the AFM limitations in this 

proposed AD and reduce the repetitive 

inspection and repetitive replacement 

requirements. We are proposing this AD 

to detect excessive freeplay or rod 

slippage in the pitch trim actuator, 

which, if not detected and corrected, 

could result in pitch trim actuator 

failure. We are also proposing this AD 

to lessen the severity of pitch upset if a 

pitch trim actuator mechanical failure 

occurs. These conditions could lead to 

possible loss of control. 

DATES: We must receive comments on 

this proposed AD by June 29, 2007. 

ADDRESSES: Use one of the following 

addresses to comment on this proposed 

AD: 

• DOT Docket web site: Go to 

http://dms.dot.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–

0001. 

• 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. 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

For service information identified in 

this proposed AD, contact M7 

Aerospace LP, P.O. Box 790490, San 

Antonio, Texas 78279–0490; telephone: 

(210) 824–9421, extension 7294. 

FOR FURTHER INFORMATION CONTACT: 

Werner Koch, Aerospace Engineer, 2601 

Meacham Blvd, Fort Worth, Texas 

76137–4298; telephone: (817) 222–5133; 

fax: (817) 222–5960. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed under the 

ADDRESSES section. Include the docket 

number ‘‘FAA–2006–25927; Directorate 

Identifier 2006–CE–52–AD’’ at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the proposed AD. We will consider all 

comments received by the closing date 

and may amend the proposed 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 we receive 

concerning this proposed AD. 

Discussion 

History of AD Actions 

Failure of a Barber-Coleman pitch 

trim actuator, which allowed the 

horizontal stabilizer to move to a full 

aircraft nose up position on an M7 

Aerospace LP Model SA227 airplane, 

caused us to issue AD 98–19–15 R1, 

Amendment 39–11507 (65 FR 1540, 

January 11, 2000). AD 98–19–15 R1 

currently requires you to revise the 

Limitations Section of the FAAapproved AFM to limit the maximum 

indicated airspeed and increase the 

minimum crew size if a Barber-Coleman 

pitch trim actuator P/N 27–19008–001, 

P/N 27–19008–002, P/N 27–19008–004, 

or P/N 27–19008–005 is installed. 

To avoid the above limitations, AD 

98–19–15 R1 allows installation of a 

Barber-Coleman P/N 27–19008–006, 

Barber Coleman P/N 27–19008–007, 

Simmonds-Precision P/N DL5040M5, 

Simmonds-Precision P/N DL5040M6, or 

Simmonds-Precision P/N DL5040M8 

pitch trim actuator. All airplane models 

are eligible for any of these installations. 

The applicable service bulletin depends 

on the airplane model and pitch trim 

actuator. 

The FAA also issued AD 2000–03–17, 

Amendment 39–11576 (65 FR 8037, 

February 17, 2000), to establish 

inspection and replacement intervals for 

the pitch trim actuators. Inspection 

times and replacement times vary 

depending on the model of the airplane 

and the P/N of the pitch trim actuator 

installed. 

Events Since Previous AD Actions 

Since we issued ADs 98–19–15 R1 

and 2000–03–17, the FAA has 

determined that the actions fall within 

the FAA’s aging commuter-class aircraft 

policy, which briefly states that reliance 

on critical repetitive inspections carries 

an unnecessary safety risk when a 

design change exists that could 

eliminate or, in certain instances, 

reduce the number of those critical 

inspections. We also determined that 

the number of repetitive replacements 

could be reduced in these AD actions 


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because of pitch trim actuator design 

changes. 

The FAA has identified installation of 

Barber-Coleman P/N 27–19008–006, 

Barber-Coleman P/N 27–19008–007, or 

Simmonds-Precision P/N DL5040M8 

pitch trim actuators on all SA226 and 

SA227 series airplanes or installation of 

Simmonds-Precision P/N DL5040M6 

pitch trim actuators on all SA226 and 

SA227 series airplanes (except Models 

SA227-CC and SA227-DC) will 

significantly reduce the number of 

repetitive inspections and repetitive 

replacements currently required by AD 

2000–03–17. 

Relevant Service Information 

We have reviewed the following 

Fairchild Aircraft service information: 

• Fairchild Aircraft SA226 Series 

Service Letter (SL) 226–SL–005, 

Revised: August 3, 1999; 

• Fairchild Aircraft SA227 Series SL 

227–SL–011, Revised August 3, 1999; 

• Fairchild Aircraft SA227 Series SL 

CC7–SL–028, Issued: August 12, 1999; 

• Fairchild Aircraft SA226 Series SL 

226–SL–014, Revised: February 1, 1999; 

• Fairchild Aircraft SA227 Series SL 

227–SL–031, Revised: February 1, 1999; 

and 

• Fairchild Aircraft SA227 Series SL 

CC7–SL–021, Revised: February 1, 1999. 

The service information describes 

procedures for inspecting the various 

pitch trim actuators that can be installed 

in SA226 and SA227 series airplanes. 

This service information is currently 

referenced in the existing ADs. 

FAA’s Determination and Requirements 

of the Proposed AD 

We are proposing this AD because we 

evaluated all information and 

determined the unsafe condition 

described previously is likely to exist or 

develop on other products of the same 

type design. This proposed AD would 

supersede AD 98–19–15 R1 and AD 

2000–03–17 with a new AD that would 

retain all of the actions of the previously 

referenced ADs, but limit the part 

numbers of the pitch trim actuators that 

can be used for replacement. This 

proposed AD would also place a life 

limit on Barber-Coleman P/N 27–19008–

001, Barber-Coleman P/N 27–19008–

002, Barber-Coleman P/N 27–19008–

004, and Barber-Coleman P/N 27–

19008–005 pitch trim actuators. This 

proposed AD would require you to use 

the service information described 

previously to perform these actions. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 307 airplanes in the U.S. 

registry. 

This proposed AD requires pitch trim 

actuators to either be inspected or 

overhauled. We have no way of 

determining the number of airplanes 

that may need the inspection or 

overhaul. We have presented the fleet 

cost as the lowest cost based on all 

airplanes needing the inspection and 

the highest cost based on all airplanes 

needing the overhaul. The actual fleet 

cost will be somewhere between the 

lowest and highest fleet cost presented. 

We estimate the following costs to do 

the proposed inspection or overhaul: 

Labor cost Parts cost Total cost 

per airplane 

Total cost 

on U.S. 

operators 

4 work-hours × $80 per hour = $320 ...................................................................................................... None $320 $98,240 

4 work-hours × $80 per hour = $320 ...................................................................................................... $9,000 9,320 2,861,240 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

proposed inspection or proposed 

mandatory replacement. We have no 

way of determining the number of 

airplanes that may need this 

replacement: 

Labor cost Parts cost Total cost 

per airplane 

4 work-hours × $80 per hour = $320 .............................................................................................................................. $64,000 $64,320 

The replacement estimate is based on 

replacing the pitch trim actuator with a 

new Simmonds-Precision P/N 

DL5040M8 pitch trim actuator. If the 

pitch trim actuator is replaced with a 

different P/N FAA-approved pitch trim 

actuator or a zero-timed FAA-approved 

pitch trim actuator the cost to the 

owner/operator could be less. 

The estimated costs represented in the 

above actions include the costs 

associated with AD 98–19–15 R1, AD 

2000–03–17, and the costs of this 

proposed AD. The added cost impact 

this AD imposes upon an owner/ 

operator over that already required by 

AD 98–19–15 R1 and AD 2000–03–17 is 

the eventual replacement of the pitch 

trim actuator if the airplane currently 

has a Barber-Coleman P/N 27–19008–

001, P/N 27–19008–002, P/N 27–19008–

004, or P/N 27–19008–005 installed. 

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 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 the proposed regulation: 

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 


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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 proposed AD and placed it in the 

AD docket. 

Examining the AD Docket 

You may examine the AD docket that 

contains the proposed AD, the 

regulatory evaluation, any comments 

received, and other information on the 

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

person at the Docket Management 

Facility between 9 a.m. and 5 p.m., 

Monday through Friday, except Federal 

holidays. The Docket Office (telephone 

(800) 647–5227) is located at the street 

address stated in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 Airworthiness Directive (AD) 

98–19–15 R1, Amendment 39–11507 (65 

FR 1540, January 11, 2000), and AD 

2000–03–17, Amendment 39–11576 (65 

FR 8037, February 17, 2000); and by 

adding the following new AD: 

M7 Aerospace LP (Type Certificate No. 

A5SW, A8SW, and A18SW formerly 

held by Fairchild Aircraft 

Incorporated): Docket No. FAA–2006–

25927; Directorate Identifier 2006–CE–

52–AD. 

Comments Due Date 

(a) We must receive comments on this 

airworthiness directive (AD) action by June 

29, 2007. 

Affected ADs 

(b) This AD supersedes the following ADs: 

(1) AD 98–19–15 R1, Amendment 39–

11507; and 

(2) AD 2000–03–17, Amendment 39–

11576. 

Applicability 

(c) This AD applies to all Models SA226–

AT, SA226–T, SA226–T(B), SA226–TC, 

SA227–AC (C–26A), SA227–AT, SA227–BC 

(C–26A), SA227–CC, SA227–DC (C–26B), 

SA227–PC, and SA227–TT airplanes, all 

serial numbers, that: 

(1) are certificated in any category; and 

(2) are equipped with pitch trim actuator 

Barber-Coleman part number (P/N) 27–

19008–001, Barber-Coleman P/N 27–19008–

002, Barber-Coleman P/N 27–19008–004, 

Barber-Coleman P/N 27–19008–005, BarberColeman P/N 27–19008–006, Barber-Coleman 

P/N 27–19008–007, Simmonds-Precision P/N 

DL5040M5, Simmonds-Precision P/N 

DL5040M6, or Simmonds-Precision P/N 

DL5040M8. 

Unsafe Condition 

(d) This AD results from reports of 

mechanical failure of the pitch trim actuator 

causing the horizontal stabilizer to move to 

full aircraft nose up. We are proposing this 

AD to detect excessive freeplay or rod 

slippage in the pitch trim actuator, which, if 

not detected and corrected, could result in 

pitch trim actuator failure. We are also 

proposing this AD to lessen the severity of 

pitch upset if a pitch trim actuator 

mechanical failure occurs. These conditions 

could lead to possible loss of control. In 

addition, we are proposing this AD to 

eliminate the use of certain pitch trim 

actuators that require frequent critical 

inspections or replacements. 

Compliance 

(e) To address this problem, you must do 

the following, unless already done: 

(1) For airplanes with a Barber-Coleman 

pitch trim actuator, P/N 27–19008–001, P/N 

27–19008–002, P/N 27–19008–004, or P/N 

27–19008–005: Before further flight after 

September 25, 1998 (the effective date of AD 

98–19–15), incorporate the text in paragraphs 

(e)(1)(i) and (e)(1)(ii) of this AD into the 

Limitations Section of the FAA-approved 

Airplane Flight Manual (AFM). The owner/ 

operator holding at least a private pilot 

certificate as authorized by section 43.7 of 

the Federal Aviation Regulations (14 CFR 

43.7) may insert the information specified in 

paragraphs (e)(1)(i) and (e)(1)(ii) of this AD 

into the AFM Limitations Section. This may 

be done by inserting a copy of this AD into 

the AFM. Make an entry into the aircraft 

records showing compliance with this 

portion of the AD in accordance with section 

43.9 of the Federal Aviation Regulations (14 

CFR 43.9). 

(i) ‘‘Limit the maximum indicated airspeed 

to maneuvering airspeed (Va) as shown in the 

appropriate airplane flight manual (AFM)’’; 

and 

(ii) ‘‘The minimum crew required is two 

pilots.’’

Note 1: Fairchild Service Letter 226–SL–

017, Fairchild Service Letter 227–SL–033, 

and Fairchild Service Letter CC7–SL–023, all 

FAA Approved: August 26, 1998; Revised: 

September 2, 1998, address the subject matter 

of this AD. 

Note 2: The before further flight 

compliance time of paragraph (e)(1) of this 

AD is retained from AD 98–19–15 R1. 

Note 3: Installation of any FAA-approved 

pitch trim actuator other than the BarberColeman P/N 27–19008–001, P/N 27–19008–

002, P/N 27–19008–004, or P/N 27–19008–

005 terminates the requirements of paragraph 

(e)(1) of this AD. 

(2) For all airplanes: Do the following 

initial inspection or overhaul and repetitive 

inspection or overhaul at the times specified 

in the table in paragraph (4) of this AD: 

(i) For airplanes equipped with a 

Simmonds-Precision pitch trim actuator P/N 

DL5040M5, P/N DL5040M6, or P/N 

DL5040M8: Measure the freeplay of the pitch 

trim actuator and inspect the pitch trim 

actuator for rod slippage using the 

INSTRUCTIONS section of Fairchild Aircraft 

SA226 Series Service Letter (SL) 226–SL–005 

or Fairchild Aircraft SA227 Series SL 227–

SL–011, both Revised: August 3, 1999; or 

Fairchild Aircraft SA227 Series Service 

Letter CC7–SL–028, Issued: August 12, 1999, 

as applicable. 

(ii) For airplanes equipped with BarberColeman pitch trim actuators, P/N 27–19008–

001, P/N 27–19008–002, P/N 27–19008–004, 

or P/N 27–19008–005: Do a functional 

inspection of the pitch trim actuator using 

the INSTRUCTIONS section of Fairchild 

Aircraft SA226 Series SL 226–SL–014, 

Fairchild Aircraft SA227 Series SL 227–SL–

031, or Fairchild Aircraft SA227 Series SL 

CC7–SL–021; all Revised: February 1, 1999; 

as applicable. 

Note 4: The actions in paragraphs (e)(2)(i) 

and (e)(2)(ii) of this AD are the same as the 

actions in AD 2000–03–17. The only 

difference between this AD and AD 2000–03–

17 is the addition of life limits to BarberColeman pitch trim actuators P/N 27–19008–

001, P/N 27–19008–002, P/N 27–19008–004, 

or P/N 27–19008–005. 

(iii) For airplanes equipped with BarberColeman pitch trim actuators, P/N 27–19008–

006 or P/N 27–19008–007: Overhaul the pitch 

trim actuator following the applicable 

maintenance manual. 

(3) For all airplanes: Before further flight 

replace the pitch trim actuator following the 

applicable maintenance manual when any of 

the following occurs: 

(i) The pitch trim actuator is inspected 

following paragraphs (e)(2)(i) and (e)(2)(ii) of 

this AD and the freeplay limitations are 

exceeded, rod slippage is found, or a ratching 

sound occurs, as specified in the applicable 

service letters; or 

(ii) The installed pitch trim actuator 

reaches its repetitive replacement time as 

specified in the table in paragraph (e)(4) of 

this AD. 

(4) The table below presents the pitch trim 

actuators that could be installed and the 

compliance times for the initial inspections 

or overhaul, repetitive inspections or 

overhaul, and repetitive replacements 

required by this AD: 


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TABLE—INSPECTION/OVERHAUL AND REPLACEMENT REQUIREMENTS FOR PITCH TRIM ACTUATORS. 

Condition Initial inspection or overhaul Repetitive inspection or overhaul Repetitive replacement 

(i) For all affected airplane models 

(except for the Models SA227–

CC and SA227–DC) that have 

an original Simmonds-Precision 

pitch trim actuator, P/N 

DL5040M5, installed.

Inspect following paragraph 

(e)(2)(i) of this AD before accumulating 3,000 hours time-inservice (TIS) on the pitch trim 

actuator or within 50 hours TIS 

after April 17, 1995 (the effective date of AD 93–15–02 R1), 

whichever occurs later.

Inspect following paragraph 

(e)(2)(i) of this AD before accumulating 250 hours TIS after 

the initial inspection and repetitively thereafter at intervals not 

to exceed 250 hours TIS until 

accumulating the hours TIS 

specified in the paragraph 

(e)(4)(i) Repetitive Replacement 

column of this AD.

Replace the pitch trim actuator 

with a Simmonds-Precision P/N 

DL5040M6, Simmonds-Precision P/N DL5040M8, BarberColeman P/N 27–19008–006, 

Barber-Coleman P/N 27–

19008–007, or an FAA-approved equivalent pitch trim actuator before accumulating 

5,000 hours TIS on the pitch 

trim actuator, 500 hours TIS 

after the initial inspection, or 

within 30 days after the effective date of this AD, whichever 

occurs later. 

(ii) For all affected airplane models 

(except for the Models SA227–

CC and SA227–DC) that have a 

replacement Simmonds-Precision pitch trim actuator, P/N 

DL5040M5, installed.

Inspect following paragraph 

(e)(2)(i) of this AD before accumulating 5,000 hours TIS on 

the pitch trim actuator or within 

50 hours TIS after April 17, 

1995 (the effective date of AD 

93–15–02 R1), whichever occurs later.

Inspect following paragraph 

(e)(2)(i) of this AD before accumulating 300 hours TIS after 

the initial inspection and repetitively thereafter at intervals not 

to exceed 300 hours TIS until 

accumulating the hours TIS 

specified in the paragraph 

(e)(4)(ii) Repetitive Replacement column of this AD.

Replace the pitch trim actuator 

with a Simmonds-Precision P/N 

DL5040M6, Simmonds-Precision P/N DL5040M8, BarberColeman P/N 27–19008–006, 

Barber-Coleman P/N 27–

19008–007, or an FAA-approved equivalent pitch trim actuator before accumulating 

6,500 hours TIS on the pitch 

trim actuator or within 30 days 

after the effective date of this 

AD, whichever occurs later. 

(iii) For all affected airplane models (except for the Models 

SA227–CC and SA227–DC) that 

have a replacement SimmondsPrecision pitch trim actuator, P/N 

DL5040M6, installed. This part 

can be new, modified from a P/ 

N DL5040M5 pitch trim actuator, 

or overhauled and zero-timed.

Inspect following paragraph 

(e)(2)(i) of this AD before accumulating 7,500 hours TIS on 

the pitch trim actuator or within 

50 hours TIS after April 17, 

1995 (the effective date of AD 

93–15–02 R1), whichever occurs later.

Inspect following paragraph 

(e)(2)(i) of this AD before accumulating 300 hours TIS after 

the initial inspection and repetitively thereafter at intervals not 

to exceed 300 hours TIS until 

accumulating the hours TIS 

specified in the paragraph 

(e)(4)(iii) Repetitive Replacement column of this AD.

Replace the pitch trim actuator 

with a Simmonds-Precision P/N 

DL5040M6, Simmonds-Precision P/N DL5040M8, BarberColeman P/N 27–19008–006, 

Barber-Coleman P/N 27–

19008–007, or an FAA-approved equivalent pitch trim actuator before accumulating 

9,900 hours TIS on the pitch 

trim actuator or within 30 days 

after the effective date of this 

AD, whichever occurs later. 

(iv) For all affected airplane models (except for the Models 

SA227–CC and SA227–DC) that 

have a replacement SimmondsPrecision pitch trim actuator, P/N 

DL5040M5, installed that was 

overhauled and zero-timed 

where both nut assemblies, P/N 

AA56142, were replaced with 

new assemblies during overhaul.

Inspect following paragraph 

(e)(2)(i) of this AD before accumulating 5,000 hours TIS on 

the pitch trim actuator or within 

50 hours TIS after April 17, 

1995 (the effective date of AD 

93–15–02 R1), whichever occurs later.

Inspect following paragraph 

(e)(2)(i) of this AD before accumulating 300 hours TIS after 

the initial inspection and repetitively thereafter at intervals not 

to exceed 300 hours TIS until 

accumulating the hours TIS 

specified in the paragraph 

(e)(4)(iv) Repetitive Replacement column of this AD.

Replace the pitch trim actuator 

with a Simmonds-Precision P/N 

DL5040M6, Simmonds-Precision P/N DL5040M8, BarberColeman P/N 27–19008–006, 

Barber-Coleman P/N 27–

19008–007, or an FAA-approved equivalent pitch trim actuator before accumulating 

6,500 hours TIS on the pitch 

trim actuator or within 30 days 

after the effective date of this 

AD, whichever occurs later. 

(v) For all affected airplane models 

(except for the Models SA227–

CC and SA227–DC) that have a 

replacement Simmonds-Precision P/N DL5040M5 pitch trim 

actuator installed that was overhauled and zero-timed where 

both nut assemblies, P/N 

AA56142, were not replaced 

with new assemblies during 

overhaul.

Inspect following paragraph 

(e)(2)(i) of this AD before accumulating 3,000 hours TIS on 

the pitch trim actuator or within 

50 hours TIS after April 17, 

1995 (the effective date of AD 

93–15–02 R1), whichever occurs later.

Inspect following paragraph 

(e)(2)(i) of this AD before accumulating 250 hours TIS after 

the initial inspection and repetitively thereafter at intervals not 

to exceed 250 hours TIS until 

accumulating the hours TIS 

specified in the paragraph 

(e)(4)(v) Repetitive Replacement column of this AD.

Replace the pitch trim actuator 

with a Simmonds-Precision P/N 

DL5040M6, Simmonds-Precision P/N DL5040M8, BarberColeman P/N 27–19008–006, 

Barber-Coleman P/N 27–

19008–007, or an FAA-approved equivalent pitch trim actuator before accumulating 

5,000 hours TIS on the pitch 

trim actuator or within 30 days 

after the effective date of this 

AD, whichever occurs later. 


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TABLE—INSPECTION/OVERHAUL AND REPLACEMENT REQUIREMENTS FOR PITCH TRIM ACTUATORS.—Continued 

Condition Initial inspection or overhaul Repetitive inspection or overhaul Repetitive replacement 

(vi) For all affected airplane models (except for the Models 

SA227–CC and SA227–DC) that 

have a newly fabricated or overhauled and zero-timed BarberColman pitch trim actuator, P/N 

27–19008–001, P/N 27–19008–

002, P/N 27–19008–004, or P/N 

27–19008–005.

Inspect following paragraph 

(e)(2)(ii) of this AD before accumulating 500 hours total TIS on 

the pitch trim actuator or within 

50 hours TIS after December 1, 

1997 (the effective date of AD 

97–23–01), whichever occurs 

later.

Inspect following paragraph 

(e)(2)(ii) of this AD before accumulating 300 hours TIS after 

the initial inspection and repetitively thereafter at intervals not 

to exceed 300 hours TIS until 

accumulating the hours TIS 

specified in the paragraph 

(e)(4)(vi) Repetitive Replacement column of this AD.

Replace the pitch trim actuator 

with a Simmonds-Precision P/N 

DL5040M6, Simmonds-Precision P/N DL5040M8, BarberColeman P/N 27–19008–006, 

Barber-Coleman P/N 27–

19008–007, or an FAA-approved equivalent pitch trim actuator before accumulating 

5,000 hours TIS on the pitch 

trim actuator or within 30 days 

after the effective date of this 

AD, whichever occurs later. 

(vii) For the Models SA227–CC 

and SA227–DC that have a 

Simmonds-Precision pitch trim 

actuator, P/N DL5040M5 or P/N 

DL5040M6, installed.

None ............................................. None ............................................. Replace the pitch trim actuator 

with a Simmonds-Precision 

pitch trim actuator P/N 

DL5040M8, a Barber-Coleman 

P/N 27–19008–006 or P/N 27–

19008–007, or an FAA-approved equivalent before accumulating 1,500 hours TIS on 

the pitch trim actuator or within 

30 days after the effective date 

of this AD, whichever occurs 

later. 

(viii) For the Models SA227–CC 

and SA227–DC that have a 

newly fabricated or over-hauled 

and zero-timed Barber-Colman 

pitch trim actuator, P/N 27–

19008–001, P/N 27–19008–002, 

P/N 27–19008–004, or P/N 27–

19008–005.

Inspect following paragraph 

(e)(2)(ii) of this AD before accumulating 500 hours total TIS on 

the pitch trim actuator or within 

50 hours TIS after December 1, 

1997 (the effective date of AD 

97–23–01), whichever occurs 

later.

Inspect following paragraph 

(e)(2)(ii) of this AD before accumulating 300 hours TIS after 

the initial inspection and repetitively thereafter at intervals not 

to exceed 300 hours TIS until 

accumulating the hours TIS 

specified in the paragraph 

(e)(4)(viii) Repetitive Replacement column of this AD.

Replace the pitch trim actuator 

with a Simmonds-Precision P/N 

DL5040M8, Barber-Coleman P/ 

N 27–19008–006, Barber-Coleman P/N 27–19008–007, or an 

FAA-approved equivalent pitch 

trim actuator before accumulating 5,000 hours TIS on the 

pitch trim actuator or within 30 

days after the effective date of 

this AD, whichever occurs later. 

(ix) For all affected airplanes with 

a Simmonds-Precision pitch trim 

actuator, P/N DL5040M8, installed.

Inspect following paragraph 

(e)(2)(i) of this AD before accumulating 7,500 hours TIS on 

the pitch trim actuator or within 

the next 50 hours TIS after 

April 10, 2000 (the effective 

date of AD 2000–03–17), 

whichever occurs later.

Inspect following paragraph 

(e)(2)(i) of this AD before accumulating 300 hours TIS after 

the initial inspection and repetitively thereafter at intervals not 

to exceed 300 hours TIS until 

accumulating the hours TIS 

specified in paragraph (e)(4)(ix) 

Repetitive Replacement column 

of this AD.

Replace the pitch trim actuator 

with a Simmonds-Precision 

pitch trim actuator P/N 

DL5040M8, a Barber-Coleman 

P/N 27–19008–006 or P/N 27–

19008–007, or an FAA-approved equivalent before accumulating 9,900 hours TIS on 

the pitch trim actuator or within 

30 days after the effective date 

of this AD, whichever occurs 

later. 

(x) For all affected airplanes with a 

Barber-Colman P/N 27–19008–

006 or 27–19008–007 pitch trim 

actuator installed.

Overhaul following paragraph 

(e)(2)(iii) of this AD before accumulating 2,000 hours TIS on 

the pitch trim actuator.

Overhaul following paragraph 

(e)(2)(iii) of this AD before accumulating 2,000 hours TIS on 

the pitch trim actuator.

No replacement requirements. 

(5) For all airplane models except Models 

SA227–CC and SA227–DC: As of the effective 

date of this AD, do not install as a 

replacement any of the following pitch trim 

actuators or FAA-approved equivalent P/N: 

(i) Barber-Colman P/N 27–19008–001; 

(ii) Barber-Colman P/N 27–19008–002; 

(iii) Barber-Colman P/N 27–19008–004; 

(iv) Barber-Colman P/N 27–19008–005; or 

(v) Simmonds-Precision P/N DL5040M5. 

(6) For all airplane Models SA227–CC and 

SA227–DC: As of the effective date of this 

AD, do not install as a replacement any of the 

following pitch trim actuators or FAAapproved equivalent P/N: 

(i) Barber-Colman P/N 27–19008–001; 

(ii) Barber-Colman P/N 27–19008–002; 

(iii) Barber-Colman P/N 27–19008–004; 

(iv) Barber-Colman P/N 27–19008–005; 

(v) Simmonds-Precision P/N DL5040M5; or 

(vi) Simmonds-Precision P/N DL5040M6. 

Alternative Methods of Compliance 

(AMOCs) 

(f) The Manager, Fort Worth Airplane 

Certification Office (ACO), FAA, ATTN: 

Werner Koch, Aerospace Engineer, 2601 

Meacham Blvd, Fort Worth, Texas 76137–

4298, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Before using any 

approved AMOC on any airplane to which 

the AMOC applies, notify your appropriate 

principal inspector (PI) in the FAA Flight 

Standards District Office (FSDO), or lacking 

a PI, your local FSDO. 

Related Information 

(g) To get copies of the service information 

referenced in this AD, contact M7 Aerospace 

LP, 10823 N. E. Entrance, San Antonio, Texas 

78216. To view the AD docket, go to the 

Docket Management Facility; U.S. 

Department of Transportation, 400 Seventh 

Street, SW., Nassif Building, Room PL–401, 

Washington, DC, or on the Internet at http:// 

dms.dot.gov. The docket number is Docket 

No. FAA–2006–25927; Directorate Identifier 

2006–CE–52–AD. 


jlentini on PROD1PC65 with PROPOSAL
21176 Federal Register / Vol. 72, No. 82 / Monday, April 30, 2007 / Proposed Rules 

Issued in Kansas City, Missouri, on April 

20, 2007. 

Charles L. Smalley, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E7–8163 Filed 4–27–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF THE INTERIOR 

Office of Surface Mining Reclamation 

and Enforcement 

30 CFR Part 935 

[OH–252–FOR] 

Ohio Regulatory Program 

AGENCY: Office of Surface Mining 

Reclamation and Enforcement (OSM), 

Interior. 

ACTION: Proposed rule; public comment 

period and opportunity for public 

hearing on proposed amendment. 

SUMMARY: We (OSM) are announcing 

receipt of a proposed amendment to the 

Ohio regulatory program (the ‘‘Ohio 

program’’) under the Surface Mining 

Control and Reclamation Act of 1977 

(SMCRA or the Act). Ohio proposes to 

revise the Ohio Revised Code (ORC) 

regarding changes to the State’s 

alternate bonding system (bond pool), 

funding for its regulatory and 

abandoned mine land programs and its 

bond pool, permitting procedures for 

determining the potential that proposed 

mine sites may or may not produce 

acid-mine drainage, and authorizes rulemaking if Ohio becomes covered by a 

State programmatic general permit 

issued by the U.S. Army Corps of 

Engineers for the discharge of dredged 

or fill material into waters of the United 

States by coal mining operations. The 

amendment is primarily intended to 

satisfy a program condition codified in 

the Federal regulations. This 

amendment replaces the State’s bond 

pool amendment that the State 

previously submitted and that OSM 

announced, and requested public 

comments on, in the Federal Register 

dated February 13, 2006 (71 FR 7480). 

This document gives the times and 

locations that the Ohio program and 

proposed amendment to that program 

are available for your inspection, the 

comment period during which you may 

submit written comments on the 

amendment, and the procedures that we 

will follow for the public hearing, if one 

is requested. 

DATES: We will accept written 

comments on this amendment until 4 

p.m. (local time), May 30, 2007. If 

requested, we will hold a public hearing 

on the amendment on May 25, 2007. We 

will accept requests to speak at a 

hearing until 4 p.m., local time, on May 

15, 2007. 

ADDRESSES: You may submit comments, 

identified by OH–252–FOR, by any of 

the following methods: 

• E-mail: grieger@osmre.gov. Include 

OH–252–FOR in the subject line of the 

message; 

• Mail/Hand Delivery: Mr. George 

Rieger, Chief, Pittsburgh Field Division, 

Office of Surface Mining Reclamation 

and Enforcement, 4605 Morse Road, 

Room 102, Columbus, OH 43230. 

Telephone: 614–416–2238. 

• Federal eRulemaking Portal: http:// 

www.regulations.gov. Follow the 

instructions for submitting comments. 

Instructions: All submissions received 

must include the agency docket number 

for this rulemaking. For detailed 

instructions on submitting comments 

and additional information on the 

rulemaking process, see the ‘‘Public 

Comment Procedures’’ heading in the 

SUPPLEMENTARY INFORMATION section of 

this document. You may also request to 

speak at a public hearing by any of the 

methods listed above or by contacting 

the individual listed under FOR FURTHER

INFORMATION CONTACT. 

Docket: You may review copies of the 

Ohio program, this amendment, a listing 

of any scheduled public hearings, and 

all written comments received in 

response to this document at the 

addresses listed below during normal 

business hours, Monday through Friday, 

excluding holidays. You may also 

receive one free copy of this amendment 

by contacting OSM’s Pittsburgh Field 

Division listed below: 

Mr. George Rieger, Chief, Pittsburgh 

Field Division, Office of Surface 

Mining Reclamation and Enforcement 

4605 Morse Road, Room 102, 

Columbus, OH 43230 614–416–2238. 

E-mail: grieger@osmre.gov. 

Mr. Scott Kell, Acting Chief, Division of 

Mineral Resources Management, Ohio 

Department of Natural Resources, 

2045 Morse Road, Bldg. H–2, 

Columbus, Ohio 43229, Telephone: 

(614) 265–6633. 

FOR FURTHER INFORMATION CONTACT: Mr. 

George Rieger, Chief, Pittsburgh Field 

Division, Telephone: (717) 782–4849, 

extension 11; or 614–416–2238; or 412–

937–2153. E-mail: grieger@osmre.gov. 

SUPPLEMENTARY INFORMATION: 

I. Background on the Ohio Program 

II. Description of the Proposed Amendment 

III. Public Comment Procedures 

IV. Procedural Determinations 

I. Background on the Ohio Program 

Section 503(a) of the Act permits a 

State to assume primacy for the 

regulation of surface coal mining and 

reclamation operations on non-Federal 

and non-Indian lands within its borders 

by demonstrating that its program 

includes, among other things, ‘‘a State 

law which provides for the regulation of 

surface coal mining and reclamation 

operations in accordance with the 

requirements of the Act * * * and rules 

and regulations consistent with 

regulations issued by the Secretary 

pursuant to the Act.’’ See 30 U.S.C. 

1253(a)(1) and (7). On the basis of these 

criteria, the Secretary of the Interior 

conditionally approved the Ohio 

program on August 16, 1982. You can 

find background information on the 

Ohio program, including the Secretary’s 

findings, the disposition of comments, 

and conditions of approval of the Ohio 

program in the August 16, 1982, Federal 

Register (47 FR 34687). You can also 

find later actions concerning Ohio’s 

program and program amendments at 30 

CFR 935.11, 935.15, and 935.16. 

II. Description of the Proposed 

Amendment 

By letter dated March 6, 2007, Ohio 

sent us a proposed amendment to its 

program (Administrative Record 

Number OH–2185–28) under SMCRA 

(30 U.S.C. 1201 et seq.). In its letter, 

Ohio stated that in December of 2006, 

the Ohio legislature passed House Bill 

443, which is intended to address many 

of the issues of concern relative to 

Ohio’s bond pool. Ohio proposes to 

revise the Ohio Revised Code (ORC) 

regarding changes to the State’s 

alternate bonding system (bond pool), 

funding for its regulatory and 

abandoned mine land programs and its 

bond pool, permitting procedures for 

determining the potential that proposed 

mine sites may or may not produce 

acid-mine drainage, and authorizes rulemaking if Ohio becomes covered by a 

State programmatic general permit 

issued by the U.S. Army Corps of 

Engineers for the discharge of dredged 

or fill material into waters of the United 

States by coal mining operations. 

The amendment is intended to satisfy 

a program condition codified in the 

Federal regulations at 30 CFR 935.11(h), 

and is in response to OSM’s letter of 

May 4, 2005, issued under provisions of 

30 CFR 733.12(b). The program 

condition provides that Ohio must 

submit a program amendment that 

demonstrates how the alternative 

bonding system will assure timely 

reclamation at the site of all operations 

for which bond has been forfeited. 


jlentini on PROD1PC65 with PROPOSAL