This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

44773 

Vol. 74, No. 167 

Monday, August 31, 2009 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–1312; Directorate 

Identifier 2008–CE–065–AD] 

RIN 2120–AA64 

Airworthiness Directives; Hawker 

Beechcraft Corporation Models 1900, 

1900C, and 1900D Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

Reopening of the comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

that applies to certain Hawker 

Beechcraft Corporation Models 1900, 

1900C, and 1900D airplanes. The earlier 

NPRM would have required a one-time 

visual inspection and repetitive 

ultrasonic inspections of the left and 

right main landing gear (MLG) actuators 

for leaking and/or cracks with 

replacement of the actuator if leaking 

and/or cracks are found. The earlier 

NPRM resulted from reports of leaking 

and cracked actuators. This proposed 

AD would require the same actions as 

the earlier NPRM. Since the earlier 

NPRM, we have identified a MLG 

overhauled actuator part number and a 

MLG actuator approved by parts 

manufacturer approval (PMA) by 

identicality. We propose to expand the 

applicability to include airplanes 

equipped with these additional part 

numbers. Because this imposes an 

additional burden over that proposed in 

the earlier NPRM, we are reopening the 

comment period to allow the public the 

chance to comment on these additional 

MLG actuators. 

DATES: We must receive comments on 

this proposed AD by September 30, 

2009. 

ADDRESSES: Use one of the following 

addresses to comment on this proposed 

AD: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

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

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

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

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this proposed AD, contact Hawker 

Beechcraft Corporation, P.O. Box 85, 

Wichita, Kansas 67201–0085; telephone: 

(800) 429–5372 or (316) 676–3140; 

Internet: http:// 

pubs.hawkerbeechcraft.com. 

FOR FURTHER INFORMATION CONTACT: Don 

Ristow, Aerospace Engineer, 1801 

Airport Road, Room 100, Wichita, 

Kansas 67209; telephone: (316) 946– 

4120; fax: (316) 946–4107. 

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–2008–1312; Directorate 

Identifier 2008–CE–065–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:// 

www.regulations.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 

On December 8, 2008, we issued a 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) to 

include an AD that would apply to 

certain Hawker Beechcraft Corporation 

Models 1900, 1900C, and 1900D 

airplanes. This proposal was published 

in the Federal Register as a notice of 

proposed rulemaking (NPRM) on 

December 15, 2008 (73 FR 75977). The 

NPRM proposed to require a one-time 

visual inspection and repetitive 

ultrasonic inspections of the left and 

right main landing gear (MLG) actuators 

for leaking and/or cracks with 

replacement of the actuator if leaking 

and/or cracks are found. 

Comments 

We provided the public the 

opportunity to participate in developing 

this AD. The following presents the 

comments received on the proposal and 

FAA’s response to each comment: 

Comment Issue No. 1: Report to TypeCertificate (TC) Holder by E-Mail 

Wayne R. Modny and Hawker 

Beechcraft Corporation request the 

option of using e-mail to send the report 

required in this AD. 

The FAA agrees with allowing 

owners/operators to comply with the 

reporting requirement by e-mail. 

However, we have changed the 

proposed AD action and no longer 

require owners/operators to report to the 

TC holder. We retained the proposed 

reporting requirement to the FAA and 

provided an e-mail address for 

complying with that proposed AD 

action. 

Comment Issue No. 2: Replacement of 

Actuator With Other Part Number (P/N) 

Actuators 

Gulfstream International Airlines 

requests that we not limit replacement 

of the MLG actuator to P/N 114– 

380041–17 because other FAA-approved 

P/Ns (P/N 114–380041–7 or –9) could 

be used as terminating action. The 

commenter states that terminating 

action should consist of replacing the 

affected actuator with an actuator of a 

P/N listed in the Hawker Beechcraft 

illustrated parts catalog other than P/N 

114–380041–15. 

The FAA agrees. Our intent was to not 

allow installation of P/Ns 114–380041– 

11 and 114–380041–13 and only allow 

installation of P/N 114–380041–15 (or 

P/N 114–380041–15OVH) if the end 

caps were new or had been inspected 

per paragraph (e)(1), (e)(2), or (e)(3) of 

this proposed AD. Installation of other 

FAA-approved actuators as terminating 

action is acceptable. The service 

bulletin calls out replacement parts that 

are readily available. The P/N 114– 


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380041–17 is the latest part number 

available that is not affected by the 

inspections in this proposed AD. The 

earlier P/N 114–380041–7 or P/N 114– 

380041–9 actuator may be used as 

terminating action in place of the P/N 

114–380041–17; however, parts 

availability is not guaranteed. 

We will change the proposed AD 

action to allow installation of other 

FAA-approved actuators in paragraph 

(e)(4) of this AD. 

Comment Issue No. 3: Ultrasonic 

Inspections 

Hawker Beechcraft Corporation 

requests that we remove the words 

‘‘FAA-approved equivalent P/N’’ from 

the replacement parts language of the 

AD. Using ‘‘FAA-approved equivalent 

P/N’’ for replacement parts could be 

misintrepeted to mean that 114–380041 

actuators manufactured by Airtight or 

Tactair may also be required to do the 

ultrasonic inspections. The ultrasonic 

inspection defined in the Hawker 

Beechcraft Service Bulletin 32–3870, 

dated April 2008, is approved only for 

MLG actuators P/N 114–380041–11, 

P/N 114–380041–13, and P/N 114– 

380041–15 manufactured by Triumph 

Actuation Systems (previously 

manufactured by Frisby). 

The FAA partially agrees. We agree 

that Hawker Beechcraft Service Bulletin 

32–3870, dated April 2008, should not 

be used to do ultrasonic inspections on 

MLG actuators produced by another 

manufacturer. However, we disagree 

that the words ‘‘FAA-approved 

equivalent P/N’’ should be removed 

from the applicability or replacement 

parts language. Our research shows 

Frisby Airborne Hydraulic, Inc. (Frisby) 

has PMA approval by identicality for 

their P/N 1FA10043–3 actuator as a 

replacement for Hawker Beechcraft P/N 

114–380041–15. Therefore by including 

‘‘FAA-approved equivalent P/N’’ in both 

the applicability and replacement parts 

language of this proposed AD, P/N 

1FA10043–3 and any other actuator that 

is PMA approved by identicality can be 

used as a replacement part. They will 

also be subject to the inspection 

requirement of the AD, but the Hawker 

Beechcraft service bulletin cannot be 

used. 

We will change the proposed AD 

action by referencing Hawker Beechcraft 

Service Bulletin 32–3870, dated April 

2008, to do the visual and ultrasonic 

inspections only for P/N 114–380041– 

11, P/N 114–380041–13, and P/N 114– 

380041–15 (or P/N 114–380041– 

15OVH). For FAA-approved equivalent 

part numbers, the owner/operator must 

contact the PMA holder to obtain FAAapproved inspection instructions to do 

the visual and ultrasonic inspections. 

Comment Issue No. 4: P/Ns for 

Terminating Action 

Hawker Beechcraft Corporation 

requests that we change the words of the 

AD to make it clear that only MLG 

actuators P/N 114–380041–11, P/N 114– 

380041–13, and P/N 114–380041–15 are 

affected by the AD and that only P/N 

114–380041–17 terminates the 

requirements of the AD. The 

Applicability is for MLG actuators P/N 

114–380041–11, P/N 114–380041–13, 

and P/N 114–380041–15, but wording in 

some areas of the AD imply all P/N 114– 

380041 actuators. 

The FAA disagrees. The P/N 114– 

380041–17 is the most current part 

number available that is not affected by 

the inspections proposed in this 

proposed AD. However, installation of 

other FAA-approved actuators as 

terminating action is acceptable, such as 

P/N 114–380041–7 or P/N 114–380041– 

9. The wording ‘‘FAA-approved 

equivalent P/N’’ applies to actuators 

that are FAA-approved by identicality 

through the PMA process. Our research 

shows Frisby has PMA approval for 

their P/N 1FA10043–3 actuator as a 

replacement for Hawker Beechcraft P/N 

114–380041–15. Therefore by including 

‘‘FAA-approved equivalent P/N’’ in the 

replacement parts language of this 

proposed AD, P/N 1FA10043–3 can be 

used as a direct replacement for Hawker 

Beechcraft P/N 114–380041–15. Since 

P/N 1FA10043–3 is a PMA part through 

identicality for P/N 114–380041–15, the 

AD should also apply to that P/N and 

any other parts that may have PMA 

through identicality to P/N 114– 

380041–11, P/N 114–380041–13, and P/ 

N 114–380041–15. 

We will change the proposed AD 

action to add the language ‘‘FAAapproved equivalent P/N’’ for P/N 114– 

380041–11, P/N 114–380041–13, and 

P/N 114–380041–15 into the 

Applicability section. We will also add 

that for the purposes of this AD action 

the phrase ‘‘or FAA-approved 

equivalent part number’’ in this AD 

refers to any PMA part that is approved 

by identicality to the referenced part. 

Comment Issue No. 5: Previous 

Inspections 

Wayne R. Modny requests that the 

compliance inspection criteria defined 

in paragraphs (e)(1) and (e)(2) of the 

NPRM address previously inspected 

parts. If the initial 50-hour visual 

inspection and the initial 600-cycle 

ultrasonic inspection have been done 

following Hawker Beechcraft Mandatory 

Service Bulletin SB 32–3870, dated 

April 2008, then these initial 

inspections should not have to be 

repeated for the AD. 

The FAA agrees. The language as 

written in paragraph (e) of this proposed 

AD, ‘‘you must do the following, unless 

already done’’ allows for the inspections 

already done following Hawker 

Beechcraft Mandatory Service Bulletin 

SB 32–3870, dated April 2008. 

We will not change the proposed AD 

action based on this comment. 

Comment Issue No. 6: Overhauled 

Actuators and New End Caps 

Hawker Beechcraft Corporation 

requests that we add language to the 

actions of this AD to allow for 

overhauled actuators that have records 

that prove an internal fluorescent 

penetrant inspection had been done and 

for actuators that have records that 

prove the end caps are new. 

The FAA agrees. For MLG overhauled 

actuators that have records that prove an 

internal fluorescent penetrant 

inspection has been done and for MLG 

actuators that have records that prove 

the end caps are new, we agree that the 

Hawker Beechcraft Mandatory Service 

Bulletin SB 32–3870, dated April 2008, 

makes a compliance time allowance for 

the initial ultrasonic inspection 

proposed in this AD. 

We will change the proposed AD 

action by adding language that allows 

compliance time differences for 

overhauled MLG actuators that have had 

an internal fluorescent penetrant 

inspection and for MLG actuators that 

have new end caps. 

Comment Issue No. 7: Compliance Time 

Units 

Hawker Beechcraft Corporation 

requests that we remove the NOTE with 

the conversion formula to determine 

hours time-in-service (TIS) in lieu of 

cycles because it is not needed or to add 

the words ‘‘If the number of cycles is 

not known’’ at the beginning of the note. 

The 1900 series fleet tracks cycles, and 

the landing gear component inspections, 

specifically, are tracked by cycles. The 

conversion formula could lead to an 

interpretation that hours TIS should be 

used even if the number of cycles is 

known. 

The FAA agrees that the note could 

include language to indicate the formula 

applies if the number of cycles is not 

known. However, since an owner/ 

operator must use the conversion 

formula if the number of cycles is 

unknown, we are changing the note to 

an action statement in this proposed 

AD. NOTES are for information 

purposes only and do not include 

required actions. The proposed actions 


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in the AD use cycles for the compliance 

time. 

We will change the note in the 

Compliance section of this proposed AD 

to an action and add the words ‘‘If the 

number of cycles is not known’’ at the 

beginning of that paragraph. 

FAA’s Determination and Requirements 

of This Proposed AD 

We have carefully reviewed the 

available data and determined that the 

unsafe condition referenced in this 

document exists or could develop on 

other products of the same type design; 

and we should take AD action to correct 

this unsafe condition. 

Certain changes described above 

expand the scope of the earlier NPRM. 

As a result, we have determined that it 

is necessary to reopen the comment 

period to provide additional 

opportunity for the public to comment 

on the proposed AD. 

The Supplemental NPRM 

Since we issued the earlier NPRM, we 

have expanded the Applicability section 

to include airplanes equipped with not 

only part numbers (P/Ns) 114–380041– 

11, 114–380041–13, or 114–380041–15 

MLG actuators but also airplanes 

equipped with FAA-approved 

equivalent P/Ns that have PMA by 

identicality to those referenced parts. 

Frisby P/N 1FA10043–3 has PMA by 

identicality to P/N 114–380041–15; 

therefore, it is considered an FAAapproved equivalent P/N and the 

proposed AD applies to airplanes with 

this part installed. We have also 

identified an overhauled MLG actuator 

part number and have included that part 

number in the Applicability section. 

This goes beyond the scope of what 

was originally proposed in the NPRM. 

Therefore, we are reopening the 

comment period and allowing the 

public the chance to comment on these 

additional actions. 

Costs of Compliance 

We estimate that this AD affects 300 

airplanes in the U.S. registry. 

The ultrasonic inspection includes 

the time allowed for removing and 

reinstalling the actuator. We estimate 

the following costs to do the 

inspections: 

Labor cost Parts cost Total cost 

per airplane 

Total cost 

on U.S. 

operators 

Visual Inspection: .5 work-hour × $80 per hour = $40 ................................... Not applicable .................................... $40 $12,000 

Ultrasonic Inspection: 6 work-hours × $80 per hour = $480 (If the mechanic 

does not remove the actuator for the ultrasonic inspection, the labor cost 

will be less).

Not applicable .................................... 480 144,000 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

inspections. We have no way of 

determining the number of airplanes 

that may need this replacement: 

Labor cost Parts cost Total cost 

per airplane 

6 work-hours × $80 per hour = $480 (If the mechanic removes the actuator for the 

ultrasonic inspection, then the labor cost will be less).

$4,600 per actuator .................................... $5,080 

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 

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) 647–5527) 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, Incorporation by reference, 

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. 


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§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new AD: 

Hawker Beechcraft Corporation: Docket No. 

FAA–2008–1312; Directorate Identifier 

2008–CE–065–AD. 

Comments Due Date 

(a) We must receive comments on this 

airworthiness directive (AD) action by 

September 30, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the airplane models 

and serial numbers listed below that are 

certificated in any category and equipped 

with a Hawker Beechcraft part number (P/N) 

114–380041–11 (or FAA-approved equivalent 

P/N), 114–380041–13 (or FAA-approved 

equivalent P/N), 114–380041–15 (or FAAapproved equivalent P/N), or 114–380041– 

15OVH main landing gear (MLG) actuator. 

For the purposes of this AD action the phrase 

‘‘or FAA-approved equivalent part number’’ 

in this AD refers to any PMA part that is 

approved by identicality to the referenced 

part. Frisby Airborne Hydraulic, Inc. (Frisby) 

P/N 1FA10043–3 has parts manufacturer 

approval (PMA) by identicality to P/N 114– 

380041–15; therefore, it is considered an 

FAA-approved equivalent P/N and the AD 

applies to airplanes with this part installed. 

Models Serial Nos. 

(1) 1900 ........ UA–3. 

(2) 1900C ..... UB–1 through UB–74, UC–1 

through UC–174, and UD–1 

through UD–6. 

(3) 1900D ..... UE–1 through UE–439. 

Unsafe Condition 

(d) This AD results from reports of leaking 

and cracked actuators. We are issuing this 

AD to detect and correct leaking and cracks 

in the MLG actuators, which could result in 

loss of hydraulic fluid. This condition could 

lead to an inability to extend or lock down 

the landing gear, which could result in a gear 

up landing or a gear collapse on landing. 

Compliance 

(e) To address this problem, you must do 

the following, unless already done: 

Note: The phrase ‘‘or FAA-approved 

equivalent part number’’ in this AD refers to 

any PMA part that is approved by 

identicality to the referenced part. 

Actions Compliance Procedures 

(1) Do a one-time visual inspection of the MLG 

actuator for cracks. 

Within the next 50 hours time–in–service after 

the effective date of this AD or within the 

next 30 days after the effective date of this 

AD, whichever occurs later. 

(i) For Hawker Beechcraft parts: Follow Hawker Beechcraft Mandatory Service Bulletin 

SB 32–3870, dated April 2008. 

(ii) For PMA by identicality: Either contact the 

aircraft certification office (ACO) using the 

contact information in paragraph (g)(2) of 

this AD for FAA-approved procedures provided by the PMA holder; or install Hawker 

Beechcraft parts and follow Hawker 

Beechcraft Mandatory Service Bulletin SB 

32–3870, dated April 2008, and follow any 

inspection required by this AD. 

(2) Do an initial ultrasonic inspection of the 

MLG actuator. 

Initially within the next 600 cycles after the effective date of this AD or within the next 3 

months after the effective date of this AD, 

whichever occurs first. 

(A) For Hawker Beechcraft parts: Follow 

Hawker Beechcraft Mandatory Service Bulletin SB 32–3870, dated April 2008. 

(i) For those airplanes with overhauled MLG 

actuators (with less than 1,200 cycles) that 

have records that prove an internal fluorescent penetrant inspection has been done, 

you may do the initial ultrasonic inspection 

within the next 600 cycles after the effective 

date of this AD or within the next 1,200 cycles since the last overhaul, whichever occurs later. 

(B) For PMA by identicality: Either contact the 

ACO using the contact information in paragraph (g)(2) of this AD for FAA-approved 

procedures provided by the PMA holder; or 

install Hawker Beechcraft parts and follow 

Hawker Beechcraft Mandatory Service Bulletin SB 32–3870, dated April 2008, and follow any inspection required by this AD. 

(ii) For those airplanes with MLG actuators 

with less than 8,000 cycles since new or 

MLG actuators that have records that prove 

the end caps are new (less than 8,000 cycles), you may do the initial ultrasonic inspection within the next 1,200 cycles after 

the effective date of this AD or upon accumulation of 8,000 cycles since the end caps 

were new, whichever occurs later. 

(3) For all airplanes, do repetitive ultrasonic inspections of the MLG actuator. Repetitively at intervals not to exceed every 

1,200 cycles since the last ultrasonic inspection. 

(i) For Hawker Beechcraft parts: Follow Hawker Beechcraft Mandatory Service Bulletin 

SB 32–3870, dated April 2008. 

(ii) For PMA by identicality: Either contact the 

ACO using the contact information in paragraph (g)(2) of this AD for FAA-approved 

procedures provided by the PMA holder; or 

install Hawker Beechcraft parts and follow 

Hawker Beechcraft Mandatory Service Bulletin SB 32–3870, dated April 2008, and follow any inspection required by this AD. 


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Actions Compliance Procedures 

(4) If cracks are found during any inspection required in paragraph (e)(1), (e)(2), and (e)(3) 

of this AD, replace the MLG actuator with 

one of the following: 

(i) MLG actuator P/N 114–380041–15 (or FAAapproved equivalent P/N) or 114–380041– 

15OVH that is new or has been inspected 

following paragraphs (e)(1), (e)(2), and (e)(3) 

of this AD and has been found to not have 

cracks; or 

(ii) An FAA-approved actuator. Installation of an 

MLG actuator P/N other than 114–380041– 

11 (or FAA-approved equivalent P/N), 114– 

380041–13 (or FAA-approved equivalent P/ 

N), 114–380041–15 (or FAA-approved equivalent P/N), or 114–380041–15OVH terminates the inspection requirements of paragraphs (e)(1), (e)(2), and (e)(3) of this AD. 

Before further flight after the inspection where 

the cracks are found. 

(A) For Hawker Beechcraft parts: Follow 

Hawker Beechcraft Mandatory Service Bulletin SB 32–3870, dated April 2008. 

(B) For PMA by identicality: Either contact the 

ACO using the contact information in paragraph (g)(2) of this AD for FAA–approved 

procedures provided by the PMA holder; or 

install Hawker Beechcraft parts and follow 

Hawker Beechcraft Mandatory Service Bulletin SB 32–3870, dated April 2008, and follow any inspection required by this AD. 

(5) Do not install any MLG actuator P/N 114– 

380041–11 (or FAA-approved equivalent P/ 

N) or 114–380041–13 (or FAA-approved 

equivalent P/N). 

As of the effective date of this AD. Not applicable. 

(f) If the number of cycles is unknown, 

calculate the compliance times of cycles in 

this AD by using hours time-in-service (TIS). 

Multiply the number of hours TIS on the 

MLG actuator by 4 to come up with the 

number of cycles. For the purposes of this 

AD: 

(1) 600 cycles equals 150 hours TIS; and 

(2) 1,200 cycles equals 300 hours TIS. 

(g) If cracks are found during any 

inspection required in paragraphs (e)(1), 

(e)(2), or (e)(3) of this AD, report the size and 

location of the cracks to the FAA within 10 

days after the cracks are found or within 10 

days after the effective date of this AD, 

whichever occurs later. 

(1) Send report to Don Ristow, Aerospace 

Engineer, Wichita ACO, 1801 Airport Road, 

Room 100, Wichita, Kansas 67209; e-mail: 

donald.ristow@faa.gov. 

(2) The Office of Management and Budget 

(OMB) approved the information collection 

requirements contained in this regulation 

under the provisions of the Paperwork 

Reduction Act of 1980 (44 U.S.C. 3501 et 

seq.) and assigned OMB Control Number 

2120–0056. 

Alternative Methods of Compliance 

(AMOCs) 

(h) The Manager, Wichita Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. Send information to ATTN: Don 

Ristow, Aerospace Engineer, 1801 Airport 

Road, Room 100, Wichita, Kansas 67209; 

telephone: (316) 946–4120; fax: (316) 946– 

4107. 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 

(i) To get copies of the service information 

referenced in this AD, contact Hawker 

Beechcraft Corporation, P.O. Box 85, Wichita, 

Kansas 67201–0085; telephone: (800) 429– 

5372 or (316) 676–3140; Internet: http:// 

pubs.hawkerbeechcraft.com. To view the AD 

docket, go to the U.S. Department of 

Transportation, Docket Operations, M–30, 

West Building Ground Floor, Room W12– 

140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, or on the Internet at 

http://dms.dot.gov. The docket number is 

Docket No. FAA–2008–1312; Directorate 

Identifier 2008–CE–065–AD. 

Issued in Kansas City, Missouri, on August 

20, 2009. 

Kim Smith, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. E9–20866 Filed 8–28–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0800; Directorate 

Identifier 2009–CE–041–AD] 

RIN 2120–AA64 

Airworthiness Directives; ScheibeFlugzeugbau GmbH Models BergfalkeIII, Bergfalke-II/55, SF 25C, and SF–26A 

Standard Gliders 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

The manufacturer has advised of receiving 

a report of looseness of the drive arm of the 

mechanical elevator trim tab, found during 

an annual inspection. This kind of damage is 

likely caused by penetrated humidity over 

the years. 

If left uncorrected, this condition could 

lead to the separation of the drive arm which 

could result in flutter of the elevator and 

possible loss of control of the aircraft. 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by October 15, 2009. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

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

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

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

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 


sroberts on DSKD5P82C1PROD with PROPOSALS