Airworthiness Directives; Hawker Beechcraft Corporation Models 1900, 1900C, and 1900D Airplanes, 44773-44777 [E9-20866]

Download as PDF 44773 Proposed Rules Federal Register Vol. 74, No. 167 Monday, August 31, 2009 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. 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 sroberts on DSKD5P82C1PROD with PROPOSALS 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: VerDate Nov<24>2008 16:24 Aug 28, 2009 Jkt 217001 • Federal eRulemaking Portal: Go to https://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: https:// 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 https:// 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 PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 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– E:\FR\FM\31AUP1.SGM 31AUP1 44774 Federal Register / Vol. 74, No. 167 / Monday, August 31, 2009 / Proposed Rules 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. sroberts on DSKD5P82C1PROD with PROPOSALS 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 FAA- VerDate Nov<24>2008 16:24 Aug 28, 2009 Jkt 217001 approved 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 PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 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 E:\FR\FM\31AUP1.SGM 31AUP1 44775 Federal Register / Vol. 74, No. 167 / Monday, August 31, 2009 / Proposed Rules 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: Total cost per airplane Labor cost Parts cost Visual Inspection: .5 work-hour × $80 per hour = $40 ................................... 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 .................................... Not applicable .................................... 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 $40 480 $12,000 144,000 determining the number of airplanes that may need this replacement: Labor cost Parts cost 6 work-hours × $80 per hour = $480 (If the mechanic removes the actuator for the ultrasonic inspection, then the labor cost will be less). Total cost per airplane $4,600 per actuator .................................... Authority for This Rulemaking sroberts on DSKD5P82C1PROD with PROPOSALS Total cost on U.S. operators 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 VerDate Nov<24>2008 16:24 Aug 28, 2009 Jkt 217001 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. $5,080 received, and other information on the Internet at https://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 Examining the AD Docket You may examine the AD docket that contains the proposed AD, the regulatory evaluation, any comments PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. E:\FR\FM\31AUP1.SGM 31AUP1 44776 § 39.13 Federal Register / Vol. 74, No. 167 / Monday, August 31, 2009 / Proposed Rules [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 ........ (2) 1900C ..... UA–3. UB–1 through UB–74, UC–1 through UC–174, and UD–1 through UD–6. UE–1 through UE–439. (3) 1900D ..... 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. (2) Do an initial ultrasonic inspection of the MLG actuator. sroberts on DSKD5P82C1PROD with PROPOSALS (3) For all airplanes, do repetitive ultrasonic inspections of the MLG actuator. VerDate Nov<24>2008 16:24 Aug 28, 2009 Jkt 217001 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. (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. (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. Repetitively at intervals not to exceed every 1,200 cycles since the last ultrasonic inspection. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 (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. (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. (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. E:\FR\FM\31AUP1.SGM 31AUP1 Federal Register / Vol. 74, No. 167 / Monday, August 31, 2009 / Proposed Rules 44777 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. (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). 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. As of the effective date of this AD. Not applicable. sroberts on DSKD5P82C1PROD with PROPOSALS (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– VerDate Nov<24>2008 16:24 Aug 28, 2009 Jkt 217001 5372 or (316) 676–3140; Internet: https:// 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 https://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 PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 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 https://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 https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through E:\FR\FM\31AUP1.SGM 31AUP1

Agencies

[Federal Register Volume 74, Number 167 (Monday, August 31, 2009)]
[Proposed Rules]
[Pages 44773-44777]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-20866]

========================================================================
Proposed Rules
Federal Register
________________________________________________________________________

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.

========================================================================

Federal Register / Vol. 74, No. 167 / Monday, August 31, 2009 /
Proposed Rules

[[Page 44773]]

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 https://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: https://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 https://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 Type-Certificate (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-

[[Page 44774]]

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 FAA-approved 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 ``FAA-
approved 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

[[Page 44775]]

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 FAA-approved 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:

------------------------------------------------------------------------
Total cost Total cost
Labor cost Parts cost per on U.S.
airplane operators
------------------------------------------------------------------------
Visual Inspection: .5 work- Not applicable. $40 $12,000
hour x $80 per hour = $40.
Ultrasonic Inspection: 6 work- Not applicable. 480 144,000
hours x $80 per hour = $480
(If the mechanic does not
remove the actuator for the
ultrasonic inspection, the
labor cost will be less).
------------------------------------------------------------------------

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:

------------------------------------------------------------------------
Total cost
Labor cost Parts cost per
airplane
------------------------------------------------------------------------
6 work-hours x $80 per hour = $480 $4,600 per actuator... $5,080
(If the mechanic removes the
actuator for the ultrasonic
inspection, then the labor cost
will be less).
------------------------------------------------------------------------

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 https://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.

[[Page 44776]]

Sec. 39.13 [Amended]

2. The FAA amends Sec. 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 FAA-approved 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 Within the next 50 hours time-in- (i) For Hawker Beechcraft parts:
of the MLG actuator for cracks. service after the effective date of Follow Hawker Beechcraft Mandatory
this AD or within the next 30 days Service Bulletin SB 32-3870, dated
after the effective date of this April 2008.
AD, whichever occurs later.
.................................... (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 Initially within the next 600 cycles (A) For Hawker Beechcraft parts:
inspection of the MLG actuator. after the effective date of this AD Follow Hawker Beechcraft Mandatory
or within the next 3 months after Service Bulletin SB 32-3870, dated
the effective date of this AD, April 2008.
whichever occurs first.
(i) For those airplanes with (B) For PMA by identicality: Either
overhauled MLG actuators (with less contact the ACO using the contact
than 1,200 cycles) that have information in paragraph (g)(2) of
records that prove an internal this AD for FAA-approved procedures
fluorescent penetrant inspection provided by the PMA holder; or
has been done, you may do the install Hawker Beechcraft parts and
initial ultrasonic inspection follow Hawker Beechcraft Mandatory
within the next 600 cycles after Service Bulletin SB 32-3870, dated
the effective date of this AD or April 2008, and follow any
within the next 1,200 cycles since inspection required by this AD.
the last overhaul, whichever occurs
later.
(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 Repetitively at intervals not to (i) For Hawker Beechcraft parts:
ultrasonic inspections of the MLG exceed every 1,200 cycles since the Follow Hawker Beechcraft Mandatory
actuator. last ultrasonic inspection. 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.

[[Page 44777]]

(4) If cracks are found during any Before further flight after the (A) For Hawker Beechcraft parts:
inspection required in paragraph inspection where the cracks are Follow Hawker Beechcraft Mandatory
(e)(1), (e)(2), and (e)(3) of this found. Service Bulletin SB 32-3870, dated
AD, replace the MLG actuator with April 2008.
one of the following: (B) For PMA by identicality: Either
(i) MLG actuator P/N 114-380041-15 contact the ACO using the contact
(or FAA-approved equivalent P/N) or information in paragraph (g)(2) of
114-380041-15OVH that is new or has this AD for FAA-approved procedures
been inspected following paragraphs provided by the PMA holder; or
(e)(1), (e)(2), and (e)(3) of this install Hawker Beechcraft parts and
AD and has been found to not have follow Hawker Beechcraft Mandatory
cracks; or Service Bulletin SB 32-3870, dated
(ii) An FAA-approved actuator. April 2008, and follow any
Installation of an MLG actuator P/N inspection required by this AD.
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.
(5) Do not install any MLG actuator As of the effective date of this AD. Not applicable.
P/N 114-380041-11 (or FAA-approved
equivalent P/N) or 114-380041-13
(or FAA-approved equivalent P/N).
----------------------------------------------------------------------------------------------------------------

(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: https://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 https://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

This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.