Airworthiness Directives; Hawker Beechcraft Corporation Model 1900, 1900C, and 1900D Airplanes, 56710-56713 [E9-26199]

Download as PDF 56710 Federal Register / Vol. 74, No. 211 / Tuesday, November 3, 2009 / Rules and Regulations 7. Inadvertent deployment of the inflatable lap belt, during the most critical part of the flight, must be shown to either not cause a hazard to the airplane or be extremely improbable. 8. The inflatable lap belt must be shown to not impede rapid egress of occupants 10 seconds after its deployment. 9. The system must be protected from lightning and HIRF. The threats specified in existing regulations regarding lightning, § 25.1316, and HIRF, § 25.1317, are incorporated by reference for the purpose of measuring lightning and HIRF protection. For the purposes of complying with HIRF requirements, the inflatable lap-belt system is considered a ‘‘critical system’’ if its deployment could have a hazardous effect on the airplane; otherwise it is considered an ‘‘essential’’ system. 10. The inflatable lap belt must function properly after loss of normal aircraft electrical power, and after a transverse separation of the fuselage at the most critical location. A separation at the location of the lap belt does not have to be considered. 11. The inflatable lap belt must be shown to not release hazardous quantities of gas or particulate matter into the cabin. 12. The inflatable lap-belt installation must be protected from the effects of fire such that no hazard to occupants will result. 13. A means must be available for a crewmember to verify the integrity of the inflatable-lap-belt-activation system prior to each flight or it must be demonstrated to reliably operate between inspection intervals. 14. The inflatable material may not have an average burn rate of greater than 2.5 inches per minute when tested using the horizontal-flammability test as defined in 14 CFR part 25, appendix F, part I, paragraph (b)(5). Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–26356 Filed 11–2–09; 8:45 am] dcolon on DSK2BSOYB1PROD with RULES BILLING CODE 4910–13–P VerDate Nov<24>2008 15:13 Nov 02, 2009 Jkt 220001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–1312; Directorate Identifier 2008–CE–065–AD; Amendment 39–16072; AD 2009–23–01] RIN 2120–AA64 Airworthiness Directives; Hawker Beechcraft Corporation Model 1900, 1900C, and 1900D Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. We are adopting a new airworthiness directive (AD) for certain Hawker Beechcraft Corporation Models 1900, 1900C, and 1900D airplanes. This AD requires 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. 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. DATES: This AD becomes effective on December 8, 2009. On December 8, 2009, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD. ADDRESSES: To get the service information identified 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 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:// www.regulations.gov. The docket number is FAA–2008–1312; Directorate Identifier 2008–CE–065–AD. 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: SUMMARY: PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 Discussion On August 20, 2009, 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 supplemental notice of proposed rulemaking (NPRM) on August 31, 2009 (74 FR 44773). 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 comment received on the proposal and FAA’s response to the comment: Comment Issue: Superseding Previous ADs Hawker Beechcraft Corporation requests that with this AD action we supersede AD 99–04–08 and AD 97–26– 15, which affect earlier configurations of part number 114–380041 MLG actuator. They believe that one AD correcting all of the unsafe conditions concerned with the MLG actuator would eliminate confusion concerning which AD to comply with. The FAA disagrees. We did consider supersedure of the previous two ADs, AD 99–04–08 and AD 97–26–15. The previous two ADs and this new AD action each address different unsafe conditions on the MLG actuators. AD 99–04–08 concerns lubrication and replacement of the rod end, and AD 97– 26–15 concerns replacement of the actuator head end cap. This new AD action concerns replacement of the rod end cap. AD 99–04–08 uses a prorated time of compliance starting with actuators that have accumulated 6,000 hours time-in-service and may still apply to low usage aircraft or aircraft that have been in storage. This current AD action specifies compliance based on actuator cycles. The only common feature in the three ADs is that the actuators were manufactured by Frisby Airborne Hydraulic, Inc. Based on the differences in the two previous ADs and in this new AD, we determined that combining the three into a single AD would confuse the unsafe conditions, rather than simplify them. If combined into one AD, each unsafe condition would still have different inspections, different E:\FR\FM\03NOR1.SGM 03NOR1 Federal Register / Vol. 74, No. 211 / Tuesday, November 3, 2009 / Rules and Regulations replacements, and different compliance times. To incorporate those differences into a single AD would create a complicated AD to understand. By keeping the AD actions separate, the corrective actions for each unsafe condition can be complied with individually. For these reasons, we decided a new AD action would be appropriate. We will not change the final rule AD action based on this comment. • Do not add any additional burden upon the public than was already proposed in the NPRM. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed except for minor editorial corrections. We have determined that these minor corrections: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and 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.). Total cost on U.S. operators $40 480 $12,000 144,000 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 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.). $4,600 per actuator .................................. 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 AD. dcolon on DSK2BSOYB1PROD with RULES Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: VerDate Nov<24>2008 15:13 Nov 02, 2009 Jkt 220001 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 summary of the costs to comply with this AD (and other information as included in the Regulatory Evaluation) and placed it in the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under ADDRESSES. Include ‘‘Docket No. FAA–2008–1312; Directorate Identifier 2008–CE–065– AD’’ in your request. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: ■ PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 56711 Total cost per airplane $5,080 Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. FAA amends § 39.13 by adding a new AD to read as follows: ■ 2009–23–01 Hawker Beechcraft Corporation: Amendment 39–16072; Docket No. FAA–2008–1312; Directorate Identifier 2008–CE–065–AD. Effective Date (a) This AD becomes effective on December 8, 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. E:\FR\FM\03NOR1.SGM 03NOR1 56712 Federal Register / Vol. 74, No. 211 / Tuesday, November 3, 2009 / Rules and Regulations Models Serial Nos. (1) 1900 ..................................................... (2) 1900C ................................................... (3) 1900D ................................................... UA–3. UB–1 through UB–74, UC–1 through UC–174, and UD–1 through UD–6. 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 December 8, 2009 (the effective date of this AD) or within the next 30 days after December 8, 2009 (the effective date of this AD), whichever occurs later. (2) Do an initial ultrasonic inspection of the MLG actuator. Initially within the next 600 cycles after December 8, 2009 (the effective date of this AD) or within the next 3 months after December 8, 2009 (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 December 8, 2009 (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 December 8, 2009 (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. (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)(1) 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)(1) 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. dcolon on DSK2BSOYB1PROD with RULES (3) For all airplanes, do repetitive ultrasonic inspections of the MLG actuator. VerDate Nov<24>2008 15:13 Nov 02, 2009 Jkt 220001 PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 (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)(1) 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\03NOR1.SGM 03NOR1 Federal Register / Vol. 74, No. 211 / Tuesday, November 3, 2009 / Rules and Regulations 56713 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 FAA-approved 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)(1) 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 December 8, 2009 (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 December 8, 2009 (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. dcolon on DSK2BSOYB1PROD with RULES Actions by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified 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. (3) You may review copies of the service information incorporated by reference for this AD at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the Central Region, call (816) 329–3768. (4) You may also review copies of the service information incorporated by reference for this AD at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: http://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. DEPARTMENT OF TRANSPORTATION 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. Issued in Kansas City, Missouri, on October 23, 2009. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–26199 Filed 11–2–09; 8:45 am] BILLING CODE 4910–13–P 15:13 Nov 02, 2009 Jkt 220001 PO 00000 14 CFR Part 39 [Docket No. FAA–2009–0999; Directorate Identifier 2009–NM–155–AD; Amendment 39–16069; AD 2008–04–19 R1] RIN 2120–AA64 Airworthiness Directives; ATR Model ATR42 and ATR72 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above that would revise an existing AD. This 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: Subsequent to accidents involving Fuel Tank System explosions in flight * * * and on ground, * * * Special Federal Aviation Regulation 88 (SFAR88) * * * required a safety review of the aircraft Fuel Tank System * * *. * * * * * Fuel Airworthiness Limitations are items arising from a systems safety analysis that have been shown to have failure mode(s) associated with an ‘unsafe condition’ * * *. These are identified in Failure Conditions for which an unacceptable probability of ignition risk could exist if specific tasks and/or Material Incorporated by Reference (i) You must use Hawker Beechcraft Mandatory Service Bulletin SB 32–3870, dated April 2008, to do the actions required VerDate Nov<24>2008 Federal Aviation Administration Frm 00021 Fmt 4700 Sfmt 4700 E:\FR\FM\03NOR1.SGM 03NOR1

Agencies

[Federal Register Volume 74, Number 211 (Tuesday, November 3, 2009)]
[Rules and Regulations]
[Pages 56710-56713]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-26199]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-1312; Directorate Identifier 2008-CE-065-AD; 
Amendment 39-16072; AD 2009-23-01]
RIN 2120-AA64


Airworthiness Directives; Hawker Beechcraft Corporation Model 
1900, 1900C, and 1900D Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Hawker Beechcraft Corporation Models 1900, 1900C, and 1900D airplanes. 
This AD requires 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. 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.

DATES: This AD becomes effective on December 8, 2009.
    On December 8, 2009, the Director of the Federal Register approved 
the incorporation by reference of certain publications listed in this 
AD.

ADDRESSES: To get the service information identified 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 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://www.regulations.gov. The docket number is FAA-2008-1312; 
Directorate Identifier 2008-CE-065-AD.

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: 

Discussion

    On August 20, 2009, 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 supplemental notice of proposed rulemaking (NPRM) on 
August 31, 2009 (74 FR 44773). 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 comment received on the proposal 
and FAA's response to the comment:

Comment Issue: Superseding Previous ADs

    Hawker Beechcraft Corporation requests that with this AD action we 
supersede AD 99-04-08 and AD 97-26-15, which affect earlier 
configurations of part number 114-380041 MLG actuator. They believe 
that one AD correcting all of the unsafe conditions concerned with the 
MLG actuator would eliminate confusion concerning which AD to comply 
with.
    The FAA disagrees. We did consider supersedure of the previous two 
ADs, AD 99-04-08 and AD 97-26-15. The previous two ADs and this new AD 
action each address different unsafe conditions on the MLG actuators. 
AD 99-04-08 concerns lubrication and replacement of the rod end, and AD 
97-26-15 concerns replacement of the actuator head end cap. This new AD 
action concerns replacement of the rod end cap. AD 99-04-08 uses a 
prorated time of compliance starting with actuators that have 
accumulated 6,000 hours time-in-service and may still apply to low 
usage aircraft or aircraft that have been in storage. This current AD 
action specifies compliance based on actuator cycles. The only common 
feature in the three ADs is that the actuators were manufactured by 
Frisby Airborne Hydraulic, Inc.
    Based on the differences in the two previous ADs and in this new 
AD, we determined that combining the three into a single AD would 
confuse the unsafe conditions, rather than simplify them. If combined 
into one AD, each unsafe condition would still have different 
inspections, different

[[Page 56711]]

replacements, and different compliance times. To incorporate those 
differences into a single AD would create a complicated AD to 
understand. By keeping the AD actions separate, the corrective actions 
for each unsafe condition can be complied with individually. For these 
reasons, we decided a new AD action would be appropriate.
    We will not change the final rule AD action based on this comment.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD as proposed 
except for minor editorial corrections. We have determined that these 
minor corrections:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

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   Total cost on
                  Labor cost                               Parts cost                airplane     U.S. operators
----------------------------------------------------------------------------------------------------------------
Visual Inspection: .5 work-hour x $80 per hour  Not applicable..................             $40         $12,000
 = $40.
Ultrasonic Inspection: 6 work-hours x $80 per   Not applicable..................             480         144,000
 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 per
            Labor cost                   Parts cost          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 AD.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under 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 summary of the costs to comply with this AD (and 
other information as included in the Regulatory Evaluation) and placed 
it in the AD Docket. You may get a copy of this summary by sending a 
request to us at the address listed under ADDRESSES. Include ``Docket 
No. FAA-2008-1312; Directorate Identifier 2008-CE-065-AD'' in your 
request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends part 39 of the Federal 
Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

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


Sec.  39.13  [Amended]

0
2. FAA amends Sec.  39.13 by adding a new AD to read as follows:

2009-23-01 Hawker Beechcraft Corporation: Amendment 39-16072; Docket 
No. FAA-2008-1312; Directorate Identifier 2008-CE-065-AD.

Effective Date

    (a) This AD becomes effective on December 8, 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.

[[Page 56712]]



----------------------------------------------------------------------------------------------------------------
                           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    Within the next 50 hours    (i) For Hawker
 inspection of the MLG       time-in-service after       Beechcraft
 actuator for cracks.        December 8, 2009 (the       parts: Follow
                             effective date of this      Hawker
                             AD) or within the next 30   Beechcraft
                             days after December 8,      Mandatory
                             2009 (the effective date    Service
                             of this AD), whichever      Bulletin SB 32-
                             occurs later.               3870, dated
                                                         April 2008.
                                                        (ii) For PMA by
                                                         identicality:
                                                         Either contact
                                                         the aircraft
                                                         certification
                                                         office (ACO)
                                                         using the
                                                         contact
                                                         information in
                                                         paragraph
                                                         (g)(1) 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           Initially within the next   (A) For Hawker
 ultrasonic inspection of    600 cycles after December   Beechcraft
 the MLG actuator.           8, 2009 (the effective      parts: Follow
                             date of this AD) or         Hawker
                             within the next 3 months    Beechcraft
                             after December 8, 2009      Mandatory
                             (the effective date of      Service
                             this AD), whichever         Bulletin SB 32-
                             occurs first.               3870, dated
                            (i) For those airplanes      April 2008.
                             with overhauled MLG        (B) For PMA by
                             actuators (with less than   identicality:
                             1,200 cycles) that have     Either contact
                             records that prove an       the ACO using
                             internal fluorescent        the contact
                             penetrant inspection has    information in
                             been done, you may do the   paragraph
                             initial ultrasonic          (g)(1) of this
                             inspection within the       AD for FAA-
                             next 600 cycles after       approved
                             December 8, 2009 (the       procedures
                             effective date of this      provided by the
                             AD) or within the next      PMA holder; or
                             1,200 cycles since the      install Hawker
                             last overhaul, whichever    Beechcraft
                             occurs later.               parts and
                            (ii) For those airplanes     follow Hawker
                             with MLG actuators with     Beechcraft
                             less than 8,000 cycles      Mandatory
                             since new or MLG            Service
                             actuators that have         Bulletin SB 32-
                             records that prove the      3870, dated
                             end caps are new (less      April 2008, and
                             than 8,000 cycles), you     follow any
                             may do the initial          inspection
                             ultrasonic inspection       required by
                             within the next 1,200       this AD.
                             cycles after December 8,
                             2009 (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   Repetitively at intervals   (i) For Hawker
 repetitive ultrasonic       not to exceed every 1,200   Beechcraft
 inspections of the MLG      cycles since the last       parts: Follow
 actuator.                   ultrasonic inspection.      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)(1) 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 56713]]

 
(4) If cracks are found     Before further flight       (A) For Hawker
 during any inspection       after the inspection        Beechcraft
 required in paragraph       where the cracks are        parts: Follow
 (e)(1), (e)(2), and         found.                      Hawker
 (e)(3) of this AD,                                      Beechcraft
 replace the MLG actuator                                Mandatory
 with one of the                                         Service
 following:                                              Bulletin SB 32-
(i) MLG actuator P/N 114-                                3870, dated
 380041-15 (or FAA-                                      April 2008.
 approved equivalent P/N)                               (B) For PMA by
 or 114-380041-15OVH that                                identicality:
 is new or has been                                      Either contact
 inspected following                                     the ACO using
 paragraphs (e)(1),                                      the contact
 (e)(2), and (e)(3) of                                   information in
 this AD and has been                                    paragraph
 found to not have cracks;                               (g)(1) of this
 or                                                      AD for FAA-
(ii) An FAA-approved                                     approved
 actuator. Installation of                               procedures
 an MLG actuator P/N other                               provided by the
 than 114-380041-11 (or                                  PMA holder; or
 FAA-approved equivalent P/                              install Hawker
 N), 114-380041-13 (or FAA-                              Beechcraft
 approved equivalent P/N),                               parts and
 114-380041-15 (or FAA-                                  follow Hawker
 approved equivalent P/N),                               Beechcraft
 or 114-380041-15OVH                                     Mandatory
 terminates the inspection                               Service
 requirements of                                         Bulletin SB 32-
 paragraphs (e)(1),                                      3870, dated
 (e)(2), and (e)(3) of                                   April 2008, and
 this AD.                                                follow any
                                                         inspection
                                                         required by
                                                         this AD.
(5) Do not install any MLG  As of December 8, 2009      Not applicable.
 actuator P/N 114-380041-    (the effective date of
 11 (or FAA-approved         this AD).
 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 December 8, 2009 (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.

Material Incorporated by Reference

    (i) You must use Hawker Beechcraft Mandatory Service Bulletin SB 
32-3870, dated April 2008, to do the actions required by this AD, 
unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified 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.
    (3) You may review copies of the service information 
incorporated by reference for this AD at the FAA, Central Region, 
Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 
64106. For information on the availability of this material at the 
Central Region, call (816) 329-3768.
    (4) You may also review copies of the service information 
incorporated by reference for this AD at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Kansas City, Missouri, on October 23, 2009.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E9-26199 Filed 11-2-09; 8:45 am]
BILLING CODE 4910-13-P