Airworthiness Directives; Hawker Beechcraft Corporation Model 390 Airplanes, 44142-44145 [E8-17329]

Download as PDF 44142 Federal Register / Vol. 73, No. 147 / Wednesday, July 30, 2008 / Rules and Regulations Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: I 2008–15–04 Bell Helicopter Textron Canada: Amendment 39–15616. Docket No. FAA–2007–0177; Directorate Identifier 2007–SW–19–AD. Effective Date (a) This airworthiness directive (AD) becomes effective on September 3, 2008. Other Affected ADs (b) None. Applicability (c) This AD applies to Model 430 helicopters, serial numbers 49001 through 49122, certificated in any category. rwilkins on PROD1PC63 with RULES Reason (d) The mandatory continuing airworthiness information (MCAI) states: ‘‘It has been determined that the existing rigging procedures for the tail rotor pitch change mechanism have to be changed due to possibility of parts interference.’’ This ‘‘possibility of parts interference’’ occurs because the cumulative effect of the tolerances on the various parts may result in the total assemblage outboard of the counterweight bellcrank being out of tolerance and the tail rotor yoke may contact the nut, part number (P/N ) 222–012–731– 001, before contacting the flapping stop. Further, the manufacturer has indicated that the tail rotor counterweight bellcranks may be misaligned, resulting in higher tail rotor pedal forces and higher pilot workload after failure of the #1 hydraulic system. Both the parts interference and the higher pedal forces constitute unsafe conditions. This AD requires actions that are intended to address these unsafe conditions. Actions and Compliance (e) Within the next 150 hours time-inservice (TIS) or at the next annual inspection, whichever occurs first, unless already accomplished, do the following: (1) Adjust the rigging of the tail rotor pitch change mechanism in accordance with the Accomplishment Instructions, paragraphs 1 and 2, in Bell Helicopter Textron Alert Service Bulletin 430–07–39, dated January 9, 2007 (ASB). (2) If either at full left pedal position or full right pedal position a gap exists between the tail rotor yoke and the flapping stop, replace the tail rotor yoke with an airworthy tail rotor yoke. (3) If no gap exists between the tail rotor yoke and the flapping stop at either full right or full left pedal position, measure the gap between the tail rotor yoke and nut, P/N 222– 012–731–001, adjust the tail rotor pitch change mechanism, and adjust the tail rotor pedal forces in accordance with the Accomplishment Instruction, paragraphs 4 through 6 of the ASB. hours TIS or at the next annual inspection, whichever occurs first, instead of ‘‘at the next 150 hour or annual inspection, but no later than 31 December 2007.’’ DEPARTMENT OF TRANSPORTATION Other Information 14 CFR Part 39 (g) Alternative Methods of Compliance (AMOCs): The Manager, Safety Management Group, FAA, ATTN: Tyrone Millard, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Rotorcraft Standards Staff, Fort Worth, Texas 76193–0111, telephone (817) 222–5439, fax (817) 222–5961 has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. [Docket No. FAA–2008–0353; Directorate Identifier 2007–CE–101–AD; Amendment 39–15620; AD 2008–16–02] Related Information (h) MCAI Transport Canada Airworthiness Directive No. CF–2007–04, dated April 5, 2007, contains related information. Air Transport Association of America (ATA) Tracking Code (i) ATA Code JASC 6720: Tail Rotor Control System, Tail Rotor Pitch Change. Material Incorporated by Reference (j) You must use the specified portions of Bell Helicopter Textron Alert Service Bulletin No. 430–07–39, dated January 9, 2007, to do the actions required. (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 Bell Helicopter Textron Canada, 12,800 Rue de l’Avenir, Mirabel, Quebec J7J1R4, telephone (450) 437–2862 or (800) 363–8023, fax (450) 433–0272. (3) You may review copies at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Fort Worth, Texas, 76193; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: https://www.archives.gov/federal-register/ cfr/ibr-locations.html. Issued in Fort Worth, Texas, on July 9, 2008. Mark R. Schilling, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E8–17275 Filed 7–29–08; 8:45 am] BILLING CODE 4910–13–P Differences Between This AD and the MCAI (f) This AD differs from the MCAI in that it requires compliance within the next 150 VerDate Aug<31>2005 16:51 Jul 29, 2008 Jkt 214001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Federal Aviation Administration RIN 2120–AA64 Airworthiness Directives; Hawker Beechcraft Corporation Model 390 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for certain Hawker Beechcraft Corporation Model 390 airplanes. This AD requires you to repetitively do a post-flight check (owner/operator holding at least a private pilot certificate checking for residual heat in the angle-of-attack (AOA) probes or an appropriately-rated mechanic doing a maintenance manual operational test of the heat of the AOA probes) after every flight and replace or modify (upload software) the stall warning AOA transmitters. This AD results from reports of the potential for unannunciated loss of the heating function in the left-hand (LH) and righthand (RH) stall warning AOA transmitters of Model 390 airplanes. We are issuing this AD to correct potentially inadequate stall warning with loss of stick pusher function. DATES: This AD becomes effective on September 3, 2008. On September 3, 2008, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD. ADDRESSES: For service information identified in this AD, contact Hawker Beechcraft Corporation, 9709 East Central, Wichita, Kansas 67291; telephone: (800) 429–5372 or (316) 676– 3140. 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 https:// www.regulations.gov. The docket number is FAA–2008–0353; Directorate Identifier 2007–CE–101–AD. FOR FURTHER INFORMATION CONTACT: Philip Petty, Aerospace Engineer, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946– 4139; fax: (316) 946–4107. E:\FR\FM\30JYR1.SGM 30JYR1 Federal Register / Vol. 73, No. 147 / Wednesday, July 30, 2008 / Rules and Regulations SUPPLEMENTARY INFORMATION: Discussion On March 19, 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 Model 390 airplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on March 25, 2008 (73 FR 15678). The NPRM proposed to require you to repetitively do a post-flight check (owner/operator holding at least a private pilot certificate checking for residual heat in the angle-of-attack (AOA) probes or an appropriately-rated mechanic doing a maintenance manual operational test of the heat of the AOA probes) after every flight and replace or modify (upload software) the stall warning AOA transmitters. Comments We provided the public the opportunity to participate in developing this AD. We received no comments on the proposal or on the determination of the cost to the public. 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 152 airplanes in the U.S. registry. We estimate the following costs to incorporate and remove the temporary change to the AFM. Labor cost Parts cost 0.5 work-hour × $80 per hour = $40 ......................................................................... Total cost per airplane Not Applicable ......................................... We estimate that the post-flight residual heat check requires about 3 minutes to do. We estimate the following costs to do 10 of the post- flight residual heat checks. We have no way of determining the number of airplanes that would have this postflight residual heat check, or how many $40 times this will need to be performed before the terminating action is done: Labor cost to do 10 post-flight residual heat checks Parts cost 0.5 work-hour × $80 per hour = $40 ......................................................................... Total cost per airplane Not Applicable ......................................... We estimate the following costs to do the maintenance manual operational test of the heat of the AOA probes. We have no way of determining the number of airplanes that would have this operational test, or how many times this Parts cost 0.5 work-hour × $80 per hour = $40 ......................................................................... Not Applicable ......................................... We estimate the following costs to do any upload of software to the AOA transmitters. We have no way of Parts cost 4 work-hours × $80 per hour = $320 ........................................................................ Not Applicable ......................................... Parts cost 2 work-hours × $80 per hour = $160 ........................................................................ $18,600 .................................................... Title 49 of the United States Code specifies the FAA’s authority to issue VerDate Aug<31>2005 16:51 Jul 29, 2008 Jkt 214001 $40 Total cost per airplane $320 determining the number of airplanes that would have this replacement: Labor cost Authority for This Rulemaking Total cost per airplane determining the number of airplanes that would have this modification: Labor cost We estimate the following costs to do any replacement of 2 stall warning AOA transmitters. We have no way of $40 will need to be performed before the terminating action is done: Labor cost rwilkins on PROD1PC63 with RULES 44143 rules on aviation safety. Subtitle I, Section 106 describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 Total cost per airplane $18,760 detail the scope of the agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, E:\FR\FM\30JYR1.SGM 30JYR1 44144 Federal Register / Vol. 73, No. 147 / Wednesday, July 30, 2008 / Rules and Regulations 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–2008–0353; Directorate Identifier 2007–CE–101– 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: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. Within 15 hours time-in-service (TIS) after September 3, 2008 (the effective date of the AD) or within 30 days after September 3, 2008 (the effective date of the AD), whichever occurs first. Begin the post-flight checks within 15 hours TIS after September 3, 2008 (the effective date of the AD) or within 30 days after September 3, 2008 (the effective date of the AD), whichever occurs first. Completion of paragraph (e)(3)(i) or (e)(3)(ii) of this AD terminates the required repetitive post-flight checks of this AD. Replace any AOA probe that fails the operational test before further flight. [Amended] I 2. FAA amends § 39.13 by adding the following new AD: 2008–16–02 Hawker Beechcraft Corporation: Amendment 39–15620; Docket No. FAA–2008–0353; Directorate Identifier 2007–CE–101–AD. Effective Date (a) This AD becomes effective on September 3, 2008. Affected ADs (b) None. Applicability (c) This AD applies to Model 390 airplanes, serial numbers RB–4 through RB–204, that are certificated in any category. Unsafe Condition (d) This AD results from reports of the potential for unannunciated loss of the heating function in the left-hand (LH) and right-hand (RH) stall warning angle-of-attack (AOA) transmitters of Model 390 airplanes. We are issuing this AD to correct potentially inadequate stall warning with loss of stick pusher function. Compliance (e) To address this problem, you must do the following, unless already done: Compliance (1) Incorporate Raytheon Aircraft Company Temporary Change to the FAA Approved Airplane Flight Manual P/N 390–590001– 0003CTC7, issued: March 15, 2007, into the airplane flight manual (AFM). (2) After every flight do the following: (i) Do a post-flight check for residual heat in the AOA probes. CAUTION: TO PREVENT POSSIBLE BURNS, USE EXTREME CAUTION TOUCHING HEATED AREAS. TO CHECK HEATING AND AVOID BURNS, HOLD HAND NEAR HEATED AREA OR MOVE HAND GRADUALLY FROM AMBIENT AREA TOWARD HEATED AREA UNTIL WARMTH CAN BE FELT. If you do not feel heat in the AOA probes, then do paragraph (e)(2)(ii) of this AD; or (ii) Do a post-flight maintenance manual operational test of the heat of the AOA probes. If the AOA probe fails the operational test, replace the AOA probe. rwilkins on PROD1PC63 with RULES Actions § 39.13 VerDate Aug<31>2005 16:51 Jul 29, 2008 Jkt 214001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 Procedures Not Applicable. (A) For the post-flight check for residual heat in the AOA probes: Follow Raytheon Aircraft Company Temporary Change to the FAA Approved Airplane Flight Manual Temporary Change P/N 390–590001– 0003CTC7, issued: March 15, 2007. The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7) may do this post-flight check required by paragraph (e)(2)(i) of this AD. Make an entry into the aircraft records showing compliance with this AD following section 43.9 of the Federal Aviation Regulations (14 CFR 43.9). (B) For the post-flight maintenance manual operational test of the heat of the AOA probes: Follow Raytheon Aircraft Company Temporary Change to the FAA Approved Airplane Flight Manual Temporary Change P/N 390–590001–0003CTC7, issued: March 15, 2007, and Hawker Beechcraft Mandatory Service Bulletin No. SB 27– 3787, issued: May 2007. The maintenance manual operational test must be done by an appropriately rated mechanic. (C) For AOA probe replacement: Follow Hawker Beechcraft Mandatory Service Bulletin No. SB 27–3787, issued: May 2007. E:\FR\FM\30JYR1.SGM 30JYR1 Federal Register / Vol. 73, No. 147 / Wednesday, July 30, 2008 / Rules and Regulations 44145 Actions Compliance Procedures (3) Replace or modify (upload software) the stall warning AOA transmitters by doing one of the following: (i) Upload new software Kit No. 123–3436 (Field Software Upload SLZ8060–3,–4) to the AOA transmitters; or (ii) Replace any part number (P/N) SLZ8060–3 and/or P/N SLZ8060–4 AOA transmitters with new P/N SLZ8060–5 AOA transmitters. (4) Remove Raytheon Aircraft Company Temporary Change to the FAA Approved Airplane Flight Manual P/N 390–590001–0003CTC7, issued: March 15, 2007, from the AFM. (5) Do not install any P/N SLZ8060–3 or P/N SLZ8060–4 AOA transmitter that does not have the new upgraded software required by paragraph (e)(3)(i) of this AD. Within 250 hours TIS after September 3, 2008 (the effective date of this AD) or within 12 months after September 3, 2008 (the effective date of this AD), whichever occurs first. Completion of either paragraph (e)(3)(i) or (e)(3)(ii) of this AD terminates the required repetitive post-flight check of this AD. Follow Hawker Beechcraft Mandatory Service Bulletin No. SB 27–3787, issued: May 2007. Before further flight after doing the actions required by paragraph (e)(3)(i) or paragraph (e)(3)(ii) of this AD. Follow Hawker Beechcraft Mandatory Service Bulletin No. SB 27–3787, issued: May 2007. As of September 3, 2008 (the effective date of this AD). Not Applicable. DEPARTMENT OF TRANSPORTATION Material Incorporated by Reference (g) You must use Raytheon Aircraft Company Temporary Change to the FAA Approved Airplane Flight Manual P/N 390– 590001–0003CTC7, issued: March 15, 2007, and Hawker Beechcraft Mandatory Service Bulletin No. SB 27–3787, issued: May 2007, 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, 9709 East Central, Wichita, Kansas 67291; telephone: (800) 429–5372 or (316) 676–3140. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. rwilkins on PROD1PC63 with RULES Alternative Methods of Compliance (AMOCs) (f) 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: Philip Petty, Aerospace Engineer, Wichita ACO, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946–4139; 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. AGENCY: Issued in Kansas City, Missouri, on July 23, 2008. John Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–17329 Filed 7–29–08; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 16:51 Jul 29, 2008 Jkt 214001 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0822; Directorate Identifier 2008–CE–045–AD; Amendment 39–15621; AD 2008–16–03] RIN 2120–AA64 Airworthiness Directives; Pilatus Aircraft Ltd. Model PC–6 Series Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: This Airworthiness Directive (AD) is prompted due to the discovery of cracked or broken leaf springs P/N 6232.0175.01 installed in the overhead flap-operating mechanism of some PC–6 aircraft. A broken leaf spring could lead to an uncommanded flap retraction which could lead to hazardous situations and subsequent loss of control of the aircraft. This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective August 11, 2008. On August 11, 2008, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD. PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 We must receive comments on this AD by August 29, 2008. 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 Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone (800) 647– 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4059; fax: (816) 329–4090. SUPPLEMENTARY INFORMATION: Discussion The Federal Office of Civil Aviation (FOCA), which is the aviation authority for Switzerland, has issued FOCA EMERGENCY AD HB–2008–242 E:\FR\FM\30JYR1.SGM 30JYR1

Agencies

[Federal Register Volume 73, Number 147 (Wednesday, July 30, 2008)]
[Rules and Regulations]
[Pages 44142-44145]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-17329]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0353; Directorate Identifier 2007-CE-101-AD;
Amendment 39-15620; AD 2008-16-02]
RIN 2120-AA64

Airworthiness Directives; Hawker Beechcraft Corporation Model 390
Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Hawker Beechcraft Corporation Model 390 airplanes. This AD requires you
to repetitively do a post-flight check (owner/operator holding at least
a private pilot certificate checking for residual heat in the angle-of-
attack (AOA) probes or an appropriately-rated mechanic doing a
maintenance manual operational test of the heat of the AOA probes)
after every flight and replace or modify (upload software) the stall
warning AOA transmitters. This AD results from reports of the potential
for unannunciated loss of the heating function in the left-hand (LH)
and right-hand (RH) stall warning AOA transmitters of Model 390
airplanes. We are issuing this AD to correct potentially inadequate
stall warning with loss of stick pusher function.

DATES: This AD becomes effective on September 3, 2008.
On September 3, 2008, the Director of the Federal Register approved
the incorporation by reference of certain publications listed in this
AD.

ADDRESSES: For service information identified in this AD, contact
Hawker Beechcraft Corporation, 9709 East Central, Wichita, Kansas
67291; telephone: (800) 429-5372 or (316) 676-3140.
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
https://www.regulations.gov. The docket number is FAA-2008-0353;
Directorate Identifier 2007-CE-101-AD.

FOR FURTHER INFORMATION CONTACT: Philip Petty, Aerospace Engineer,
Wichita Aircraft Certification Office, 1801 Airport Road, Room 100,
Wichita, Kansas 67209; telephone: (316) 946-4139; fax: (316) 946-4107.

[[Page 44143]]

SUPPLEMENTARY INFORMATION:

Discussion

On March 19, 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 Model 390
airplanes. This proposal was published in the Federal Register as a
notice of proposed rulemaking (NPRM) on March 25, 2008 (73 FR 15678).
The NPRM proposed to require you to repetitively do a post-flight check
(owner/operator holding at least a private pilot certificate checking
for residual heat in the angle-of-attack (AOA) probes or an
appropriately-rated mechanic doing a maintenance manual operational
test of the heat of the AOA probes) after every flight and replace or
modify (upload software) the stall warning AOA transmitters.

Comments

We provided the public the opportunity to participate in developing
this AD. We received no comments on the proposal or on the
determination of the cost to the public.

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 152 airplanes in the U.S.
registry.
We estimate the following costs to incorporate and remove the
temporary change to the AFM.

------------------------------------------------------------------------
Total cost per
Labor cost Parts cost airplane
------------------------------------------------------------------------
0.5 work-hour x $80 per hour = Not Applicable..... $40
$40.
------------------------------------------------------------------------

We estimate that the post-flight residual heat check requires about
3 minutes to do. We estimate the following costs to do 10 of the post-
flight residual heat checks. We have no way of determining the number
of airplanes that would have this post-flight residual heat check, or
how many times this will need to be performed before the terminating
action is done:

------------------------------------------------------------------------
Labor cost to do 10 post-flight Total cost per
residual heat checks Parts cost airplane
------------------------------------------------------------------------
0.5 work-hour x $80 per hour = Not Applicable..... $40
$40.
------------------------------------------------------------------------

We estimate the following costs to do the maintenance manual
operational test of the heat of the AOA probes. We have no way of
determining the number of airplanes that would have this operational
test, or how many times this will need to be performed before the
terminating action is done:

We estimate the following costs to do any upload of software to the
AOA transmitters. We have no way of determining the number of airplanes
that would have this modification:

------------------------------------------------------------------------
Total cost per
Labor cost Parts cost airplane
------------------------------------------------------------------------
4 work-hours x $80 per hour = Not Applicable..... $320
$320.
------------------------------------------------------------------------

We estimate the following costs to do any replacement of 2 stall
warning AOA transmitters. We have no way of determining the number of
airplanes that would have this replacement:

------------------------------------------------------------------------
Total cost per
Labor cost Parts cost airplane
------------------------------------------------------------------------
2 work-hours x $80 per hour = $18,600............ $18,760
$160.
------------------------------------------------------------------------

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,

[[Page 44144]]

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-2008-0353; Directorate Identifier 2007-CE-101-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 the following new AD:

2008-16-02 Hawker Beechcraft Corporation: Amendment 39-15620; Docket
No. FAA-2008-0353; Directorate Identifier 2007-CE-101-AD.

Effective Date

(a) This AD becomes effective on September 3, 2008.

Affected ADs

(b) None.

Applicability

Unsafe Condition

(d) This AD results from reports of the potential for
unannunciated loss of the heating function in the left-hand (LH) and
right-hand (RH) stall warning angle-of-attack (AOA) transmitters of
Model 390 airplanes. We are issuing this AD to correct potentially
inadequate stall warning with loss of stick pusher function.

Compliance

(e) To address this problem, you must do the following, unless
already done:

----------------------------------------------------------------------------------------------------------------
Actions Compliance Procedures
----------------------------------------------------------------------------------------------------------------
(1) Incorporate Raytheon Aircraft Within 15 hours time-in-service Not Applicable.
Company Temporary Change to the FAA (TIS) after September 3, 2008 (the
Approved Airplane Flight Manual P/N effective date of the AD) or within
390-590001-0003CTC7, issued: March 30 days after September 3, 2008
15, 2007, into the airplane flight (the effective date of the AD),
manual (AFM). whichever occurs first.
(2) After every flight do the Begin the post-flight checks within (A) For the post-flight check for
following: 15 hours TIS after September 3, residual heat in the AOA probes:
(i) Do a post-flight check for 2008 (the effective date of the AD) Follow Raytheon Aircraft Company
residual heat in the AOA probes. or within 30 days after September Temporary Change to the FAA
CAUTION: TO PREVENT POSSIBLE BURNS, 3, 2008 (the effective date of the Approved Airplane Flight Manual
USE EXTREME CAUTION TOUCHING HEATED AD), whichever occurs first. Temporary Change P/N 390-590001-
AREAS. TO CHECK HEATING AND AVOID Completion of paragraph (e)(3)(i) 0003CTC7, issued: March 15, 2007.
BURNS, HOLD HAND NEAR HEATED AREA or (e)(3)(ii) of this AD terminates The owner/operator holding at least
OR MOVE HAND GRADUALLY FROM AMBIENT the required repetitive post-flight a private pilot certificate as
AREA TOWARD HEATED AREA UNTIL checks of this AD. Replace any AOA authorized by section 43.7 of the
WARMTH CAN BE FELT. If you do not probe that fails the operational Federal Aviation Regulations (14
feel heat in the AOA probes, then test before further flight. CFR 43.7) may do this post-flight
do paragraph (e)(2)(ii) of this AD; check required by paragraph
or (e)(2)(i) of this AD. Make an entry
(ii) Do a post-flight maintenance into the aircraft records showing
manual operational test of the heat compliance with this AD following
of the AOA probes. If the AOA probe section 43.9 of the Federal
fails the operational test, replace Aviation Regulations (14 CFR 43.9).
the AOA probe. (B) For the post-flight maintenance
manual operational test of the heat
of the AOA probes: Follow Raytheon
Aircraft Company Temporary Change
to the FAA Approved Airplane Flight
Manual Temporary Change P/N 390-
590001-0003CTC7, issued: March 15,
2007, and Hawker Beechcraft
Mandatory Service Bulletin No. SB
27-3787, issued: May 2007. The
maintenance manual operational test
must be done by an appropriately
rated mechanic.
.................................... (C) For AOA probe replacement:
Follow Hawker Beechcraft Mandatory
Service Bulletin No. SB 27-3787,
issued: May 2007.

[[Page 44145]]

(3) Replace or modify (upload Within 250 hours TIS after September Follow Hawker Beechcraft Mandatory
software) the stall warning AOA 3, 2008 (the effective date of this Service Bulletin No. SB 27-3787,
transmitters by doing one of the AD) or within 12 months after issued: May 2007.
following: September 3, 2008 (the effective
(i) Upload new software Kit No. 123- date of this AD), whichever occurs
3436 (Field Software Upload SLZ8060- first.
3,-4) to the AOA transmitters; or Completion of either paragraph
(ii) Replace any part number (P/N) (e)(3)(i) or (e)(3)(ii) of this AD
SLZ8060-3 and/or P/N SLZ8060-4 AOA terminates the required repetitive
transmitters with new P/N SLZ8060-5 post-flight check of this AD.
AOA transmitters.
(4) Remove Raytheon Aircraft Company Before further flight after doing Follow Hawker Beechcraft Mandatory
Temporary Change to the FAA the actions required by paragraph Service Bulletin No. SB 27-3787,
Approved Airplane Flight Manual P/N (e)(3)(i) or paragraph (e)(3)(ii) issued: May 2007.
390-590001-0003CTC7, issued: March of this AD.
15, 2007, from the AFM.
(5) Do not install any P/N SLZ8060-3 As of September 3, 2008 (the Not Applicable.
or P/N SLZ8060-4 AOA transmitter effective date of this AD).
that does not have the new upgraded
software required by paragraph
(e)(3)(i) of this AD.
----------------------------------------------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

(f) 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: Philip Petty, Aerospace Engineer, Wichita ACO, 1801 Airport
Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-4139;
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

(g) You must use Raytheon Aircraft Company Temporary Change to
the FAA Approved Airplane Flight Manual P/N 390-590001-0003CTC7,
issued: March 15, 2007, and Hawker Beechcraft Mandatory Service
Bulletin No. SB 27-3787, issued: May 2007, 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, 9709 East Central, Wichita, Kansas
67291; telephone: (800) 429-5372 or (316) 676-3140.
(3) You may review copies at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or at
the National Archives and Records Administration (NARA). For
information on the availability of this material at NARA, call 202-
741-6030, or go to: https://www.archives.gov/federal_register/code_
of_federal_regulations/ibr_locations.html.

Issued in Kansas City, Missouri, on July 23, 2008.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-17329 Filed 7-29-08; 8:45 am]
BILLING CODE 4910-13-P

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