Airworthiness Directives; Pratt & Whitney Canada Corp. JT15D-5; -5B; -5F; and -5R Turbofan Engines, 72328-72330 [E8-28062]

Download as PDF dwashington3 on PROD1PC60 with RULES 72328 Federal Register / Vol. 73, No. 230 / Friday, November 28, 2008 / Rules and Regulations 2008–22–52 MD Helicopters, Inc.: Amendment 39–15752. Docket No. FAA–2008–1244; Directorate Identifier 2008–SW–59–AD. Supersedes Emergency AD 2008–18–52, Directorate Identifier 2008–SW–52–AD. Applicability: Model 500N and 600N helicopters, with a Yaw Stability Augmentation System (YSAS) adapter tube, part number 500N7218–1, installed, certificated in any category. Adapter tubes that have a production date code stamp are not included in the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent loss of yaw control and subsequent loss of control of the helicopter, do the following: (a) Before further flight: (1) Turn OFF the YSAS switch. (2) Install a placard on the instrument panel as close as practicable to the airspeed indicator that states: ‘‘YSAS SYSTEM IS OFF. AIRSPEED LIMIT 100 KIAS or VNE, WHICHEVER IS LESS.’’ Note: MDHI Service Bulletin SB500N– 040R1/SB600N–047R1, dated August 27, 2008, and maintenance manual CSP–HMI–3, Section 96–00–00, pertain to the subject of this AD. (3) Make pen and ink changes or place a copy of this AD in the limitations section of the rotorcraft flight manual (RFM) to revise the limitations as follows: ‘‘VNE is limited to 100 KIAS or less as determined by referring to the airspeed VNE placard already installed on the helicopter.’’ (b) Within 45 days, replace each affected adapter tube with an airworthy adapter tube that has a production date code stamp. This replacement is terminating action for the requirements of this AD. Once this replacement has been done, remove the placards, remove the airspeed restriction revisions that were made to the RFM, and return the YSAS system to its normal position. (c) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Los Angeles Aircraft Certification Office, FAA, ATTN: Eric D. Schrieber, Aviation Safety Engineer, Airframe Branch, 3960 Paramount Blvd., Lakewood, California 90712, telephone 562– 627–5348, fax 562–627–5210, for information about previously approved alternative methods of compliance. (d) Copies of the applicable service information may be obtained from MD Helicopters Inc., Attn: Customer Support Division, 4555 E. McDowell Rd., Mail Stop M615, Mesa, Arizona 85215–9734, telephone 1–800–388–3378, fax 480–346–6813, or on the Web at http://www.mdhelicopters.com. (e) This amendment becomes effective on December 15, 2008, to all persons except those persons to whom it was made immediately effective by Emergency AD 2008–22–52, issued October 23, 2008, which contained the requirements of this amendment. VerDate Aug<31>2005 14:57 Nov 26, 2008 Jkt 217001 Issued in Fort Worth, Texas, on November 14, 2008. Scott A. Horn, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E8–28110 Filed 11–26–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0752; Directorate Identifier 2008–NE–22–AD; Amendment 39– 15750; AD 2008–24–10] RIN 2120–AA64 Airworthiness Directives; Pratt & Whitney Canada Corp. JT15D–5; –5B; –5F; and –5R Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: 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 an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as follows: There have been several reported incidents of high altitude, dual engine flameout on JT15D–5 engine powered aircraft operating in certain meteorological conditions. Subsequent to the investigation of incidents, review of the engine design has revealed that the Fuel Control Hydro Mechanical Unit (HMU) P3 servo can be exposed to excessive moisture and freezing. We are issuing this AD to prevent engine flameouts of one or both engines, caused by excessive moisture and freezing in the P3 servo during certain flight conditions. DATES: This AD becomes effective January 2, 2009. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of January 2, 2009. ADDRESSES: The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. FOR FURTHER INFORMATION CONTACT: Ian Dargin, Aerospace Engineer, Engine Certification Office, FAA, Engine and PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: ian.dargin@faa.gov; telephone (781) 238–7178; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on August 22, 2008 (73 FR 49619). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states the following: There have been several reported incidents of high altitude, dual engine flameout on JT15D–5 engine powered aircraft operating in certain meteorological conditions. Subsequent to the investigation of incidents, review of the engine design has revealed that the Fuel Control Hydro Mechanical Unit (HMU) P3 servo can be exposed to excessive moisture and freezing. Comments We gave the public the opportunity to participate in developing this AD. We considered the comments received. Request To Reference Hawker Beechcraft Service Bulletin for Wire Harness One commenter, Flight Options, requests that we reference Hawker Beechcraft Service Bulletin (SB) No. SB 73–3888, Revision 1, dated July, 2008, in the AD. That SB instructs to re-route and secure the throttle solenoid wire harness, and instructs to install a serviceable compressor air to HMU delivery tube, using Pratt & Whitney Canada Corp. (P&WC) Alert SB No. JT15D–72–A7611, Revision 1, dated June 16, 2008. The commenter states that without the proposed AD referring to the Hawker Beechcraft SB, operators could leave wire harnesses unsecured, potentially leading to other system failures. We partially agree. We recognize that instructions to re-route and secure the throttle solenoid wire harness are contained in the Hawker Beechcraft SB, and operators should refer to these requirements during the modification. We do not agree that securing the throttle solenoid wire harness needs to be mandated by this AD. However, we have added the Hawker Beechcraft SB reference to the Related Information paragraph in the AD. Suggestion To Use Hawker Beechcraft SB for AD Compliance Flight Options suggests that the Hawker Beechcraft SB No. SB 73–3888, E:\FR\FM\28NOR1.SGM 28NOR1 Federal Register / Vol. 73, No. 230 / Friday, November 28, 2008 / Rules and Regulations Revision 1, or later Revision, is a satisfactory method of compliance with the proposed AD. We agree that the SB contains a satisfactory method of compliance, but it also imposes additional requirements which are unnecessary. Accordingly, we do not agree that compliance to the Hawker Beechcraft SB needs to be mandated to prevent flameouts of one or both engines. We did not change the AD. Request To Change Compliance Period Flight Options requests that we change the proposed compliance period of ‘‘200 hours after the effective date of this AD or by December 31, 2008’’ to ‘‘400 hours after the effective date of this AD or by March 31, 2009’’. The commenter did not provide any data to substantiate their request. We do not agree. A short compliance period is necessary, in the interest of safety. However, we changed the compliance to ‘‘within 200 flight hours after the effective date of this AD or within 30 days after the effective date of this AD, whichever occurs first’’. Suggestion To Add P&WC Alert SB No. JT15D–72–A7611, Revision 1, to Previous Credit Paragraph Flight Options suggests that we add P&WC Alert SB No. JT15D–72–A7611, Revision 1, dated June 16, 2008 to the Previous Credit paragraph (h). The commenter notes that P&WC added two engine models to that SB revision. We do not agree. Engines that have been made compliant per that SB before the effective date of the AD are covered by compliance paragraph (e) which states ‘‘Unless already done, do the following actions.’’ We did not change the AD. Request To Remove Cessna Airplanes From Applicability One commenter, Cessna Aircraft Company, requests that we remove the references to Cessna airplanes from the applicability, as the affected engines are not installed on Cessna airplanes. We agree. We removed the Cessna references from the AD. dwashington3 on PROD1PC60 with RULES Request To Remove Mitsubishi Airplanes From Applicability Hawker Beechcraft requests that we remove the references to Mitsubishi MU–300 and MU–300–10 airplanes from the applicability, as the affected engines are not installed on Mitsubishi airplanes. We agree. We removed the Mitsubishi references from the AD. VerDate Aug<31>2005 14:57 Nov 26, 2008 Jkt 217001 Claim That AD Is Not Needed One commenter, Hawker Beechcraft, claims that the AD is not needed. The commenter states that the earlier FAA AD 2006–21–02 addresses the problem, which at the time of AD issuance, was believed to be the result of ice buildup in the engine core. We do not agree. While icing of the engine core stators remains the most obvious contributor to the engine flameout issue, more recent tests by P&WC have shown that freezing of the compressor air to HMU delivery tube at altitudes of 37,000 feet and higher, is also a contributing element. This AD is necessary to address required engine installation changes. Request To Revise AD 2006–21–02 Hawker Beechcraft requests that we revise FAA AD 2006–21–02 to incorporate the replacement of the compressor air to HMU delivery tube, which is the subject of the proposed AD. The commenter states that having two ADs addressing dual-engine flameouts will be confusing to operators. We do not agree. While the first AD addresses operational issues at the airplane level, a separate AD is required to mandate an engine configuration change to incorporate improvements to the compressor air to HMU delivery tube. This will eliminate a second contributor to the in-flight engine shutdowns seen in service. Request To Add the JT15D–5F Engine Model to the Costs of Compliance Hawker Beechcraft requests that we add the JT15D–5F engine model to the costs of compliance, as this model is also affected by P&WC ASB No. JT15D– 72–A7611, Revision 1, dated June 16, 2008. We agree. We inadvertently listed the JT15D–5R engine model twice; the second listing should have been –5F. We changed the costs of compliance to read ‘‘* * * and $3,169 per product for JT15D–5B and –5F engines’’. Conclusion We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We determined that these changes will not increase the economic burden on any operator or increase the scope of the AD. Costs of Compliance Based on the service information, we estimate that this AD will affect about 1,500 products of U.S. registry. We also estimate that it will take about 3 work- PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 72329 hours per product to comply with this AD. The average labor rate is $80 per work-hour. Required parts will cost about $1,981 per product for JT15D–5 and –5R engines, and $3,169 per product for JT15D–5B and –5F engines. Based on these figures, we estimate the cost of the AD on U.S. operators to be $4,222,500. Our cost estimate is exclusive of possible warranty coverage. 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 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 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 regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket E:\FR\FM\28NOR1.SGM 28NOR1 72330 Federal Register / Vol. 73, No. 230 / Friday, November 28, 2008 / Rules and Regulations contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is provided 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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: ■ PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ 2008–24–10 Pratt & Whitney Canada Corp.: Amendment 39–15750. Docket No. FAA–2008–0752; Directorate Identifier 2008–NE–22–AD. Effective Date (a) This airworthiness directive (AD) becomes effective January 2, 2009. Affected ADs (b) None. dwashington3 on PROD1PC60 with RULES Applicability (c) This AD applies to the following Pratt & Whitney Canada Corp. (P&WC) turbofan engines with compressor air to HMU delivery tube, part number (P/N) 3119150–01 installed: (1) JT15D–5 turbofan engines, serial numbers (SNs) below and including SN PCE– 100411. (2) JT15D–5 turbofan engines, SNs below and including SN PCE–JA0818. (3) All JT15D–5B turbofan engines. (4) All JT15D–5F turbofan engines. (5) JT15D–5R turbofan engines SNs below and including SN PCE–JG0104. (6) All JT15D–5 turbofan engines converted to model JT15D–5R by incorporation of P&WC Service Bulletin No. 7605. These engines are installed on, but not limited to, Hawker Beechcraft models 400, 400A, and 400T airplanes. Reason (d) Transport Canada AD CF–2008–23, dated June 27, 2008, states: There have been several reported incidents of high altitude, dual engine flameout on JT15D–5 engine powered aircraft operating in certain meteorological conditions. Subsequent to the investigation of incidents, review of the engine design has revealed that VerDate Aug<31>2005 14:57 Nov 26, 2008 Jkt 217001 the Fuel Control Hydro Mechanical Unit (HMU) P3 servo can be exposed to excessive moisture and freezing. To preclude P3 servo freezing, P&WC has issued JT15D Alert Service Bulletin (ASB) JT15D–72–A7611 to re-route compressor delivery air to the HMU and improve moisture separation. Considering the potentially hazardous consequence of possible in-flight dual engine flameout, this airworthiness directive is issued to mandate the incorporation of P&WC ASB JT15D–72–A7611 to the affected JT15D– 5 engines, in order to minimize the possibility of this hazard. We are issuing this AD to prevent engine flameouts of one or both engines caused by excessive moisture and freezing in the P3 servo during certain flight conditions. Actions and Compliance (e) Unless already done, do the following actions. (1) Within 200 flight hours after the effective date of this AD or within 30 days after the effective date of this AD, whichever occurs first, remove from service compressor air to HMU delivery tube, P/N 3119150–01. (2) Install a serviceable compressor air to HMU delivery tube in accordance with P&WC Alert Service Bulletin (ASB) No. JT15D–72–A7611, Revision 1, dated June 16, 2008. Prohibition of Compressor Air to HMU Delivery Tube, P/N 3119150–01 (3) After the effective date of this AD, do not install any compressor air to HMU delivery tube, P/N 3119150–01, onto any engine. Definition (f) For the purpose of this AD, a serviceable compressor air to HMU delivery tube is a compressor air to HMU delivery tube that is other than the tube part number listed in this AD. (g) Alternative Methods of Compliance (AMOCs): The Manager, Engine Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Previous Credit (h) Replacement of the compressor air to HMU delivery tube using P&WC ASB No. JT15D–72–A7611, dated March 26, 2008, before the effective date of this AD, meets the requirements of this AD. Related Information (i) Refer to Transport Canada AD CF–2008– 23, dated June 27, 2008, for related information. (j) Hawker Beechcraft Service Bulletin No. SB 73–3888, Revision 1, dated July 2008, also pertains to the subject of this AD. (k) Contact Ian Dargin, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park; Burlington, MA 01803; e-mail: ian.dargin@faa.gov; telephone (781) 238–7178; fax (781) 238–7199, for more information about this AD. Material Incorporated by Reference (l) You must use Pratt & Whitney Canada Corp. Alert Service Bulletin No. JT15D–72– PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 A7611, Revision 1, dated June 16, 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 Pratt & Whitney Canada Corp., 1000 Marie-Victorin, Longueuil, Quebec, Canada J4G 1A1, telephone: (800) 268–8000. (3) You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; 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: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Burlington, Massachusetts, on November 19, 2008. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E8–28062 Filed 11–26–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 97 [Docket No. 30638; Amdt. No 3296] Standard Instrument Approach Procedures, and Takeoff Minimums and Obstacle Departure Procedures; Miscellaneous Amendments Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: This establishes, amends, suspends, or revokes Standard Instrument Approach Procedures (SIAPs) and associated Takeoff Minimums and Obstacle Departure Procedures for operations at certain airports. These regulatory actions are needed because of the adoption of new or revised criteria, or because of changes occurring in the National Airspace System, such as the commissioning of new navigational facilities, adding new obstacles, or changing air traffic requirements. These changes are designed to provide safe and efficient use of the navigable airspace and to promote safe flight operations under instrument flight rules at the affected airports. This rule is effective November 28, 2008. The compliance date for each SIAP, associated Takeoff Minimums, and ODP is specified in the amendatory provisions. DATES: E:\FR\FM\28NOR1.SGM 28NOR1

Agencies

[Federal Register Volume 73, Number 230 (Friday, November 28, 2008)]
[Rules and Regulations]
[Pages 72328-72330]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-28062]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0752; Directorate Identifier 2008-NE-22-AD; 
Amendment 39-15750; AD 2008-24-10]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney Canada Corp. JT15D-5; -
5B; -5F; and -5R Turbofan Engines

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

ACTION: Final rule.

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

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 an aviation authority of 
another country to identify and correct an unsafe condition on an 
aviation product. The MCAI describes the unsafe condition as follows:

    There have been several reported incidents of high altitude, 
dual engine flameout on JT15D-5 engine powered aircraft operating in 
certain meteorological conditions. Subsequent to the investigation 
of incidents, review of the engine design has revealed that the Fuel 
Control Hydro Mechanical Unit (HMU) P3 servo can be exposed to 
excessive moisture and freezing.

    We are issuing this AD to prevent engine flameouts of one or both 
engines, caused by excessive moisture and freezing in the P3 servo 
during certain flight conditions.

DATES: This AD becomes effective January 2, 2009. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in this AD as of January 2, 2009.

ADDRESSES: The Docket Operations office is located at Docket Management 
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, 
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.

FOR FURTHER INFORMATION CONTACT: Ian Dargin, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
ian.dargin@faa.gov; telephone (781) 238-7178; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on August 22, 2008 (73 
FR 49619). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states the following:

    There have been several reported incidents of high altitude, 
dual engine flameout on JT15D-5 engine powered aircraft operating in 
certain meteorological conditions. Subsequent to the investigation 
of incidents, review of the engine design has revealed that the Fuel 
Control Hydro Mechanical Unit (HMU) P3 servo can be exposed to 
excessive moisture and freezing.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comments received.

Request To Reference Hawker Beechcraft Service Bulletin for Wire 
Harness

    One commenter, Flight Options, requests that we reference Hawker 
Beechcraft Service Bulletin (SB) No. SB 73-3888, Revision 1, dated 
July, 2008, in the AD. That SB instructs to re-route and secure the 
throttle solenoid wire harness, and instructs to install a serviceable 
compressor air to HMU delivery tube, using Pratt & Whitney Canada Corp. 
(P&WC) Alert SB No. JT15D-72-A7611, Revision 1, dated June 16, 2008. 
The commenter states that without the proposed AD referring to the 
Hawker Beechcraft SB, operators could leave wire harnesses unsecured, 
potentially leading to other system failures.
    We partially agree. We recognize that instructions to re-route and 
secure the throttle solenoid wire harness are contained in the Hawker 
Beechcraft SB, and operators should refer to these requirements during 
the modification. We do not agree that securing the throttle solenoid 
wire harness needs to be mandated by this AD. However, we have added 
the Hawker Beechcraft SB reference to the Related Information paragraph 
in the AD.

Suggestion To Use Hawker Beechcraft SB for AD Compliance

    Flight Options suggests that the Hawker Beechcraft SB No. SB 73-
3888,

[[Page 72329]]

Revision 1, or later Revision, is a satisfactory method of compliance 
with the proposed AD.
    We agree that the SB contains a satisfactory method of compliance, 
but it also imposes additional requirements which are unnecessary. 
Accordingly, we do not agree that compliance to the Hawker Beechcraft 
SB needs to be mandated to prevent flameouts of one or both engines. We 
did not change the AD.

Request To Change Compliance Period

    Flight Options requests that we change the proposed compliance 
period of ``200 hours after the effective date of this AD or by 
December 31, 2008'' to ``400 hours after the effective date of this AD 
or by March 31, 2009''. The commenter did not provide any data to 
substantiate their request.
    We do not agree. A short compliance period is necessary, in the 
interest of safety. However, we changed the compliance to ``within 200 
flight hours after the effective date of this AD or within 30 days 
after the effective date of this AD, whichever occurs first''.

Suggestion To Add P&WC Alert SB No. JT15D-72-A7611, Revision 1, to 
Previous Credit Paragraph

    Flight Options suggests that we add P&WC Alert SB No. JT15D-72-
A7611, Revision 1, dated June 16, 2008 to the Previous Credit paragraph 
(h). The commenter notes that P&WC added two engine models to that SB 
revision.
    We do not agree. Engines that have been made compliant per that SB 
before the effective date of the AD are covered by compliance paragraph 
(e) which states ``Unless already done, do the following actions.'' We 
did not change the AD.

Request To Remove Cessna Airplanes From Applicability

    One commenter, Cessna Aircraft Company, requests that we remove the 
references to Cessna airplanes from the applicability, as the affected 
engines are not installed on Cessna airplanes.
    We agree. We removed the Cessna references from the AD.

Request To Remove Mitsubishi Airplanes From Applicability

    Hawker Beechcraft requests that we remove the references to 
Mitsubishi MU-300 and MU-300-10 airplanes from the applicability, as 
the affected engines are not installed on Mitsubishi airplanes.
    We agree. We removed the Mitsubishi references from the AD.

Claim That AD Is Not Needed

    One commenter, Hawker Beechcraft, claims that the AD is not needed. 
The commenter states that the earlier FAA AD 2006-21-02 addresses the 
problem, which at the time of AD issuance, was believed to be the 
result of ice buildup in the engine core.
    We do not agree. While icing of the engine core stators remains the 
most obvious contributor to the engine flameout issue, more recent 
tests by P&WC have shown that freezing of the compressor air to HMU 
delivery tube at altitudes of 37,000 feet and higher, is also a 
contributing element. This AD is necessary to address required engine 
installation changes.

Request To Revise AD 2006-21-02

    Hawker Beechcraft requests that we revise FAA AD 2006-21-02 to 
incorporate the replacement of the compressor air to HMU delivery tube, 
which is the subject of the proposed AD. The commenter states that 
having two ADs addressing dual-engine flameouts will be confusing to 
operators.
    We do not agree. While the first AD addresses operational issues at 
the airplane level, a separate AD is required to mandate an engine 
configuration change to incorporate improvements to the compressor air 
to HMU delivery tube. This will eliminate a second contributor to the 
in-flight engine shutdowns seen in service.

Request To Add the JT15D-5F Engine Model to the Costs of Compliance

    Hawker Beechcraft requests that we add the JT15D-5F engine model to 
the costs of compliance, as this model is also affected by P&WC ASB No. 
JT15D-72-A7611, Revision 1, dated June 16, 2008.
    We agree. We inadvertently listed the JT15D-5R engine model twice; 
the second listing should have been -5F. We changed the costs of 
compliance to read ``* * * and $3,169 per product for JT15D-5B and -5F 
engines''.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the changes described previously. We determined that these 
changes will not increase the economic burden on any operator or 
increase the scope of the AD.

Costs of Compliance

    Based on the service information, we estimate that this AD will 
affect about 1,500 products of U.S. registry. We also estimate that it 
will take about 3 work-hours per product to comply with this AD. The 
average labor rate is $80 per work-hour. Required parts will cost about 
$1,981 per product for JT15D-5 and -5R engines, and $3,169 per product 
for JT15D-5B and -5F engines. Based on these figures, we estimate the 
cost of the AD on U.S. operators to be $4,222,500. Our cost estimate is 
exclusive of possible warranty coverage.

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 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 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 regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket

[[Page 72330]]

contains this AD, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Operations office 
(telephone (800) 647-5527) is provided 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.

Adoption of the Amendment

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Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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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]

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2. The FAA amends Sec.  39.13 by adding the following new AD:

2008-24-10 Pratt & Whitney Canada Corp.: Amendment 39-15750. Docket 
No. FAA-2008-0752; Directorate Identifier 2008-NE-22-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective January 
2, 2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to the following Pratt & Whitney Canada 
Corp. (P&WC) turbofan engines with compressor air to HMU delivery 
tube, part number (P/N) 3119150-01 installed:
    (1) JT15D-5 turbofan engines, serial numbers (SNs) below and 
including SN PCE-100411.
    (2) JT15D-5 turbofan engines, SNs below and including SN PCE-
JA0818.
    (3) All JT15D-5B turbofan engines.
    (4) All JT15D-5F turbofan engines.
    (5) JT15D-5R turbofan engines SNs below and including SN PCE-
JG0104.
    (6) All JT15D-5 turbofan engines converted to model JT15D-5R by 
incorporation of P&WC Service Bulletin No. 7605.
    These engines are installed on, but not limited to, Hawker 
Beechcraft models 400, 400A, and 400T airplanes.

Reason

    (d) Transport Canada AD CF-2008-23, dated June 27, 2008, states:

    There have been several reported incidents of high altitude, 
dual engine flameout on JT15D-5 engine powered aircraft operating in 
certain meteorological conditions. Subsequent to the investigation 
of incidents, review of the engine design has revealed that the Fuel 
Control Hydro Mechanical Unit (HMU) P3 servo can be exposed to 
excessive moisture and freezing. To preclude P3 servo freezing, P&WC 
has issued JT15D Alert Service Bulletin (ASB) JT15D-72-A7611 to re-
route compressor delivery air to the HMU and improve moisture 
separation. Considering the potentially hazardous consequence of 
possible in-flight dual engine flameout, this airworthiness 
directive is issued to mandate the incorporation of P&WC ASB JT15D-
72-A7611 to the affected JT15D-5 engines, in order to minimize the 
possibility of this hazard.

    We are issuing this AD to prevent engine flameouts of one or 
both engines caused by excessive moisture and freezing in the P3 
servo during certain flight conditions.

Actions and Compliance

    (e) Unless already done, do the following actions.
    (1) Within 200 flight hours after the effective date of this AD 
or within 30 days after the effective date of this AD, whichever 
occurs first, remove from service compressor air to HMU delivery 
tube, P/N 3119150-01.
    (2) Install a serviceable compressor air to HMU delivery tube in 
accordance with P&WC Alert Service Bulletin (ASB) No. JT15D-72-
A7611, Revision 1, dated June 16, 2008.

Prohibition of Compressor Air to HMU Delivery Tube, P/N 3119150-01

    (3) After the effective date of this AD, do not install any 
compressor air to HMU delivery tube, P/N 3119150-01, onto any 
engine.

Definition

    (f) For the purpose of this AD, a serviceable compressor air to 
HMU delivery tube is a compressor air to HMU delivery tube that is 
other than the tube part number listed in this AD.
    (g) Alternative Methods of Compliance (AMOCs): The Manager, 
Engine Certification Office, FAA, has the authority to approve AMOCs 
for this AD, if requested using the procedures found in 14 CFR 
39.19.

Previous Credit

    (h) Replacement of the compressor air to HMU delivery tube using 
P&WC ASB No. JT15D-72-A7611, dated March 26, 2008, before the 
effective date of this AD, meets the requirements of this AD.

Related Information

    (i) Refer to Transport Canada AD CF-2008-23, dated June 27, 
2008, for related information.
    (j) Hawker Beechcraft Service Bulletin No. SB 73-3888, Revision 
1, dated July 2008, also pertains to the subject of this AD.
    (k) Contact Ian Dargin, Aerospace Engineer, Engine Certification 
Office, FAA, Engine and Propeller Directorate, 12 New England 
Executive Park; Burlington, MA 01803; e-mail: ian.dargin@faa.gov; 
telephone (781) 238-7178; fax (781) 238-7199, for more information 
about this AD.

Material Incorporated by Reference

    (l) You must use Pratt & Whitney Canada Corp. Alert Service 
Bulletin No. JT15D-72-A7611, Revision 1, dated June 16, 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 Pratt 
& Whitney Canada Corp., 1000 Marie-Victorin, Longueuil, Quebec, 
Canada J4G 1A1, telephone: (800) 268-8000.
    (3) You may review copies at the FAA, New England Region, 12 New 
England Executive Park, Burlington, MA; 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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on November 19, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
 [FR Doc. E8-28062 Filed 11-26-08; 8:45 am]
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