Airworthiness Directives; Pratt & Whitney (PW) PW4164, PW4168, and PW4168A Turbofan Engines, 394-395 [E7-25505]

Download as PDF jlentini on PROD1PC65 with RULES 394 Federal Register / Vol. 73, No. 2 / Thursday, January 3, 2008 / Rules and Regulations 2. With descent velocity of 12.25 feet per second UNLESS mitigating design features are incorporated that address: i. Independent load path ii. Fuel management iii. Location/Geometry iv. Other safety enhancing design features as proposed by the applicant. If adequate mitigation is demonstrated for all the above design features, the FAA will reduce the descent velocity to no less then 5 feet per second; and 3. By defining, based on a rational analysis, supported by tests: i. A downward ultimate inertia force; and ii. A coefficient of friction of 0.5, or a rational analysis for a coefficient of friction, at the ground. Compliance with SC 23.561(c)(2) will be demonstrated by dynamic drop test. 2. SC 23.721: The following general requirements for the landing gear apply: 1. The landing-gear system must be designed so that if it fails due to overloads during takeoff and landing (assuming the overloads to act in the upward and aft directions), the failure mode is not likely to cause the spillage of enough fuel from any part of the external fuel tank system(s) located beneath the fuselage to constitute a fire hazard. 2. The airplane must be designed so that, with the airplane under control, it can be landed on a paved runway with any one or more landing-gear legs not extended without sustaining a structural component failure that is likely to cause the spillage of enough fuel to constitute a fire hazard. 3. Compliance with the provisions of this section may be shown by analysis or tests, or both. 3. SC 23.994: Fuel system components in external fuel tank system(s) located beneath the fuselage must be protected from damage which could result in spillage of enough fuel to constitute a fire hazard as a result of a wheels-up landing on a paved runway. 4. SC 23.XXX: Fuel tanks within and below the fuselage contour must be installed in accordance with the requirements prescribed in Sec. 23.967. External fuel tank system(s) located beneath the fuselage must have the following design mitigations: 1. The external fuel tank system(s) must be in a protected position so that exposure of the tank to scraping action, or impact, with the ground is unlikely during a gear-up landing of the most critical landing gear or landing gears, when landing on a paved runway. 2. The external fuel tank system(s) must be protected by dedicated protective structure, and the protective structure load paths must be VerDate Aug<31>2005 16:54 Jan 02, 2008 Jkt 214001 independent of the fuel system during a gear-up landing of the most critical landing gear or landing gears, when landing on a paved runway. 3. The hazard to the external fuel tank system(s) that results from impact by landing gear tire fragments or other likely debris must be minimized. 4. The fuel management of the external fuel tank system(s) must be such that fuel in the external fuel tank system(s) is to be emptied prior to fuel in the main tanks. Issued in Kansas City, Missouri on December 26, 2007. John Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–25466 Filed 1–2–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–27230; Directorate Identifier 2007–NE–04–AD] Amendment 39– 15322; AD 2007–26–20] RIN 2120–AA64 Airworthiness Directives; Pratt & Whitney (PW) PW4164, PW4168, and PW4168A Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for PW PW4164, PW4168, and PW4168A turbofan engines with certain low pressure turbine (LPT) stage 4 disks, part number (P/N) 51N404, installed. This AD requires removing certain LPT stage 4 disks, listed by serial number at the next piece-part exposure or within 7,500 cycles-since-new (CSN). This AD results from a report of improperly manufactured LPT stage 4 disks. We are issuing this AD to prevent an uncontained engine failure due to lowcycle fatigue (LCF), which could result in damage to the airplane. DATES: This AD becomes effective February 7, 2008. 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: V. Rose Len, Aerospace Engineer, Engine PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238–7772; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to PW PW4164, PW4168, and PW4168A. We published the proposed AD in the Federal Register on May 21, 2007 (72 FR 28459). That action proposed to require removing certain LPT stage 4 disks, P/N 51N404, listed by serial number in the proposed AD, at the next piece-part exposure, or within 7,500 CSN, whichever occurs first. Examining the AD Docket You may examine the AD docket on the Internet at https:// 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 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. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comment received. Pratt & Whitney proposes that we not write an AD. Pratt & Whitney states that they performed additional testing for low-cycle fatigue (LCF). They state the testing shows the disks with the 1-hour heat treatment are equivalent to the disks treated with a 4-hour heat treatment. We do not agree. The data that PW presents to us doesn’t conclusively show the 1-hour heat-treat LCF capability is equivalent to the 4hour heat-treat disks. We didn’t change the AD. Conclusion We have carefully reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance We estimate that this AD will affect 11 engines installed on airplanes of U.S. registry. We also estimate that it will take about 250 work-hours per engine to perform the required action, if not done at piece-part exposure, and that the average labor rate is $80 per work-hour. Required parts will cost about $186,288 E:\FR\FM\03JAR1.SGM 03JAR1 Federal Register / Vol. 73, No. 2 / Thursday, January 3, 2008 / Rules and Regulations per engine. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $2,269,168. 1. The authority citation for part 39 continues to read as follows: I Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this 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 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 placed it in the AD Docket. You may get a copy of this summary at the address listed under ADDRESSES. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. jlentini on PROD1PC65 with RULES Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends 14 CFR part 39 as follows: I VerDate Aug<31>2005 19:37 Jan 02, 2008 Jkt 214001 PART 39—AIRWORTHINESS DIRECTIVES Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: I 2007–26–20 Pratt & Whitney: Amendment 39–15322. Docket No. FAA–2007–27230; Directorate Identifier 2007–NE–04–AD. Effective Date (a) This airworthiness directive (AD) becomes effective February 7, 2008. (b) None. Applicability (c) This AD applies to Pratt & Whitney PW4164, PW4168, and PW4168A turbofan engines with certain low pressure turbine (LPT) stage 4 disks, part number (P/N) 51N404, that have a serial number (S/N) listed in the following Table 1, installed. These engines are installed on, but not limited to, Airbus A330–200 and A330–300 series airplanes. TABLE 1.—AFFECTED LPT STAGE 4 DISKS BY SERIAL NUMBER LPT Stage 4 Disk Serial Nos. CLDLC01142 CLDLC01143 CLDLC01144 CLDLC01145 CLDLC01146 CLDLC01148 CLDLC01149 CLDLC01150 CLDLC01151 CLDLC01152 CLDLC01181 CLDLC01182 CLDLC01183 CLDLC01185 CLDLC01186 CLDLC01187 Prohibition Against Installing an Affected Disk (g) After the effective date of this AD, do not install any disk, P/N 51N404, that has an S/N listed in Table 1 of this AD or any disk removed as specified in paragraph (f) of this AD except as allowed by paragraph (h) of this AD. Alternative Methods of Compliance (h) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Related Information (j) Contact V. Rose Len, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238–7772; fax (781) 238–7199, for more information about this AD. Material Incorporated by Reference (k) None. Issued in Burlington, Massachusetts, on December 20, 2007. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7–25505 Filed 1–2–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–0379; Directorate Identifier 2007–NM–331–AD; Amendment 39–15318; AD 2007–26–16] RIN 2120–AA64 Airworthiness Directives; Cessna Model 680 Airplanes Unsafe Condition (d) This AD results from a report of improperly manufactured LPT stage 4 disks. We are issuing this AD to prevent an uncontained engine failure due to low-cycle fatigue, which could result in damage to the airplane. Compliance (e) You are responsible for having the actions required by this AD performed at the next piece-part exposure after the effective date of this AD or within 7,500 cycles-sincenew, unless the actions have already been done. Frm 00007 Removing the LPT Stage 4 Disk (f) Remove from service any LPT stage 4 disk that has an S/N listed in Table 1 of this AD. Special Flight Permits (i) Under 14 CFR part 39.23, we are prohibiting the special flight permits for this AD. Affected ADs PO 00000 395 Fmt 4700 Sfmt 4700 Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for certain Cessna Model 680 airplanes. This AD requires inspecting the routing of the aft fairing wire bundle assembly for adequate separation between the wiring and the hydraulic line; inspecting for chafing or damage of the wire bundle E:\FR\FM\03JAR1.SGM 03JAR1

Agencies

[Federal Register Volume 73, Number 2 (Thursday, January 3, 2008)]
[Rules and Regulations]
[Pages 394-395]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-25505]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-27230; Directorate Identifier 2007-NE-04-AD] 
Amendment 39-15322; AD 2007-26-20]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney (PW) PW4164, PW4168, 
and PW4168A Turbofan Engines

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

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for PW 
PW4164, PW4168, and PW4168A turbofan engines with certain low pressure 
turbine (LPT) stage 4 disks, part number (P/N) 51N404, installed. This 
AD requires removing certain LPT stage 4 disks, listed by serial number 
at the next piece-part exposure or within 7,500 cycles-since-new (CSN). 
This AD results from a report of improperly manufactured LPT stage 4 
disks. We are issuing this AD to prevent an uncontained engine failure 
due to low-cycle fatigue (LCF), which could result in damage to the 
airplane.

DATES: This AD becomes effective February 7, 2008.

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: V. Rose Len, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; telephone (781) 238-
7772; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed AD. The proposed AD applies to PW PW4164, PW4168, and 
PW4168A. We published the proposed AD in the Federal Register on May 
21, 2007 (72 FR 28459). That action proposed to require removing 
certain LPT stage 4 disks, P/N 51N404, listed by serial number in the 
proposed AD, at the next piece-part exposure, or within 7,500 CSN, 
whichever occurs first.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
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 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.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comment received.
    Pratt & Whitney proposes that we not write an AD. Pratt & Whitney 
states that they performed additional testing for low-cycle fatigue 
(LCF). They state the testing shows the disks with the 1-hour heat 
treatment are equivalent to the disks treated with a 4-hour heat 
treatment. We do not agree. The data that PW presents to us doesn't 
conclusively show the 1-hour heat-treat LCF capability is equivalent to 
the 4-hour heat-treat disks. We didn't change the AD.

Conclusion

    We have carefully reviewed the available data, including the 
comment received, and determined that air safety and the public 
interest require adopting the AD as proposed.

Costs of Compliance

    We estimate that this AD will affect 11 engines installed on 
airplanes of U.S. registry. We also estimate that it will take about 
250 work-hours per engine to perform the required action, if not done 
at piece-part exposure, and that the average labor rate is $80 per 
work-hour. Required parts will cost about $186,288

[[Page 395]]

per engine. Based on these figures, we estimate the total cost of the 
AD to U.S. operators to be $2,269,168.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this 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 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 
placed it in the AD Docket. You may get a copy of this summary at the 
address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends 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. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2007-26-20 Pratt & Whitney: Amendment 39-15322. Docket No. FAA-2007-
27230; Directorate Identifier 2007-NE-04-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective February 
7, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Pratt & Whitney PW4164, PW4168, and 
PW4168A turbofan engines with certain low pressure turbine (LPT) 
stage 4 disks, part number (P/N) 51N404, that have a serial number 
(S/N) listed in the following Table 1, installed. These engines are 
installed on, but not limited to, Airbus A330-200 and A330-300 
series airplanes.

          Table 1.--Affected LPT Stage 4 Disks by Serial Number
------------------------------------------------------------------------
 
-------------------------------------------------------------------------
                      LPT Stage 4 Disk Serial Nos.
------------------------------------------------------------------------
CLDLC01142
CLDLC01143
CLDLC01144
CLDLC01145
CLDLC01146
CLDLC01148
CLDLC01149
CLDLC01150
CLDLC01151
CLDLC01152
CLDLC01181
CLDLC01182
CLDLC01183
CLDLC01185
CLDLC01186
CLDLC01187
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from a report of improperly manufactured LPT 
stage 4 disks. We are issuing this AD to prevent an uncontained 
engine failure due to low-cycle fatigue, which could result in 
damage to the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed at the next piece-part exposure after the effective 
date of this AD or within 7,500 cycles-since-new, unless the actions 
have already been done.

Removing the LPT Stage 4 Disk

    (f) Remove from service any LPT stage 4 disk that has an S/N 
listed in Table 1 of this AD.

Prohibition Against Installing an Affected Disk

    (g) After the effective date of this AD, do not install any 
disk, P/N 51N404, that has an S/N listed in Table 1 of this AD or 
any disk removed as specified in paragraph (f) of this AD except as 
allowed by paragraph (h) of this AD.

Alternative Methods of Compliance

    (h) The Manager, Engine Certification Office, has the authority 
to approve alternative methods of compliance for this AD if 
requested using the procedures found in 14 CFR 39.19.

Special Flight Permits

    (i) Under 14 CFR part 39.23, we are prohibiting the special 
flight permits for this AD.

Related Information

    (j) Contact V. Rose Len, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; telephone (781) 238-
7772; fax (781) 238-7199, for more information about this AD.

Material Incorporated by Reference

    (k) None.

    Issued in Burlington, Massachusetts, on December 20, 2007.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
 [FR Doc. E7-25505 Filed 1-2-08; 8:45 am]
BILLING CODE 4910-13-P
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