Airworthiness Directives; CFM International, S.A. CFM56-5C4/1 Series Turbofan Engines, 65445-65446 [E7-22647]

Download as PDF Federal Register / Vol. 72, No. 224 / Wednesday, November 21, 2007 / Rules and Regulations the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (i) Mandatory continuing Airworthiness Information (MCAI) Transport Canada Airworthiness Directive No. CF–2006–23–R1, dated March 12, 2007, and Bell Helicopter Textron Alert Service Bulletin No. 206–06– 109, dated July 25, 2006, contain related information. Issued in Fort Worth, Texas, on November 2, 2007. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. E7–22415 Filed 11–20–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–0108; Directorate Identifier 2001–NE–15–AD; Amendment 39–15270; AD 2007–24–04] RIN 2120–AA64 Airworthiness Directives; CFM International, S.A. CFM56–5C4/1 Series Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. rmajette on PROD1PC64 with RULES AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for CFM International, S.A. CFM56–5C4/1 series turbofan engines. That AD currently requires that the low pressure turbine (LPT) conical support, part number (P/N) 337–002–407–0, be removed from service at or before reaching the cyclic life limit of 9,350 cycles-since-new (CSN). This AD requires that the same P/N LPT conical support be removed from service before reaching the new, relaxed cyclic life limit of 20,000 CSN. This AD results from CFM International, S.A. performing a life extension study of the LPT conical support, P/N 337–002–407–0. We are issuing this AD to prevent LPT conical supports from remaining in service beyond their certified cyclic life limit, which could result in an uncontained engine failure and damage to the airplane. DATES: Effective December 6, 2007. We must receive any comments on this AD by January 22, 2008. ADDRESSES: Use one of the following addresses to comment on this AD: VerDate Aug<31>2005 15:23 Nov 20, 2007 Jkt 214001 • Federal eRulemaking Portal: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: U.S. Docket Management Facility, Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: (202) 493–2251. FOR FURTHER INFORMATION CONTACT: Stephen Sheely, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: stephen.k.sheely@faa.gov; telephone (781) 238–7750; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: On August 15, 2001, we issued AD 2001–17–14, Amendment 39–12405 (66 FR 44297, August 23, 2001). That AD requires that the CFM56–5C4/1 series turbofan engine LPT conical support, P/N 337–002–407–0, be removed from service at or before reaching the cyclic life limit of 9,350 CSN. That AD was the result of the discovery of an error in the Time Limits Section of Chapter 5 of the CFM56–5C Engine Shop Manual. The manual incorrectly listed the published cyclic life limit of the CFM56–5C4/1 turbofan engine LPT conical support, P/N 337–002–407–0, as 15,000 CSN, rather than the certified value of 9,350 CSN. Actions Since We Issued AD 2001–17– 14 Since we issued AD 2001–17–14, CFM International, S.A. performed a life extension study of the CFM56–5C4/1 engine LPT conical support, P/N 337– 002–407–0. The results of the study show that the calculated cyclic life limit is above 20,000 CSN. Based on the study, CFM International, S.A. has now established a relaxed certified cyclic life limit of 20,000 CSN for this part. FAA’s Determination and Requirements of This AD Although no airplanes that are registered in the United States use these CFM56–5C4/1 turbofan engines, the possibility exists that the engines could be used on airplanes that are registered in the United States in the future. The unsafe condition described previously is likely to exist or develop on other turbofan engines of the same type design. We are issuing this AD to prevent LPT conical supports from remaining in service beyond their PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 65445 certified cyclic life limit, which could result in an uncontained engine failure and damage to the airplane. This AD requires that the CFM56–5C4/1 series turbofan engine LPT conical support, P/N 337–002–407–0, be removed from service at or before reaching the new, relaxed cyclic life limit of 20,000 CSN. Applicability Paragraph Correction In AD 2001–17–14, we incorrectly stated that the engines were installed on, but not limited to, Airbus A320 series airplanes. In this AD we corrected the airplane model to A340 series airplanes. FAA’s Determination of the Effective Date Since there are currently no domestic operators of this engine model, notice and opportunity for public comment before issuing this AD are unnecessary. Therefore, a situation exists that allows the immediate adoption of this regulation. Comments Invited This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to send us any written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES. Include ‘‘AD Docket No. FAA–2007–0108; Directorate Identifier 2001–NE–15–AD’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify it. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this AD. Using the search function of the Federal Docket Management System Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–19478). 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, E:\FR\FM\21NOR1.SGM 21NOR1 65446 Federal Register / Vol. 72, No. 224 / Wednesday, November 21, 2007 / Rules and Regulations 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 the same as the Mail address provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. Docket Number Change We are transferring the docket for this AD to the Federal Docket Management System as part of our on-going docket management consolidation efforts. The new Docket No. is FAA–2007–0108. The old Docket No. became the Directorate Identifier, which is 2001–NE–15–AD. rmajette on PROD1PC64 with RULES 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 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 placed it in the AD Docket. You may get a copy of VerDate Aug<31>2005 15:23 Nov 20, 2007 Jkt 214001 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 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–12405 (66 FR 44297, August 23, 2001), and by adding a new airworthiness directive, Amendment 39–15270, to read as follows: I 2007–24–04 CFM International, S.A.: Amendment 39–15270. Docket No. FAA–2007–0108; Directorate Identifier 2001–NE–15–AD. Effective Date (a) This airworthiness directive (AD) becomes effective December 6, 2007. 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. Material Incorporated by Reference (i) None. Related Information (j) Contact Stephen Sheely, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: stephen.k.sheely@faa.gov; telephone (781) 238–7750; fax (781) 238– 7199, for more information about this AD. Issued in Burlington, Massachusetts, on November 14, 2007. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7–22647 Filed 11–20–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–0211; Directorate Identifier 2007–NM–221–AD; Amendment 39–15268; AD 2007–24–02] RIN 2120–AA64 Affected ADs (b) This AD supersedes AD 2001–17–14, Amendment 39–12405. Airworthiness Directives; Boeing Model 737–100, –200, –200C, –300, –400, and –500 Series Airplanes Applicability (c) This AD applies to CFM International, S.A. CFM56–5C4/1 series turbofan engines with low pressure turbine (LPT) conical support, part number (P/N) 337–002–407–0, installed. These engines are installed on, but not limited to, Airbus A340 series airplanes. AGENCY: Unsafe Condition (d) This AD results from CFM International, S.A. performing a life extension study of the LPT conical support, P/N 337–002–407–0. We are issuing this AD to prevent LPT conical supports from remaining in service beyond their certified cyclic life limit, which could result in an uncontained engine failure and damage to the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. (f) Remove LPT conical support, P/N 337– 002–407–0, at or before accumulating 20,000 cycles-since-new (CSN) and replace with a serviceable part. (g) After the effective date of this AD, do not install any LPT conical support, P/N 337–002–407–0, with 20,000 or more CSN, into CFM56–5C4/1 series turbofan engines. PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. SUMMARY: The FAA is superseding an existing airworthiness directive (AD) that applies to all Model 737–100, –200, –200C, –300, –400, and –500 series airplanes. The existing AD currently requires repetitive detailed inspections for damage of the electrical wire and sleeve that run to the fuel boost pump through a conduit in the fuel tank, and arcing damage of the conduit and signs of fuel leakage into the conduit; replacement of the sleeve with a new, smaller-diameter sleeve; and related investigative and corrective actions, as applicable. This new AD reduces the inspection threshold for certain airplanes. This AD results from a report of a fuel tank explosion on a Model 727–200F airplane on the ground, and a report of chafed wires and a damaged power cable sleeve of a fuel boost pump discovered during an inspection on a Model 737–300 airplane. (The fuel boost E:\FR\FM\21NOR1.SGM 21NOR1

Agencies

[Federal Register Volume 72, Number 224 (Wednesday, November 21, 2007)]
[Rules and Regulations]
[Pages 65445-65446]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-22647]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0108; Directorate Identifier 2001-NE-15-AD; 
Amendment 39-15270; AD 2007-24-04]
RIN 2120-AA64


Airworthiness Directives; CFM International, S.A. CFM56-5C4/1 
Series Turbofan Engines

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

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) for CFM International, S.A. CFM56-5C4/1 series turbofan engines. 
That AD currently requires that the low pressure turbine (LPT) conical 
support, part number (P/N) 337-002-407-0, be removed from service at or 
before reaching the cyclic life limit of 9,350 cycles-since-new (CSN). 
This AD requires that the same P/N LPT conical support be removed from 
service before reaching the new, relaxed cyclic life limit of 20,000 
CSN. This AD results from CFM International, S.A. performing a life 
extension study of the LPT conical support, P/N 337-002-407-0. We are 
issuing this AD to prevent LPT conical supports from remaining in 
service beyond their certified cyclic life limit, which could result in 
an uncontained engine failure and damage to the airplane.

DATES: Effective December 6, 2007.
    We must receive any comments on this AD by January 22, 2008.

ADDRESSES: Use one of the following addresses to comment on this AD:
     Federal eRulemaking Portal: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: U.S. Docket Management Facility, Department of 
Transportation, 1200 New Jersey Avenue, SE., West Building Ground 
Floor, Room W12-140, Washington, DC 20590-0001.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax: (202) 493-2251.

FOR FURTHER INFORMATION CONTACT: Stephen Sheely, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
stephen.k.sheely@faa.gov; telephone (781) 238-7750; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: On August 15, 2001, we issued AD 2001-17-14, 
Amendment 39-12405 (66 FR 44297, August 23, 2001). That AD requires 
that the CFM56-5C4/1 series turbofan engine LPT conical support, P/N 
337-002-407-0, be removed from service at or before reaching the cyclic 
life limit of 9,350 CSN. That AD was the result of the discovery of an 
error in the Time Limits Section of Chapter 5 of the CFM56-5C Engine 
Shop Manual. The manual incorrectly listed the published cyclic life 
limit of the CFM56-5C4/1 turbofan engine LPT conical support, P/N 337-
002-407-0, as 15,000 CSN, rather than the certified value of 9,350 CSN.

Actions Since We Issued AD 2001-17-14

    Since we issued AD 2001-17-14, CFM International, S.A. performed a 
life extension study of the CFM56-5C4/1 engine LPT conical support, P/N 
337-002-407-0. The results of the study show that the calculated cyclic 
life limit is above 20,000 CSN. Based on the study, CFM International, 
S.A. has now established a relaxed certified cyclic life limit of 
20,000 CSN for this part.

FAA's Determination and Requirements of This AD

    Although no airplanes that are registered in the United States use 
these CFM56-5C4/1 turbofan engines, the possibility exists that the 
engines could be used on airplanes that are registered in the United 
States in the future. The unsafe condition described previously is 
likely to exist or develop on other turbofan engines of the same type 
design. We are issuing this AD to prevent LPT conical supports from 
remaining in service beyond their certified cyclic life limit, which 
could result in an uncontained engine failure and damage to the 
airplane. This AD requires that the CFM56-5C4/1 series turbofan engine 
LPT conical support, P/N 337-002-407-0, be removed from service at or 
before reaching the new, relaxed cyclic life limit of 20,000 CSN.

Applicability Paragraph Correction

    In AD 2001-17-14, we incorrectly stated that the engines were 
installed on, but not limited to, Airbus A320 series airplanes. In this 
AD we corrected the airplane model to A340 series airplanes.

FAA's Determination of the Effective Date

    Since there are currently no domestic operators of this engine 
model, notice and opportunity for public comment before issuing this AD 
are unnecessary. Therefore, a situation exists that allows the 
immediate adoption of this regulation.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment; however, we invite you to send us any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. FAA-2007-0108; 
Directorate Identifier 2001-NE-15-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify it.
    We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact 
with FAA personnel concerning this AD. Using the search function of the 
Federal Docket Management System Web site, anyone can find and read the 
comments in any of our dockets, including the name of the individual 
who sent the comment (or signed the comment on behalf of an 
association, business, labor union, etc). You may review the DOT's 
complete Privacy Act Statement in the Federal Register published on 
April 11, 2000 (65 FR 19477-19478).

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,

[[Page 65446]]

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 
the same as the Mail address provided in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

Docket Number Change

    We are transferring the docket for this AD to the Federal Docket 
Management System as part of our on-going docket management 
consolidation efforts. The new Docket No. is FAA-2007-0108. The old 
Docket No. became the Directorate Identifier, which is 2001-NE-15-AD.

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 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 
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
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. The FAA amends Sec.  39.13 by removing Amendment 39-12405 (66 FR 
44297, August 23, 2001), and by adding a new airworthiness directive, 
Amendment 39-15270, to read as follows:

2007-24-04 CFM International, S.A.: Amendment 39-15270. Docket No. 
FAA-2007-0108; Directorate Identifier 2001-NE-15-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective December 
6, 2007.

Affected ADs

    (b) This AD supersedes AD 2001-17-14, Amendment 39-12405.

Applicability

    (c) This AD applies to CFM International, S.A. CFM56-5C4/1 
series turbofan engines with low pressure turbine (LPT) conical 
support, part number (P/N) 337-002-407-0, installed. These engines 
are installed on, but not limited to, Airbus A340 series airplanes.

Unsafe Condition

    (d) This AD results from CFM International, S.A. performing a 
life extension study of the LPT conical support, P/N 337-002-407-0. 
We are issuing this AD to prevent LPT conical supports from 
remaining in service beyond their certified cyclic life limit, which 
could result in an uncontained engine failure and damage to the 
airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified unless the 
actions have already been done.
    (f) Remove LPT conical support, P/N 337-002-407-0, at or before 
accumulating 20,000 cycles-since-new (CSN) and replace with a 
serviceable part.
    (g) After the effective date of this AD, do not install any LPT 
conical support, P/N 337-002-407-0, with 20,000 or more CSN, into 
CFM56-5C4/1 series turbofan engines.

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.

Material Incorporated by Reference

    (i) None.

Related Information

    (j) Contact Stephen Sheely, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
stephen.k.sheely@faa.gov; telephone (781) 238-7750; fax (781) 238-
7199, for more information about this AD.

    Issued in Burlington, Massachusetts, on November 14, 2007.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E7-22647 Filed 11-20-07; 8:45 am]
BILLING CODE 4910-13-P