Airworthiness Directives; General Electric Company Aircraft Engine Group (GEAE) CF6-45A Series, CF6-50A, CF6-50C Series and CF6-50E Series Turbofan Engines, 53106-53108 [E7-18134]

Download as PDF 53106 Federal Register / Vol. 72, No. 180 / Tuesday, September 18, 2007 / Rules and Regulations to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Hawker Beechcraft Corporation, 9709 East Central, Wichita, Kansas 67206, for a copy of this service information. You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; 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. BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–25239; Directorate Identifier 2006–NE–23–AD; Amendment 39– 15196; AD 2007–19–06] RIN 2120–AA64 Airworthiness Directives; General Electric Company Aircraft Engine Group (GEAE) CF6–45A Series, CF6– 50A, CF6–50C Series and CF6–50E Series Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. mstockstill on PROD1PC66 with RULES AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for GEAE CF6–45A, –45A2, –50A, –50C, –50CA, –50C1, –50C2, –50C2B, –50C2D, –50C2F, –50C2R, –50E, –50E1, – 50E2, and –50E2B turbofan engines. This AD requires replacing the compressor discharge pressure (CDP) restoring spring assembly on certain main engine controls (MECs) or re-marking MECs that already incorporate GEAE Service Bulletin (SB) No. CF6–50 S/B 73–0119, dated March 21, 2005. This AD results from reports of five events involving fractured CDP restoring spring assemblies. We are issuing this AD to prevent loss of engine thrust control that could lead to loss of control of the airplane. DATES: This AD becomes effective October 23, 2007. The Director of the Federal Register approved the incorporation by reference of certain VerDate Aug<31>2005 18:27 Sep 17, 2007 Jkt 211001 Costs of Compliance Examining the AD Docket Issued in Renton, Washington, on August 31, 2007. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–18048 Filed 9–17–07; 8:45 am] publications listed in the regulations as of October 23, 2007. ADDRESSES: You can get the service information identified in this AD from General Electric Company via GE– Aviation, Attn: Distributions, 111 Merchant St., Room 230, Cincinnati, Ohio 45246; telephone (513) 552–3272; fax (513) 552–3329. The Docket Operations office is located at U.S. Department of Transportation, Docket Operations, M– 30, West Building, Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Tara Chaidez, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238–7773; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to GEAE CF6–45A, –45A2, –50A, –50C, –50CA, –50C1, –50C2, –50C2B, –50C2D, –50C2F, –50C2R, –50E, –50E1, –50E2, and –50E2B turbofan engines. We published the proposed AD in the Federal Register on May 31, 2007 (74 FR 30300). That action proposed to require replacing the CDP restoring spring assembly on certain MECs and re-marking MECs that already incorporate GEAE SB No. CF6–50 S/B 73–0119, dated March 21, 2005 or GEAE SB No. CF6–50 S/B 73–0119, Revision 01, dated May 26, 2006. Regulatory Findings You may examine the AD docket on the Internet at http://dms.dot.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. 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. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. The commenters support the proposal. Conclusion We have carefully reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD as proposed. PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 We estimate that this proposed AD would affect 756 GEAE CF6–45A, –50C, and –50E series turbofan engines installed on airplanes of U.S. registry. We also estimate that it would take about 40 work-hours per engine to perform the proposed actions, and that the average labor rate is $80 per workhour. Required parts would cost about $1,787 per engine. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $3,770,172. 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. E:\FR\FM\18SER1.SGM 18SER1 Federal Register / Vol. 72, No. 180 / Tuesday, September 18, 2007 / Rules and Regulations List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 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: 2007–19–06 General Electric Company Aircraft Engine Group: Amendment 39– 15196. Docket No. FAA–2006–25239; Directorate Identifier 2006–NE–23–AD. PART 39—AIRWORTHINESS DIRECTIVES Effective Date I (a) This airworthiness directive (AD) becomes effective October 23, 2007. 1. The authority citation for part 39 continues to read as follows: I Affected ADs (b) None. [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: I 53107 Applicability (c) This AD applies to General Electric Company Aircraft Engine Group (GEAE) CF6–45A, 45A2, –50A, –50C, –50CA, –50C1, –50C2, –50C2B, –50C2D, –50C2F, –50C2R, –50E, –50E1, –50E2, and –50E2B turbofan engines that have a main engine control (MEC) with a part number (P/N) specified in Table 1 of this AD installed. These engines are installed on, but not limited to, Airbus A300 series airplanes, McDonnell Douglas DC–10, KC–10, and MD–10 series airplanes, and Boeing 747 series airplanes. TABLE 1.—AFFECTED WOODWARD AND GEAE P/NS FOR MECS BY ENGINE MODEL SERIES Engine model series Woodward P/N CF6–50A, –50C, –50CA, –50C1, –50C2, –50C2B, –50C2D, –50C2F, –50C2R. .......................................... 8062–275 8062–279 8062–287 8062–289 8062–819 8062–822 8062–824 8062–823 8062–826 8062–827 8062–828 8062–829 8062–276 8062–280 8062–290 8062–291 8062–817 8062–820 8062–896 8062–897 8062–898 8062–899 CF6–45A, –45A2, –50E, –50E1, –50E2, –50E2B .......................................................................................... (d) This AD results from reports of five events involving fractured compressor discharge pressure (CDP) restoring spring assembly. We are issuing this AD to prevent loss of engine thrust control that could lead to loss of control of 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. GEAE P/N 9070M55P42 9070M55P44 9070M55P49 9070M55P51 9070M55P101 9070M55P102 9070M55P103 9070M55P104 9070M55P105 9070M55P106 9070M55P107 9070M55P108 9187M29P10 9187M29P11 9187M29P14 9187M29P15 9187M29P100 9187M29P101 9187M29P22 9187M29P23 9187M29P20 9187M29P21 Replacing the CDP Restoring Spring Assembly on CF6–50A Engines and –50C Series Engines (f) For CF6–50A model engines and –50C series engines that have an MEC that has a P/N listed in Table 1 of this AD, replace the CDP restoring spring assembly as follows in Table 2 of this AD: TABLE 2.—COMPLIANCE SCHEDULE FOR CF6–50A AND –50C ENGINES Then By Use (1) Was already replaced using GEAE CF6–50 S/B 73–0119, dated March 21, 2005. mstockstill on PROD1PC66 with RULES If the CDP restoring spring assembly in your MEC Re-mark the MEC ......................... The next time the MEC is routed for repair such as the next MEC shop visit. (2) Was already replaced within 10,000 or fewer hours time-inservice (TIS) before the effective date of this AD, and the replacement spring assembly (P/N 3018–248) had zero hours TIS. (3) Has more then 10,000 hours TIS. Replace the spring assembly and remark the MEC. The first MEC shop visit or engine shop visit after the MEC exceeds 10,000 hours TIS, but do not exceed 20,000 hours TIS. Paragraph 3.A. of the Accomplishment Instructions of SB No. CF6–50 S/B 73–0119, Revision 02, dated March 9, 2007. Paragraph 3.A. of the Accomplishment Instructions of SB No. CF6–50 S/B 73–0119, Revision 02, dated March 9, 2007. Replace the spring assembly and remark the MEC. The next MEC shop visit or engine shop visit whichever occurs first. VerDate Aug<31>2005 18:27 Sep 17, 2007 Jkt 211001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 E:\FR\FM\18SER1.SGM Paragraph 3.A. of the Accomplishment Instructions of SB No. CF6–50 S/B 73–0119, Revision 02, dated March 9, 2007. 18SER1 53108 Federal Register / Vol. 72, No. 180 / Tuesday, September 18, 2007 / Rules and Regulations Replacing the CDP Restoring Spring Assembly on CF6–45A and –50E Series Engines (g) For CF6–45A series and –50E series engines that have an MEC that has a P/N listed in Table 1 of this AD, replace the CDP restoring spring assembly as follows in Table 3 of this AD: TABLE 3.—COMPLIANCE SCHEDULE FOR CF6–45A AND –50E ENGINES If the CDP restoring spring assembly in your MEC Then By Use (1) Was already replaced within 10,000 or fewer hours time-inservice (TIS) before the effective date of this AD, and the replacement spring assembly (P/N 3018–248) had zero hours TIS. (2) Has more then 10,000 hours TIS. Replace the spring assembly and remark the MEC. The first MEC shop visit or engine shop visit after the MEC exceeds 10,000 hours TIS, but do not exceed 20,000 hours TIS. Paragraph 3.A. of the Accomplishment Instructions of SB No. CF6–50 S/B 73–0120, dated March 21, 2007. Replace the spring assembly and remark the MEC. The next MEC shop visit or engine shop visit whichever occurs first. Paragraph 3.A. of the Accomplishment Instructions of SB No. CF6–50 S/B 73–0120, dated March 21, 2007. Definition (h) For the purpose of this AD, a shop visit is induction of the engine or MEC into the shop for any cause. Installation Prohibition (i) After the effective date of the AD, do not install an MEC that: (1) Has not complied with SB No. CF6–50 S/B 73–0119, Revision 02, dated March 9, 2007 or earlier revision, or SB No. CF6–50 S/ B 73–0120, dated March 21, 2007, or (2) Has not had the CDP restoring spring replaced with a spring assembly, P/N 3018– 248, or FAA-approved equivalent spring assembly, within the previous 10,000 hours of MEC operation. Alternative Methods of Compliance (j) 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 (k) None. (l) Tara Chaidez, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238–7773; fax (781) 238– 7199, for more information about this AD. Material Incorporated by Reference (m) You must use the service information specified in Table 4 to perform the replacements required by this AD. The Director of the Federal Register approved the incorporation by reference of the documents listed in Table 4 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact General Electric Company via GE– Aviation, Attn: Distributions, 111 Merchant St., Room 230, Cincinnati, Ohio 45246; telephone (513) 552–3272; fax (513) 552– 3329, for a copy of this service information. You may review copies at the FAA, 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. TABLE 4.—INCORPORATION BY REFERENCE Service Bulletin No. Page Revision CF6–50 S/B 73–0119 ................................................................................................ Total Pages—11 CF6–50 S/B 73–0120 ................................................................................................ Total Pages—11 ALL ................... 02 ..................... March 9, 2007. ALL ................... Original ............. March 21, 2007. Issued in Burlington, Massachusetts, on September 7, 2007. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7–18134 Filed 9–17–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–27955; Directorate Identifier 2007–NE–15–AD; Amendment 39– 15201; AD 2007–19–10] RIN 2120–AA64 mstockstill on PROD1PC66 with RULES Airworthiness Directives; Rolls-Royce plc RB211 Trent 500 Series Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: VerDate Aug<31>2005 18:27 Sep 17, 2007 Jkt 211001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 Date SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) provided by an aviation authority of the United Kingdom (UK) to identify and correct an unsafe condition on RollsRoyce plc RB211 Trent 500 series turbofan engines. The MCAI states the following: This AD requires replacement of Intermediate Pressure Compressor (IP Compressor) Drums (Part Number FK30102) of nine part serial numbers. This action is necessary following the discovery of strain induced porosity in a Trent 500 IP Compressor Drum forging. Engineering assessment concluded that the problem is caused by the forging process and it is E:\FR\FM\18SER1.SGM 18SER1

Agencies

[Federal Register Volume 72, Number 180 (Tuesday, September 18, 2007)]
[Rules and Regulations]
[Pages 53106-53108]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-18134]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25239; Directorate Identifier 2006-NE-23-AD; 
Amendment 39-15196; AD 2007-19-06]
RIN 2120-AA64


Airworthiness Directives; General Electric Company Aircraft 
Engine Group (GEAE) CF6-45A Series, CF6-50A, CF6-50C Series and CF6-50E 
Series 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 
GEAE CF6-45A, -45A2, -50A, -50C, -50CA, -50C1, -50C2, -50C2B, -50C2D, -
50C2F, -50C2R, -50E, -50E1, - 50E2, and -50E2B turbofan engines. This 
AD requires replacing the compressor discharge pressure (CDP) restoring 
spring assembly on certain main engine controls (MECs) or re-marking 
MECs that already incorporate GEAE Service Bulletin (SB) No. CF6-50 S/B 
73-0119, dated March 21, 2005. This AD results from reports of five 
events involving fractured CDP restoring spring assemblies. We are 
issuing this AD to prevent loss of engine thrust control that could 
lead to loss of control of the airplane.

DATES: This AD becomes effective October 23, 2007. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of October 23, 2007.

ADDRESSES: You can get the service information identified in this AD 
from General Electric Company via GE-Aviation, Attn: Distributions, 111 
Merchant St., Room 230, Cincinnati, Ohio 45246; telephone (513) 552-
3272; fax (513) 552-3329.
    The Docket Operations office is located at U.S. Department of 
Transportation, Docket Operations, M-30, West Building, Ground Floor, 
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Tara Chaidez, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; telephone (781) 238-
7773; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed AD. The proposed AD applies to GEAE CF6-45A, -45A2, -
50A, -50C, -50CA, -50C1, -50C2, -50C2B, -50C2D, -50C2F, -50C2R, -50E, -
50E1, -50E2, and -50E2B turbofan engines. We published the proposed AD 
in the Federal Register on May 31, 2007 (74 FR 30300). That action 
proposed to require replacing the CDP restoring spring assembly on 
certain MECs and re-marking MECs that already incorporate GEAE SB No. 
CF6-50 S/B 73-0119, dated March 21, 2005 or GEAE SB No. CF6-50 S/B 73-
0119, Revision 01, dated May 26, 2006.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
dms.dot.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 comments received. The 
commenters support the proposal.

Conclusion

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

Costs of Compliance

    We estimate that this proposed AD would affect 756 GEAE CF6-45A, -
50C, and -50E series turbofan engines installed on airplanes of U.S. 
registry. We also estimate that it would take about 40 work-hours per 
engine to perform the proposed actions, and that the average labor rate 
is $80 per work-hour. Required parts would cost about $1,787 per 
engine. Based on these figures, we estimate the total cost of the 
proposed AD to U.S. operators to be $3,770,172.

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.

[[Page 53107]]

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 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:

2007-19-06 General Electric Company Aircraft Engine Group: Amendment 
39-15196. Docket No. FAA-2006-25239; Directorate Identifier 2006-NE-
23-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective October 
23, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to General Electric Company Aircraft Engine 
Group (GEAE) CF6-45A, 45A2, -50A, -50C, -50CA, -50C1, -50C2, -50C2B, 
-50C2D, -50C2F, -50C2R, -50E, -50E1, -50E2, and -50E2B turbofan 
engines that have a main engine control (MEC) with a part number (P/
N) specified in Table 1 of this AD installed. These engines are 
installed on, but not limited to, Airbus A300 series airplanes, 
McDonnell Douglas DC-10, KC-10, and MD-10 series airplanes, and 
Boeing 747 series airplanes.

   Table 1.--Affected Woodward and GEAE P/Ns for MECs by Engine Model
                                 Series
------------------------------------------------------------------------
         Engine model series            Woodward P/N        GEAE P/N
------------------------------------------------------------------------
CF6-50A, -50C, -50CA, -50C1, -50C2, -         8062-275        9070M55P42
 50C2B, -50C2D, -50C2F, -50C2R......          8062-279        9070M55P44
                                              8062-287        9070M55P49
                                              8062-289        9070M55P51
                                              8062-819       9070M55P101
                                              8062-822       9070M55P102
                                              8062-824       9070M55P103
                                              8062-823       9070M55P104
                                              8062-826       9070M55P105
                                              8062-827       9070M55P106
                                              8062-828       9070M55P107
                                              8062-829       9070M55P108
CF6-45A, -45A2, -50E, -50E1, -50E2, -         8062-276        9187M29P10
 50E2B..............................          8062-280        9187M29P11
                                              8062-290        9187M29P14
                                              8062-291        9187M29P15
                                              8062-817       9187M29P100
                                              8062-820       9187M29P101
                                              8062-896        9187M29P22
                                              8062-897        9187M29P23
                                              8062-898        9187M29P20
                                              8062-899        9187M29P21
------------------------------------------------------------------------

    (d) This AD results from reports of five events involving 
fractured compressor discharge pressure (CDP) restoring spring 
assembly. We are issuing this AD to prevent loss of engine thrust 
control that could lead to loss of control of 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.

Replacing the CDP Restoring Spring Assembly on CF6-50A Engines and -50C 
Series Engines

    (f) For CF6-50A model engines and -50C series engines that have 
an MEC that has a P/N listed in Table 1 of this AD, replace the CDP 
restoring spring assembly as follows in Table 2 of this AD:

                           Table 2.--Compliance Schedule for CF6-50A and -50C Engines
----------------------------------------------------------------------------------------------------------------
 If the CDP restoring spring assembly
             in your MEC                         Then                      By                      Use
----------------------------------------------------------------------------------------------------------------
(1) Was already replaced using GEAE    Re-mark the MEC........  The next time the MEC    Paragraph 3.A. of the
 CF6-50 S/B 73-0119, dated March 21,                             is routed for repair     Accomplishment
 2005.                                                           such as the next MEC     Instructions of SB No.
                                                                 shop visit.              CF6-50 S/B 73-0119,
                                                                                          Revision 02, dated
                                                                                          March 9, 2007.
(2) Was already replaced within        Replace the spring       The first MEC shop       Paragraph 3.A. of the
 10,000 or fewer hours time-in-         assembly and remark      visit or engine shop     Accomplishment
 service (TIS) before the effective     the MEC.                 visit after the MEC      Instructions of SB No.
 date of this AD, and the replacement                            exceeds 10,000 hours     CF6-50 S/B 73-0119,
 spring assembly (P/N 3018-248) had                              TIS, but do not exceed   Revision 02, dated
 zero hours TIS.                                                 20,000 hours TIS.        March 9, 2007.
(3) Has more then 10,000 hours TIS...  Replace the spring       The next MEC shop visit  Paragraph 3.A. of the
                                        assembly and remark      or engine shop visit     Accomplishment
                                        the MEC.                 whichever occurs first.  Instructions of SB No.
                                                                                          CF6-50 S/B 73-0119,
                                                                                          Revision 02, dated
                                                                                          March 9, 2007.
----------------------------------------------------------------------------------------------------------------


[[Page 53108]]

Replacing the CDP Restoring Spring Assembly on CF6-45A and -50E Series 
Engines

    (g) For CF6-45A series and -50E series engines that have an MEC 
that has a P/N listed in Table 1 of this AD, replace the CDP 
restoring spring assembly as follows in Table 3 of this AD:

                           Table 3.--Compliance Schedule for CF6-45A and -50E Engines
----------------------------------------------------------------------------------------------------------------
 If the CDP restoring spring assembly
             in your MEC                         Then                      By                      Use
----------------------------------------------------------------------------------------------------------------
(1) Was already replaced within        Replace the spring       The first MEC shop       Paragraph 3.A. of the
 10,000 or fewer hours time-in-         assembly and remark      visit or engine shop     Accomplishment
 service (TIS) before the effective     the MEC.                 visit after the MEC      Instructions of SB No.
 date of this AD, and the replacement                            exceeds 10,000 hours     CF6-50 S/B 73-0120,
 spring assembly (P/N 3018-248) had                              TIS, but do not exceed   dated March 21, 2007.
 zero hours TIS.                                                 20,000 hours TIS.
(2) Has more then 10,000 hours TIS...  Replace the spring       The next MEC shop visit  Paragraph 3.A. of the
                                        assembly and remark      or engine shop visit     Accomplishment
                                        the MEC.                 whichever occurs first.  Instructions of SB No.
                                                                                          CF6-50 S/B 73-0120,
                                                                                          dated March 21, 2007.
----------------------------------------------------------------------------------------------------------------

Definition

    (h) For the purpose of this AD, a shop visit is induction of the 
engine or MEC into the shop for any cause.

Installation Prohibition

    (i) After the effective date of the AD, do not install an MEC 
that:
    (1) Has not complied with SB No. CF6-50 S/B 73-0119, Revision 
02, dated March 9, 2007 or earlier revision, or SB No. CF6-50 S/B 
73-0120, dated March 21, 2007, or
    (2) Has not had the CDP restoring spring replaced with a spring 
assembly, P/N 3018-248, or FAA-approved equivalent spring assembly, 
within the previous 10,000 hours of MEC operation.

Alternative Methods of Compliance

    (j) 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

    (k) None.
    (l) Tara Chaidez, Aerospace Engineer, Engine Certification 
Office, FAA, Engine & Propeller Directorate, 12 New England 
Executive Park, Burlington, MA 01803; telephone (781) 238-7773; fax 
(781) 238-7199, for more information about this AD.

Material Incorporated by Reference

    (m) You must use the service information specified in Table 4 to 
perform the replacements required by this AD. The Director of the 
Federal Register approved the incorporation by reference of the 
documents listed in Table 4 of this AD in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51. Contact General Electric Company via GE-
Aviation, Attn: Distributions, 111 Merchant St., Room 230, 
Cincinnati, Ohio 45246; telephone (513) 552-3272; fax (513) 552-
3329, for a copy of this service information. You may review copies 
at the FAA, 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.

                                      Table 4.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
      Service Bulletin No.                 Page                   Revision                      Date
----------------------------------------------------------------------------------------------------------------
CF6-50 S/B 73-0119.............  ALL....................  02.....................  March 9, 2007.
    Total Pages--11
CF6-50 S/B 73-0120.............  ALL....................  Original...............  March 21, 2007.
    Total Pages--11
----------------------------------------------------------------------------------------------------------------


    Issued in Burlington, Massachusetts, on September 7, 2007.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E7-18134 Filed 9-17-07; 8:45 am]
BILLING CODE 4910-13-P