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: https://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 https://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: https:// 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 https://
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: https://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

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