Airworthiness Directives; General Electric Company Turbofan Engines, 76045-76047 [2013-29055]

Download as PDF Federal Register / Vol. 78, No. 241 / Monday, December 16, 2013 / Rules and Regulations 76045 5. Take readings inside each square on the grid or at 1⁄4-inch increments along the ruler and record the results. When taking a thickness reading, rotate the transducer slightly back and forth and experiment with the angle of contact to produce the lowest thickness reading possible. Pay close attention to the A-scan display to assure that the thickness gate is triggering off of maximized backwall echoes. • NOTE: A reading shall not exceed .041 inch. If a reading exceeds .041-inch, repeat steps 13 and 14 of the INSTRUMENT SETUP section before proceeding further. 6. If the A-trace is unsteady or the thickness reading is clearly wrong, adjust the signal gain and/or gate setting to obtain reasonable and steady readings. If any instrument setting is adjusted, repeat steps 13 and 14 of the INSTRUMENT SETUP section before proceeding further. 7. In areas where obstructions are present, take a data point as close to the correct area as possible. • NOTE: The strut wall contains a fabrication bead at approximately 40% of the strut chord. The bead may interfere with accurate measurements in that specific location. 8. A measurement of 0.024-inch or less shall require replacement of the strut prior to further flight. 9. If at any time during testing an area is encountered where a valid thickness measurement cannot be obtained due to a loss of signal strength or quality, the area shall be considered suspect. These areas may have a remaining wall thickness of less than 0.020-inch, which is below the range of this setup, or they may have small areas of localized corrosion or pitting present. The latter case will result in a reduction in signal strength due to the sound being scattered from the rough surface and may result in a signal that includes echoes from the pits as well as the backwall. The suspect area(s) shall be tested with a Maule ‘‘Fabric Tester’’ as specified in Piper SB No. 528D, dated October 19, 1990, or Piper SB No. 910A, dated October 10, 1989. 10. Record the lift strut inspection in the aircraft log book. Issued in Kansas City, Missouri, on November 22, 2013. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service. DEPARTMENT OF TRANSPORTATION [FR Doc. 2013–29679 Filed 12–13–13; 8:45 am] [Docket No. FAA–2013–0879; Directorate Identifier 2013–NE–30–AD; Amendment 39– 17694; AD 2013–24–17] rotor stage 2–5 spools installed. This AD requires removing these spools from service at times determined by a drawdown plan. This AD was prompted by reports of cracks in HPC rotor stage 2–5 spool aft spacer arms. We are issuing this AD to prevent failure of a critical life-limited rotating engine part, which could result in an uncontained engine failure and damage to the airplane. 14 CFR Part 39 RIN 2120–AA64 Airworthiness Directives; General Electric Company Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. pmangrum on DSK3VPTVN1PROD with RULES AGENCY: We are adopting a new airworthiness directive (AD) for General Electric Company (GE) GE90–110B1 and GE90–115B turbofan engines with certain high pressure compressor (HPC) SUMMARY: VerDate Mar<15>2010 13:31 Dec 13, 2013 Jkt 232001 PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 This AD is effective December 31, 2013. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 31, 2013. We must receive comments on this AD by January 30, 2014. DATES: You may send comments, using the procedures found in 14 CFR ADDRESSES: E:\FR\FM\16DER1.SGM 16DER1 ER16DE13.001</GPH> BILLING CODE 4910–13–P Federal Aviation Administration 76046 Federal Register / Vol. 78, No. 241 / Monday, December 16, 2013 / Rules and Regulations 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact General Electric Company, GE Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 45215, phone: (513) 552–3272; email: geae.aoc@ge.com. You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call (781) 238– 7125. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2013– 0879; or in person at the Docket Management Facility 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 Office (phone: 800–647– 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Tomasz Rakowski, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: (781) 238–7735; fax: (781) 238– 7199; email: tomasz.rakowski@faa.gov. SUPPLEMENTARY INFORMATION: pmangrum on DSK3VPTVN1PROD with RULES Discussion We received reports from GE of cracks in the aft spacer arms of several HPC rotor stage 2–5 spools, which occurred before the spools reached their published cyclic life limit. The cracks developed under the seal teeth coating, so they were undetectable by maintenance inspections. This AD requires removal of these spools at a reduced cyclic life threshold, earlier than the published cyclic life limit. VerDate Mar<15>2010 13:31 Dec 13, 2013 Jkt 232001 Because some engines have spools installed that already exceed the reduced cyclic life threshold, this AD provides a drawdown program to remove the spools within risk guidelines without grounding airplanes. This AD also prohibits spare spools that exceed the reduced cyclic life threshold from re-entering service. This AD is intended to prevent HPC rotor stage 2– 5 spool cracks from growing and causing the spool to separate. This condition, if not corrected, could result in failure of a critical life-limited rotating engine part, which could result in an uncontained engine failure and damage to the airplane. Relevant Service Information We reviewed GE Service Bulletin (SB) No. GE90–100 S/B 72–0499, dated August 14, 2013. The SB lists part serial numbers affected by this AD. FAA’s Determination We are issuing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. AD Requirements This AD requires removing certain HPC rotor stage 2–5 spools from service at times determined by a drawdown plan outlined in the paragraph (f) of the compliance section of this AD. Differences Between the AD and the Service Information The schedule for removal of HPC rotor spools in this AD differs from that of GE SB GE90–100 S/B 72–0499, dated August 14, 2013. This AD uses cycles to determine compliance time rather than calendar dates, which are used in the SB, because the unsafe condition is driven by cycles rather than time. FAA’s Justification and Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because of the short compliance times for HPC rotor stage 2–5 spools that are at or over the removal thresholds. Therefore, we find that notice and opportunity for prior public comment are impracticable and that good cause exists for making this amendment effective in less than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety and PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 was not preceded by notice and an opportunity for public comment. However, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number FAA–2013–0879 and Directorate Identifier 2013–NE–30–AD at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. 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 we receive about this AD. Costs of Compliance We estimate that this AD will affect two GE90 engines installed on airplanes of U.S. registry. There is no additional labor cost to comply with this AD. We estimate that the cost of a replacement HPC rotor stage 2–5 spool prorated part is $192,800. Based on these figures, we estimate the total cost of this AD to U.S. operators to be $385,600. 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 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 E:\FR\FM\16DER1.SGM 16DER1 Federal Register / Vol. 78, No. 241 / Monday, December 16, 2013 / Rules and Regulations 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), (3) Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction, and (4) 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2013–24–17 General Electric Company: Amendment 39–17694; Docket No. FAA–2013–0879; Directorate Identifier 2013–NE–30–AD. (a) Effective Date This AD is effective December 31, 2013. pmangrum on DSK3VPTVN1PROD with RULES (b) Affected ADs None. (c) Applicability This AD applies to General Electric Company (GE) GE90–110B1 and GE90–115B turbofan engines with high pressure compressor (HPC) rotor stage 2–5 spools, part numbers (P/Ns) 351–103–106–0, 351–103– 107–0, 351–103–141–0, 351–103–142–0, 351–103–144–0, 351–103–145–0, 351–103– 148–0, 351–103–149–0, and 351–103–151–0, with spool serial numbers listed in paragraph 4, Appendix A of GE Service Bulletin (SB) No. GE90–100 S/B 72–0499, dated August 14, 2013. (d) Unsafe Condition This AD was prompted by reports of cracks in HPC rotor stage 2–5 spool aft spacer arms. We are issuing this AD to prevent failure of a critical life-limited rotating engine part, which could result in an uncontained engine failure and damage to the airplane. VerDate Mar<15>2010 13:31 Dec 13, 2013 Jkt 232001 (e) Compliance Comply with this AD within the compliance times specified, unless already done. (f) Parts Removal Remove from service HPC rotor stage 2–5 spools with serial numbers listed in paragraph 4, Appendix A of GE SB No. GE90–100 S/B 72–0499, dated August 14, 2013, as follows: (1) For spools with fewer than 4,500 cycles since new (CSN) on the effective date of this AD, before exceeding 5,000 CSN. (2) For spools with 4,500 CSN or more but fewer than 5,200 CSN on the effective date of this AD, within an additional 500 cycles in service (CIS) after the effective date of this AD but not to exceed 5,500 CSN. (3) For spools with 5,200 CSN or more but fewer than 5,600 CSN on the effective date of this AD, within an additional 300 CIS after the effective date of this AD but not to exceed 5,800 CSN. (4) For spools with 5,600 CSN or more but fewer than 5,800 CSN on the effective date of this AD, within an additional 200 CIS after the effective date of this AD but not to exceed 5,850 CSN. (5) For spools with 5,800 CSN or more but fewer than 6,000 CSN on the effective date of this AD, within an additional 50 CIS after the effective date of this AD but not to exceed 6,000 CSN. (6) For spools with 6,000 CSN or more on the effective date of this AD, before the next flight. (7) For spools that are not installed on the effective date of this AD and are subsequently installed onto any engine after the effective date of this AD, before exceeding 5,000 CSN. (g) Prohibition Statement After the effective date of this AD, do not install or re-install onto any engine any HPC rotor stage 2–5 spool with a serial number listed in paragraph 4, Appendix A of GE SB No. GE90–100 S/B 72–0499, dated August 14, 2013, that exceeds 5,000 CSN. (h) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, may approve alternative methods of compliance for this AD. Use the procedures found in 14 CFR 39.19 to make your request. (i) Related Information For more information about this AD, contact Tomasz Rakowski, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: (781) 238–7735; fax: (781) 238–7199; email: tomasz.rakowski@faa.gov. (j) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 76047 (i) General Electric Company (GE) Service Bulletin No. GE90–100 S/B 72–0499, dated August 14, 2013. (ii) Reserved. (3) For GE service information identified in this AD, contact General Electric Company, GE Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 45215, phone: (513) 552– 3272; email: geae.aoc@ge.com. (4) You may view this service information at FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call (781) 238–7125. (5) You may view this service information 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. Issued in Burlington, Massachusetts, on November 27, 2013. Carlos A. Pestana, Acting Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2013–29055 Filed 12–13–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0704; Directorate Identifier 2013–NM–074–AD; Amendment 39–17695; AD 2013–24–18] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747–200B, –200C, –200F, –300, and 747SR series airplanes. This AD was prompted by reports of cracks of both lower chords and web on certain outboard struts. This AD requires repetitive inspections for cracking of the lower spar chords and web, web lower spar chord modification, which includes inspections for cracking of the lower spar chords, and repetitive post modification inspections for cracking of the lower spar web and chord; and applicable corrective actions. We are issuing this AD to prevent cracked chords and web on certain outboard struts, which, if the chord severs, could result in reduced structural integrity of the diagonal brace load path and of the strut-to-wing attachment, and SUMMARY: E:\FR\FM\16DER1.SGM 16DER1

Agencies

[Federal Register Volume 78, Number 241 (Monday, December 16, 2013)]
[Rules and Regulations]
[Pages 76045-76047]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-29055]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0879; Directorate Identifier 2013-NE-30-AD; 
Amendment 39-17694; AD 2013-24-17]
RIN 2120-AA64


Airworthiness Directives; General Electric Company Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for General 
Electric Company (GE) GE90-110B1 and GE90-115B turbofan engines with 
certain high pressure compressor (HPC) rotor stage 2-5 spools 
installed. This AD requires removing these spools from service at times 
determined by a drawdown plan. This AD was prompted by reports of 
cracks in HPC rotor stage 2-5 spool aft spacer arms. We are issuing 
this AD to prevent failure of a critical life-limited rotating engine 
part, which could result in an uncontained engine failure and damage to 
the airplane.

DATES: This AD is effective December 31, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 31, 
2013.
    We must receive comments on this AD by January 30, 2014.

ADDRESSES: You may send comments, using the procedures found in 14 CFR

[[Page 76046]]

11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact General 
Electric Company, GE Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 
45215, phone: (513) 552-3272; email: geae.aoc@ge.com. You may view this 
service information at the FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA. For information on the 
availability of this material at the FAA, call (781) 238-7125.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2013-
0879; or in person at the Docket Management Facility 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 Office (phone: 
800-647-5527) is in the ADDRESSES section. Comments will be available 
in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Tomasz Rakowski, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; phone: (781) 238-
7735; fax: (781) 238-7199; email: tomasz.rakowski@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We received reports from GE of cracks in the aft spacer arms of 
several HPC rotor stage 2-5 spools, which occurred before the spools 
reached their published cyclic life limit. The cracks developed under 
the seal teeth coating, so they were undetectable by maintenance 
inspections. This AD requires removal of these spools at a reduced 
cyclic life threshold, earlier than the published cyclic life limit. 
Because some engines have spools installed that already exceed the 
reduced cyclic life threshold, this AD provides a drawdown program to 
remove the spools within risk guidelines without grounding airplanes. 
This AD also prohibits spare spools that exceed the reduced cyclic life 
threshold from re-entering service. This AD is intended to prevent HPC 
rotor stage 2-5 spool cracks from growing and causing the spool to 
separate. This condition, if not corrected, could result in failure of 
a critical life-limited rotating engine part, which could result in an 
uncontained engine failure and damage to the airplane.

Relevant Service Information

    We reviewed GE Service Bulletin (SB) No. GE90-100 S/B 72-0499, 
dated August 14, 2013. The SB lists part serial numbers affected by 
this AD.

FAA's Determination

    We are issuing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

AD Requirements

    This AD requires removing certain HPC rotor stage 2-5 spools from 
service at times determined by a drawdown plan outlined in the 
paragraph (f) of the compliance section of this AD.

Differences Between the AD and the Service Information

    The schedule for removal of HPC rotor spools in this AD differs 
from that of GE SB GE90-100 S/B 72-0499, dated August 14, 2013. This AD 
uses cycles to determine compliance time rather than calendar dates, 
which are used in the SB, because the unsafe condition is driven by 
cycles rather than time.

FAA's Justification and Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because of 
the short compliance times for HPC rotor stage 2-5 spools that are at 
or over the removal thresholds. Therefore, we find that notice and 
opportunity for prior public comment are impracticable and that good 
cause exists for making this amendment effective in less than 30 days.

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 any written data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include the docket number FAA-2013-0879 and 
Directorate Identifier 2013-NE-30-AD at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD because of 
those comments.
    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 we 
receive about this AD.

Costs of Compliance

    We estimate that this AD will affect two GE90 engines installed on 
airplanes of U.S. registry. There is no additional labor cost to comply 
with this AD. We estimate that the cost of a replacement HPC rotor 
stage 2-5 spool prorated part is $192,800. Based on these figures, we 
estimate the total cost of this AD to U.S. operators to be $385,600.

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

    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

[[Page 76047]]

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),
    (3) Will not affect intrastate aviation in Alaska to the extent 
that it justifies making a regulatory distinction, and
    (4) 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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 (AD):

2013-24-17 General Electric Company: Amendment 39-17694; Docket No. 
FAA-2013-0879; Directorate Identifier 2013-NE-30-AD.

(a) Effective Date

    This AD is effective December 31, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to General Electric Company (GE) GE90-110B1 and 
GE90-115B turbofan engines with high pressure compressor (HPC) rotor 
stage 2-5 spools, part numbers (P/Ns) 351-103-106-0, 351-103-107-0, 
351-103-141-0, 351-103-142-0, 351-103-144-0, 351-103-145-0, 351-103-
148-0, 351-103-149-0, and 351-103-151-0, with spool serial numbers 
listed in paragraph 4, Appendix A of GE Service Bulletin (SB) No. 
GE90-100 S/B 72-0499, dated August 14, 2013.

(d) Unsafe Condition

    This AD was prompted by reports of cracks in HPC rotor stage 2-5 
spool aft spacer arms. We are issuing this AD to prevent failure of 
a critical life-limited rotating engine part, which could result in 
an uncontained engine failure and damage to the airplane.

(e) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(f) Parts Removal

    Remove from service HPC rotor stage 2-5 spools with serial 
numbers listed in paragraph 4, Appendix A of GE SB No. GE90-100 S/B 
72-0499, dated August 14, 2013, as follows:
    (1) For spools with fewer than 4,500 cycles since new (CSN) on 
the effective date of this AD, before exceeding 5,000 CSN.
    (2) For spools with 4,500 CSN or more but fewer than 5,200 CSN 
on the effective date of this AD, within an additional 500 cycles in 
service (CIS) after the effective date of this AD but not to exceed 
5,500 CSN.
    (3) For spools with 5,200 CSN or more but fewer than 5,600 CSN 
on the effective date of this AD, within an additional 300 CIS after 
the effective date of this AD but not to exceed 5,800 CSN.
    (4) For spools with 5,600 CSN or more but fewer than 5,800 CSN 
on the effective date of this AD, within an additional 200 CIS after 
the effective date of this AD but not to exceed 5,850 CSN.
    (5) For spools with 5,800 CSN or more but fewer than 6,000 CSN 
on the effective date of this AD, within an additional 50 CIS after 
the effective date of this AD but not to exceed 6,000 CSN.
    (6) For spools with 6,000 CSN or more on the effective date of 
this AD, before the next flight.
    (7) For spools that are not installed on the effective date of 
this AD and are subsequently installed onto any engine after the 
effective date of this AD, before exceeding 5,000 CSN.

(g) Prohibition Statement

    After the effective date of this AD, do not install or re-
install onto any engine any HPC rotor stage 2-5 spool with a serial 
number listed in paragraph 4, Appendix A of GE SB No. GE90-100 S/B 
72-0499, dated August 14, 2013, that exceeds 5,000 CSN.

(h) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, may approve 
alternative methods of compliance for this AD. Use the procedures 
found in 14 CFR 39.19 to make your request.

(i) Related Information

    For more information about this AD, contact Tomasz Rakowski, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: (781) 238-7735; fax: (781) 238-7199; email: 
tomasz.rakowski@faa.gov.

(j) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) General Electric Company (GE) Service Bulletin No. GE90-100 
S/B 72-0499, dated August 14, 2013.
    (ii) Reserved.
    (3) For GE service information identified in this AD, contact 
General Electric Company, GE Aviation, Room 285, 1 Neumann Way, 
Cincinnati, OH 45215, phone: (513) 552-3272; email: geae.aoc@ge.com.
    (4) You may view this service information at FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, 
MA. For information on the availability of this material at the FAA, 
call (781) 238-7125.
    (5) You may view this service information 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.

    Issued in Burlington, Massachusetts, on November 27, 2013.
Carlos A. Pestana,
Acting Assistant Directorate Manager, Engine & Propeller Directorate, 
Aircraft Certification Service.
[FR Doc. 2013-29055 Filed 12-13-13; 8:45 am]
BILLING CODE 4910-13-P
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