SUPPLEMENTARY INFORMATION:

The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to CFM International CFM56-5 and -5B series turbofan engines. We published the proposed AD in the Federal Register on June 16, 2006 (71 FR 34852). That action proposed to require, for an increased population of affected EGT harnesses:

• EGT harness replacement or the establishment of an EGT baseline and trend monitoring; and
• Replacement, if necessary, of certain EGT harnesses and EGT couplings as soon as a slow and continuous EGT drift downward is noticed after the effective date of that AD.

Examining the AD Docket

You may examine the docket that contains the AD, any comments received, and any final disposition in person at the Docket Management Facility Docket Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647-5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in ADDRESSES . Comments will be available in the AD docket shortly after the DMS receives them.

Comments

We provided the public the opportunity to participate in the development of this AD. We received no comments on the proposal or on the determination of the cost to the public.

Conclusion

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

Docket Number Change

We are transferring the docket for this AD to the Docket Management System as part of our on-going docket management consolidation efforts. The new Docket No. is FAA-2007-27112. The old Docket No. became the Directorate Identifier, which is 2001-NE-49-AD. This AD might get logged into the DMS docket, ahead of the previously collected documents from the old docket file, as we are in the process of sending those items to the DMS.

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 .

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:

1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

2. The FAA amends § 39.13 by removing Amendment 39-13020 ( 68 FR 3171, January 23, 2003) and by adding a new airworthiness directive, ( printed page 6458) Amendment 39-14926, to read as follows:

2007-03-15 CFM International: Amendment 39-14926; Docket No. FAA-2007-27112; Directorate Identifier 2001-NE-49-AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective March 19, 2007.

Affected ADs

(b) This AD supersedes AD 2003-02-04, Amendment 39-13020.

Applicability

(c) This AD applies to CFM International CFM56-5 and -5B series turbofan engines:

(1) With an exhaust gas temperature (EGT) upper harness part number (P/N) CA170-00, with a serial number (SN):

(i) Listed in Table 1, Table 4, or Table 5 of CFM56 Service Bulletin (SB) No. CFM56-5B S/B 77-0008, Revision 3, dated April 4, 2005, or

(ii) Listed in Table 1 or Table 4 of CFM56 SB No. CFM56-5 S/B 77-0020, Revision 3, dated April 4, 2005.

(2) With an EGT lower harness P/N CA171-00, with a SN:

(i) Listed in Table 2, Table 4, or Table 5 of CFM56 SB No. CFM56-5B S/B 77-0008, Revision 3, dated April 4, 2005; or

(ii) Listed in Table 2 or Table 4 of CFM56 SB No. CFM56-5 S/B 77-0020, Revision 3, dated April 4, 2005.

(3) With an EGT coupling P/N CA172-02 with a SN:

(i) Listed in Table 3, Table 4, or Table 5 of CFM56 Service Bulletin (SB) No. CFM56-5B S/B 77-0008, Revision 3, dated April 4, 2005, or

(ii) Listed in Table 3 or Table 4 of CFM56 SB No. CFM56-5 S/B 77-0020, Revision 3, dated April 4, 2005.

(4) These engines are installed on, but not limited to Airbus Industrie A318, A319, A320, and A321 airplanes.

Unsafe Condition

(d) This AD results from CFM International adding subsequently certified engine models, CFM56-5B3/P1, CFM56-5B3/2P1, CFM56-5B4/P1, and CFM56-5B4/2P1, to the list of engines that could have affected harnesses installed, and increasing the population of affected EGT harnesses. We are issuing this AD to prevent unexpected deterioration of critical rotating engine parts due to higher than desired engine operating EGTs.

Compliance

(e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done.

(f) If an EGT harness or EGT coupling has a serial number that is followed by the letter “W”, no further action is required for that part.

(g) For affected EGT harnesses and EGT couplings identified using paragraph (c) of this AD, with fewer than 3,000 engine flight hours-since-installation, do the following:

(1) Replace affected EGT harnesses and EGT couplings, not being trend monitored, with serviceable parts within 500 flight hours after the effective date of this AD; or

(2) After the effective date of this AD:

(i) Review the smooth data EGT trend via the System for Analysis of Gas Turbine Engines (SAGE), or equivalent, since the affected components were first installed on the current engine.

(ii) Continue this trend monitoring for the affected EGT harnesses and EGT couplings to ensure that the system does not show a minimum of 30 °C downward (i.e. cooler) indication, or more, without a corresponding change in other associated engine parameters such as N1 (LPT rotor speed), N2 (HPT rotor speed), and fuel flow.

(iii) Provided that there is sufficient, actual EGT margin to do so, replace the EGT harnesses and EGT couplings within 100 flight hours after they have been determined to be defective.

(iv) Continue to monitor the EGT indications for 3,000 engine flight hours since the first installation on the current engine.

Terminating Action

(h) Any of the following three conditions is terminating action for the trend monitoring requirements specified in paragraphs (g)(2)(i) through (g)(2)(iv) of this AD:

(1) Replacing an EGT harness and EGT coupling with a serviceable part, or

(2) Replacing an EGT harness and EGT coupling with an EGT harness and EGT coupling that has a letter “W” following the SN, or

(3) Accumulating 3,000 engine flight hours on an EGT harness and EGT coupling.

Alternative Methods of Compliance

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

Related Information

(j) Airworthiness directive No. F-2003-001 R2, dated June 8, 2005, which is from the Direction Generale de L'Aviation Civile airworthiness authority for France, also addresses the subject of this AD.

(k) Contact James Rosa, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238-7152; fax (781) 238-7199; e-mail: james.rosa@faa.gov for more information about this AD.

Material Incorporated by Reference

(l) You must use the CFM56 Service Bulletin Tables specified in the compliance of this AD, to determine applicability to this AD. The following Table 1 lists the Service Bulletins. The Director of the Federal Register approved the incorporation by reference of the documents listed in Table 1 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact CFM International, Technical Publications Department, 1 Neumann Way, Cincinnati, OH 45215; telephone (513) 552-2800; fax (513) 552-2816, for a copy of this service information. You may review copies 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.

72 FR 6457