Costs of Compliance

We estimate that this proposed AD would affect 94 engines installed on airplanes of U.S. registry. We also estimate that it would take about 101 workhours per engine to perform the proposed actions, and that the average labor rate is $80 per workhour. The prorated cost due to a life reduction from 12,000 CSN to 9,370 CSN for the front turbine hub is about $66,460 per engine. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $6,247,240. 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
[[Page 57503]]
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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 the proposed AD:

1. Is not a ``significant regulatory action'' under Executive Order 12866;

2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and

3. Would 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 regulatory evaluation of the estimated costs to comply with this proposed AD. You may get a copy of this summary at the address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment

Under the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 14 CFR part 39 as follows:

PART 39AIRWORTHINESS DIRECTIVES

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]

2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive:
Pratt & Whitney: Docket No. FAA200729110; Directorate Identifier 2007NE35AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by December 10, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Pratt & Whitney (PW) PW4090 and PW40903 turbofan engines with front turbine hub part number (P/N) 53L601, installed. These engines are installed on, but not limited to, Boeing 777200 series and 777300 series airplanes.
Unsafe Condition
(d) This AD results from PW updating the lowcyclefatigue (LCF) life analysis for front turbine hubs, P/N 53L601. We are proposing this AD to prevent an uncontained failure of the front turbine hub, resulting in an inflight engine shutdown and possible damage to the airplane.
Compliance
(e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done.
(f) Remove front turbine hubs, P/N 53L601, from service and install a serviceable front turbine hub, as follows:
(1) For front turbine hubs that have accumulated fewer than 3,370 cyclessincenew (CSN) on the effective date of this AD, remove from service before the hub accumulates 9,370 CSN.
(2) For front turbine hubs that have accumulated 3,370 or more CSN, but fewer than 9,370 CSN on the effective date of this AD, do the following:
(i) For engines that have an engine shop visit (ESV) before the front turbine hub accumulates 9,370 CSN, remove the front turbine hub from service before the hub accumulates 9,370 CSN.
(ii) For engines that do not have an ESV before the front turbine hub accumulates 9,370 CSN, remove the front turbine hub from service at the next ESV, or before the hub accumulates an additional 6,000 cyclessincelast high pressure turbine overhaul, whichever occurs first, but not to exceed 12,000 CSN.
(3) For front turbine hubs that have accumulated 9,370 or more CSN on the effective date of this AD, remove the front turbine hub from service at the next ESV, or before the hub accumulates 12,000 CSN, whichever occurs first.
(g) This AD establishes a new reduced published life limit for the PW4090 turbine front hub, P/N 53L601, of 9,370 CSN, which is published in Chapter 05, Time Limits Section 051001, of the PW4000 Series Engine Shop Manual, P/N 51A751. The following conditions also apply:
(1) Except as provided in paragraphs (f)(2)(ii) and (f)(3) of this AD, no alternative retirement lives may be approved for the PW4090 front turbine hub, P/N 53L601.
(2) After the effective date of this AD, PW4090 front turbine hub, P/N 53L601, may not be installed or reinstalled on an engine if the hub has accumulated more than 9,370 CSN.
(h) For the purposes of this AD, an ``engine shop visit'' is: (1) The induction of an engine into the shop for maintenance involving the separation of any major mating engine flange, except that for the separation of engine flanges solely for the purposes of transportation without subsequent engine maintenance does not constitute an engine shop visit; or
(2) The removal of a disk or spool.
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) Information on an approved front turbine hub rework procedure for increased life is available from the manufacturer. See Pratt & Whitney Service Bulletin PW4G11272290, dated July 2, 2007. The reworked front turbine hub, P/N 53L601001, is not affected by this AD.
(k) Contact Mark Riley, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; email: mark.riley@faa.gov, telephone (781) 2387758; fax (781) 2387199, for more information about this AD.

Issued in Burlington, Massachusetts, on October 2, 2007. Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service.
[FR Doc. E719927 Filed 10907; 8:45 am]
BILLING CODE 491013P

FOR FURTHER INFORMATION CONTACT Mark Riley, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; email:
mark.riley@faa.gov, telephone (781) 2387758; fax (781) 2387199.