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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

CFR Citation: 14 CFR Part 39

Docket ID: [Docket No. 2003-NE-40-AD; Amendment 39-13407; AD 2003-26-09]

RIN ID: RIN 2120-AA64

NOTICE: RULES

ACTION: Airworthiness directives:

DOCUMENT ACTION: Final rule; request for comments.

SUBJECT CATEGORY: Airworthiness Directives; Pratt & Whitney PW4074, PW4074D, PW4077, PW4077D, PW4084, PW4084D, PW4090, PW4090D, PW4090-3, and PW4098 Turbofan Engines

DATES: Effective December 3, 2003. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of December 3, 2003.

We must receive any comments on this AD by March 1, 2004.

DOCUMENT SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for Pratt & Whitney PW4074, PW4074D, PW4077, PW4077D, PW4084, PW4084D, PW4090, PW4090D, PW40903, and PW4098 turbofan engines. That AD requires initial and repetitive visual and borescope inspections of the No. 3 bearing weep tube and turbine exhaust case (TEC), and removal of the high pressure turbine (HPT) assembly and replacement of any heat distressed HPT assembly hardware if oil wetting or staining is found.

This ad requires the same actions. This AD results from the finding of a significant reference error in one of the borescope inspection compliance paragraphs. We are issuing this AD to prevent thermal distressed HPT assembly hardware from remaining in service, which could result in a cracked HPT stage 1 disk or HPT stage 12 air seal and an uncontained engine failure.

SUMMARY: Pratt & Whitney,

SUPPLEMENTAL INFORMATION

On October 24, 2003, the FAA issued AD 2003- 2209, Amendment 3913357 (68 FR 62228, November 3, 2003). That AD requires:
[sbull] Borescope inspection of the No. 3 bearing weep tube, on engines with high oil consumption that troubleshooting procedures fail to determine the source of oil loss.
[sbull] For all engines, initial and repetitive visual inspections of the turbine exhaust case (TEC) in the vicinity of the No. 3 bearing oil vent tube for evidence of oil wetting or staining. If the vent tube borescope inspection is unsuccessful due to tube blockage, that AD also requires borescope inspections of the HPT assembly for oil wetting or staining.
[sbull] Removal of the HPT assembly and replacement of any heat distressed HPT assembly hardware if oil wetting or staining is found.

That AD is the result of engine HPT assembly hardware being damaged as a result of thermal distress from oil igniting after leaking from the No. 3 bearing compartment. That condition, if not corrected, could result in a cracked HPT stage 1 disk or HPT stage 12 air seal and an uncontained engine failure.

Actions Since AD 20032209 Was Issued

Since that AD was issued, a comment was received that revealed an error in the compliance section. We have considered that comment. Incorrect Inspection Reference

One commenter states that paragraph (i)(3) of the AD contains an incorrect reference. In that paragraph, the wording ``since performing the visual inspection of the TEC specified in paragraph (h)(1) of this AD'', is misleading as it should be referencing borescope inspection and not visual inspection.

We agree. Therefore, we have corrected the wording to read ``since performing the borescope inspection of the No. 3 bearing oil vent tube specified in paragraph (i)(1) of this AD'.

AD Effectivity

The effective date of this AD is the same as AD 20032209. We discussed the reference error in AD 20032209 with the one U.S. operator, and conclude that there is no adverse impact from using the same effective date.

Relevant Service Information

We have reviewed and approved the technical contents of Pratt & Whitney Alert Service Bulletin (ASB) No. PW4G112A72257, Revision 1, dated August 22, 2003, that describes procedures for:
[sbull] Borescope inspection of the No. 3 bearing weep tube, on engines with high oil consumption that troubleshooting procedures fail to determine the source of oil loss.
[sbull] For all engines, initial and repetitive visual inspections of the TEC, in the vicinity of the No. 3 bearing oil vent tube assembly and borescope inspections of the No. 3 bearing oil vent tube assembly, for evidence of oil wetting or staining.
[sbull] Borescope inspection of the HPT assembly for evidence of oil wetting or staining if the borescope inspection of the No. 3 bearing oil vent tube assembly is unsuccessful due to blockage. [sbull] Removal of the engine if oil wetting or staining is found. Differences Between This AD and the Service Information

Although ASB No. PW4G112A72257, Revision 1, dated August 22, 2003, requires removal of the engine from service if oil wetting or staining is found, this AD requires removal of the HPT assembly and replacement of any heat distressed HPT assembly hardware if oil wetting or staining is found.

FAA's Determination and Requirements of This AD

The unsafe condition described previously is likely to exist or develop on other Pratt & Whitney PW4074,
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PW4074D, PW4077, PW4077D, PW4084, PW4084D, PW4090, PW4090D, PW40903, and PW4098 turbofan engines of the same type design. We are issuing this AD to prevent thermal distressed HPT assembly hardware to remain in service, which could result in a cracked HPT stage 1 disk or HPT stage 12 air seal and an uncontained engine failure. This AD requires: [sbull] Borescope inspection of the No. 3 bearing weep tube on engines with high oil consumption that troubleshooting procedures fail to determine the source of oil loss.
[sbull] For all engines, initial and repetitive visual inspections of the TEC, in the vicinity of the No. 3 bearing oil vent tube assembly and borescope inspections of the No. 3 bearing oil vent tube assembly, for evidence of oil wetting or staining.
[sbull] Borescope inspections of the HPT assembly for oil wetting or staining, if the vent tube borescope inspection is unsuccessful due to tube blockage.
[sbull] Removal of the HPT assembly and replacement of any heat distressed HPT assembly hardware if oil wetting or staining is found.

You must use the service information described previously to perform the actions required by this AD.

FAA's Determination of the Effective Date

Since an unsafe condition exists that requires the immediate adoption of this AD, we have found that notice and opportunity for public comment before issuing this AD are impracticable, and that good cause exists for making this amendment effective in less than 30 days. Changes to 14 CFR Part 39Effect on the AD

On July 10, 2002, we issued a new version of 14 CFR part 39 (67 FR 47998, July 22, 2002), which governs our AD system. This regulation now includes material that relates to special flight permits, alternative methods of compliance, and altered products. This material previously was included in each individual AD. Since this material is included in 14 CFR part 39, we will not include it in future AD actions. Interim Action

These actions are interim actions and we may take further rulemaking actions in the future.

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 submit any written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES. Include ``AD Docket No. 2003NE40AD'' in the subject line of your comments. If you want us to acknowledge receipt of your mailed comments, send us a selfaddressed, stamped postcard with the docket number written on it; we will datestamp your postcard and mail it back to you. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify it. If a person contacts us verbally, and that contact relates to a substantive part of this AD, we will summarize the contact and place the summary in the docket. We will consider all comments received by the closing date and may amend the AD in light of those comments.

We are reviewing the writing style we currently use in regulatory documents. We are interested in your comments on whether the style of this document is clear, and your suggestions to improve the clarity of our communications with you. You may get more information about plain language at http://www .plainlanguage.gov.

Examining the AD Docket

You may examine the AD Docket (including any comments and service information), by appointment, between 8:00 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. See ADDRESSES for the location.

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 the regulation:

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. 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 by sending a request to us at the address listed under ADDRESSES. Include ``AD Docket No. 2003NE40AD'' in your request.

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 Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (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 removing Amendment 3913357 (68 FR 62228, November 3, 2003), and by adding a new airworthiness directive, Amendment 3913407, to read as follows:
20032609 Pratt & Whitney: Amendment 3913407. Docket No. 2003NE 40AD. Supersedes AD 20032209, Amendment 3913357.
Effective Date
(a) The effective date of this AD is the same as AD 20032209, which is December 3, 2003.
Affected ADs
(b) This AD supersedes AD 20032209.
Applicability
(c) This AD applies to Pratt & Whitney PW4074, PW4074D, PW4077, PW4077D, PW4084, PW4084D, PW4090, PW4090D, PW40903, and PW4098 turbofan engines. These engines are installed on, but not limited to, Boeing 777 series airplanes.
Unsafe Condition
(d) This AD results from the finding of a significant reference error in one of the borescope inspection compliance paragraphs of AD 20032209. This AD also results from reports of engine high pressure turbine (HPT) assembly hardware being damaged as a result of thermal distress from oil igniting after leaking from the No. 3 bearing compartment. We are issuing this AD to prevent thermal distressed HPT assembly hardware from remaining in service, which could result in a cracked HPT stage 1 disk and HPT stage 12 air seal and an uncontained engine failure.
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.
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Credit for Previous Inspections
(f) Inspections performed before the effective date of this AD, using AD 20032209 or Pratt & Whitney Alert Service Bulletin (ASB) No. PW4G112A72257, dated June 30, 2003, may be counted toward satisfying the initial and repetitive inspection requirements of paragraphs (g) through (k) of this AD.
Borescope Inspection of Engines With High Oil Consumption
(g) For engines with high oil consumption that troubleshooting procedures fail to determine the source of oil loss, borescope inspect No. 3 bearing oil vent tube assembly and or HPT assembly within 100 cyclesinservice (CIS) of the high oil consumption event, using paragraphs (g)(1) through (g)(2) of this AD.
Information on troubleshooting engines with high oil consumption can be found in Boeing 777 Fault Isolation Manual (FIM), section 7105, Task 830. See paragraph (l) of this AD for a definition of high oil consumption.
(1) Borescopeinspect the No. 3 bearing oil vent tube assembly for evidence of oil wetting or staining. Follow Step 3, paragraphs 1. through 1.A.(8)(a) of Accomplishment Instructions of Pratt & Whitney ASB No. PW4G112A72257, Revision 1, dated August 22, 2003. (2) If the No. 3 bearing oil vent tube is blocked and attempts to clear it are unsuccessful, borescopeinspect the HPT assembly, following Step 4, paragraphs 1. through 1.B(14) of Accomplishment Instructions of ASB No. PW4G112A72257, Revision 1, dated August 22, 2003.
(3) Remove the HPT assembly within 100 CIS of the high oil consumption event if evidence of oil wetting or staining is found in the No. 3 bearing oil vent tube or on the HPT first stage disk. (4) Replace any heat distressed HPT assembly hardware if oil wetting or staining is found.
Turbine Exhaust Case (TEC) Inspections Of All Engines
(h) Inspect the TEC of all engines, within 500 hoursinservice (HIS) after the effective date of this AD as follows:
(1) Visually inspect the TEC in the vicinity of the No. 3 bearing oil vent tube assembly for evidence of oil wetting or staining, using Figure 2 of Pratt & Whitney ASB No. PW4G112A72 257, Revision 1, dated August 22, 2003, for location of inspection. (2) If evidence of oil wetting or staining is found at the TEC, borescopeinspect the No. 3 bearing oil vent tube assembly within 100 additional CIS, to confirm the oil is from the vent tube. Follow Step 1, paragraphs 1.B. through 1.D.(8)(a) of Accomplishment Instructions of Pratt & Whitney ASB No. PW4G112A72257, Revision 1, dated August 22, 2003.
(3) If the No. 3 bearing oil vent tube is blocked and attempts to clear it are unsuccessful, borescopeinspect the HPT assembly following Step 4, paragraphs 1. through 1.B.(14) of Accomplishment Instructions of ASB No. PW4G112A72257, Revision 1, dated August 22, 2003.
(4) Remove the HPT assembly within 100 CIS since performing the visual inspection of the TEC specified in paragraph (h)(1) of this AD, if evidence of oil wetting or staining is found in the No. 3 bearing oil vent tube or found on the HPT first stage disk. (5) Replace any heat distressed HPT assembly hardware if oil wetting or staining is found.
Borescope Inspections of All Engines
(i) Borescopeinspect the No. 3 bearing oil vent tube assembly of all engines at or before accumulating 600 CIS or 2,000 HIS, whichever occurs first, after the effective date of this AD, as follows:
(1) Borescopeinspect the No. 3 bearing oil vent tube assembly for evidence of oil wetting or staining. Follow Step 2, paragraphs 1. through 1.A.(8) of Accomplishment Instructions of Pratt & Whitney ASB No. PW4G112A72257, Revision 1, dated August 22, 2003.
(2) If the No. 3 bearing oil vent tube is blocked and attempts to clear it are unsuccessful, borescopeinspect the HPT assembly following Step 4, paragraphs 1. through 1.B.(14) of Accomplishment Instructions of ASB No. PW4G112A72257, Revision 1, dated August 22, 2003.
(3) Remove the HPT assembly within 100 CIS since performing the borescope inspection of the No. 3 bearing oil vent tube specified in paragraph (i)(1) of this AD, if evidence of oil wetting or staining is found in the No. 3 bearing oil vent tube or found on the HPT first stage disk.
(4) Replace any heat distressed HPT assembly hardware if oil wetting or staining is found.
Repetitive Inspections of All Engines
(j) Repeat the inspections of the TEC of all engines by following paragraphs (h)(1) through (h)(3) of this AD, at intervals not to exceed 500 HIS since last visual check of the TEC, and disposition the engine as specified in paragraphs (h)(4) through (h)(5) of this AD.
(k) Repeat borescope inspections of all engines by following paragraphs (i)(1) through (i)(2) of this AD, at intervals not to exceed 600 CIS or 2,000 HIS since last borescope inspection of the No. 3 oil vent tube, and disposition the engine as specified in paragraphs (i)(3) through (i)(4) of this AD.
Definition
(l) For the purposes of this AD, high oil consumption is defined as an engine consuming more than 0.5 quarts of oil per hour, as provided in the Boeing 777 FIM.
Alternative Methods of Compliance
(m) 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.
Material Incorporated by Reference
(n) You must follow Pratt & Whitney Alert Service Bulletin specified in Table 1 to perform the inspections required by this AD. The Director of the Federal Register approved the incorporation by reference of this service bulletin as of December 3, 2003 (68 FR 62228, November 3, 2003) in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You can get a copy from Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone (860) 5657700; fax (860) 565 1605. You may review copies at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC.
Table 1Incorporation by Reference Alert service bulletin No. Page No. Revision Date PW4G112A72257......................... 15 1.......................... August 22, 2003. 67 Original................... June 30, 2003. 8 1.......................... August 22, 2003. 9 Original................... June 30, 2003. 10 1.......................... August 22, 2003. 11 Original................... June 30, 2003. 12 1.......................... August 22, 2003. 1322 Original................... June 30, 2003.

Total Pages: 22
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Related Information
(o) Boeing 777 Fault Isolation Manual, section 7105, Task 830, pertains to high oil consumption troubleshooting procedures referred to in this AD.

Issued in Burlington, Massachusetts, on December 23, 2003. Mark C. Fulmer,
Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service.
[FR Doc. 0332156 Filed 123003; 8:45 am]
BILLING CODE 491013P

FOR FURTHER INFORMATION CONTACT Keith Lardie, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 018035299; telephone (781) 2387189; fax (781) 2387199.