Airworthiness Directives; Pratt & Whitney JT8D-209, -217, -217C, and -219 Turbofan Engines

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0883; Directorate Identifier 97-ANE-08; Amendment 39-16237; AD 97-17-04R1]

RIN 2120-AA64

Airworthiness Directives; Pratt & Whitney JT8D-209, -217, -217C, and -219 Turbofan Engines

AGENCY:

Federal Aviation Administration (FAA), Department of Transportation (DOT).

ACTION:

Final rule.

SUMMARY:

The FAA is revising an existing airworthiness directive (AD) for Pratt & Whitney JT8D-209, -217, -217C, and -219 turbofan engines with front compressor front hub (fan hub), part number (P/N) 5000501-01 installed. That AD currently requires cleaning the front compressor front hubs (fan hubs), initial and repetitive eddy current (ECI) and fluorescent penetrant inspections (FPI) of tierod and counterweight holes for cracks, removal of bushings, cleaning and ECI and FPI of bushed holes for cracks and, if necessary, replacement with serviceable parts. In addition, that AD currently requires reporting the findings of cracked fan hubs and monthly reports of the number of inspections completed. This AD requires the same actions, except for the monthly reporting of the number of completed inspections. This AD results from the FAA determining that it has collected a sufficient amount of data since issuing AD 97-17-04 and that therefore, it no longer needs the monthly reporting of the number of completed inspections. We are issuing this AD to prevent fan hub failure due to tierod, counterweight, or bushed hole cracking, which could result in an uncontained engine failure and damage to the airplane.

DATES:

This AD becomes effective April 22, 2010. The Director of the Federal Register previously approved the incorporation by reference of the publications listed in the regulations as of March 5, 1997 (62 FR 4902).

ADDRESSES:

You can get the service information identified in this AD from Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone (860) 565-8770; fax (860) 565-4503.

The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-0001.

FOR FURTHER INFORMATION CONTACT:

Kevin Dickert, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail:

kevin.dickert@faa.gov;

telephone (781) 238-7117; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:

The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to Pratt & Whitney JT8D-209, -217, -217C, and -219 turbofan engines with front compressor front hub (fan hub), P/N 5000501-01 installed. We published the proposed AD in the

Federal Register

on December 21, 2009 (74 FR 67831). That action proposed to require cleaning the front compressor front hubs (fan hubs), initial and repetitive ECI and FPI of tierod and counterweight holes for cracks, removal of bushings, cleaning and ECI and FPI of bushed holes for cracks and, if necessary, replacement with serviceable parts. That action also proposed to eliminate the monthly reporting of the number of completed inspections.

Examining the AD Docket

You may examine the AD docket on the Internet at

http://www.regulations.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 one comment received. The commenter supports the proposal.

Conclusion

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

Costs of Compliance

We estimate that this AD revision will affect 1,170 JT8D-209, -217, -217C, and -219 turbofan engines installed on airplanes of U.S. registry. We estimate that it will take four work-hours per engine to complete one inspection of the fan hub at piece-part exposure. The average labor rate is $80 per work-hour. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $374,400.

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

.

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 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 removing Amendment 39-10106 (62 FR 45152, August 26, 1997), and by adding a new airworthiness directive, Amendment 39-16237, to read as follows:

97-17-04R1 Pratt & Whitney:

Amendment 39-16237. Docket No. FAA-2009-0883; Directorate Identifier 97-ANE-08.

Effective Date

(a) This airworthiness directive (AD) becomes effective April 22, 2010.

Affected ADs

(b) This AD revises AD 97-17-04, Amendment 39-10106.

Applicability

(c) This AD applies to Pratt & Whitney (PW) JT8D-209, -217, -217C, and -219 turbofan engines with front compressor front hub (fan hub), part number (P/N) 5000501-01, installed. These engines are installed on, but not limited to, McDonnell Douglas MD-80 series airplanes.

Unsafe Condition

(d) This AD results from the FAA determining that it has collected a sufficient amount of data since issuing AD 97-17-04 and that therefore, it no longer needs the monthly reporting of the number of completed inspections. We are issuing this AD to prevent fan hub failure due to tierod, counterweight, or bushed hole cracking, which could result in an uncontained engine failure and 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) Inspect fan hubs for cracks in accordance with the Accomplishment Instructions, Paragraph A, Part 1, and, if applicable, Paragraph B, of PW Alert Service Bulletin (ASB) No. A6272, dated September 24, 1996, as follows:

(1) For fan hubs identified by serial numbers (S/Ns) in Table 2 of this AD, after the fan hub has accumulated more than 4,000 cycles-since-new (CSN), as follows:

(i) Initially inspect within 315 cycles-in-service (CIS) from the effective date of this AD, or 4,315 CSN, whichever occurs later.

(ii) Thereafter, re-inspect after accumulating 2,500 CIS since last inspection, but not to exceed 10,000 CIS since last inspection.

(2) For fan hubs identified by S/Ns in Appendix A of PW ASB No. A6272, dated September 24, 1996, after the fan hub has accumulated more than 4,000 CSN, as follows:

(i) Select an initial inspection interval from Table 1 of this AD, and inspect accordingly.

Table 1—Inspections

Initial inspection

Re-inspection

(A) Within 1,050 CIS after the effective date of AD 97-02-11, March 5, 1997, or prior to accumulating 5,050 CSN, whichever occurs later;

After accumulating 2,500 CIS since-last-inspection, but not to exceed 6,000 CIS since-last-inspection.

OR

OR

(B) Within 990 CIS after the effective date of AD 97-02-11, March 5, 1997, or prior to accumulating 4,990 CSN, whichever occurs later;

After accumulating 2,500 CIS since-last-inspection, but not to exceed 8,000 CIS since-last-inspection.

OR

OR

(C) Within 965 CIS after the effective date of AD 97-02-11, March 5, 1997, or prior to accumulating 4,965 CSN, whichever occurs later.

After accumulating 2,500 CIS since-last-inspection, but not to exceed 10,000 CIS since-last-inspection.

Table 2—Hubs With Traveler Notations

M67663

M67802

P66880

S25545

P66747

R33099

S25292

M67671

M67812

P66885

S25558

P66756

R33107

S25299

M67675

M67826

R32732

S25564

P66800

R33113

S25301

M67681

M67829

R32733

S25598

P66814

R33124

S25302

M67685

M67830

R32735

S25618

P66819

R33131

S25308

M67686

M67831

R32740

S25621

P66831

R33132

S25312

M67687

M67832

R32741

S25637

R32767

R33133

S25316

M67697

M67834

R32810

S25640

R32787

R33136

S25323

M67700

M67843

R32849

T50693

R32792

R33152

S25334

M67706

M67849

R32850

T50752

R32795

R33157

S25335

M67710

M67858

S25222

T50785

R32796

R33163

S25337

M67712

M67866

S25464

T50791

R32800

R33165

S25344

M67713

M67868

S25481

T50792

R32807

R33168

S25369

M67714

M67869

S25483

T50819

R32856

R33171

S25377

M67715

M67872

S25484

T50823

R32860

R33173

S25378

M67716

M67888

S25486

T50827

R32870

R33180

S25381

M67717

N71771

S25488

T50874

R32883

R33181

S25394

M67722

N71804

S25489

T50875

R32905

R33189

S25399

M67723

N71806

S25490

T51058

R32926

R33194

S25402

M67725

N71810

S25491

T51104

R32930

R33198

S25406

M67726

N71811

S25492

R32952

R33201

S25411

M67730

N71875

S25494

R32964

R33202

S25413

M67731

N71876

S25495

R32966

R33207

S25414

M67746

N71921

S25497

R32971

S25193

S25415

M67751

N71965

S25498

R32976

S25195

S25418

M67753

N72062

S25499

R32981

S25207

S25419

M67764

N72126

S25500

R32990

S25208

S25421

M67765

N72152

S25501

R32994

S25221

S25422

M67784

N72162

S25502

R33000

S25229

S25430

M67791

N72207

S25505

R33004

S25238

S25437

M67792

N72216

S25506

R33040

S25246

S25439

M67793

N72219

S25507

R33055

S25248

S25449

M67794

N72242

S25508

R33059

S25250

R33186

M67795

P66693

S25509

R33077

S25256

S25528

M67796

P66695

S25514

R33080

S25262

M67797

P66696

S25529

R33082

S25268

M67798

P66698

S25532

R33086

S25278

M67799

P66699

S25541

R33087

S25287

M67800

P66737

S25543

R33089

S25288

M67801

P66753

S25544

R33090

(ii) Thereafter, re-inspect at intervals that correspond to the selected inspection interval.

(3) If a fan hub is identified in both Table 2 of this AD and Appendix A of PW ASB No. A6272, dated September 24, 1996, inspect in accordance with paragraph (f)(1) or (f)(2) of this AD, whichever occurs first.

(4) For fan hubs with S/Ns not listed in Table 2 of this AD or in Appendix A of PW ASB No. A6272, dated September 24, 1996, after the fan hub has accumulated more than 4,000 CSN, inspect the next time the fan hub is in the shop at piece-part level, but not to exceed 10,000 CIS after March 5, 1997.

(5) Prior to further flight, remove from service fan hubs found cracked or that exceed the bushed hole acceptance criteria described in PW ASB No. A6272, dated September 24, 1996.

Reporting Requirements

(g) Report findings of cracked fan hubs using Accomplishment Instructions, Paragraph F, of Attachment 1 to PW ASB No. A6272, dated September 24, 1996, within 48 hours to Kevin Dickert, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238-7117; fax (781) 238-7199; e-mail:

kevin.dickert@faa.gov.

(h) The Office of Management and Budget (OMB) has approved the reporting requirements and assigned OMB control number 2120-0056.

Alternative Methods of Compliance

(i) The Manager, Engine Certification Office, FAA, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Alternate methods of compliance approved in accordance with AD 97-17-04 are approved as alternate methods of compliance with this AD.

Material Incorporated by Reference

(j) You must use the Pratt & Whitney service information specified in Table 3 of this AD to perform the inspections required by this AD. The Director of the Federal Register previously approved the incorporation by reference of the documents listed in the following Table 3 as of March 5, 1997 (62 FR 4902) in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone (860) 565-8770; fax (860) 565-4503, for a copy of this service information. You may review copies at the FAA, New England Region, 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:

http://www.archives.gov/federal-register/cfr/ibr-locations.html.

Table 3—Incorporation by Reference

Service information

Page

Revision

Date

Alert Service Bulletin No. A6272

All

Original

September 24, 1996.

Total Pages: 21

Non-Destruct Inspection Procedure No. NDIP-892

All

A

September 15, 1996.

Total Pages: 30

Attachment I

All

A

September 15, 1996.

Total Pages: 4

Issued in Burlington, Massachusetts, on March 9, 2010.

Peter A. White,

Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service.

[FR Doc. 2010-5778 Filed 3-17-10; 8:45 am]

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