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

Federal Register: December 21, 2009 (Volume 74, Number 243)

Proposed Rules

Page 67831-67834

From the Federal Register Online via GPO Access [wais.access.gpo.gov]

DOCID:fr21de09-14

Page 67831

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 14 CFR Part 39

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

RIN 2120-AA64

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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

SUMMARY: The FAA proposes to revise 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 proposed AD would require the same actions, except for the monthly reporting of the number of completed inspections. This proposed 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 proposing this AD revision 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: We must receive any comments on this proposed AD by February 19, 2010.

ADDRESSES: Use one of the following addresses to comment on this proposed AD.

Federal eRulemaking Portal: Go to http:// www.regulations.gov and follow the instructions for sending your comments electronically.

Mail: Docket Management Facility, U.S. Department of

Transportation, 1200 New Jersey Avenue, SE., West Building Ground

Floor, Room W12-140, Washington, DC 20590-0001.

Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Fax: (202) 493-2251.

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: alan.strom@faa.gov; telephone (781) 238-7117; fax (781) 238-7199.

Contact Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone (860) 565-8770; fax (860) 565-4503, for the service information referenced in this proposed AD.

SUPPLEMENTARY INFORMATION:

Comments Invited

We invite you to send any written relevant data, views, or arguments regarding this proposal. Send your comments to an address listed under ADDRESSES. Include ``Docket No. FAA-2009-0883; Directorate

Identifier 97-ANE-08'' in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments.

We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of the Web site, anyone can find and read the comments in any of our dockets, including, if provided, the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT's complete Privacy

Act Statement in the Federal Register published on April 11, 2000 (65

FR 19477-78).

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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647-5527) is the same as the Mail address provided in the ADDRESSES section.

Comments will be available in the AD docket shortly after receipt.

Discussion

The FAA proposes to amend 14 CFR part 39 by revising AD 97-17-04,

Amendment 39-10106 (62 FR 45152, August 26, 1997). That AD requires cleaning of front compressor front hubs (fan hubs), initial and repetitive ECI and FPI of tierod and counterweight holes for cracks, removal of bushings, the cleaning and ECI and FPI of bushed holes for cracks, and, if necessary, replacement with serviceable parts. In addition, that AD requires reporting the findings of cracked fan hubs and monthly reporting of the number of inspections performed.

Since AD 97-17-04 was issued, we have collected sufficient data on inspections and determined that we do not need further monthly reports of inspections performed.

FAA's Determination and Requirements of the Proposed AD

We have evaluated all pertinent information, and we are proposing this AD, which would revise AD 97-17-04 to eliminate the monthly requirement to report the number of completed inspections back to the

FAA. All other requirements contained in AD 97-17-04 would still be maintained.

Cost of Compliance

We estimate that this proposed AD revision would affect 1,170 JT8D- 209, -217, -217C, and -219 turbofan engines installed on airplanes of

U.S. registry. We estimate that it would 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 proposed 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

Page 67832

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. See the ADDRESSES section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, 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 39--AIRWORTHINESS 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 39-10106 (62 FR 45152, August 26, 1997) and by adding a new airworthiness directive to read as follows:

Pratt & Whitney: Docket No. FAA-2009-0883; Directorate Identifier 97-ANE-08.

Comments Due Date

(a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by February 19, 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

After accumulating 2,500 CIS since- effective date of AD 97-02-11,

last-inspection, but not to exceed

March 5, 1997, or prior to

6,000 CIS since-last-inspection. accumulating 5,050 CSN, whichever occurs later;

OR

OR

(B) Within 990 CIS after the

After accumulating 2,500 CIS since- effective date of AD 97-02-11,

last-inspection, but not to exceed

March 5, 1997, or prior to

8,000 CIS since-last-inspection. accumulating 4,990 CSN, whichever occurs later;

OR

OR

(C) Within 965 CIS after the

After accumulating 2,500 CIS since- effective date of AD 97-02-11,

last-inspection, but not to exceed

March 5, 1997, or prior to

10,000 CIS since-last-inspection. accumulating 4,965 CSN, whichever occurs later.

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

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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.

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.

All....................... Original.................. September 24, 1996.

A6272.

Total Pages: 21

Non-Destruct Inspection

All....................... A......................... September 15, 1996.

Procedure No. NDIP-892.

Total Pages: 30

Attachment I

All....................... A......................... September 15, 1996.

Total Pages: 4

Page 67834

Issued in Burlington, Massachusetts, on December 10, 2009.

Peter A. White,

Assistant Manager, Engine and Propeller Directorate, Aircraft

Certification Service.

FR Doc. E9-30221 Filed 12-18-09; 8:45 am

BILLING CODE 4910-13-P

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