Airworthiness Directives; Bell Helicopter Textron Canada Model 206A, B, L, L-1, L-3, and L-4 Helicopters

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22696; Directorate Identifier 2005-SW-22-AD]

RIN 2120-AA64

Airworthiness Directives; Bell Helicopter Textron Canada Model 206A, B, L, L-1, L-3, and L-4 Helicopters

AGENCY:

Federal Aviation Administration, DOT.

ACTION:

Notice of proposed rulemaking (NPRM).

SUMMARY:

This document proposes superseding an existing airworthiness directive (AD) for the specified Bell Helicopter Textron Canada (BHTC) model helicopters. That AD currently requires an initial inspection and at specified intervals checks and inspections of the tail rotor blade (blade) for a deformation, a crack, and a bent or deformed tail rotor weight (weight). Also, that AD requires, before further flight, replacing each blade with an airworthy blade if a deformation, a crack, or a bent or deformed weight is found. This action would contain the same actions as the existing AD and would also propose adding certain serial-numbered blades to the applicability that were inadvertently omitted from the current AD and would require replacing each affected blade, which would be terminating action. This proposal is prompted by three reports of skin cracks originating near the blade trailing edge balance weight. The actions specified by the proposed AD are intended to prevent blade failure and subsequent loss of control of the helicopter.

DATES:

Comments must be received on or before December 16, 2005.

ADDRESSES:

Use one of the following addresses to submit comments on this proposed AD:

• DOT Docket Web Site: Go to

http://dms.dot.gov

and follow the instructions for sending your comments electronically;

• Government-Wide Rulemaking Web Site: Go to

http://www.regulations.gov

and follow the instructions for sending your comments electronically;

• Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590;

• Fax: 202-493-2251; or

• Hand Delivery: Room PL-401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

• You may get the service information identified in this proposed AD from Bell Helicopter Textron Canada, 12,800 Rue de l'Avenir, Mirabel, Quebec J7J1R4, telephone (450) 437-2862 or (800) 363-8023, fax (450) 433-0272

• You may examine the comments to this proposed AD in the AD docket on the Internet at

http://dms.dot.gov

.

FOR FURTHER INFORMATION CONTACT:

Sharon Miles, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort Worth, Texas 76193-0111, telephone (817) 222-5122, fax (817) 222-5961.

SUPPLEMENTARY INFORMATION:

Comments Invited

We invite you to submit any written data, views, or arguments regarding this proposed AD. Send your comments to the address listed under the caption

ADDRESSES

. Include the docket number “FAA-2005-22696, Directorate Identifier 2005-SW-22-AD” at the beginning 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://dms.dot.gov

, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed rulemaking. Using the search function of our docket web site, you can find and read the comments to any of our dockets, including the name of the individual who sent or signed the comment. You may review the DOT's complete Privacy Act Statement in the

Federal Register

published on April 11, 2000 (65 FR 19477-78), or you may visit

http://dms.dot.gov

. The postcard will be date stamped and returned to the commenter.

Examining the Docket

You may examine the docket that contains the proposed AD, any comments, and other information in person at the Docket Management System (DMS) Docket Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone 1-800-647-5227) is located at the plaza level of the Department of Transportation NASSIF Building in Room PL-401 at 400

Seventh Street, SW., Washington, DC. Comments will be available in the AD docket shortly after the DMS receives them.

Discussion

On November 22, 2004, the FAA issued AD 2004-24-08, Docket No. 2004-SW-12-AD, Amendment 39-13884 (69 FR 69810, December 1, 2004). That AD requires an initial inspection and at intervals not to exceed 12 hours time-in-service (TIS), a 10X inspection or at intervals not to exceed 24 hours TIS a 10X inspection and a 3-hour TIS check between each 24 hour TIS inspection of the blade for a deformation, a crack, and a bent or deformed weight. Also, that AD requires, before further flight, replacing each blade with an airworthy blade if a deformation, a crack, or a bent or deformed weight is found. That action was prompted by three reports of skin cracks originating near the blade trailing edge balance weight. The requirements of that AD are intended to prevent blade failure and subsequent loss of control of the helicopter.

Since issuing AD 2004-24-08, BHTC has issued Alert Service Bulletin 206-04-100 for Bell Model 206A and B helicopters, and 206L-04-127 for Bell Model 206L series helicopters, both Revision C, both dated March 5, 2005 (ASB). These ASBs add two warnings in the compliance section specifying returning the blade for balancing to Rotor Blades, Inc., and introduce new skin damage limits that supersede the previous damage limits. The ASB also gives a new address for Rotor Blades Inc.

When we issued AD 2004-24-08, we intentionally did not include the long-term requirement (no later than April 27, 2007) for removing and sending the affected blades to Rotor Blades, Inc. as specified by the manufacturer. We are including in this proposal a long-term requirement that the affected blades be replaced on or before April 27, 2007, as terminating action. This will allow public comments before any adoption of the long-term proposal. Additionally, in AD 2004-24-08, we inadvertently omitted blade serial numbers 10102 through 10114 from the applicability. We propose to correct that oversight with this action.

Transport Canada, the airworthiness authority for Canada, notified the FAA that an unsafe condition may exist on these helicopter models. Transport Canada advises of three reports of skin cracks originating near the blade trailing edge balance weight. Two of the occurrences caused a loss of the weight and a strip of material along the trailing edge leading to an imbalance, which caused the fracture of three of the four tail rotor gearbox attachments. One of these occurrences resulted in the gearbox shifting that caused failure of the drive shaft and resulting loss of yaw control. Transport Canada issued AD No. CF-2004-05R1, dated June 28, 2004, to ensure the continued airworthiness of these helicopters in Canada.

These helicopter models are manufactured in Canada and are type certificated for operation in the United States under the provisions of 14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the applicable bilateral agreement, Transport Canada has kept the FAA informed of the situation described above. The FAA has examined the findings of Transport Canada, reviewed all available information, and determined that AD action is necessary for products of these type designs that are certificated for operation in the United States.

Interested persons were afforded an opportunity to participate in the making of AD 2004-24-08, Amendment 39-13884, Docket No. 2004-SW-12-AD, which we are proposing to supersede. Due consideration has been given to the one comment received.

The commenter expresses concern about the 12-hour blade inspection by a mechanic and states the inspection will make this helicopter unsuitable for its intended use. The commenter states the alternate pilot check and mechanic inspection would require them to shut down 4-5 times each day increasing engine cycles. The commenter further states that since the only difference between the pilot check and the mechanic inspection is the 10X magnifier, pilots need to be certified to perform the 12-hour inspection.

While the FAA agrees the checks and inspections could increase engine cycles, the primary purpose of issuing an AD is to correct an unsafe condition. However, the terminating action proposed in this AD would eliminate the current mandated inspections. We do not agree that pilots need to be certified to perform inspections. Current FAA policy allows pilots holding at least a private pilot certificate to perform checks that do not require the use of tools, precision measuring equipment, training, pilot logbook endorsements, or reference to technical data not contained in the body of the AD. Pilots may only perform simple maintenance tasks that do not require special maintenance training. The inspection in the AD requires the use of a 10X or higher magnifying glass, which is not considered a simple visual check. In the interest of safety, the inspection must occur at the specified intervals and be performed by a qualified mechanic until the terminating action is accomplished.

The previously described unsafe condition is likely to exist or develop on other helicopters of these same type designs. Therefore, the proposed AD would supersede AD 2004-24-08 to require:

• Before further flight, unless accomplished previously, and before installing any blade with an affected part number and serial number (S/N), cleaning the blade. Then, using a 10X or higher magnifying glass, inspecting both sides of each blade for a deformation, a crack, and a bent or deformed weight.

• Thereafter, cleaning both sides of each blade and using a 10X or higher magnifying glass, inspecting for a deformation, a crack, and a bent or deformed weight as follows:

• At intervals not to exceed 12 hours TIS, or

• At intervals not to exceed 24 hours TIS and checking both sides of each blade for a deformation, a crack, and a bent or deformed weight at intervals not to exceed 3 hours TIS between inspections. An owner/operator (pilot) holding at least a private pilot certificate may perform the 3-hour TIS check for deformed or cracked blades and for bent or deformed weights. Pilots may perform these checks because they require no tools, can be done by observation, and can be done equally well by a pilot or a mechanic. However, the pilot must enter compliance with these requirements into the helicopter maintenance records by following 14 CFR 43.11 and 91.417(a)(2)(v).

• Before further flight, replacing each blade with an airworthy blade if you find a deformation, a crack, or a bent or deformed weight.

• On or before April 27, 2007, replacing each affected blade with an airworthy blade that is identified by a “V” at the end of the blade S/N or an airworthy blade with a S/N other than one listed in the applicability section of this AD.

Replacing each blade with an airworthy blade that is identified by a “V” at the end of the blade S/N or an airworthy blade with a S/N other than one listed in the applicability section of this AD constitutes terminating action for the requirements of this AD.

The FAA estimates that this proposed AD would:

• Affect 2194 helicopters of U.S. registry,

• Take about

1/4

work hour for a blade check or inspection, and

• Take 3 work hours to replace a blade at an average labor rate of $65 per work hour. Required parts would cost about $5848 per helicopter. (In its ASB, the manufacturer states it will give warranty credit based on hour usage on the blade with remaining life hours and other restrictions.) Based on these figures, we estimate the total cost impact of the proposed AD on U.S. operators to be $19,989,973. Costs assume—200 pilot checks, 26 mechanic inspections, and one blade replacement for 90 percent of the fleet with a nonconforming blade.

Regulatory Findings

The regulations proposed herein 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. Therefore, it is determined that this proposal would not have federalism implications under Executive Order 13132.

For the reasons discussed above, I certify that this proposed 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); on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A copy of the draft regulatory evaluation prepared for this action is contained in the Rules Docket. A copy of it may be obtained by contacting the Rules Docket at the location provided under the caption

ADDRESSES

.

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.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by removing Amendment 39-13884 (69 FR 69810, December 1, 2004), and by adding a new airworthiness directive (AD), to read as follows:

Bell Helicopter Textron Canada:

Docket No. FAA-2005, Directorate Identifier 2005-SW-22-AD. Supersedes AD 2004-24-08, Amendment 39-13884, Docket No. 2004-SW-12-AD.

Applicability:

Model 206A, B, L, L-1, L-3, and L-4 helicopters, with a tail rotor blade (blade) with the following part number (P/N) and serial number (S/N) installed, certificated in any category.

Model 206A & B; Blade, P/N 206-016-201-133, S/N with prefix “CS” and no “V” suffix

Model 206A, B, L, L-1, L-3, & L-4; Blade, P/N P/N 206-016-201-131, S/N with prefix “CS” and no “V” suffix

1381 through 1442

7000 through 7018

10174 through 10218

1492 through 1517

7020 through 7043

10220

1520 through 1542

7045 through 7050

10232

1550

7052 through 7132

10235

1556

7134 through 7246

10237 through 10241

1560

7248 through 7270

10244

1562

7272 through 7277

10245

1564 through 1567

7279 through 7339

10248

1569 through 1606

7342 through 7368

10250 through 10264

1609

7784

10266 through 10268

1611

7786

10270 through 10274

1612

7788

10276 through 10278

1614 through 1631

7790 through 7796

10280 through 10282

1633 through 1675

7798 through 7819

10284 through 10292

1677

7821 through 7833

10296

1678

7835 through 7839

10300 through 10330

1680 through 1682

7841 through 8001

10332

1684 through 1787

8003 through 8026

10333

1789 through 1803

8029 through 8061

10335 through 10347

1810 through 1812

8064 through 8117

10349

1814

8119

10351 through 10359

1816

8121 through 8139

10363 through 10365

1820

8142 through 8176

10367

1823 through 1831

8178 through 8262

10373

1834 through 1836

8264 through 8294

10374

1838

8298 through 8368

10377 through 10385

1840 through 1844

8370 through 8375

10387 through 10408

1846

8378 through 8416

10410

1848 through 1882

8419

10414 through 10417

1884 through 1887

8421

10419 through 10427

1889 through 1893

8425 through 8428

10430

1896 through 1898

8430 through 8438

10432

1900

8440

10437

1904

8441

10438

Model 206A & B; Blade, P/N 206-016-201-133, S/N with prefix “CS” and no “V” suffix

Model 206A, B, L, L-1, L-3, & L-4; Blade, P/N P/N 206-016-201-131, S/N with prefix “CS” and no “V” suffix

1909 through 1912

8443

10442 through 10445

1915

8445 through 8447

10458 through 10466

1916

8449 through 8606

10469

1919 through 1921

8608 through 8622

10470

1924

8624 through 8626

10474

1928 through 1931

8628 through 8632

10476 through 10478

1933

8635 through 8653

10480 through 10487

1934 through 1939

8655 through 8686

10489 through 10491

1943

8690

10493 through 10495

1945

8692 through 8700

10497 through 10503

1947

8703 through 8715

10505 through 10588

1948

8717 through 8722

10591 through 10606

1952 through 1957

8724 through 8742

10608 through 10610

1960

8745 through 8828

10612 through 10620

1962 through 1965

8830 through 8835

10623

8838 through 8840

10624

8842 through 8881

10631 through 10655

8883 through 9032

10657 through 10669

9034 through 9139

10672

9141 through 9198

10673

9200

10676 through 10678

9202 through 9302

10680 through 10683

9304 through 9339

10685

9341 through 9371

10687

9373 through 9411

10689 through 10702

9413

10707

9415 through 9417

10712

9419 through 9496

10715

9498 through 9585

10730

9587 through 9594

10732 through 10734

9596 through 9618

10736

9621 through 9629

10738

9632 through 9642

10739

9645 through 9651

10746

9653 through 9673

10750

9675 through 9707

10756

9709 through 9724

10760

9727 through 9731

10761

9733 through 9735

10765

9737 through 9739

10770

9741 through 9748

10774 through 10776

9751 through 9785

10778

9787

10781

9788

10783 through 10785

9790 through 9792

10792

9795 through 9847

10794

9849 through 9928

10798

9930 through 9937

10799

9940 through 9942

10806 through 10808

9944 through 9952

10811

9955 through 9972

10814 through 10822

9974 through 9989

10824

9991 through 9995

10825

9997 through 10004

10829

10006 through 10009

10831

10011

10917

10013 through 10018

10923

10021 through 10030

10931

10034

10936

10036 through 10057

10937

10061 through 10082

10940

10090 through 10092

10943

10094 through 10100

10945

10102 through 10114

10947

10116

10948

10119

10964

10121

10965

10123 through 10134

10973

10136 through 10140

10982

10142 through 10144

10985

10146 through 10172

10986

Compliance:

Required as indicated.

To prevent blade failure and subsequent loss of control of the helicopter, do the following:

(a) Before further flight, unless accomplished previously, and before installing any blade with a P/N and S/N listed in the applicability section of this AD, clean the blade. Using a 10X or higher magnifying glass, inspect both sides of each blade for a deformation, a crack, and a bent or deformed weight in the area shown in Figure 1 of this AD.

Note 1:

Paint irregularities on the blade may indicate a crack.

EP17OC05.002

(b) After doing paragraph (a) of this AD, at the following intervals, clean both sides of each blade and do either paragraph (1) or (2) as follows:

(1) At intervals not to exceed 12 hours time-in-service (TIS), using a 10X or higher magnifying glass, inspect both sides of each blade for a deformation, a crack, and a bent or deformed weight in the area shown in Figure 1 of this AD, or

(2) Inspect and check both sides of each blade for a deformation, a crack, and a bent or deformed weight in the area shown in Figure 1 of this AD as follows:

(i) Using a 10X or higher magnifying glass, inspect at intervals not to exceed 24 hours TIS, and

(ii) Check at intervals not to exceed 3 hours TIS between the inspections required by paragraph (b)(2)(i) of this AD. An owner/operator (pilot), holding at least a private pilot certificate, may perform this visual check and must enter compliance with this paragraph into the helicopter maintenance records by following 14 CFR sections 43.11 and 91.417(a)(2)(v).

(c) Before further flight, replace any blade that has a deformation, a crack, or a bent or deformed weight with an airworthy blade.

Note 2:

Bell Helicopter Textron Alert Service Bulletin No. 206-04-100 for Model 206A and B and No. 206L-04-127 for Model 206L series, both Revision C, both dated March 5, 2005, pertain to the subject of this AD.

(d) On or before April 27, 2007, for any affected part-numbered blade with a S/N listed in the applicability section of this AD:

(1) Replace the blade with a blade that has a S/N other than one listed in the applicability section of this AD, or

(2) Replace the blade with a blade that has a S/N listed in the applicability section of this AD and also has a “V” suffix.

(e) Replacing each blade with an airworthy blade as required by paragraph (d) of this AD constitutes terminating action for the requirements of this AD.

(f) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Safety Management Group, Rotorcraft Directorate, FAA, for information about previously approved alternative methods of compliance.

Note 3:

The subject of this AD is addressed in Transport Canada (Canada) AD No. CF-2004-05R1, dated June 28, 2004.

Issued in Fort Worth, Texas, on October 7, 2005.

David A. Downey,

Manager, Rotorcraft Directorate, Aircraft Certification Service.

[FR Doc. 05-20681 Filed 10-14-05; 8:45 am]

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