Federal Register / Vol. 63, No. 92 /Wednesday, May 13, 1998 /Rules and Regulations 26429

(1) For all serial numbered airplanes,

inspect the nose wheel steering, the sliding

canopy and canopy locking mechanism, the

attachment of the horizontal stabilizer, the

elevator installation, the vertical stabilizer,

the rudder installation, and the weights and

residual moments of the control surfaces in

accordance with the instructions in Grob

Service Bulletin No. 1078–59/3, dated

October 24, 1996. Prior to further flight,

repair any discrepancies in accordance with

the above-referenced service bulletin.

(2) For airplanes incorporating a serial

number in the range of 82001 through 82077,

replace the elevator hinges with parts of

improved design in accordance with Grob

Installation Instructions 1078–64, dated

December 11, 1996, as specified in both Grob

Service Bulletin No. 1078–64/2, dated April

8, 1997; and Grob Service Bulletin No. 1078–

64, dated December 11, 1996.

(3) For airplanes incorporating a serial

number in the range of 82001 through 82077,

after accomplishing the replacement required

by paragraph (b)(2) of this AD, adjust the

mass and residual moments in accordance

with Grob Service Bulletin No. 1078–66,

dated February 10, 1997.

(c) Accomplishing the actions required by

paragraphs (b)(1), (b)(2), and (b)(3) of this AD

eliminates the placard and flight restriction

requirements of paragraph (a), including all

subparagraphs, of this AD.

(d) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

(e) An alternative method of compliance or

adjustment of the compliance times that

provides an equivalent level of safety may be

approved by the Manager, Small Airplane

Directorate, 1201 Walnut, suite 900, Kansas

City, Missouri 64106.

(1) The request shall be forwarded through

an appropriate FAA Maintenance Inspector,

who may add comments and then send it to

the Manager, Small Airplane Directorate.

(2) Alternative methods of compliance

approved in accordance with AD 96–19–07

are not considered approved as alternative

methods of compliance for this AD.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Small Airplane

Directorate.

(f) Questions or technical information

related to service information previously

referenced should be directed to Burkhart

Grob Luft-und Raumfahrt, D–8939 Mattsies,

Germany. This service information may be

examined at the FAA, Central Region, Office

of the Regional Counsel, Room 1558, 601 E.

12th Street, Kansas City, Missouri 64106.

(g) The inspection required by this AD

shall be done in accordance with Grob

Service Bulletin No. 1078–59/3, dated

October 24, 1996. The replacement required

by this AD shall be done in accordance with

Grob Installation Instructions 1078–64, dated

December 11, 1996, as specified in both Grob

Service Bulletin No. 1078–64/2, dated April

8, 1997; and Grob Service Bulletin No. 1078–

64, dated December 11, 1996. The adjustment

required by this AD shall be done in

accordance with Grob Service Bulletin No.

1078–66, dated February 10, 1997. This

incorporation by reference was approved by

the Director of the Federal Register in

accordance with 5 U.S.C. 552(a) and 1 CFR

part 51. Copies may be obtained from

Burkhart Grob Luft-und Raumfahrt, D–8939

Mattsies, Germany. Copies may be inspected

at the FAA, Central Region, Office of the

Regional Counsel, Room 1558, 601 E. 12th

Street, Kansas City, Missouri, or at the Office

of the Federal Register, 800 North Capitol

Street, NW, suite 700, Washington, DC.

Note 4: The subject of this AD is addressed

in German AD 96–270/2, dated December 5,

1996; German AD 96–270/3, dated December

4, 1997; and German AD 97–143, dated May

22, 1997.

(h) This amendment supersedes AD 96–

19–07, Amendment 39–9765.

(i) This amendment becomes effective on

June 28, 1998.

Issued in Kansas City, Missouri, on May 1,

1998.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 98–12355 Filed 5–12–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–SW–32–AD; Amendment

39–10520; AD 97–18–11]

RIN 2120–AA64

Airworthiness Directives; Bell

Helicopter Textron (Bell) Model 204B,

205A, and 205A–1 Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This document publishes in

the Federal Register an amendment

adopting Airworthiness Directive (AD)

97–18–11, issued on August 29, 1997,

which was sent previously to all known

U.S. owners and operators of Bell Model

204B, 205A, and 205A–1 helicopters by

individual letters. This AD requires

modification and inspections of the

vertical fin spar. If any crack is

discovered, replacement of the vertical

fin spar with an airworthy vertical fin

spar is required before further flight.

This amendment is prompted by several

failures of the vertical fin spar,

including those with steel doublers,

caused by fatigue cracks that result from

a large number of high-power events.

The actions specified by this AD are

intended to prevent in-flight failure of

the vertical fin spar and subsequent loss

of control of the helicopter.

DATES: Effective May 28, 1998, to all

persons except those persons to whom

it was made immediately effective by

priority letter AD 97–18–11, issued on

August 29, 1997, which contained the

requirements of this amendment.

Comments for inclusion in the Rules

Docket must be received on or before

July 13, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Office of the

Regional Counsel, Southwest Region,

Attention: Rules Docket No. 97–SW–32–

AD, 2601 Meacham Blvd., Room 663,

Fort Worth, Texas 76137.

FOR FURTHER INFORMATION CONTACT: Mr.

Charles Harrison, Aerospace Engineer,

FAA, Rotorcraft Directorate, Rotorcraft

Certification Office, 2601 Meacham

Blvd., Fort Worth, Texas 76137,

telephone (817) 222–5447, fax (817)

222–5783.

SUPPLEMENTARY INFORMATION: On August

29, 1997, the FAA issued priority letter

AD 97–18–11, applicable to Bell Model

204B, 205A, and 205A–1 helicopters,

which requires modification and

inspections of the vertical fin spar. If

any crack is discovered, replacement of

the vertical fin spar with an airworthy

vertical fin spar is required before

further flight. Priority letter AD 97–18–

11 superseded priority letter AD 97–18–

01, issued on August 19, 1997. AD 97–

18–01 contained the same basic

requirements as is contained in AD 97–

18–11. However, AD 97–18–11 was

needed to clarify the method of

compliance for the Model 204B

helicopters, and to correct an error in a

vertical fin spar part number (P/N). AD

97–18–01 incorrectly stated the P/N as

P/N 205–030–851 instead of P/N 205–

032–851. This AD is prompted by an

accident involving the in-flight failure

of the vertical fin spar on a Model

205A–1 helicopter. Two other accidents

on restricted category (military surplus)

aircraft of similar type design have

occurred. One of the accidents resulted

in a fatality. In 1971, the FAA issued AD

71–21–02, which addressed this

problem by requiring the addition of a

steel doubler to the inside edge of the

vertical fin spar. There have been

several additional failures since that AD

was issued. A large number of highpower events can cause fatigue cracks

which will cause the vertical fin spar to

fail. This condition, if not corrected,

could result in in-flight failure of the

vertical fin spar and subsequent loss of

control of the helicopter.

Since the unsafe condition described

is likely to exist or develop on other Bell
26430 Federal Register / Vol. 63, No. 92 /Wednesday, May 13, 1998 /Rules and Regulations

Model 204B, 205A, and 205A–1

helicopters of the same type design, the

FAA issued priority letter AD 97–18–11

to prevent in-flight failure of the vertical

fin spar and subsequent loss of control

of the helicopter. The AD requires,

within 8 hours time-in-service (TIS)

after the effective date of this AD,

modification and inspection of the

vertical fin spar. Then, at intervals not

to exceed 8 hours TIS, further

inspections of the vertical fin spar for

cracks are required. If any crack is

discovered, replacement of the vertical

fin spar with an airworthy vertical fin

spar is required before further flight.

Since it was found that immediate

corrective action was required, notice

and opportunity for prior public

comment thereon were impracticable

and contrary to the public interest, and

good cause existed to make the AD

effective immediately by individual

letters issued on August 29, 1997 to all

known U.S. owners and operators of

Bell Model 204B, 205A, and 205A–1

helicopters. These conditions still exist,

and the AD is hereby published in the

Federal Register as an amendment to

section 39.13 of the Federal Aviation

Regulations (14 CFR 39.13) to make it

effective to all persons.

The FAA estimates that 265

helicopters will be affected by this

proposed AD, that it will take

approximately 203 work hours to

accomplish the modification,

inspection, and spar replacement, and

that the average labor rate is $60 per

work hour. Based on these figures, the

total cost impact of the AD on U.S.

operators is estimated to be $3,227,700.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an opportunity

for public comment, comments are

invited on this rule. Interested persons

are invited to comment on this rule by

submitting such written data, views, or

arguments as they may desire.

Communications should identify the

Rules Docket number and be submitted

in triplicate to the address specified

under the caption ADDRESSES. All

communications received on or before

the closing date for comments will be

considered, and this rule may be

amended in light of the comments

received. Factual information that

supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report that

summarizes each FAA-public contact

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket No. 97–SW–32–AD.’’ The

postcard will be date stamped and

returned to the commenter.

The regulations adopted herein will

not have substantial direct effects 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, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and that it is not a ‘‘significant

regulatory action’’ under Executive

Order 12866. It has been determined

further that this action involves an

emergency regulation under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979). If it is

determined that this emergency

regulation otherwise would be

significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, may be obtained from the

Rules Docket at the location provided

under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

Adoption of the Amendment

Accordingly, pursuant to 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 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

adding a new airworthiness directive

(AD) to read as follows:

AD 97–18–11 Bell Helicopter Textron:

Amendment 39–10520. Docket No. 97–SW–

32–AD.

Applicability: Model 204B, 205A, and

205A–1 helicopters, with tailboom vertical

fin spar, part number (P/N) 205–032-899,

205–030–846, or 205–032–851, all dash

numbers, installed, certificated in any

category.

Note 1: This AD applies to each helicopter

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

helicopters that have been modified, altered,

or repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must use the authority

provided in paragraph (c) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition, or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any helicopter

from the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously. To prevent inflight failure of the tailboom vertical fin spar

(vertical fin spar) and subsequent loss of

control of the helicopter, accomplish the

following:

(a) For Model 204B helicopters, within 8

hours time-in-service (TIS) after the effective

date of this AD, modify the vertical fin spar

as follows:

(1) Remove the 42° gearbox cover and open

the drive shaft cover on the vertical fin spar

assembly (see Figure 1).

(i) Remove the first four rivets from the

vertical fin spar located at the bottom of the

vertical fin spar left-hand side at the tailboom

and vertical fin spar junction, and the first

four rivets aft of the junction along the lower

edge of the vertical fin spar skin (skin) as

shown (see Figure 2). CAUTION: Extreme

care must be taken when drilling and

removing rivets from the side of vertical fin

spar to ensure the vertical fin spar assembly

is not damaged.

(ii) Trim the vertical fin spar left-hand skin

using extreme care to not damage the vertical

fin spar assembly (see Figure 3).

(iii) Deburr the rivet holes and trimmed

skin edges. Remove all debris. In a ventilated

work area, remove any surface contaminants

with a cloth that has been dampened with

aliphatic naphtha or an equivalent cleaning

solvent.
Federal Register / Vol. 63, No. 92 /Wednesday, May 13, 1998 /Rules and Regulations 26431

(iv) Reattach the skin to the vertical fin

spar using MS 20470AD rivets. DO NOT

install the bottom two rivets into the vertical

fin spar where the skin was trimmed.

(v) Reinstall the vertical fin spar skin lower

edge rivets using M 7885/6–5 rivets (see

Figure 6).

(vi) Refinish all reworked areas.

(vii) After modifying the vertical fin spar,

immediately inspect the vertical fin spar in

accordance with paragraphs (a)(2)(iii) and

(a)(2)(iv) of this AD.

(2) After the initial modification and

inspection of the vertical fin spar have been

accomplished in accordance with paragraph

(a)(1) of this AD, thereafter, at intervals not

to exceed 8 hours TIS, inspect the vertical fin

spar in accordance with paragraphs (a)(2)(iii)

and (a)(2)(iv) of this AD for cracks as follows:

(i) Remove the lower aft tailboom

inspection door, located at tailboom station

180 (see Figure 4).

(ii) Remove the 42° gearbox cover and open

the drive shaft cover on the vertical fin (see

Figure 1).

(iii) Through the lower aft tailboom

inspection door, using a bright light and an

inspection mirror, inspect the vertical fin

spar assembly adjacent to the tailboom top

skin on the forward side, paying special

attention to the left-hand edge and the

adjacent surfaces (see Figure 5).

(iv) In a ventilated work area, clean all

surfaces to be inspected with a cloth

dampened with aliphatic naphtha or an

equivalent cleaning solvent. Using a bright

light and a 10x magnifying glass, inspect the

vertical fin spar assembly adjacent to the

tailboom top-skin on the in-board and outboard sides, the vertical edge, and the two

open rivet holes. Using a bright light and a

mirror, inspect the aft side of the vertical fin

spar in the same area. Special attention must

be given to the left-hand edge of the vertical

fin spar and any adjacent surfaces between

fin stations 66.31 and 71.31 (see Figure 5).

(3) If any crack is discovered on the

vertical fin spar as a result of the inspection

specified in paragraphs (a)(2)(iii) or (a)(2)(iv)

of this AD, replace the vertical fin spar

assembly with an airworthy vertical fin spar

assembly before further flight.

(b) For Model 205A and 205A–1

helicopters, within 8 hours TIS after the

effective date of this AD, modify the vertical

fin spar as follows:

(1) Remove the 42° gearbox cover and open

the drive shaft cover on the vertical fin spar

assembly (see Figure 1).

(i) Remove the clip, P/N 212–030–099–091,

and the radius block, P/N 212–030–099–095,

(see Figures 5 and 6).

(ii) Remove the first four rivets from the

vertical fin spar, located at the bottom of the

vertical fin spar left-hand side at the tailboom

and vertical fin spar junction as shown (see

Figure 5). CAUTION: Extreme care must be

taken when drilling and removing rivets from

the side of vertical fin spar to ensure the

vertical fin spar assembly is not damaged.

(iii) Trim the vertical fin left-hand side

skin and retainer, P/N 205–032–851–045,

using extreme care to not damage the vertical

fin spar assembly (see Figure 7).

(iv) Deburr the rivet holes and trimmed

retainer and skin edges. Remove all debris. In

a ventilated work area, remove any surface

contaminants with a cloth that has been

dampened with aliphatic naphtha or an

equivalent cleaning solvent.

(v) Reattach the skin and retainer to the

vertical fin spar using MS 20470AD rivets.

DO NOT install the bottom two rivets into

the vertical fin spar where the skin and

retainer were trimmed.

(vi) Reinstall the clip and radius block with

M 7885/6–5 rivets (see Figure 5).

(vii) Refinish all reworked areas.

(viii) After modifying the vertical fin spar,

immediately inspect the vertical fin spar in

accordance with paragraphs (b)(2)(iii) and

(b)(2)(iv) of this AD.

(2) After the initial modification and

inspection of the vertical fin spar have been

accomplished in accordance with paragraph

(b)(1) of this AD, thereafter, at intervals not

to exceed 8 hours TIS, inspect the vertical fin

spar in accordance with paragraphs (b)(2)(iii)

and (b)(2)(iv) of this AD for cracks as follows:

(i) Remove the lower aft tailboom

inspection door, located at tailboom station

180 (see Figure 4).

(ii) Remove the 42° gearbox cover and open

the drive shaft cover on the vertical fin spar

(see Figure 1).

(iii) Through the lower aft tailboom

inspection door, using a bright light and an

inspection mirror, inspect the vertical fin

spar assembly adjacent to the tailboom top

skin on the forward side, paying special

attention to the left-hand edge and the

adjacent surfaces (see Figure 5).

(iv) In a ventilated work area, clean all

surfaces to be inspected with a cloth

dampened with aliphatic naphtha or an

equivalent cleaning solvent. Using a bright

light and a 10x magnifying glass, inspect the

vertical fin spar assembly adjacent to the

tailboom top-skin on the in-board and outboard sides, the vertical edge and the two

open rivet holes. Using a bright light and a

mirror, inspect the aft side of the vertical fin

spar in the same area. Special attention must

be given to the left-hand edge of the vertical

fin spar and any adjacent surfaces between

fin stations 66.31 and 71.31 (see Figure 5).

(3) If any crack is discovered on the

vertical fin spar as a result of the inspection

specified in paragraphs (b)(2)(iii) or (b)(2)(iv)

of this AD, replace the vertical fin spar

assembly with an airworthy vertical fin spar

assembly before further flight.

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager, Rotorcraft

Certification Office, FAA. Operators shall

submit their requests through an FAA

Principal Maintenance Inspector, who may

concur or comment and then send it to the

Manager, Rotorcraft Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Rotorcraft Certification

Office.

(d) Special flight permits may be issued in

accordance with §§ 21.197 and 21.199 of the

Federal Aviation Regulations (14 CFR 21.197

and 21.199) to operate the helicopter to a

location where the requirements of this AD

can be accomplished.

BILLING CODE 4910–13–U
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Federal Register / Vol. 63, No. 92 /Wednesday, May 13, 1998 /Rules and Regulations 26433
26434 Federal Register / Vol. 63, No. 92 /Wednesday, May 13, 1998 /Rules and Regulations
Federal Register / Vol. 63, No. 92 /Wednesday, May 13, 1998 /Rules and Regulations 26435
26436 Federal Register / Vol. 63, No. 92 /Wednesday, May 13, 1998 /Rules and Regulations
Federal Register / Vol. 63, No. 92 /Wednesday, May 13, 1998 /Rules and Regulations 26437
26438 Federal Register / Vol. 63, No. 92 /Wednesday, May 13, 1998 /Rules and Regulations
Federal Register / Vol. 63, No. 92 /Wednesday, May 13, 1998 /Rules and Regulations 26439

(e) This amendment becomes effective

on May 28, 1998, to all persons except

those persons to whom it was made

immediately effective by Priority Letter

AD 97–18–11, issued August 29, 1997,

which contained the requirements of

this amendment.

Issued in Fort Worth, Texas, on May 4,

1998.

Eric Bries.

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 98–12508 Filed 5–12–98; 8:45 am]

BILLING CODE 4910–13–C

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–SW–35–AD; Amendment

39–10521; AD 97–20–09]

RIN 2120–AA64

Airworthiness Directives; Bell

Helicopter Textron (Bell)-manufactured

Model HH–1K, TH–1F, TH–1L, UH–1A,

UH–1B, UH–1E, UH–1F, UH–1H, UH–1L,

and UH–1P Helicopters; and

Southwest Florida Aviation SW204,

SW204HP, SW205, and SW205A–1

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment supersedes

an existing priority letter airworthiness

directive (AD), applicable to Bellmanufactured Model HH–1K, TH–1F,

TH–1L, UH–1A, UH–1B, UH–1E, UH–

1F, UH–1H, UH–1L, and UH–1P

helicopters; and Southwest Florida

Aviation SW204, SW204HP, and SW205

helicopters, that currently requires

modification and inspections of the

vertical fin spar. This amendment

requires the same modification and

inspections required by the existing

priority letter AD, but adds the

Southwest Florida Aviation Model

SW205A–1 and Utah State University

UH–1H helicopters to the applicability

of this AD. This amendment is

prompted by accidents involving inflight failure of the tailboom vertical fin

spar. The actions specified by this AD

are intended to prevent in-flight failure

of the vertical fin spar and subsequent

loss of control of the helicopter.

DATES: Effective May 28, 1998.

Comments for inclusion in the Rules

Docket must be received on or before

July 13, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Office of the

Regional Counsel, Southwest Region,

Attention: Rules Docket No. 97–SW–35–

AD, 2601 Meacham Blvd., Room 663,

Fort Worth, Texas 76137.

FOR FURTHER INFORMATION CONTACT: Mr.

Charles Harrison, Aerospace Engineer,

FAA, Rotorcraft Directorate, Rotorcraft

Certification Office, 2601 Meacham

Blvd., Fort Worth, Texas 76137,

telephone (817) 222–5447, fax (817)

222–5960.