Federal Register / Vol. 60, No. 102 / Friday, May 26, 1995 / Rules and Regulations 27873

Simmering Graz Pauker A.G. Model SGP–

222.

Note 1: This airworthiness directive (AD)

applies to each propeller 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 propellers 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 (e)

to request approval from the Federal Aviation

Administration (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 propeller from the

applicability of this AD.

Note 2: The above is not an exhaustive list

of aircraft which may contain the affected

Hartzell Models HC–92WK–( ) and HC–

92ZK–( ) propellers because of installation

approvals made by, for example,

Supplemental Type Certificate or field

approval under FAA Form 337 ‘‘Major Repair

and Alteration.’’ It is the responsibility of the

owner, operator, and person returning the

aircraft to service to determine if an aircraft

has an affected propeller.

Compliance: Required as indicated, unless

accomplished previously.

To prevent propeller blade separation,

which could result in loss of control of the

aircraft, accomplish the following:

(a) For all affected propellers, within 10

hours time in service (TIS) after the effective

date of this AD, perform a blade clamp screw

inspection in accordance with Procedure No.

1 of Hartzell Propeller Inc. Service Bulletin

(SB) No. 202, dated January 5, 1995. If any

clamp screws are loose (i.e., screws turn

when applying torque in a clockwise

rotation) or broken, remove propeller and

send to an authorized repair station for

disassembly and inspection in accordance

with paragraph (b) of this AD prior to further

flight.

(b) For affected propellers whose time

since last blade dye penetrant inspection or

compliance with AD 73–02–01 is unknown,

within the next 10 hours TIS after the

effective date of this AD, accomplish the

following:

(1) Disassemble, perform a dye penetrant

inspection of the blade shank, perform

compressive rolling of the blade shank, and

replace clamp socket screws with Part

Number (P/N) A–321 clamp socket screws in

accordance with Procedure No. 2 of Hartzell

Propeller Inc. SB No. 202, dated January 5,

1995. If cracks are found during a dye

penetrant inspection of the blade shank,

replace with a serviceable blade that has been

compressively rolled in the blade shank.

(2) At intervals not to exceed 500 hours TIS

since last inspection, repeat paragraph (b)(1)

of this AD. The P/N A–321 clamp screws are

to be used one time only and are to be

replaced with new screws each time the

propeller blade clamp is disassembled.

(c) For affected propellers whose time

since last blade dye penetrant inspection or

compliance with AD 73–02–01 is greater than

275 hours TIS, within the next 25 hours TIS

after the effective date of this AD, accomplish

paragraphs (b)(1) and (b)(2) of this AD.

(d) For affected propellers whose time

since last blade dye penetrant inspection or

compliance with AD 73–02–01 is less than or

equal to 275 hours TIS, prior to reaching 300

hours TIS since last blade dye penetrant

inspection or compliance with AD 73–02–01,

accomplish paragraphs (b)(1) and (b)(2) of

this AD.

(e) 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, Chicago

Aircraft Certification Office. The request

should be forwarded through an appropriate

FAA Maintenance Inspector, who may add

comments and then send it to the Manager,

Chicago Aircraft Certification Office.

Note: Information concerning the existence

of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Chicago

Aircraft Certification Office.

(f) 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 aircraft to

a location where the requirements of this AD

can be accomplished. Special flight permits

should not be issued if loose or broken

screws are found.

(g) The actions required by this AD shall

be done in accordance with the following

Hartzell Propeller Inc. SB:

Document No. SB No. 202.

Pages: 1–5.

Date: January 5, 1995.

Total pages: 5.

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 Hartzell Propeller Inc., One Propeller

Place, Piqua, OH 45356–2634; telephone

(513) 778–4200, fax (513) 778–4391. Copies

may be inspected at the FAA, New England

Region, Office of the Assistant Chief 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.

(h) This amendment becomes effective on

June 12, 1995.

Issued in Burlington, Massachusetts, on

May 17, 1995.

James C. Jones,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 95–12825 Filed 5–24–95; 2:35 pm]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–SW–08–AD; Amendment

39–9247; AD 95–11–14]

Airworthiness Directives; Bell

Helicopter Textron, Inc. Model 206A,

206B, 206L, 206L–1, 206L–3, and 206L–

4 Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Bell Helicopter Textron,

Inc. Model 206A, 206B, 206L, 206L–1,

206L–3, and 206L–4 helicopters, that

requires removal and replacement of

certain crosstube assemblies

(crosstubes). This amendment is

prompted by two accidents attributed to

crosstube failures and 27 field reports

that indicated corrosion or metal fatigue

may cause a failure of the affected

crosstubes. The actions specified by this

AD are intended to prevent failure of the

crosstubes and subsequent loss of

control of the helicopter.

DATE: Effective June 30, 1995.

FOR FURTHER INFORMATION CONTACT: Mr.

Tony Nguyen, Aerospace Engineer,

FAA, Rotorcraft Directorate, Rotorcraft

Certification Office, Fort Worth, Texas

76193–0170, telephone (817) 222–5177,

fax (817) 222–5959.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to Bell Helicopter

Textron, Inc. Model 206A, 206B, 206L,

206L–1, 206L–3, and 206L–4 helicopters

was published in the Federal Register

on November 14, 1994 (59 FR 56438).

That action proposed to require removal

and replacement of certain crosstubes

within the next 90 calendar days.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the one

comment received.

The commenter states that the FAA

should require an annual skid gear

inspection rather than requiring the

more costly replacement of the

crosstubes. The FAA does not concur.

The FAA has determined that, due to

the location of the potential crack and

the speed at which a crack could

propagate, an annual inspection would

not be a sufficient interval to detect a

potentially critical crack. The economic

impact of a repetitive inspection at an

interval short enough to detect the crack

would have a greater adverse economic

impact on owners/operators than the
27874 Federal Register / Vol. 60, No. 102 / Friday, May 26, 1995 / Rules and Regulations

economic impact which would be

incurred by replacing the crosstubes.

After careful review of the available

data, including the comment noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed, except

for editorial changes and adding

explanatory Note 1, relating to the scope

of the applicability statement when

modifications, alterations, or repairs

have been made in the area subject to

the requirements of the AD.

The FAA estimates that 5,700

helicopters of U.S. registry will be

affected by this AD, that it will take

approximately 10 work hours per

helicopter to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Required parts

will cost approximately $6,400 per

helicopter. Based on these figures, the

total cost impact of the AD on U.S.

operators is estimated to be $39,900,000

to replace two crosstubes per helicopter.

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.

For the reasons discussed above, I

certify that this action (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. A final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it 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. App. 1354(a), 1421

and 1423; 49 U.S.C. 106(g); and 14 CFR

11.89.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new airworthiness directive to

read as follows:

95–11–14 Bell Helicopter Textron, Inc

(BHTI): Amendment 39–9247 Docket No.

94–SW–08–AD.

Applicability: Model 206A, 206B, 206L,

206L–1, 206L–3, and 206L–4 helicopters,

with crosstube assemblies (crosstubes), BHTI

part numbers (P/N) 206–050–107, 206–050–

119, 206–050–134, 206–050–157, 206–050–

169, 206–053–109, 206–053–119, and 206–

053–129 (all dash numbers), or Airborne

Supply, Inc. P/N AB206–050–107, AB206–

050–119, or AB206–053–109 (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 failure

of the crosstubes and subsequent loss of

control of the helicopter, accomplish the

following:

(a) Within 90 calendar days after the

effective date of this AD, remove any affected

crosstube and replace it with an airworthy

crosstube in accordance with the appropriate

maintenance manual or service instructions.

Any crosstubes removed as a result of this

AD shall be permanently marked as

unairworthy.

Note 2: For BHTI P/N 206–053–109 and

206–053–119, the P/N are vibro-etched on

the upper cuff of the crosstube on the aft side

on both forward and aft crosstubes; for BHTI

P/N 206–053–129, the P/N is vibro-etched on

the bottom of the cuff on the aft side on both

forward and aft crosstubes; for BHTI P/N

206–050–107, 206–050–119, 206–050–134,

206–050–157, and 206–050–169, the P/N are

stamped in ink on the crosstube, which is

shipped without paint (once the helicopter is

painted, the P/N are covered); and for

Airborne Supply, Inc., P/N AB206–050–107,

AB206–050–119, and AB206–053–109, the P/

N are rubber stamped at the bottom end of

the crosstube.

(b) If the crosstubes’ P/N cannot be

determined by reference to the crosstubes, if

possible, determine the P/N by reference to

the maintenance records or other aircraft

records. If the crosstubes’ P/N cannot be

determined, replace the crosstubes with

airworthy crosstubes within 90 calendar days

after the effective date of this AD in

accordance with the appropriate

maintenance manual or service instructions.

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used when approved by the Manager,

Rotorcraft Certification Office, FAA,

Rotorcraft Directorate. 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 3: 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 sections 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.

(e) This amendment becomes effective on

June 30, 1995.

Issued in Fort Worth, Texas, on May 19,

1995.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 95–12957 Filed 5–25–95; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 71

[Airspace Docket No. 94–ASW–18]

Amendment of Class D Airspace; New

Orleans NAS, Alvin Callender Field, LA

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This action amends the Class

D airspace at New Orleans Naval Air

Station (NAS), Alvin Callender Field,

New Orleans, LA. The decommissioning

of the New Orleans NAS Nondirectional Radio Beacon (NDB)

removes the need for controlled airspace

to protect the standard instrument

approach for the NDB. This action is

intended to eliminate the Class D

airspace that is no longer necessary as

a result of the decommissioning of the

New Orleans NAS NDB at New Orleans

NAS, Alvin Callender Field, New

Orleans, LA.

EFFECTIVE DATE: 0901 UTC, July 20,

1995.