24220 Federal Register / Vol. 61, No. 94 / Tuesday, May 14, 1996 / Rules and Regulations

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new airworthiness directive to

read as follows:

AD 96–06–12 Bell Helicopter Textron, Inc.:

Amendment 39–9616. Docket No. 96–

SW–01–AD.

Applicability: Model 47B, 47B–3, 47D,

47D–1, 47G, 47G–2, 47G–2A, 47G–2A–1,

47G–3, 47G–3B, 47G–3B–1, 47G–3B–2, 47G–

3B–2A, 47G–4, 47G–4A, 47G–5, 47G–5A,

47H–1, 47J, 47J–2, 47J–2A, and 47–K

helicopters, with tail rotor blade assembly,

part number (P/N) 047–642–117–105, serial

numbers (S/N) A–1943 through A–2068,

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 (f) 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 premature delamination or

separation of the tail rotor blade (blade) tip

block or the abrasion strip, which could lead

to failure of the blade and subsequent loss of

control of the helicopter, accomplish the

following:

(a) Prior to the first flight of each day,

visually inspect each blade tip, abrasion

strip, blade skin and blade butt as follows:

(1) Inspect each blade tip for corrosion or

delamination adjacent to the abrasion strip

and tip block.

(2) Inspect each abrasion strip for corrosion

or delamination, paying particular attention

to the abrasion strip leading edge.

(3) Inspect each blade skin for corrosion,

paying particular attention to any areas of

paint cracking or damage. Inspect all bonded

joints for corrosion or delamination.

(4) Inspect each blade butt around the

bearings for corrosion or delamination.

(b) Thereafter, conduct the visual

inspections specified in paragraph (a) of this

AD at intervals not to exceed 10 hours timein-service.

(c) If the inspections required by

paragraphs (a) and (b) of this AD reveal any

corrosion or delamination, replace the blade

with an airworthy blade before further flight.

(d) Installation of any airworthy tail rotor

blade assembly which has been FAAapproved for the particular Model 47

helicopter, except for P/N 047–642–117–105

with S/N A–1943 through A–2068,

constitutes a terminating action for the

requirements of this AD.

(e) Installation of tail rotor blade assembly,

P/N 047–642–117–105M, including those

with S/N A–1943 through A–2068,

constitutes a terminating action for the

requirements of this AD.

Note 2: Bell Helicopter Textron Alert

Service Bulletin No. 47–96–21, dated January

29, 1996, pertains to this AD.

(f) 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, 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.

(g) 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.

(h) This amendment becomes effective on

May 29, 1996, to all persons except those

persons to whom it was made immediately

effective by Priority Letter AD 96–06–12,

issued March 13, 1996, which contained the

requirements of this amendment.

Issued in Fort Worth, Texas, on May 3,

1996.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 96–11958 Filed 5–13–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–SW–02–AD; Amendment

39–9615; AD 96–10–09]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Helicopter Systems Model

369, 369A, 369D, 369E, 369F, 369FF,

369H, 369HE, 369HM, 369HS, and 500N

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to McDonnell Douglas

Helicopter Systems (MDHS) Model 369,

369A, 369D, 369E, 369F, 369FF, 369H,

369HE, 369HM, 369HS, and 500N

helicopters. This action requires initial

and repetitive inspections of each main

rotor blade (blade) root for either cracks

or paint and sealant cracking or

separation between the lower surface

root end fitting and the doubler. This

amendment is prompted by one

accident in which a blade separated

from the helicopter, as well as eight

other reports of cracked blades. The

actions specified in this AD are

intended to prevent failure of a blade

resulting in separation of the blade and

subsequent loss of control of the

helicopter.

DATES: Effective May 29, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of 15 days

after the date of publication in the

Federal Register.

Comments for inclusion in the Rules

Docket must be received on or before

July 15, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Office of the

Assistant Chief Counsel, Attention:

Rules Docket No. 96–SW–02–AD, 2601

Meacham Blvd., Room 663, Fort Worth,

Texas 76137.

The service information referenced in

this AD may be obtained from MDHS,

Technical Publications, Bldg. 530/B111,

5000 E. McDowell Rd., Mesa, Arizona

85215–9797. This information may be

examined at the FAA, Office of the

Assistant Chief Counsel, 2601 Meacham

Blvd., Room 663, Fort Worth, Texas

76137; or at the Office of the Federal

Register, 800 North Capitol Street NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr.

John Cecil, Aerospace Engineer, ANM–

120L, Los Angeles Aircraft Certification

Office, Northwest Mountain Region,

3960 Paramount Blvd., Lakewood,

California, telephone (310) 627–5322,

fax (310) 627–5210.

SUPPLEMENTARY INFORMATION: This

amendment adopts a new AD that is

applicable to MDHS Model 369, 369A,

369D, 369E, 369F, 369FF, 369H, 369HE,

369HM, 369HS, and 500N helicopters.

One accident occurred in August 1995

in which one blade separated from the

rotor system while the helicopter was

on the ground. Additionally, there were

eight reports of blade cracking prior to

the one accident, all of which were

discovered during either routine

inspections or inspections resulting

from reported abnormal vibrations.

Subsequent investigations revealed that

bonding separation occurred between

the lower surface root end fitting and

the doubler. This condition, if not

corrected, could result in failure of a

blade resulting in separation of the

blade and subsequent loss of control of

the helicopter.
Federal Register / Vol. 61, No. 94 / Tuesday, May 14, 1996 / Rules and Regulations 24221

The FAA has reviewed McDonnell

Douglas Helicopter Systems Service

Information Notice No. HN–239, DN–

188, EN–81, FN–67, and NN–008, dated

October 27, 1995, which describes

procedures for a one-time visual

inspection of the blade root end for

chordwise cracking and paint or sealant

cracking between the lower surface root

end fitting and the doubler, and then

repetitive inspections at intervals of 100

hours time-in-service (TIS).

Since an unsafe condition has been

identified that it is likely to exist or

develop on other MDHS Model 369,

369A, 369D, 369E, 369F, 369FF, 369H,

369HE, 369HM, 369HS, and 500N

helicopters of the same type design, this

AD is being issued to prevent failure of

a blade at the root end due to fatigue

cracking that initiates at the outboard

bolt hole and usually travels in a

chordwise direction. This AD requires,

within 10 hours TIS after the effective

date of this AD, a one-time visual

inspection of each blade root end near

the doubler paying particular attention

to chordwise cracks and paint or sealant

cracking or separation between the

lower surface root end fitting and the

doubler. Additionally, this AD requires

repetitive visual inspections of each

blade, at intervals not to exceed 100

hours TIS, for bond separation between

the lower surface root end fitting and

doubler paying particular attention to

chordwise cracks. The actions are

required to be accomplished in

accordance with the service information

notice described previously.

Due to the critical need to ensure the

integrity of the main rotor system, and

to comply with the requirements of this

AD within 10 hours TIS, this rule must

be issued immediately to correct an

unsafe condition in the affected

helicopters.

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

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. 96–SW–02–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, Incorporation by reference,

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 USC 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new airworthiness directive to

read as follows:

AD 96–10–09 McDonnell Douglas

Helicopter Systems: Amendment 39–

9615. Docket No. 96–SW–02–AD.

Applicability: Model 369, 369A, 369D,

369E, 369F, 369FF, 369H, 369HE, 369HM,

369HS, and 500N helicopters, 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 a main rotor blade

(blade) resulting in separation of the blade

and subsequent loss of control of the

helicopter, accomplish the following:

(a) Within 10 hours time-in-service (TIS)

after the effective date of this AD, perform a

visual inspection of each blade root end for

cracking and paint or sealant cracking,

paying particular attention to chordwise

cracking, and for separation between the

lower surface root end fitting and doubler, in

accordance with Part I of the

Accomplishment Instructions of McDonnell

Douglas Helicopter Systems Service

Information Notice (SIN) HN–239, DN–188,

EN–81, FN–67, and NN–008, dated October

27, 1995. If any blade crack is noted, before

further flight, remove the blade and replace

it with an airworthy blade. If paint or sealant

cracking or separation is noted, accomplish

the inspection in paragraph 3E of Part II of

the Accomplishment Instructions of SIN HN–

239, DN–188, EN–81, FN–67, and NN–008,

dated October 27, 1995, using a piece of

Mylar/viewfoil that is no thicker than .004-

inch and that is cut to a size between 0.9 inch
24222 Federal Register / Vol. 61, No. 94 / Tuesday, May 14, 1996 / Rules and Regulations

and 1.1 inches wide and between 3.9 inches

and 4.1 inches long. If any corner of the

Mylar can be inserted between the lower

surface root end fitting and doubler surface

to a depth of 0.1 inch or greater, remove the

blade from service and replace it with an

airworthy blade.

(b) Thereafter, at intervals not to exceed

100 hours TIS, remove the blades and inspect

for cracking, paying particular attention to

chordwise cracking, and separation between

the lower surface root end fitting and doubler

in accordance with Part II of the

Accomplishment Instructions of McDonnell

Douglas Helicopter Systems SIN HN–239,

DN–188, EN–81, FN–67, and NN–008, dated

October 27, 1995. If missing or cracked

adhesive or paint is detected at the lower

surface root end fitting to doubler bonding

line, accomplish the inspection in paragraph

3E of Part II of the Accomplishment

Instructions of SIN HN–239, DN–188, EN–81,

FN–67, and NN–008, dated October 27, 1995

using a piece of Mylar/viewfoil that is no

thicker than .004-inch that is cut to a size

between 0.9 inch and 1.1 inches wide and

between 3.9 inches and 4.1 inches long. If

any corner of the Mylar can be inserted

between the lower surface root end fitting

and doubler surface to a depth of 0.1 inch or

greater, remove the blade from service and

replace it with an airworthy blade.

(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, Los

Angeles Aircraft 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, Los Angeles Aircraft

Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles Aircraft

Certification Office.

(d) Special flight permits will not be

issued.

(e) The inspections shall be done in

accordance with McDonnell Douglas

Helicopter Systems Service Information

Notice (SIN) HN–239, DN–188, EN–81, FN–

67, and NN–008, dated October 27, 1995.

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 McDonnell Douglas Helicopter Systems,

Technical Publications, Bldg. 530/B111, 5000

E. McDowell Rd., Mesa, Arizona 85215–9797.

Copies may be inspected at the FAA, Office

of the Assistant Chief Counsel, 2601

Meacham Blvd., Room 663, Fort Worth,

Texas; or at the Office of the Federal Register,

800 North Capitol Street, NW., suite 700,

Washington, DC.

(f) This amendment becomes effective May

29, 1996.

Issued in Fort Worth, Texas, on May 2,

1996.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 96–11959 Filed 5–13–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 71

[Airspace Docket No. 96–AWP–6]

Amendment of Class E Airspace;

Visalia, CA

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This action amends the Class

E airspace area at Visalia, CA. The

abandonment of Ianni Strip, CA has

made this action necessary. This action

will remove reference of Ianni Strip, CA

from the Class E airspace description for

Visalia, CA.

EFFECTIVE DATE: 0901 UTC August 15,

1996.

FOR FURTHER INFORMATION CONTACT:

William Buck, Airspace Specialist,

System Management Branch, AWP–530,

Air Traffic Division, Western-Pacific

Region, Federal Aviation

Administration, 15000 Aviation

Boulevard, Lawndale, California, 90261,

telephone (310) 725–6556.

SUPPLEMENTARY INFORMATION:

History

On March 11, 1996, the FAA

proposed to amend part 71 of the

Federal Aviation Regulations (14 CFR

part 71) by revising the Class E airspace

area at Visalia, CA. The abandonment of

Ianni Strip, CA has made this action

necessary.

Interested parties were invited to

participate in this rulemaking

proceeding by submitting written

comments on the proposal to the FAA.

No comments to the proposal were

received.

Class E airspace designations are

published in paragraph 6005 of FAA

Order 7400.9C dated August 17, 1995,

and effective September 16, 1995, which

is incorporated by reference in 14 CFR

71.1. The Class E airspace designation

listed in this document will be

published subsequently in this Order.

The Rule

This amendment to part 71 of the

Federal Aviation Regulations (14 CFR

part 71) amends the Class E airspace

area a Visalia, CA. The abandonment of

Ianni Strip, CA has made this action

necessary. This action will remove the

reference of Ianni Strip, CA from the

Class E airspace description for Visalia,

CA.

The FAA has determined that this

regulation only involves an established

body of technical regulations for which

frequent and routine amendments are

necessary to keep them operationally

current. Therefore, this regulation—(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 10034; February 26, 1979); and (3)

does not warrant preparation of a

Regulatory Evaluation as the anticipated

impact is so minimal. Since this is a

routine matter that will only affect air

traffic procedures and air navigation, it

is certified that this rule will not have

a significant economic impact on a

substantial number of small entities

under the criteria of the Regulatory

Flexibility Act.

List of Subjects in 14 CFR Part 71

Airspace, Incorporation by reference,

Navigation (air).

Adoption of the Amendment

In consideration of the foregoing, the

Federal Aviation Administration

amends 14 CFR part 71 as follows:

PART 71—[AMENDED]

1. The authority citation for 14 CFR

part 71 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40103, 40113,

40120; E.O. 10854, 24 FR 9565, 3 CFR, 1959–

1963 Comp., p. 389; 14 CFR 11.69.

§ 71.1 [Amended]

2. The incorporation by reference in

14 CFR 71.1 of the Federal Aviation

Administration Order 7400.9C, Airspace

Designations and Reporting Points,

dated August 17, 1995, and effective

September 16, 1995, is amended as

follows:

Paragraph 6005 Class E airspace areas

extending upward from 700 feet or more

above the surface of the earth.

* * * * *

AWP CA E5 Visalia, CA [Revised]

Visalia Municipal Airport, CA

(lat. 36°19′07′′ N, long. 119°23′34′′ W)

Visalia VOR/DME

(lat. 36°22′02′′ N, long. 119°28′56′′ W)

Swanson Ranch NR1 Airport, CA

(lat. 36°24′00′′ N, long 119°37′03′′ W)

That airspace extending upward from 700

feet above the surface within a 5-mile radius

of the Visalia Municipal Airport and within

1.8 miles each side of the Visalia VOR 302°

radial, extending from the 5-mile radius to 7

miles northwest of the VOR and within 4

miles each side of the Visalia VOR 150°

radial, extending from 1.7 mile southeast