Federal Register / Vol. 61, No. 177 /Wednesday, September 11, 1996 /Rules and Regulations 47813

(d) Perform a fluorescent penetrant

inspection of blades for cracks in accordance

with Hartzell Propeller Inc. Service Bulletin

136H, dated March 12, 1993, prior to

installing a serviceable hub.

(e) Perform magnetic particle inspection of

blade clamps for cracks in accordance with

Hartzell Service Manual 202A, dated March

1993, pages 201 to 215, prior to installing a

serviceable hub.

(f) If cracks are found in either the blade

or the blade clamps, prior to further flight

replace with serviceable blade or blade

clamps.

(g) Reassemble the propeller in accordance

with Hartzell Propeller Inc. Service Manual

118F, Revision 2, dated May 1992, pages 57

to 96, for 3- and 4-bladed hub models, and

Service Manual 132A, Revision 2, dated June

1992, pages VII–1 to VII–46, for 5-blade hub

models.

(h) 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 Principal 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.

(i) 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.

(j) The actions required by this AD shall be

done in accordance with the following

service documents:

Document No. Pages Date

Hartzell Propeller Inc., SB No. 136H ............................................................................................. 1–18 March 12, 1993.

Total Pages: 18.

Hartzell Propeller Inc., Service Manual No. 202A ........................................................................ 201–215 March 1993.

Total Pages: 15.

TRW Hartzell Propeller Overhaul Manual, No. 118–E ................................................................. 57, 58 April 1985.

Hartzell Propeller Inc., Manual No. 118F, Revision 2 .................................................................. 59, 60 May 1992.

TRW Hartzell Propeller Overhaul Manual No. 119–E .................................................................. 61–83 April 1985.

Hartzell Propeller Inc., Manual No. 118F, Revision 2 .................................................................. 84, 84a, 84b May 1992.

TRW Hartzell Propeller Overhaul Manual No. 118–E .................................................................. 85, 86 April 1985.

Hartzell Propeller Inc., Manual No. 118F, Revision 2 .................................................................. 87, 88, 88a, 88b April 1985, May 1992.

TRW Hartzell Propeller, Overhaul Manual No. 118–E ................................................................. 89–96 April 1985.

Total Pages: 44.

Hartzell Propeller, Products Division, Instruction Manual No. 132–A ....................................... VII–1–VII–30 Sept. 1, 1985.

Hartzell Propeller Inc., Instruction Manual No. 132–A ................................................................ VII–31 Sept. 1, 1985.

Hartzell Propeller Inc., Manual No. 132A ..................................................................................... VII–32 No Date.

Hartzell Propeller, Products Division, Instruction Manual No. 132–A ....................................... VII–33–VII–40 Sept. 1, 1985.

Hartzell Propeller Inc., Instruction Manual No. 132–A ................................................................ VII–41 Sept. 1, 1985.

Hartzell Propeller Inc., Manual No. 132A, Revision #1 ............................................................... VII–42, VII–43 April 1990.

Hartzell Propeller Inc., Instruction Manual No. 132–A ................................................................ VII–44 Sept. 1, 1985.

Hartzell Propeller Inc., Manual No. 132A, Revision #1 ............................................................... VII–45, VII–46 April 1990.

Total Pages: 46.

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, ATTN:

Product Support; telephone (513) 778–4388,

fax (513) 778–4321. 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.

(k) This amendment becomes effective on

October 16, 1996.

Issued in Burlington, Massachusetts, on

August 26, 1996.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 96–22770 Filed 9–10–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–224–AD; Amendment

39–9752; AD 96–19–04]

RIN 2120–AA64

Airworthiness Directives; Fokker

Model F28 Mark 1000, 2000, 3000, and

4000 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Fokker Model F28

Mark 1000, 2000, 3000, and 4000 series

airplanes. This action requires a onetime inspection to detect cracks of the

dimpled lap joints in the fuselage skin,

and repair of cracked lap joints. This

amendment is prompted by a report

indicating that cracks were found at

various locations in the outer skin of the

dimpled longitudinal lap joints of the

fuselage skin. The actions specified in

this AD are intended to prevent such

cracking, which could result in reduced

structural integrity of the fuselage and/

or rapid decompression of the airplane.

DATES: Effective September 26, 1996.

The incorporation by reference of

Fokker Service Bulletin F28/53–144,

dated July 15, 1996, as listed in the

regulations is approved by the Director

of the Federal Register as of September

26, 1996.

The incorporation by reference of

Fokker Service Bulletin F28/53–121,

Revision 1, dated December 13, 1991, as

listed in the regulations, was approved

previously by the Director of the Federal

Register as of October 8, 1992 (57 FR

40311, September 3, 1992).

Comments for inclusion in the Rules

Docket must be received on or before

November 12, 1996.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96–NM–

224–AD, 1601 Lind Avenue SW.,

Renton, WA 98055–4056.

The service information referenced in

this AD may be obtained from Fokker

Aircraft USA, Inc., 1199 North Fairfax

Street, Alexandria, VA 22314. This
47814 Federal Register / Vol. 61, No. 177 /Wednesday, September 11, 1996 /Rules and Regulations

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue SW., Renton, WA; or

at the Office of the Federal Register, 800

North Capitol Street NW., Suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Tim Dulin, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue SW., Renton, WA

98055–4056; telephone (206) 227–2141;

fax (206) 227–1149.

SUPPLEMENTARY INFORMATION: The

Rijksluchtvaartdienst (RLD), which is

the airworthiness authority for the

Netherlands, recently notified the FAA

that an unsafe condition may exist on

certain Fokker Model F28 Mark 1000,

2000, 3000, and 4000 series airplanes.

The RLD advises that it recently

received a report indicating that, during

a walk-around inspection of a Model

F28 Mark 4000 series airplane, two

cracks were found in the outer skin of

the left- and right-hand dimpled

longitudinal lap joints of the fuselage

skin between stations 15263 and 15733,

stringers 16 and 17, and stringers 58 and

59. These cracks were approximately 20

inches long. The exact cause of such

cracking is unknown at this time.

Currently, AD 93–13–04, amendment

39–8617 (58 FR 38513, July 19, 1993)

requires inspection of these airplanes in

the area where the recent cracking was

found. The inspection is required to be

accomplished in accordance with Item

53–30–08 of the Fokker Structural

Integrity Program (SIP) Document

28438. AD 93–13–04 requires that the

inspection be accomplished by the time

that the airplane has accumulated

32,000 total flight cycles, and that it be

repeated thereafter at intervals not to

exceed 2,700 flight cycles. However, the

subject cracking was found on the

affected airplane some 3,520 flight

cycles before the airplane had reached

inspection threshold of 32,000 flight

cycles.

In addition, AD 92–19–02,

amendment 39–8359 (57 FR 40311,

September 3, 1992), requires

modification of the subject area in

accordance with Fokker Service Bulletin

F28/53–121, prior to the accumulation

of 32,000 flight cycles. However, the

affected airplane had accumulated only

28,480 total flight cycles; therefore, it

had not been modified in accordance

with that AD at the time cracking was

detected.

Cracking in the outer skin of the leftand right-hand dimpled longitudinal lap

joints of the fuselage skin between

stations 15263 and 15733, stringers 16

and 17, and stringers 58 and 59, if not

corrected, could result in reduced

structural integrity of this area of the

fuselage and/or rapid decompression of

the airplane.

The configuration of the subject area

on Fokker Model Mark 1000, 2000, and

3000 series airplanes is identical to that

on the affected Model Mark 4000 series

airplane. Therefore, all of these models

may be subject to this same unsafe

condition.

Explanation of Relevant Service

Information

Fokker has issued Service Bulletin

F28/53–144, dated July 15, 1996. This

service bulletin describes procedures for

a one-time low frequency eddy current

inspection to detect cracks of the

dimpled lap joints in the fuselage skin

between stringers 16 and 17, stringers

58 and 59, and frames 13345 and 14285.

It also describes procedures for

submitting a report of the inspection

results to Fokker.

Fokker also has issued Service

Bulletin F28/53–121, Revision 1, dated

December 13, 1991, which describes

procedures for repair of cracked

dimpled lap joints. The repair consists

of cutting out the lap joint and installing

a repair plate and shim on the outside

of the fuselage. The repair will

minimize the possibility of cracks

developing in the subject area of the

fuselage.

The RLD classified these service

bulletins as mandatory and issued

Dutch airworthiness directive BLA

1996–081 (A), dated July 24, 1996, in

order to assure the continued

airworthiness of these airplanes in the

Netherlands.

FAA’s Conclusions

This airplane model is manufactured

in the Netherlands and is type

certificated for operation in the United

States under the provisions of section

21.29 of the Federal Aviation

Regulations (14 CFR 21.29) and the

applicable bilateral airworthiness

agreement. Pursuant to this bilateral

airworthiness agreement, the RLD has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the RLD,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Explanation of Requirements of Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States, this AD is being issued to

prevent cracking in the subject area of

the fuselage skin, which could result in

reduced structural integrity of the

fuselage and/or rapid decompression of

the airplane. This AD requires a onetime low frequency eddy current

inspection to detect cracks of the

dimpled lap joints in the fuselage skin

between stringers 16 and 17, stringers

58 and 59, and frames 13345 and 14285;

and repair, if necessary. After

accomplishing the inspection, the AD

also requires operators to submit a

report of the inspection results to

Fokker. The actions are required to be

accomplished in accordance with the

service bulletins described previously.

Interim Action

This is considered to be interim

action. The inspection reports that are

required by this AD will enable the

manufacturer to obtain better insight

into the nature, cause, and extent of

cracking; and eventually to determine if

additional corrective action is necessary

to address the unsafe condition. Once

final action has been identified, the

FAA may consider further rulemaking.

Determination of Rule’s Effective Date

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 shall 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
Federal Register / Vol. 61, No. 177 /Wednesday, September 11, 1996 /Rules and Regulations 47815

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 Number 96–NM–224–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Regulatory Impact

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 U.S.C. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

96–19–04 Fokker: Amendment 39–9752.

Docket 96–NM–224–AD.

Applicability: Model F28 Mark 1000, 2000,

3000, and 4000 series airplanes, serial

numbers 11017 through 11241 inclusive; on

which Fokker Service Bulletin F28/53–121,

Revision 1, dated December 13, 1991, has not

been accomplished; certificated in any

category.

Note 1: This AD applies to each airplane

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

airplanes that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must request approval for an

alternative method of compliance in

accordance with paragraph (c) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent cracking of the fuselage skin,

which could result in reduced structural

integrity of the fuselage and/or rapid

decompression of the airplane, accomplish

the following:

(a) Within 60 days after the effective date

of this AD, perform a one-time low frequency

eddy current inspection to detect cracks of

the dimpled lap joints in the fuselage skin

between stringers 16 and 17, stringers 58 and

59, and frames 13345 and 14285, in

accordance with Fokker Service Bulletin

F28/53–144, dated July 15, 1996.

(1) If no crack is detected, no further action

is required by this paragraph.

(2) If any crack is detected, prior to further

flight, repair the affected lap joint in

accordance with Fokker Service Bulletin

F28/53–121, Revision 1, dated December 13,

1991. Accomplishment of the repair is

considered acceptable for compliance with

AD 92–19–02, amendment 39–8359 (57 FR

40311, September 3, 1992), and constitutes

terminating action for the inspection

identified as item 53–30–08 of the Fokker

structural integrity program, which is

required by AD 93–13–04, amendment 39–

8617 (58 FR 38513, July 17, 1993).

(b) Within 10 days after accomplishing the

inspection required by paragraph (a) of this

AD, submit a report of the inspection results

(both positive and negative findings) to

Fokker Services, ATTN: Manager Service

Engineering Jet Aircraft, P.O. Box 75047,

1117 ZN, Schiphol, The Netherlands.

Information collection requirements

contained in this regulation have been

approved by the Office of Management and

Budget (OMB) under the provisions of the

Paperwork Reduction Act of 1980 (44 U.S.C.

3501 et seq.) and have been assigned OMB

Control Number 2120–0056.

(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,

Standardization Branch, ANM–113, FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Standardization

Branch, ANM–113.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(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) The inspection shall be done in

accordance with Fokker Service Bulletin

F28/53–144, dated July 15, 1996. The

replacement shall be done in accordance

with Fokker Service Bulletin F28/53–121,

Revision 1, dated December 13, 1991. The

incorporation by reference of Fokker Service

Bulletin F28/53–144, dated July 15, 1996, is

approved by the Director of the Federal

Register in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51. The incorporation by

reference of Fokker Service Bulletin F28/53–

121, Revision 1, dated July 15, 1996, was

approved previously by the Director of the

Federal Register in accordance with 5 U.S.C.

552(a) and 1 CFR part 51 as of October 8,

1992 (57 FR 40311, September 3, 1992.

Copies may be obtained from Fokker Aircraft

USA, Inc., 1199 North Fairfax Street,

Alexandria, Virginia 22314. Copies may be

inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

(f) This amendment becomes effective on

September 26, 1996.

Issued in Renton, Washington, on

September 3, 1996.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 96– 22917 Filed 9–10–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 71

[Airspace Docket No. 94–AWA–2]

RIN 2120–AA66

Modification of the Dallas-Fort Worth

Class B Airspace Area; TX

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This action modifies the

Dallas-Forth Worth (DFW) Class B

airspace area. Specifically, this rule

raises the upper limit of the DFW Class