63294 Federal Register / Vol. 62, No. 229 / Friday, November 28, 1997 / Proposed Rules

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:

Fokker: Docket 97–NM–249–AD.

Applicability: Model F28 Mark 0070 and

Mark 0100 series airplanes; as listed in

Fokker Service Bulletin SBF100–53–084,

dated July 6, 1996; if equipped with any

corrujoint seal having part number (P/N)

BE20061 (Rolls-Royce P/N 3405891);

certificated in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise modified, altered, or repaired in

the area subject to the requirements of this

AD. For airplanes that have been otherwise

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 (e)

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 the leakage of hot air from the

corrujoint seals of low-and high-pressure

check valves located in the stubwings, which

could result in heat damage to the fuselage

skin and stubwing structure and consequent

reduced structural integrity, accomplish the

following:

(a) Within 3,000 flight hours or 12 months

after the effective date of this AD, whichever

occurs first, perform a one-time visual

inspection of the fuselage skin in the left-and

right-hand stubwings to detect heat damage;

in accordance with Part 2 of the

Accomplishment Instructions of Fokker

Service Bulletin SBF100–53–084, dated July

6, 1996.

(b) If no heat damage is found during the

inspection required by paragraph (a) of this

AD, prior to further flight, perform a leak test

of each corrujoint seal at the 7th stage lowpressure and 12th stage high-pressure check

valves of the left-and right-hand bleed air

systems, in accordance with Part 3 of the

Accomplishment Instructions of Fokker

Service Bulletin SBF100–53–084, dated July

6, 1996.

(1) If any leakage is found at a seal, prior

to further flight, replace that seal with a new

improved seal having part number EU15969,

in accordance with the Accomplishment

Instructions of Fokker Service Bulletin

SBF100–36–026, Revision 1, dated July 6,

1996.

(2) If no leakage is found at a seal, perform

an additional leak test of that seal within 250

flight hours after the initial test.

(i) If no leakage is found during the

additional test of the seal, within 3,000 flight

hours after the additional test, replace the

seal with an improved seal having P/N

EU15969, in accordance with the

Accomplishment Instructions of Fokker

Service Bulletin SBF100–36–026, Revision 1,

dated July 6, 1996.

(ii) If any leakage is found during the

additional test of the seal, prior to further

flight, accomplish paragraphs (b)(2)(ii)(A)

and (b)(2)(ii)(B) of this AD.

(A) Replace the seal with a new improved

seal having P/N EU15969, in accordance with

the Accomplishment Instructions of Fokker

Service Bulletin SBF100–36–026, Revision 1,

dated July 6, 1996.

(B) Inspect the fuselage skin in the

applicable left-or right-hand stubwing to

detect heat damage, in accordance with Part

2 of the Accomplishment Instructions of

Fokker Service Bulletin SBF100–53–084,

dated July 6, 1996.

(c) If any heat damage is found during the

inspection required by paragraph (a) or

paragraph (b)(2)(ii)(B) of this AD, prior to

further flight, perform a detailed inspection

of the fuselage skin and stubwing structure

to detect the extent of heat damage, in

accordance with Parts 4 and 5 of the

Accomplishment Instructions of Fokker

Service Bulletin SBF100–53–084, dated July

6, 1996; and accomplish paragraphs (c)(1)

and (c)(2) of this AD.

(1) Repair the affected structure, in

accordance with Part 6 of the

Accomplishment Instructions of Fokker

Service Bulletin SBF100–53–084, dated July

6, 1996. And

(2) Replace all corrujoint seals having P/N

BE20061 (Rolls-Royce P/N 3405891) at the

7th stage low-pressure and 12th stage highpressure check valves of the left-and righthand bleed air systems with new improved

corrujoint seals having P/N EU15969, in

accordance with the Accomplishment

Instructions of Fokker Service Bulletin

SBF100–36–026, Revision 1, dated July 6,

1996.

(d) As of the effective date of this AD, no

person shall install a corrujoint seal having

P/N BE20061 (Rolls-Royce P/N 3405891) on

any airplane.

(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,

International Branch, ANM–116, 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, International Branch,

ANM–116.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(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 airplane to

a location where the requirements of this AD

can be accomplished.

Note 3: The subject of this AD is addressed

in Dutch airworthiness directive BLA 1995–

076/2 (A), dated August 30, 1996.

Issued in Renton, Washington, on

November 20, 1997.

Stewart R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–31159 Filed 11–26–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–264–AD]

RIN 2120–AA64

Airworthiness Directives; Fokker

Model F28 Mark 0070 and Mark 0100

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to all

Fokker Model F28 Mark 0070 and Mark

0100 series airplanes. This proposal

would require a one-time visual

inspection to detect cracking of the

brake torque tube lever, and corrective

action, if necessary. This proposal is

prompted by the issuance of mandatory

continuing airworthiness information by

a foreign civil airworthiness authority.

The actions specified by the proposed

AD are intended to prevent failure of the

brake torque tube lever, which could

result in a disconnection between the

brake pedal and brake system, and

consequent reduced directional

controllability of the airplane during

landing.

DATES: Comments must be received by

December 29, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 97–NM–

264–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

Fokker Service B.V., Technical Support

Department, P.O. Box 75047, 1117 ZN

Schiphol Airport, the Netherlands. This

information may be examined at the
Federal Register / Vol. 62, No. 229 / Friday, November 28, 1997 / Proposed Rules 63295

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington.

FOR FURTHER INFORMATION CONTACT:

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed 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 above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this notice may be changed in light

of the comments received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed 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

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 97–NM–264–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–103, Attention: Rules Docket No.

97–NM–264–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Rijksluchtvaartdienst (RLD),

which is the airworthiness authority for

the Netherlands, notified the FAA that

an unsafe condition may exist on all

Fokker Model F28 Mark 0070 and Mark

0100 series airplanes. The RLD advises

that it has received a report of the

failure of a brake torque tube lever,

which occurred while the operator of a

Fokker Model F28 Mark 0100 series

airplane was attempting to set the

parking brake. Subsequent inspection

during routine maintenance on two

other airplanes in the fleet revealed

small cracks in the same lever. Such

cracking, if not corrected, could result

in failure of the captain’s left-hand

brake torque tube lever, which could

result in a disconnection between the

captain’s left-hand brake pedal and lefthand brake system, and consequent

reduced directional controllability of

the airplane during landing.

Explanation of Relevant Service

Information

Fokker has issued Service Bulletin

SBF100–32–108, dated February 7,

1997, which describes procedures for a

one-time visual inspection using a

mirror or borescope to detect cracking of

the captain’s left-hand brake torque tube

lever. The service bulletin also describes

procedures for replacement of any

cracked lever with a new or serviceable

lever, or, as an alternative, replacement

of the entire brake torque tube assembly

with a new or serviceable assembly. The

RLD classified this service bulletin as

mandatory and issued Dutch

airworthiness directive 1997–025 (A),

dated February 28, 1997, in order to

assure the continued airworthiness of

these airplanes in the Netherlands.

FAA’s Conclusions

These airplane models are

manufactured in the Netherlands and

are 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

Proposed 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, the proposed AD would require

accomplishment of the actions specified

in the service bulletin described

previously.

Interim Action

This is considered to be interim

action until final action is identified, at

which time the FAA may consider

further rulemaking.

Cost Impact

The FAA estimates that 131 Fokker

Model F28 Mark 0070 and Mark 0100

series airplanes of U.S. registry would

be affected by this proposed AD, that it

would take approximately 3 work hours

per airplane to accomplish the

inspection proposed by this AD, and

that the average labor rate is $60 per

work hour. Based on these figures, the

cost impact of the proposed inspection

of this AD on U.S. operators is estimated

to be $23,580, or $180 per airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the proposed requirements of this AD

action, and that no operator would

accomplish those actions in the future if

this AD were not adopted.

Regulatory Impact

The regulations proposed herein

would 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

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

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); and (3) if

promulgated, 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 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.

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:
63296 Federal Register / Vol. 62, No. 229 / Friday, November 28, 1997 / Proposed Rules

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:

Fokker: Docket 97–NM–264–AD.

Applicability: All Model F28 Mark 0070

and Mark 0100 series airplanes, certificated

in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise 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 (b) 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 failure of the captain’s left-hand

brake torque tube lever, which could result

in a disconnection between the captain’s lefthand brake pedal and left-hand brake system,

and consequent reduced directional

controllability of the airplane during landing,

accomplish the following:

(a) Perform a one-time visual inspection

using a mirror or borescope to detect cracking

of the brake torque tube lever having part

number (P/N) D75669–001, in accordance

with Fokker Service Bulletin SBF100–32–

108, dated February 7, 1997, at the time

specified in paragraph (a)(1) or (a)(2), as

applicable, of this AD. If any crack is

detected, prior to further flight, replace either

the lever or the entire assembly with a new

or serviceable component, in accordance

with the Accomplishment Instructions of the

service bulletin.

(1) For airplanes that have accumulated

15,000 or more total flight cycles as of the

effective date of this AD: Inspect within 30

days after the effective date of this AD.

(2) For airplanes that have accumulated

fewer than 15,000 total flight cycles as of the

effective date of this AD: Inspect prior to the

accumulation of 10,000 total flight cycles, or

within 2 months after the effective date of

this AD, whichever occurs later.

(b) 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,

International Branch, ANM–116, 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, International Branch,

ANM–116.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(c) 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.

Note 3: The subject of this AD is addressed

in Dutch airworthiness directive 1997–025

(A), dated February 28, 1997.

Issued in Renton, Washington, on

November 20, 1997.

Stewart R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–31161 Filed 11–26–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–188–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300, A310, and A300–600 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to all

Airbus Model A300, A310, and A300–

600 series airplanes. For certain

airplanes, this proposal would require

replacing the bearings of the throttle

control levers with new sealed bearings.

For certain other airplanes, this

proposal would require replacing the

throttle control assemblies with new

assemblies. This proposal is prompted

by the issuance of mandatory

continuing airworthiness information by

a foreign civil airworthiness authority.

The actions specified by the proposed

AD are intended to prevent asymmetric

engine thrust on the airplane when the

autothrottle is engaged, which could

result in roll and yaw disturbances, and

consequent reduced controllability of

the airplane.

DATES: Comments must be received by

December 29, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 97–NM–

188–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4556, telephone (425) 227–2110;

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed 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 above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this notice may be changed in light

of the comments received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed 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

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 97-NM–188-AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–103, Attention: Rules Docket No.

97–NM–188–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.