39252 Federal Register / Vol. 63, No. 140 /Wednesday, July 22, 1998 / Proposed Rules

the FAA, Central Region, Office of the

Regional Counsel, Room 1558, 601 E. 12th

Street, Kansas City, Missouri 64106.

Issued in Kansas City, Missouri, on July 9,

1998.

Michael Gallagher,

Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 98–19046 Filed 7–21–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–140–AD]

RIN 2120–AA64

Airworthiness Directives; Dornier

Model 328–100 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

certain Dornier Model 328–100 series

airplanes. This proposal would require

repetitive tests to detect internal leakage

of hydraulic fluid within the hydraulic

components of the ground spoiler

system and to detect a buildup of

pressure in the return line of the bypass

valve, and corrective action, if

necessary; installation of additional

hydraulic lines and an additional

hydraulic shutoff valve in the ground

spoiler system; and replacement of the

valve block of the ground spoiler system

with a new part. This proposal also

would require eventual replacement of

the relief restrictor valves of the ground

spoiler system with redesigned parts,

which would constitute terminating

action for the repetitive tests. This

proposal is prompted by issuance of

mandatory continuing airworthiness

information by a foreign civil

airworthiness authority. The actions

specified by the proposed AD are

intended to prevent the ground spoilers

from unlocking and deploying during

takeoff or in flight, and consequent

reduced controllability of the airplane.

DATES: Comments must be received by

August 21, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

140–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

FAIRCHILD DORNIER, DORNIER

Luftfahrt GmbH, P.O. Box 1103, D–

82230 Wessling, Germany. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington.

FOR FURTHER INFORMATION CONTACT:

Norman B. Martenson, Manager,

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 98–NM–140–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–114, Attention: Rules Docket No.

98–NM–140–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Luftfahrt-Bundesamt (LBA),

which is the airworthiness authority for

Germany, notified the FAA that an

unsafe condition may exist on certain

Dornier Model 328–100 series airplanes.

The LBA advises that two conditions

may lead to the uncommanded

unlocking of the ground spoilers. First,

a manufacturing defect in a certain

batch of relief restrictor valves can lead

to internal leakage of hydraulic fluid

within the hydraulic components of the

ground spoiler system. Second, the

design of certain hydraulic components

may cause the hydraulic system to be

susceptible to the buildup of pressure in

the hydraulic return line and in the

bypass valve return line. These

conditions, if not corrected, could result

in the uncommanded unlocking and

deployment of the ground spoilers

during takeoff or in flight, and

consequent reduced controllability of

the airplane.

Explanation of Relevant Service

Information

Dornier has issued Service Bulletin

SB–328–29–220, dated May 20, 1997,

and Revision 1, dated May 4, 1998,

which describe procedures for

performing repetitive tests to detect

internal leakage of hydraulic fluid

within the hydraulic components of the

ground spoiler system and to detect a

buildup of pressure in the return line of

the bypass valve. These tests include: a

major leakage test of the hydraulic

components, a functional test of the

return filter element, a functional test of

the bypass valve of the return filter

element, and a functional test of the

shutoff valve with the bypass valve.

Dornier has issued Service Bulletin

SB–328–29–237, Revision 1, dated

December 17, 1997, which describes

procedures for installation of additional

hydraulic lines and an additional

hydraulic shutoff valve in the ground

spoiler system.

In addition, Dornier has issued

Service Bulletin SB–328–27–243,

Revision 1, dated December 18, 1997,

which describes procedures for

replacement of the relief restrictor

valves of the ground spoiler system with

redesigned parts, which would

eliminate the need for the repetitive

tests described previously.

Dornier also has issued Service

Bulletin SB–328–27–228, Revision 1,

dated December 18, 1997, which

describes procedures for replacement of

the valve block of the ground spoiler

system with a new part.

Accomplishment of the actions

specified in the service bulletins is
Federal Register / Vol. 63, No. 140 /Wednesday, July 22, 1998 / Proposed Rules 39253

intended to adequately address the

identified unsafe condition. The LBA

classified these service bulletins as

mandatory and issued German

airworthiness directives 97–189, dated

June 19, 1997; 1998–031, dated January

15, 1998; 1998–046, dated January 29,

1998; and 1997–331/2, dated March 12,

1998; in order to assure the continued

airworthiness of these airplanes in

Germany.

FAA’s Conclusions

This airplane model is manufactured

in Germany 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 LBA has kept the FAA informed of

the situation described above. The FAA

has examined the findings of the LBA,

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 bulletins described

previously, except as discussed below.

Differences Between Proposed Rule and

Service Bulletins

Operators should note that Dornier

Service Bulletins SB–328–29–220, dated

May 20, 1997, and SB–328–29–220,

Revision 1, dated May 4, 1998, do not

specify corrective action for disposition

of certain discrepant conditions.

However, if any discrepancy is detected

during the testing to detect internal

leakage of hydraulic fluid within the

hydraulic components of the ground

spoiler system and to detect a buildup

of pressure in the return line of the

bypass valve, this proposal would

require, prior to further flight,

replacement of the relief restrictor

valves of the ground spoiler system with

a redesigned part, in accordance with

Dornier Service Bulletin SB–328–27–

243, Revision 1, dated December 18,

1997.

Cost Impact

The FAA estimates that 11 airplanes

of U.S. registry would be affected by this

proposed AD.

It would take approximately 3 work

hours per airplane to accomplish the

proposed tests, at an average labor rate

of $60 per work hour. Based on these

figures, the cost impact of the tests

proposed by this AD on U.S. operators

is estimated to be $180 per airplane, per

test cycle.

It would take approximately 16 work

hours per airplane to accomplish the

proposed installation, at an average

labor rate of $60 per work hour.

Required parts would be supplied by

the manufacturer at no cost to operators.

Based on these figures, the cost impact

of the installation proposed by this AD

on U.S. operators is estimated to be

$960 per airplane.

It would take approximately 2 work

hours per airplane to accomplish the

proposed replacement of the relief

restrictor valves, at an average labor rate

of $60 per work hour. Required parts

would be supplied by the manufacturer

at no cost to operators. Based on these

figures, the cost impact of this

replacement proposed by this AD on

U.S. operators is estimated to be $120

per airplane.

It would take approximately 2 work

hours per airplane to accomplish the

proposed replacement of the valve

block, at an average labor rate of $60 per

work hour. Required parts would be

supplied by the manufacturer at no cost

to operators. Based on these figures, the

cost impact of this replacement

proposed by this AD on U.S. operators

is estimated to be $120 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:

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:

Dornier Luftfahrt GMBH: Docket 98–NM–

140–AD.

Applicability: Model 328–100 series

airplanes, certificated in any category,

equipped with active ground spoiler option

040–001; as listed in the following service

bulletins:

• Dornier Service Bulletin SB–328–29–

220, Revision 1, dated May 4, 1998;

• Dornier Service Bulletin SB–328–29–

237, Revision 1, dated December 17, 1997;

• Dornier Service Bulletin SB–328–27–

243, Revision 1, dated December 18, 1997;

and

• Dornier Service Bulletin SB–328–27–

228, Revision 1, dated December 18, 1997.

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 (f) 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 ground spoilers from

unlocking and deploying during takeoff or in

flight, and consequent reduced

controllability of the airplane, accomplish

the following:
39254 Federal Register / Vol. 63, No. 140 /Wednesday, July 22, 1998 / Proposed Rules

(a) Prior to the accumulation of 3,000 total

flight hours, or within 300 flight hours after

the effective date of this AD, whichever

occurs later: Perform tests to detect internal

leakage of hydraulic fluid within the

hydraulic components of the ground spoiler

system and to detect a buildup of pressure in

the return line of the bypass valve, in

accordance with Dornier Service Bulletin

SB–328–29–220, dated May 20, 1997, or

Dornier Service Bulletin SB–328–29–220,

Revision 1, dated May 4, 1998.

(1) If no discrepancy is detected, repeat the

tests thereafter at intervals not to exceed

3,000 flight hours, until accomplishment of

the replacement required by paragraph (c) of

this AD.

(2) If any discrepancy is detected, prior to

further flight, accomplish the replacement

required by paragraph (c) of this AD.

(b) Install additional hydraulic lines and an

additional hydraulic shutoff valve in the

ground spoiler system, in accordance with

Dornier Service Bulletin SB–328–29–237,

Revision 1, dated December 17, 1997, at the

applicable time specified in either paragraph

(b)(1) or (b)(2) of this AD.

(1) For airplanes having serial numbers up

to and including 3086, equipped with ground

spoiler actuator, part number 1059A0000–02:

Install within 12 months after the effective

date of this AD.

(2) For airplanes having serial numbers up

to and including 3086, and equipped with

ground spoiler actuator, part number

1059A0000–03: Install within 7 days after the

effective date of this AD.

(c) Replace the relief restrictor valves of the

ground spoiler system, part number ZRV87–

2, with a redesigned valve having part

number ZRV87–3, in accordance with

Dornier Service Bulletin SB–328–27–243,

Revision 1, dated December 18, 1997, at the

applicable time specified in either paragraph

(c)(1) or (c)(2) of this AD. Accomplishment of

this replacement constitutes terminating

action for the repetitive tests required by

paragraph (a) of this AD.

(1) For airplanes having serial numbers up

to and including 3098, equipped with ground

spoiler actuator, part number 1059A0000–02:

Replace within 12 months after the effective

date of this AD.

(2) For airplanes having serial numbers up

to and including 3098, equipped with ground

spoiler actuator, part number 1059A0000–03:

Replace within 7 days after the effective date

of this AD.

(d) Replace the valve block of the ground

spoiler system with a new part, in

accordance with Dornier Service Bulletin

SB–328–27–228, Revision 1, dated December

18, 1997, at the applicable time specified in

either paragraph (d)(1) or (d)(2) of this AD.

(1) For airplanes having serial numbers up

to and including 3095, equipped with ground

spoiler actuator, part number 1059A0000–02:

Replace within 12 months after the effective

date of this AD.

(2) For airplanes having serial numbers up

to and including 3095, equipped with ground

spoiler actuator, part number 1059A0000–03:

Replace within 7 days after the effective date

of this AD.

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

person shall install on the ground spoiler

system of any airplane, a valve block, part

number 1060A0000–05, or a relief restrictor

valve, part number ZRV87–2.

(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,

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.

(g) 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 airplane to a

location where the requirements of this AD

can be accomplished.

Note 3: The subject of this AD is addressed

in German airworthiness directives 97–189,

dated June 19, 1997; 1998–031, dated January

15, 1998; 1998–046, dated January 29, 1998;

and 1997–331/2, dated March 12, 1998.

Issued in Renton, Washington, on July 15,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–19458 Filed 7–21–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–CE–20–AD]

RIN 2120–AA64

Airworthiness Directives; Mooney

Aircraft Corporation Models M20B,

M20C, M20D, M20E, M20F, M20G,

M20J, M20K, M20L, M20M, and M20R

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes to

adopt a new airworthiness directive

(AD) that would apply to certain

Mooney Aircraft Corporation (Mooney)

Models M20B, M20C, M20D, M20E,

M20F, M20G, M20J, M20K, M20L,

M20M, and M20R airplanes. The

proposed AD would require repetitively

inspecting the aileron control link

welded area, and if cracks are found,

replacing the control link with a part of

improved design. Service difficulty

reports (SDR’s) on the aileron control

link and reported failures of the aileron

control link prompted the proposed

action. The actions specified by the

proposed AD are intended to detect and

correct cracked aileron control links,

which could result in loss of aileron

control and loss of the airplane.

DATES: Comments must be received on

or before September 30, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Central Region,

Office of the Regional Counsel,

Attention: Rules Docket No. 98–CE–20–

AD, Room 1558, 601 E. 12th Street,

Kansas City, Missouri 64106. Comments

may be inspected at this location

between 8 a.m. and 4 p.m., Monday

through Friday, holidays excepted.

Service information that applies to the

proposed AD may be obtained from

Mooney Aircraft Corporation, Louis

Schreiner Field, Kerrville, Texas, 78028.

This information also may be examined

at the Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Bob

D. May, Aerospace Engineer, FAA,

Airplane Certification Office, 2601

Meacham Boulevard, Fort Worth, Texas

76193–0150; telephone: (817) 222–5156;

facsimile: (817) 222–5960.

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

should 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 that

summarizes 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 No. 98–CE–20–AD.’’ The