Federal Register / Vol. 62, No. 212 / Monday, November 3, 1997 / Rules and Regulations 59277

PART 110—EXPORT AND IMPORT OF

NUCLEAR EQUIPMENT AND

MATERIAL

19. The authority citation for Part 110

continues to read as follows:

Authority: Secs. 51, 53, 54, 57, 63, 64, 65,

81, 82, 103, 104, 109, 111, 126, 127, 128, 129,

161, 181, 182, 183, 187, 189, 68 Stat. 929,

930, 931, 932, 933, 936, 937, 948, 953, 954,

955, 956, as amended (42 U.S.C. 2071, 2073,

2074, 2077, 2092–2095, 2111, 2112, 2133,

2134, 2139, 2139a, 2141, 2154–2158, 2201,

2231–2233, 2237, 2239); sec. 201, 88 Stat.

1242, as amended (42 U.S.C. 5841); sec 5,

Pub. L. 101–575, 104 Stat 2835 (42 U.S.C.

2243).

Sections 110.1(b)(2) and 110.1(b)(3) also

issued under Pub. L. 96–92, 93 Stat. 710 (22

U.S.C. 2403). Section 110.11 also issued

under sec. 122, 68 Stat. 939 (42 U.S.C. 2152)

and secs. 54c and 57d, 88 Stat. 473, 475 (42

U.S.C. 2074). Section 110.27 also issued

under sec. 309(a), Pub. L. 99–440. Section

110.50(b)(3) also issued under sec. 123, 92

Stat. 142 (42 U.S.C. 2153).Section 110.51 also

issued under sec. 184, 68 Stat. 954, as

amended (42 U.S.C. 2234). Section 110.52

also issued under sec. 186, 68 Stat. 955 (42

U.S.C. 2236). Sections 110.80–110.113 also

issued under 5 U.S.C. 552, 554. Sections

110.130–110.135 also issued under 5 U.S.C.

553. Sections 110.2 and 110.42(a)(9) also

issued under sec. 903, Pub. L. 102–496 (42

U.S.C. 2151 et seq.).

§ 110.4 [Amended]

20. In § 110.4, the telephone number

is revised to read ‘‘(301) 415–2344.’’

§ 110.26 [Amended]

21. In § 110.26(a)(2), the words

‘‘South Korea’’ are revised to read

‘‘Republic of Korea.’’

§ 110.52 [Amended]

22. In § 110.52(c), ‘‘subpart J’’ is

revised to read ‘‘subpart I.’’

§ 110.111 [Amended]

23. In § 110.111(f), ‘‘subpart L’’ is

revised to read ‘‘subpart K.’’

Dated at Rockville, Maryland, this 21st day

of October 1997.

For the Nuclear Regulatory Commission.

L. Joseph Callan,

Executive Director for Operations.

[FR Doc. 97–28988 Filed 10–31–97; 8:45 am]

BILLING CODE 7590–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–90–AD; Amendment 39–

10188; AD 97–23–01]

RIN 2120–AA64

Airworthiness Directives; Fairchild

Aircraft, Inc. SA226 and SA227 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment supersedes

Airworthiness Directive (AD) 93–15–02

R2, which currently requires the

following on Fairchild Aircraft, Inc.

(Fairchild Aircraft) SA226 and SA227

series airplanes that are equipped with

a certain Simmonds-Precision pitch trim

actuator: repetitively measuring the

freeplay of the pitch trim actuator and

repetitively inspecting the actuator for

rod slippage; immediately replacing any

actuator if certain freeplay limitations

are exceeded or rod slippage is evident;

and, eventually replacing the actuator

regardless of the inspection results. This

action retains the repetitive inspections

and replacement requirements, adds the

repetitive inspections after the

installation of certain Barber-Coleman

pitch time actuators, and removes the

terminating action. This action is the

result of failure of the no-backs on a

Barber-Colman pitch time actuator

installed on a Fairchild Aircraft SA227

series airplane. The actions specified by

this AD are intended to prevent failure

of the pitch trim actuator, which could

cause loss of control of the airplane.

DATES: Effective December 1, 1997.

The incorporation by reference of

Fairchild Aircraft SA226 Series Service

Letter 226–SL–014, Fairchild Aircraft

SA227 Series Service Letter 227–SL–

031, and Fairchild Aircraft SA227 Series

Service Letter CC7–SL–021, all Issued:

October 3, 1997, is approved by the

Director of the Federal Register as of

December 1, 1997.

The incorporation by reference of

Fairchild Aircraft SA226 Series Service

Letter 226–SL–005, and Fairchild

Aircraft SA227 Series Service Letter

227–SL–011, both Issued: April 8, 1993,

Revised: May 22, 1996, listed in the

regulations was previously approved by

the Director of the Federal Register as of

July 25, 1996 (61 FR 36817, July 15,

1996).

Comments for inclusion in the Rules

Docket must be receive on or before

January 2, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Central Region,

Office of the Regional Counsel,

Attention: Rules Docket 97–CE–90–AD,

Room 1558, 601 E. 12th Street, Kansas

City, Missouri 64106.

Service information that applies to

this AD may be obtained from Field

Support Engineering, Fairchild Aircraft,

Inc., P.O. Box 790490, San Antonio,

Texas 78279–0490; telephone (210)

824–9421; facsimile (210) 820–8609.

This information may also be examined

at the FAA, Central Region, Office of the

Regional Counsel, Attention: Rules

Docket 97–CE–90–AD, Room 1558, 601

E. 12th Street, Kansas City, Missouri

64106; or at the Office of the Federal

Register, 800 North Capitol Street, NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr.

Werner Koch, Aerospace Engineer,

FAA, Airplane Certification Office, 2601

Meacham Boulevard, Fort Worth, Texas

76193–0150; telephone (817) 222–5133;

facsimile (817) 222–5960.

SUPPLEMENTARY INFORMATION:

Discussion

Airworthiness Directive (AD) 93–15–

02 R2, Amendment 39–9689 (61 FR

36817, July 25, 1996), currently requires

the following on Fairchild Aircraft

SA226 and SA227 series airplanes that

are equipped with a certain SimmondsPrecision pitch trim actuator:

repetitively measuring the freeplay of

the pitch trim actuator and repetitively

inspecting the actuator for rod slippage;

immediately replacing any actuator if

certain freeplay limitations are exceeded

or rod slippage is evident; and

eventually replacing the actuator

regardless of the inspection results.

Accomplishment of the inspections

required by AD 93–15–02 R2 is in

accordance with Fairchild Aircraft

SA226 Series Service Letter (SL) 226–

SL–005, or Fairchild Aircraft SA227

Series SL 227–SL–011, both Issued:

April 8, 1993, Revised: May 22, 1996.

In addition, AD 93–15–02 R2,

Amendment 39–9689 (61 FR 36817, July

15, 1996), eliminates the initial

inspection and the repetitive inspection

if a Barber-Colman actuator (part

number (P/N) 27–19008–001 or –002 is

installed.

Actions Since Issuance of the Previous

Rule

Since issuance of AD 93–15–02 R2,

the FAA received an incident report of

a failure of a pitch trim actuator

installed on a Fairchild SA227 series

airplane during a landing approach. The

failure was specifically of the no-backs
59278 Federal Register / Vol. 62, No. 212 / Monday, November 3, 1997 / Rules and Regulations

on a Barber-Colman pitch trim actuator

(P/N 27–19008–002), which caused the

horizontal stabilizer to go full leading

edge down, resulting in a violent pitchup of the airplane. According to the

report, both pilots had to use extreme

force on the control column to recover

from the pitch-up and get the airplane

safely on the ground.

Because of this incident, Fairchild reexamined the possible fail rate of these

pitch trim actuators. This examination

shows that the no-backs in the BarberColeman pitch trim actuators installed

on the Fairchild SA226 and SA227

series airplanes are subject to failure

after accumulating a certain amount of

hours time-in-service (TIS). As a result,

Fairchild now recommends repetitive

inspections of the Barber-Colman pitch

trim actuators (P/N 27–19008–001/–

002).

Relevant Service Information

Fairchild has issued SA226 Series

Service Letter (SL) 226–SL–014,

Fairchild Aircraft SA227 Series SL 227–

SL–031, and Fairchild Aircraft SA227

Series SL CC7–SL–021, all Issued:

October 3, 1997, which specify

procedures for inspecting and testing all

Fairchild SA226 and SA227 series

airplanes equipped with a BarberColman pitch trim actuator P/N 27–

19008–001 or –002.

The FAA’s Determination

After examining the circumstances

and reviewing all available information

related to the incidents described above,

including the referenced service

information, the FAA has determined

that AD action should be taken in order

to prevent failure of the pitch trim

actuator, which could cause loss of

control of the airplane.

Explanation of the Provisions of This

AD

Since an unsafe condition has been

identified that is likely to exist or

develop in other Fairchild SA226 and

SA227 series airplanes of the same type

design, the FAA is issuing this AD to

supersede AD 93–15–02 R2. This AD

retains the inspection requirements for

airplanes equipped with the SimmondsPrecision pitch trim actuators, and

changes the inspection requirements for

airplanes equipped with Barber-Colman

pitch trim actuators to require

repetitively inspecting the actuator. This

action eliminates the terminating action

in AD 93–15–02 R2. Inspecting the

Barber-Colman actuator (P/N 27–19008–

001 or –002) is required in accordance

with the instructions in Fairchild SL

226–SL–014, SL 227–SL–031, or CC7–

SL–021, all Issued: October 3, 1997,

whichever is applicable. Inspecting the

Simmonds-Precision actuators will

continue to be accomplished in

accordance with Fairchild Aircraft

SA226 Series SL 226–SL–005, or

Fairchild Aircraft SA227 Series SL 227–

SL–011, both Issued: April 8, 1993,

Revised: May 22, 1996.

Determination of the Effective Date of

the AD

Since a situation exists (failure of the

pitch-trim actuators) that requires the

immediate adoption of this regulation, it

is found that notice and opportunity for

public prior 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 immediate flight safety and,

thus, was not preceded by notice and

opportunity to 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

above. 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. 97–CE–90–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 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

(otherwise, an evaluation is not

required). A copy of it, if filed, may be

obtained from the Rules Docket.

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

removing AD 93–15–02 R2, Amendment

39–9689 (61 FR 36817, July 15, 1996),

and by adding a new airworthiness

directive (AD) to read as follows:

97–23–01 Fairchild Aircraft, Inc.:

Amendment 39–10188; Docket No. 97–

CE–90–AD. Supersedes AD 93–15–01

R2, Amendment 39–9689.

Applicability: All SA226 and SA227 series

airplanes (all models and serial numbers),

certificated in any category, that are

equipped with a Simmonds-Precision pitch

trim actuator, (part number (P/N) DL5040M5

or P/N DL5040M6) or a Barber-Colman pitch

trim actuator (P/N 27–19008–001 or P/N 27–

19008–002).

Note 1: This AD applies to each airplane

identified in the preceding applicability
Federal Register / Vol. 62, No. 212 / Monday, November 3, 1997 / Rules and Regulations 59279

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 (d) 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 in the

body of this AD, unless already

accomplished.

To prevent failure of the pitch trim

actuator, which could cause loss of control of

the airplane, accomplish the following:

Note 2: The paragraph structure of this AD

is as follows:

Level 1: (a), (b), (c), etc.

Level 2: (1), (2), (3), etc.

Level 3: (i), (ii), (iii), etc.

Level 2 and Level 3 structures are

designations of the Level 1 paragraph they

immediately follow.

(a) Accomplish the following at the times

specified in the chart in paragraph (b) of this

AD:

(1) Initial and repetitive inspections:

(i) For airplanes equipped with a

Simmonds-Precision actuator, P/N

DL5040M5 and P/N DL5040M6, measure the

freeplay (inspection) of the pitch trim

actuator and inspect the actuator for rod

slippage in accordance with the

INSTRUCTIONS section of Fairchild Aircraft

SA226 Series Service Letter (SL) 226–SL–

005, or Fairchild Aircraft SA227 Series SL

227–SL–011, both Issued: April 8, 1993,

Revised: May 22, 1996, as applicable.

(ii) For airplanes equipped with BarberColman actuators, P/N 27–19008–001 or P/N

27–19008–002, conduct a functional

inspection of the actuator in accordance with

the INSTRUCTIONS section of Fairchild

Aircraft SL 226–SL–014, 227–SL–031, or

CC7–SL–021, Issued: October 3, 1997,

whichever is applicable.

Note 3: the actions in this AD are the same

as the actions in AD 93–15–02 R2, except for

the repetitive inspections added to the

Barber-Colman actuator, P/N 27–19008–001

or P/N 27–19008–002.

(2) Initial and repetitive replacements:

Replace the pitch trim actuator with one of

the following, in accordance with the

instructions in the applicable maintenance

manual at the time specified in the Repetitive

Replacement column of the chart in

paragraph (b) of this AD. However, if certain

freeplay limitations that are specified in the

service letters are exceeded or if rod slippage

is found, replace the pitch trim actuator prior

to further flight.

(i) A new Simmonds-Precision actuator, P/

N DL5040M5 or P/N DL5040M6.

(ii) A pitch trim actuator with an

overhauled, zero-timed part of the same

design and part number.

(iii) A Barber-Colman actuator, P/N 27–

19008–001 or P/N 27–19008–002.

(b) The following chart presents the initial

and repetitive inspection and replacement

compliance times of this AD:

Condition Initial inspection Repetitive inspection Repetitive

replacement

With an original Simmonds-Precision actuator, P/N DL5040M5,

installed.

Upon accumulating 3,000 hours

TIS on a Simmonds-Precision

P/N DL5040M5 actuator or within 50 hours TIS after April 17,

1995 (the effective date of AD

93–15–02 R1), whichever occurs later.

Every 250 hours TIS after initial

inspection until accumulating

5,000 hours TIS on the actuator

or 500 hours TIS after the last

inspection required by AD 93–

15–02 R1, whichever occurs

later.

Initially upon accumulating 5,000

hours TIS on the actuator or

500 hours TIS after the initial inspection, whichever occurs

later, and thereafter as indicated below.

With a replacement SimmondsPrecision actuator, P/N

DL5040M5, installed.

Initially upon accumulating 5,000

hours TIS on the new actuator,

or within 50 hours TIS after

April 17, 1995 (the effective

date of AD 93–15–02 R1),

whichever occurs later.

Every 300 hours TIS after the initial inspection until accumulating

6,500 hours TIS on the actuator.

Upon accumulating 6,500 hours

TIS on the actuator.

With a replacement SimmondsPrecision actuator, P/N

DL5040M6, installed. This part

can be new, modified from a P/

N DL5040M5 actuator, or overhauled and zero-timed.

Initially upon accumulating 7,500

hours TIS on the new or modified actuator, or within 50 hours

TIS after April 17, 1995 (the effective date of AD 93–15–02

R1), whichever occurs later.

Every 300 hours TIS after the initial inspection until accumulating

9,900 hours TIS on the actuator.

Upon accumulating 9,900 hours

TIS on the actuator.

With a replacement P/N

DL5040M5 actuator installed

that was overhauled and zerotimed where both nut assemblies, P/N AA56142, were replaced with new assemblies

during overhaul.

Initially upon accumulating 5,000

hours TIS on the over-hauled

actuator, or within 50 hours TIS

after April 17, 1995 (the effective date of AD 93–15–02 R1),

whichever occurs later.

Every 300 hours TIS after the initial inspection until accumulating

6,500 hours TIS on the actuator.

Upon accumulating 6,500 hours

TIS on the actuator.

With a replacement P/N

DL5040M5 actuator installed

that was overhauled and zerotimed where both nut assemblies, P/N AA56142, were not

replaced with new assemblies

during overhaul.

Initially upon accumulating 3,000

hours TIS on the over-hauled

actuator, or within 50 hours TIS

after April 17, 1995 (the effective date of AD 93–15–02 R1),

whichever occurs later.

Every 250 hours TIS after the initial inspection until accumulating

5,000 hours TIS on the actuator.

Upon accumulating 5,000 hours

TIS on the actuator.

With a Barber-Colman pitch trim

actuator installed, P/N 27–

19008–001 or 27–19008–002,

currently in-service with less

than 1,000 hours TIS since new

or overhauled, zero-timed.

Upon accumulating 500 hours

total TIS on the new or overhauled zero-timed pitch trim actuator, or within 50 hours TIS

after the effective date of this

AD, whichever occurs later.

Every 300 hours TIS after the initial inspection.None.

For newly fabricated and overhauled, zero-timed BarberColman actuator, P/N 27–

19008–001 or P/N 27–19008–

002 actuators.

Upon accumulating 500 hours

total TIS on the actuator, or

within 50 hours TIS after the effective date of this AD, whichever occurs later.

Every 300 hours TIS after the initial inspection.None.
59280 Federal Register / Vol. 62, No. 212 / Monday, November 3, 1997 / Rules and Regulations

(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.

(d) An alternative method of compliance or

adjustment of the initial or repetitive

compliance times that provides an equivalent

level of safety may be approved by the

Manager, Airplane Certification Office

(ACO), FAA, 2601 Meacham Boulevard, Fort

Worth, Texas 76193–0150. The request shall

be forwarded through an appropriate FAA

Maintenance Inspector, who may add

comments and then send it to the Manager,

Fort Worth Airplane Certification Office.

Alternative methods of compliance,

approved in accordance with AD 93–15–02–

R2, are not considered to be approved as

alternative methods of compliance with this

AD.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Forth Worth Airplane

Certification Office.

(e) The inspections required by this AD for

Fairchild SA226 and SA227 series airplanes

equipped with Barber-Colman pitch trim

actuators shall be done in accordance with

Fairchild Aircraft SA226 Series Service

Letter 226–SL–014, Fairchild Aircraft SA227

Series Service Letter 227–SL–031, or

Fairchild Aircraft SA227 Series Service

Letter CC7–SL–021, all Issued: October 3,

1997, whichever is applicable. This

incorporation by reference is approved by the

Director of the Federal Register is accordance

with 5 U.S.C. 552(a) and 1 CFR part 51. The

inspections required by this AD on Fairchild

Aircraft SA226 and SA227 series airplanes

equipped with Simmonds-Precision pitch

trim actuators shall be done in accordance

with Fairchild Aircraft SA226 Series Service

Letter (SL) 226–SL–005, and Fairchild

Aircraft SA227 Series SL 227–SL–011, both

Issued: April 8, 1993, Revised: May 22, 1996.

This incorporation by reference was

previously approved by the Director of the

Federal Register as of July 25, 1996 (61 FR

36817, July 15, 1996). Copies of all of the

documents may be obtained from Field

Support Engineering, Fairchild Aircraft Inc.,

P.O. Box 790490, San Antonio Texas 78279–

0490.

Copies may be inspected at the FAA,

Central Region, Office of the Regional

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

Kansas City, Missouri, or at the Office of the

Federal Register, 800 North Capitol Street,

NW., suite 700, Washington, DC.

(f) This amendment (39–10188) supersedes

AD 93–15–02 R2, Amendment 39–9689.

(g) This amendment (39–10188) becomes

effective on December 1, 1997.

Issued in Kansas City, Missouri, on

October 27, 1997.

Mary Ellen A. Schutt,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 97–28880 Filed 10–31–97; 8:45 am]

BILLING CODE 4910–13–M

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 84–CE–27–AD; Amendment 39–

10189; AD 85–02–05 R1]

RIN 2120–AA64

Airworthiness Directives; The New

Piper Aircraft, Inc. PA–20, PA–22, PA–

23, PA–24, PA–25, PA–30, PA–31P, PA36, PA–39, and PA–44 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; correction.

SUMMARY: This document clarifies

information in Airworthiness Directive

(AD) 85–02–05, which applies to all The

New Piper Aircraft, Inc. (Piper) PA–20,

PA–22, PA–23, PA–24, PA–25, PA–30,

PA–31P, PA–36, PA-39, and PA–44

series airplanes. AD 85–02–05 currently

requires installing on the pilot’s

instrument panel a Piper part number

(P/N) 81090–02 placard, which provides

information for operation of the parking

brake. Piper has superseded that placard

with a P/N 683–107 placard, and

operators in need of a new placard can

only obtain the P/N 683–107 placard. In

this scenario, the owners/operators of

the affected airplanes could not comply

with AD 85–02–05 as currently written.

The P/N 683–107 placard contains the

same wording as the P/N 81090–02

placard. The actions specified in that

AD are intended to prevent airplane

controllability problems while involved

in ground operation because of

improper brake operations. This

document maintains the placard

requirement of AD 85–02–05, and adds

the installation of the P/N 683–107

placard as an option of compliance.

DATES: Effective November 21, 1997.

FOR FURTHER INFORMATION CONTACT:

William Herderich, Aerospace Engineer,

Atlanta Certification Office, FAA, 1895

Phoenix Boulevard, suite 450, Atlanta,

Georgia 30349; telephone (770) 703–

6084; facsimile (770) 703-6097.

SUPPLEMENTARY INFORMATION:

Discussion

AD 85–02–05, Amendment 39–4984,

currently requires the following on

Piper PA–20, PA–22, PA–23, PA–24,

PA-25, PA–30, PA–31P, PA–36, PA–39,

and PA–44 series airplanes: installing

on the pilot’s instrument panel a Piper

part number (P/N) 81090–02 placard,

which provides information for

operation of the parking brake. The

actions required by AD 85–02–05 are

intended to prevent airplane

controllability problems while involved

in ground operation because of

improper brake operations.

Need for the Correction

Piper has superseded the P/N 81090–

02 placard with a P/N 683–107 placard,

and owners/operators in need of a new

placard can only obtain the P/N 683–

107 placard. In this scenario, the

owners/operators of the affected

airplanes could not comply with AD

85–02–05 as currently written. The P/N

683–107 placard contains the same

wording as the P/N 81090–02 placard.

Correction of Publication

This document maintains the placard

requirement of AD 85–02–05, adds the

installation of the Piper P/N 683-107

placard as an option of compliance,

adds a paragraph that allows the pilot to

install the placard, adds the standard

alternative method of compliance

paragraph, and adds the AD as an

amendment to section 39.13 of the

Federal Aviation Regulations (14 CFR

39.13).

Since this action only adds the Piper

P/N 683–107 placard as an option of

compliance, it has no adverse economic

impact and imposes no additional

burden on any person than would have

been necessary to comply with AD 85–

02–05. Therefore, the FAA has

determined that prior notice and

opportunity for public comment are

unnecessary.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

Adoption of the Correction

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

removing Airworthiness Directive (AD)