26124 Federal Register / Vol. 65, No. 88 / Friday, May 5, 2000 / Rules and Regulations

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their mailed

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. 2000–SW–

02–AD.’’ The postcard will be date

stamped and returned to the

commenter.

The regulations adopted herein will

not have a substantial direct effect 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, it is

determined that this final rule does not

have federalism implications under

Executive Order 13132.

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 a new airworthiness directive to

read as follows:

AD 2000–08–22 MD Helicopters Inc.:

Amendment 39–11708, Docket No.

2000–SW–02–AD.

Applicability: Model 369D, 369E, and

500N helicopters, with analog/digital turbine

outlet temperature (TOT) indicator, part

number (P/N) 369D24513–1, installed; and

Model 600N helicopters, with analog/digital

TOT indicator, P/N 9A3420, installed;

certificated in any category.

Note 1: This AD applies to each helicopter

identified in the preceding applicability

provision, regardless of whether it has been

otherwise modified, altered, or repaired in

the area subject to the requirements of this

AD. For helicopters that have been modified,

altered, or repaired so that the performance

of the requirements of this AD is affected, the

owner/operator must 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 an erroneous TOT indication,

damage to critical engine components, loss of

engine power, and a subsequent forced

landing, accomplish the following:

(a) For Model 369E, 369D, and 500N

helicopters: Within the next 50 hours timein-service (TIS) or on or before June 15, 2000,

whichever occurs first; test the TOT

indicating system to verify correct calibration

in accordance with the Accomplishment

Instructions, Part I, of MD Helicopters, Inc.

(MDHI) Service Bulletin SB369D–199,

SB369E–093, SB500N–019, dated January 11,

2000 (SB). Thereafter, repeat the test at

intervals not to exceed 300 hours TIS.

(b) If during any test required by paragraph

(a) of this AD the TOT indicator readings for

the tester setting temperatures in Table 1,

Part I, of the SB are not within the indicator

reading range, before further flight, perform

the actions in the Accomplishment

Instructions, Part I, paragraph (6)(b) of the

SB.

(c) For Model 600N helicopters: Within the

next 50 hours TIS or on or before June 15,

2000, whichever occurs first; test the TOT

indicating system, including the electronic

control unit (ECU) TOT sensing system, to

verify correct calibration in accordance with

the Accomplishment Instructions, Part I, of

MDHI SB600N–026, dated January 11, 2000

(SB 600N). Thereafter, repeat the test at

intervals not to exceed 300 hours TIS.

(d) If during any calibration test required

by paragraph (c) of this AD the TOT indicator

readings for the tester setting temperatures in

Table 1, Part I, of SB 600N, are not within

the indicator reading range, before further

flight, perform the actions in the

Accomplishment Instructions, Part I,

paragraph (7)(b) of SB 600N.

(e) If during any test required by paragraph

(c) of this AD the Full Authority Digital

Electronic Control (FADEC) maintenance laptop terminal does not indicate ECU TOT

within (5 degrees Celsius of the tester setting

in Table 1, Part I, of SB 600N, before further

flight, perform the actions in the

Accomplishment Instructions, Part III, of the

SB 600N.

(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, Los

Angeles Aircraft Certification Office.

Operators shall submit their requests through

an FAA Principal Maintenance Inspector,

who may concur or comment and then send

it to the Manager, Los Angeles Aircraft

Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles Aircraft

Certification Office.

(g) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the helicopter

to a location where the requirements of this

AD can be accomplished.

(h) The tests shall be done in accordance

with MD Helicopters Inc. Service Bulletin

SB369D–199, SB369E–093, SB500N–019 for

Model 369D, 369E, and 500N helicopters and

Service Bulletin SB600N–026 for Model

600N helicopters, both dated January 11,

2000. 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 MD Helicopters Inc., Attn: Customer

Support Division, 4555 E. McDowell Rd.,

Mail Stop M615–GO48, Mesa, Arizona

85215–9797, telephone 1–800–388–3378 or

480–346–6387; datafax 480–346–6813.

Copies may be inspected at the FAA, Office

of the Regional Counsel, Southwest Region,

2601 Meacham Blvd., Room 663, Fort Worth,

Texas; or at the Office of the Federal Register,

800 North Capitol Street, NW., suite 700,

Washington, DC.

(i) This amendment becomes effective on

May 22, 2000.

Issued in Fort Worth, Texas, on April 18,

2000.

Mark R. Schilling,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 00–11058 Filed 5–4–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–99–AD; Amendment

39–11713; AD 2000–07–51]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model 717–200 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

Federal Register / Vol. 65, No. 88 / Friday, May 5, 2000 / Rules and Regulations 26125

ACTION: Final rule; request for

comments.

SUMMARY: This document publishes in

the Federal Register an amendment

adopting airworthiness directive (AD)

2000–07–51 that was sent previously to

all known U.S. owners and operators of

McDonnell Douglas Model 717–200

series airplanes by individual notices.

This AD requires coiling and stowing of

electrical wires between the glareshield

control panel and the Integrated

Standby Instrument System; and

revising the abnormal procedures of the

Procedures section of the Airplane

Flight Manual to include procedures for

identifying and pulling certain circuit

breakers if the altimeter Captain’s

Primary Flight Display (PFD) data

become unreliable. This action is

prompted by a report of two incidents

in which an intermittent loss of altitude

data occurred simultaneously on the

Captain’s PFD, First Officer’s PFD, and

the Integrated Standby Instrument

System (ISIS) altitude display due to a

voltage drop in the power distribution

control unit. The actions specified by

this AD are intended to prevent loss of

all altitude information and subsequent

essential navigation data for continued

safe flight and landing.

DATES: Effective May 10, 2000, to all

persons except those persons to whom

it was made immediately effective by

emergency AD 2000–07–51, issued

April 1, 2000, which contained the

requirements of this amendment.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 10,

2000.

Comments for inclusion in the Rules

Docket must be received on or before

July 5, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

99–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The applicable service information

may be obtained from Boeing

Commercial Aircraft Group, Long Beach

Division, 3855 Lakewood Boulevard,

Long Beach, California 90846,

Attention: Technical Publications

Business Administration, Dept. C1–L51

(2–60). This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at

the FAA, Transport Airplane

Directorate, Los Angeles Aircraft

Certification Office, 3960 Paramount

Boulevard, Lakewood, California; or at

the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Thomas Phan, Aerospace Engineer,

Systems and Equipment Branch, ANM–

130L, FAA, Transport Airplane

Directorate, Los Angeles Aircraft

Certification Office, 3960 Paramount

Boulevard, Lakewood, California

90712–4137; telephone (562) 627–5342;

fax (562) 627–5210.

SUPPLEMENTARY INFORMATION: On April

1, 2000, the FAA issued emergency AD

2000–07–51, which is applicable to all

McDonnell Douglas Model 717–200

series airplanes.

The FAA has received a report of two

incidents in which an intermittent loss

of altitude data occurred simultaneously

on the Captain’s Primary Flight Display

(PFD), First Officer’s PFD, and the

Integrated Standby Instrument System

(ISIS) altitude display due to a voltage

drop in the power distribution control

unit. Additional intermittent loss of

cockpit indications included the

glareshield control panel data,

navigation data, flight management

computer mismatch annunciation,

autopilot disconnect, and autothrottle

disconnect. In both cases, the airspeed

and attitude indication remained

operational. The flights continued on to

their destination without further

incident. This condition, if not

corrected, could result in loss of all

altitude information and subsequent

essential navigation data for continued

safe flight and landing.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Boeing Alert Service Bulletin 717–

34A0002, dated March 30, 2000, which

describes procedures for coiling and

stowing of electrical wires between the

glareshield control panel and the ISIS.

The FAA also has reviewed and

approved Boeing Interim Operating

Procedure (IOP) 2–17, dated March 31,

2000, which describes procedures for

identifying and pulling certain circuit

breakers if the altimeter primary flight

display data (PFD) become unreliable.

Explanation of Requirements of the

Rule

Since the unsafe condition described

is likely to exist or develop on other

airplanes of the same type design, the

FAA issued emergency AD 2000–07–51

to prevent loss of all altitude

information and subsequent essential

navigation data for continued safe flight

and landing. The AD requires coiling

and stowing of electrical wires between

the glareshield control panel and the

Integrated Standby Instrument System;

and revising the abnormal procedures of

the Procedures section of the Airplane

Flight Manual to include procedures for

identifying and pulling certain circuit

breakers if the altimeter PFD data

become unreliable. The actions are

required to be accomplished in

accordance with the alert service

bulletin and IOP previously described.

Interim Action

This is considered to be interim

action until final action is identified, at

which time the FAA may consider

additional 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 AD effective

in less than 30 days.

Since it was found that immediate

corrective action was required, notice

and opportunity for prior public

comment thereon were impracticable

and contrary to the public interest, and

good cause existed to make the AD

effective immediately by individual

notices issued on April 1, 2000, to all

known U.S. owners and operators of

McDonnell Douglas Model 717–200

series airplanes. These conditions still

exist, and the AD is hereby published in

the Federal Register as an amendment

to section 39.13 of the Federal Aviation

Regulations (14 CFR 39.13) to make it

effective to all persons.

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.

26126 Federal Register / Vol. 65, No. 88 / Friday, May 5, 2000 / Rules and Regulations

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 Number 2000–NM–99–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Regulatory Impact

The regulations adopted herein will

not have a substantial direct effect 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, it is

determined that this final rule does not

have federalism implications under

Executive Order 13132.

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:

2000–07–51 McDonnell Douglas:

Amendment 39–11713. Docket 2000-

NM–99-AD.

Applicability: All Model 717–200 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

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 loss of all altitude information

and subsequent essential navigation data for

continued safe flight and landing,

accomplish the following:

(a) Prior to further flight, coil and stow the

electrical wires between the glareshield

control panel and the Integrated Standby

Instrument System in accordance with

Boeing Alert Service Bulletin 717–34A0002,

dated March 30, 2000.

(b) Prior to further flight, revise the

abnormal procedures of the Procedures

section of the FAA-approved Airplane Flight

Manual (AFM) to include procedures for

identifying and pulling certain circuit

breakers. This must be accomplished by

inserting Boeing Interim Operating Procedure

2–17, dated March 31, 2000, into the AFM.

Alternative Methods of Compliance

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager, Los

Angeles Aircraft Certification Office (ACO),

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, Los Angeles ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles ACO.

Special Flight Permits

(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.

Incorporation by Reference

(e) The actions shall be done in accordance

with Boeing Alert Service Bulletin 717–

34A0002, dated March 30, 2000; and Boeing

Interim Operating Procedure 2–17, dated

March 31, 2000. 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 Boeing Commercial Aircraft

Group, Long Beach Division, 3855 Lakewood

Boulevard, Long Beach, California 90846,

Attention: Technical Publications Business

Administration, Dept. C1–L51 (2–60). Copies

may be inspected at the FAA, Transport

Airplane Directorate, 1601 Lind Avenue,

SW., Renton, Washington; or at the FAA,

Transport Airplane Directorate, Los Angeles

Aircraft Certification Office, 3960 Paramount

Boulevard, Lakewood, California; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(f) This amendment becomes effective on

May 10, 2000, to all persons except those

persons to whom it was made immediately

effective by emergency AD 2000–07–51,

issued on April 1, 2000, which contained the

requirements of this amendment.

Issued in Renton, Washington, on April 27,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–11059 Filed 5–4–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 99–ACE–30]

Amendment to Class E Airspace;

Albion, NE

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Direct final rule; request for

comments.

SUMMARY: This action amends the Class

E airspace area at Albion Municipal

Airport, Albion, NE. The FAA has

developed Global Positioning System

(GPS) Runway (RWY) 15 and GPS RWY

33 Standard Instrument Approach

Procedures (SIAPs) to serve Albion

Municipal Airport, NE. Additional

controlled airspace extending upward

from 700 feet Above Ground Level

(AGL) is needed to accommodate these

SIAPs and for Instrument Flight Rules

(IFR) operations at this airport. The

enlarged area will contain the GPS RWY