28218 Federal Register / Vol. 63, No. 99 / Friday, May 22, 1998 /Rules and Regulations

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:

98–11–10 McDonnell Douglas: Amendment

39–10537. Docket 97–NM–251–AD.

Applicability: Model DC–9–10, –20, –30,

–40, and –50, and DC–9–81 (MD–81), DC–9–

82 (MD–82), DC–9–83 (MD–83), and DC–9–

87 (MD–87) series airplanes; Model MD–88

airplanes; and C–9 (military) series airplanes;

as listed in McDonnell Douglas Service

Bulletin DC9–27–346, Revision 01, dated July

29, 1997; 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 (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 a jammed speed brake handle

pin, which could result in retraction of the

spoilers and full advancement of the left

throttle during a go-around, accomplish the

following:

(a) Within 12 months after the effective

date of this AD, perform an inspection to

determine if the latching lever pin of the

speed brake passes an axial force check, and

a visual inspection to determine if the staking

of the latching lever pin is ‘‘acceptable’’, in

accordance with McDonnell Douglas Service

Bulletin DC9–27–346, Revision 01, dated July

29, 1997.

Note 2: The criteria for determining

whether the staking is ‘‘acceptable’’ are

defined in Figure 1 of the service bulletin.

(1) Condition 1. If the pin passes the axial

force check and the staking is found to be

acceptable, no further action is required by

this AD.

(2) Condition 2. If the pin passes the axial

force check and the staking is found to be

unacceptable, accomplish the actions

specified in Condition 2, Option 1, or

Condition 2, Option 2 of the

Accomplishment Instructions of the service

bulletin. These actions shall be accomplished

at the times specified in paragraph E.

‘‘Compliance’’ of the service bulletin.

Accomplishment of the replacement of the

speed brake latching lever constitutes

terminating action for the repetitive

inspection requirements of this AD.

(3) Condition 3. If the pin fails the axial

force check and the staking is found to be

unacceptable, accomplish the actions

specified in Condition 3, Option 1, or

Condition 3, Option 2 of the

Accomplishment Instructions of the service

bulletin. These actions shall be accomplished

at the times specified in paragraph E.

‘‘Compliance’’ of the service bulletin.

Accomplishment of the replacement of the

speed brake latching lever constitutes

terminating action for the repetitive

inspection requirements of this AD.

(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, 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 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles ACO.

(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) The actions shall be done in accordance

with McDonnell Douglas Service Bulletin

DC9–27–346, Revision 01, dated July 29,

1997. 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 The Boeing Company, Douglas Products

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.

(e) This amendment becomes effective on

June 26, 1998.

Issued in Renton, Washington, on May 14,

1998.

John J. Hickey,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–13407 Filed 5–21–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–165–AD; Amendment

39–10540; AD 98–11–13]

RIN 2120–AA64

Airworthiness Directives; Raytheon

Model Hawker 800XP Series Airplanes,

and Hawker 800 (U–125A Military

Derivative) Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Raytheon Model

Hawker 800XP series airplanes and

Hawker 800 (U–125A military

derivative) airplanes. This action

requires removal of the sealant from the

firewall mounting flanges and mounting

points of the fire extinguisher

assemblies; removal of sealant

obstructing the discharge tubes of the

fire extinguisher assemblies; cleaning

and flushing of the mounting flanges,

mounting points, and discharge tubes

with solvent; and installation of new

gaskets on the firewall mounting flanges

and mounting points. This amendment

is prompted by reports of excessive

sealant applied during manufacture of

the firewall mounting flanges and

mounting points of the fire extinguisher

assemblies, which subsequently entered

and obstructed the discharge tubes. The

actions specified in this AD are

intended to prevent obstructions of the

discharge tubes of the fire extinguisher

assemblies, which could result in

improper distribution of the fire

extinguishing agent within the nacelle

in the event of a fire.

DATES: Effective June 8, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 8,

1998.

Comments for inclusion in the Rules

Docket must be received on or before

July 21, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

165–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The service information referenced in

this AD may be obtained from Raytheon

Aircraft Company, Manager Service
Federal Register / Vol. 63, No. 99 / Friday, May 22, 1998 /Rules and Regulations 28219

Engineering, Hawker Customer Support

Department, P.O. Box 85, Wichita,

Kansas 67201–0085. This information

may be examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at

the FAA, Small Airplane Directorate,

Wichita Aircraft Certification Office,

1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas; or

at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Randy Griffith, Aerospace Engineer,

Systems and Propulsion Branch, ACE–

116W, FAA, Small Airplane Directorate,

Wichita Aircraft Certification Office,

1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas

67209; telephone (316) 946–4145; fax

(316) 946–4407.

SUPPLEMENTARY INFORMATION: The FAA

has received a report indicating that,

during manufacture testing of the fire

suppression system on a Raytheon

Model Hawker 800XP series airplane,

the system failed to operate properly.

Investigation has revealed that the

discharge tubes of the fire extinguisher

assemblies were obstructed. Testing of

other Model Hawker 800XP series

airplanes and a Hawker 800 (U–125A

military derivative) airplane revealed

similar obstructions of the discharge

tubes of the fire extinguisher assemblies.

The cause of the obstructions has been

attributed to excessive sealant applied

during manufacture of the firewall

mounting flanges and mounting points

of the fire extinguisher assemblies,

which subsequently entered and

obstructed the discharge tubes. This

condition, if not corrected, could result

in improper distribution of the fire

extinguishing agent within the nacelle

in the event of a fire.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Raytheon Service Bulletin SB.26–3197,

dated April 1998, which describes

procedures for removal of the sealant

from the firewall mounting flanges and

mounting points of the fire extinguisher

assemblies; removal of sealant

obstructing the discharge tubes of the

fire extinguisher assemblies; cleaning

and flushing of the mounting flanges,

mounting points, and discharge tubes

with solvent; and installation of new

gaskets on the firewall mounting flanges

and mounting points. Accomplishment

of the actions specified in the service

bulletin is intended to adequately

address the identified unsafe condition.

Explanation of the Requirements of the

Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design, this AD is being issued to

prevent obstructions of the discharge

tubes of the fire extinguisher assemblies,

which could result in improper

distribution of the fire extinguishing

agent within the nacelle in the event of

a fire. This AD requires removal of the

sealant from the firewall mounting

flanges and mounting points of the fire

extinguisher assemblies; removal of

sealant obstructing the discharge tubes

of the fire extinguisher assemblies;

cleaning and flushing of the mounting

flanges, mounting points, and discharge

tubes with solvent; and installation of

new gaskets on the firewall mounting

flanges and mounting points.

Determination of Rule’s Effective Date

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an opportunity

for public comment, comments are

invited on this rule. Interested persons

are invited to comment on this rule by

submitting such written data, views, or

arguments as they may desire.

Communications shall identify the

Rules Docket number and be submitted

in triplicate to the address specified

under the caption ADDRESSES. All

communications received on or before

the closing date for comments will be

considered, and this rule may be

amended in light of the comments

received. Factual information that

supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the rule. All comments

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 98–NM–165–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Regulatory Impact

The regulations adopted herein will

not have substantial direct effects on the

States, on the relationship between the

national government and the States, or

on the distribution of power and

responsibilities among the various

levels of government. Therefore, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and that it is not a ‘‘significant

regulatory action’’ under Executive

Order 12866. It has been determined

further that this action involves an

emergency regulation under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979). If it is

determined that this emergency

regulation otherwise would be

significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, may be obtained from the

Rules Docket at the location provided

under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends part 39 of the

Federal Aviation Regulations (14 CFR

part 39) as follows:

PART 39—AIRWORTHINESS

DIRECTIVES

1. The authority citation for part 39

continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.
28220 Federal Register / Vol. 63, No. 99 / Friday, May 22, 1998 /Rules and Regulations

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

98–11–13 Raytheon Aircraft Company

(Formerly Beech): Amendment 39–

10540. Docket 98–NM–165–AD.

Applicability: Model Hawker 800XP series

airplanes and Hawker 800 (U–125A military

derivative) airplanes, as listed in Raytheon

Service Bulletin SB.26–3197, dated April

1998; 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 (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 obstructions of the discharge

tubes of the fire extinguisher assemblies,

which could result in improper distribution

of the fire extinguishing agent within the

nacelle in the event of a fire, accomplish the

following:

(a) Within 25 days after the effective date

of this AD, accomplish paragraphs (a)(1),

(a)(2), (a)(3), and (a)(4) of this AD, in

accordance with Raytheon Service Bulletin

SB.26–3197, dated April 1998.

(1) Remove the sealant from the firewall

mounting flanges and mounting points of the

fire extinguisher assemblies;

(2) Remove all sealant obstructing the

discharge tubes of the fire extinguisher

assemblies;

(3) Clean and flush the mounting flanges,

mounting points, and discharge tubes with

solvent; and

(4) Install new gaskets on the firewall

mounting flanges and mounting points.

(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, Wichita

Aircraft Certification Office (ACO), FAA,

Small 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, Wichita ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

(c) 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.

(d) The actions shall be done in accordance

with Raytheon Service Bulletin SB.26–3197,

dated April 1998. 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 Raytheon Aircraft Company,

Manager Service Engineering, Hawker

Customer Support Department, P.O. Box 85,

Wichita, Kansas 67201–0085. Copies may be

inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Small Airplane

Directorate, Wichita Aircraft Certification

Office, 1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(e) This amendment becomes effective on

June 8, 1998.

Issued in Renton, Washington, on May 15,

1998.

John J. Hickey,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–13684 Filed 5–21–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 97

[Docket No. 29226; Amdt. No. 1869]

RIN 2120–AA65

Standard Instrument Approach

Procedures; Miscellaneous

Amendments

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This amendment establishes,

amends, suspends, or revokes Standard

Instrument Approach Procedures

(SIAPs) for operations at certain

airports. These regulatory actions are

needed because of changes occurring in

the National Airspace System, such as

the commissioning of new navigational

facilities, addition of new obstacles, or

changes in air traffic requirements.

These changes are designed to provide

safe and efficient use of the navigable

airspace and to promote safe flight

operations under instrument flight rules

at the affected airports.

DATES: An effective date for each SIAP

is specified in the amendatory

provisions.

Incorporation by reference—approved

by the Director of the Federal Register

on December 31, 1980, and reapproved

as of January 1, 1982.

ADDRESSES: Availability of matter

incorporated by reference in the

amendment is as follows:

For Examination—

1. FAA Rules Docket, FAA

Headquarters Building, 800

Independence Avenue, SW.,

Washington, DC 20591;

2. The FAA Regional Office of the

region in which affected airport is

located; or

3. The Flight Inspection Area Office

which originated the SIAP.

For Purchase—Individual SIAP

copies may be obtained from:

1. FAA Public Inquiry Center (APA–

200), FAA Headquarters Building, 800

Independence Avenue, SW.,

Washington, DC 20591; or

2. The FAA Regional Office of the

region in which the affected airport is

located.

By Subscription—Copies of all SIAPs,

mailed once every 2 weeks, are for sale

by the Superintendent of Documents,

US Government Printing Office,

Washington, DC 20402.

FOR FURTHER INFORMATION CONTACT:

Donald P. Pate, Flight Procedure

Standards Branch (AMCAFS–420),

Flight Technologies and Programs

Division, Flight Standards Service,

Federal Aviation Administration, Mike

Monroney Aeronautical Center, 6500

South MacArthur Blvd. Oklahoma City,

OK. 73169 (Mail Address: P.O. Box

25082 Oklahoma City, OK. 73125)

telephone: (405) 954–4164.

SUPPLEMENTARY INFORMATION: This

amendment to part 97 of the Federal

Aviation Regulations (14 CFR part 97)

establishes, amends, suspends, or

revokes Standard Instrument Approach

Procedures (SIAPs). The complete

regulatory description on each SIAP is

contained in the appropriate FAA Form

8620 and the National Flight Data

Center (FDC)/Permanent (P) Notices to

Airmen (NOTAM) which are

incorporated by reference in the

amendment under 5 U.S.C. 552(a), 1

CFR part 51, and § 97.20 of the Federal

Aviation’s Regulations (FAR). Materials

incorporated by reference are available

for examination or purchase as stated

above.

The large number of SIAPs, their

complex nature, and the need for a

special format make their verbatim

publication in the Federal Register

expensive and impractical. Further,

airmen do not use the regulatory text of

the SIAPs, but refer to their graphic

depiction of charts printed by

publishers of aeronautical materials.

Thus, the advantages of incorporation

by reference are realized and

publication of the complete description

of each SIAP contained in FAA form

documents is unnecessary. The

provisions of this amendment state the

affected CFR (and FAR) sections, with