Federal Register / Vol. 65, No. 220 / Tuesday, November 14, 2000 / Rules and Regulations 68067

Actions Compliance times Procedures

(1) Inspect the elevator and rudder control clevis for abnormal wear. Measure clevis thickness. The thickness at the bent section

should be at least 0.043 inch (in)/1.1 millimeter (mm).

Within the next 100 hours time-in-service

(TIS) after December 29, 2000 (the effective date of this AD), and thereafter at intervals not to exceed 600 hours TIS.

Do this inspection in accordance with the ACCOMPLISHMENT INSTRUCTIONS of

Socata Mandatory Service Bulletin SB 155–

27, dated April 2000.

(2) If, during inspection, the elevator or rudder

control clevis measures a thickness less than

0.043 in/1.1 mm, replace the clevis.

Before further flight after the inspection where

abnormal wear was found.

Do this section in accordance with the ACCOMPLISHMENT INSTRUCTIONS of

Socata Mandatory Service Bulletin SB 155–

27, dated April 2000.

(3) Lubricate the clevis ....................................... Within the next 100 hours TIS after December

29, 2000 (the effective date with the of this

AD), and thereafter at intervals not to exceed 100 hours TIS.

Do this action in accordance with the ACCOMPLISHMENT INSTRUCTIONS of

Socata Mandatory Service Bulletin SB 155–

27, dated April 2000.

(e) Can I comply with this AD in any other

way? You may use an alternative method of

compliance or adjust the compliance time if:

(1) Your alternative method of compliance

provides an equivalent level of safety; and

(2) The Manager, Small Airplane

Directorate, approves your alternative.

Submit your request through an FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Small Airplane Directorate.

Note 1: This AD applies to each airplane

identified in paragraph (a) of this AD,

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 (e)

of this AD. The request should include an

assessment of the effect of the modification,

alteration, or repair on the unsafe condition

addressed by this AD; and, if you have not

eliminated the unsafe condition, specific

actions you propose to address it.

(f) Where can I get information about any

already-approved alternative methods of

compliance? You can contact Karl

Schletzbaum, Aerospace Engineer, FAA,

Small Airplane Directorate, 901 Locust,

Room 301, Kansas City, Missouri 64016;

telephone: (816) 329–4146; facsimile: (816)

329–4090.

(g) What if I need to fly the airplane to

another location to comply with this AD? The

FAA can issue a special flight permit under

sections 21.197 and 21.199 of the Federal

Aviation Regulations (14 CFR 21.197 and

21.199) to operate your airplane to a location

where you can accomplish the requirements

of this AD.

(h) Are any service bulletins incorporated

into this AD by reference? Actions required

by this AD must be done in accordance with

Socata Mandatory Service Bulletin SB 155–

27, dated April, 2000. The Director of the

Federal Register approved this incorporation

by reference under 5 U.S.C. 552(a) and 1 CFR

part 51. You can get copies from SOCATA

Groupe AEROSPATIALE, Customer Support,

Aerodrome Tarbes-Ossun-Lourdes, BP 930—

F65009 Tarbes Cedex, France; telephone: (33)

(0)5.62.41.73.00. You can look at copies at

the FAA, Central Region, Office of the

Regional Counsel, 901 Locust, Room 506,

Kansas City, Missouri, or at the Office of the

Federal Register, 800 North Capitol Street,

NW, suite 700, Washington, DC.

(i) When does this amendment become

effective? This amendment becomes effective

on December 29, 2000.

Note 2: The subject of this AD is addressed

in French AD number 2000–174(A), dated

May 3, 2000.

Issued in Kansas City, Missouri, on

October 30, 2000.

Marvin R. Nuss,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 00–28439 Filed 11–13–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–344–AD; Amendment

39–11968; AD 2000–22–20]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model DC–9–10, –9–20, –9–30,

–9–40, and –9–50 Series Airplanes and

C–9 (Military) 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 McDonnell

Douglas Model DC–9–10, –9–20, –9–30,

–9–40, and –9–50 series airplanes and

C–9 (military) airplanes. This action

requires, among other actions,

measuring the diameter of the hole

counterbore of the outboard idler hinge

fitting of the left and right wing flap;

performing repetitive high frequency

eddy current inspections (HFEC) to

detect cracks at the flap idler hinge

fitting, if necessary; and replacing the

flap idler hinge fitting with a new like

part, if any crack is detected. This action

is necessary to prevent failure of the

outboard flap idler hinge fitting due to

fatigue cracking, which could result in

a deflected flap that may cause an

asymmetric lift and consequent reduced

controllability and structural integrity of

the airplane. This action is intended to

address the identified unsafe condition.

DATES: Effective November 29, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of November

29, 2000.

Comments for inclusion in the Rules

Docket must be received on or before

January 16, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

344–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9 a.m. and 3 p.m.,

Monday through Friday, except Federal

holidays. Comments may be submitted

via fax to (425) 227–1232. Comments

may also be sent via the Internet using

the following address: 9-anmiarcomment@faa.gov. Comments sent

via fax or the Internet must contain

‘‘Docket No. 2000–NM–344–AD’’ in the

subject line and need not be submitted

in triplicate. Comments sent via the

Internet as attached electronic files must

be formatted in Microsoft Word 97 for

Windows or ASCII text.

The service information referenced in

this AD 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, Los Angeles Aircraft

Certification Office, 3960 Paramount

Boulevard, Lakewood, California; or at

68068 Federal Register / Vol. 65, No. 220 / Tuesday, November 14, 2000 / Rules and Regulations

the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Wahib Mina, Aerospace Engineer,

Airframe Branch, ANM–120L, FAA, Los

Angeles Aircraft Certification Office,

3960 Paramount Boulevard, Lakewood,

California 90712; telephone (562) 627–

5324; fax (562) 627–5210.

SUPPLEMENTARY INFORMATION: The FAA

has received reports of a failed or

cracked flap idler hinge fitting at the

lower outboard stud location on certain

McDonnell Douglas Model DC–9 series

airplanes. Investigation revealed that

these discrepancies were caused by

fatigue cracking initiating at the lower

outboard mounting hole with a 11⁄8-inch

diameter counterbore. Such fatigue

cracking, if not corrected, could result

in failure of the outboard flap idler

hinge fitting. A failed outboard flap

idler hinge fitting could result in a

deflected flap, which may cause an

asymmetric lift and consequent reduced

controllability and structural integrity of

the airplane.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Boeing Alert Service Bulletin DC9–

57A218, including Appendix, dated

September 20, 2000, which describes

the following procedures:

1. Measuring the diameter of the hole

counterbore of the outboard idler hinge

fitting of the left and right wing flap;

2. Installing a new nut, plain washer,

and PLI washer;

3. For certain cases, performing

repetitive high frequency eddy current

inspections (HFEC) to detect cracks at

the flap idler hinge fitting; and

4. Replacing the flap idler hinge

fitting with a new like part, if any crack

is detected.

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 McDonnell Douglas

Model DC–9–10, –9–20, –9–30, –9–40,

and –9–50 series airplanes and C–9

(military) airplanes series airplanes of

the same type design, this AD is being

issued to prevent failure of the outboard

flap idler hinge fitting due to fatigue

cracking, which could result in a

deflected flap that may cause an

asymmetric lift and consequent reduced

controllability and structural integrity of

the airplane. This AD requires

accomplishment of the actions specified

in the service bulletin described

previously.

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.

Submit comments using the following

format:

• Organize comments issue-by-issue.

For example, discuss a request to

change the compliance time and a

request to change the service bulletin

reference as two separate issues.

• For each issue, state what specific

change to the AD is being requested.

• Include justification (e.g., reasons or

data) for each request.

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–344–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:

2000–22–20 McDonnell Douglas:

Amendment 39–11968. Docket 2000–

NM–344–AD.

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

30, –9–40, and –9–50 series airplanes and C–

9 (military) airplanes, as listed in Boeing

Alert Service Bulletin DC9–57A218, dated

September 20, 2000; certificated in any

category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

Federal Register / Vol. 65, No. 220 / Tuesday, November 14, 2000 / Rules and Regulations 68069

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 failure of the outboard flap

idler hinge fitting due to fatigue cracking,

which could result in a deflected flap that

may cause an asymmetric lift and consequent

reduced controllability and structural

integrity of the airplane, accomplish the

following:

Measurement

(a) Before the accumulation of 24,000 total

landings, or within 90 days after the effective

date of this AD, whichever occurs later,

measure the diameter of the hole counterbore

of the outboard idler hinge fitting of the left

and right wing flap, per Boeing Alert Service

Bulletin DC9–57A218, including Appendix,

dated September 20, 2000.

Acceptable Measurement of 0.875 (7⁄8) Inch:

Installation of Certain Parts

(1) If the diameter of any hole counterbore

is 0.875 (7⁄8) inch, before further flight, install

a new nut, plain washer, and PLI washer, per

the service bulletin.

Unacceptable Measurement of 1.125 (11⁄8)

Inches: Repetitive Inspections and

Corrective Actions, If Necessary

(2) If the diameter of any hole counterbore

is 1.125 (11⁄8) inches, before further flight, do

a high frequency eddy current inspection

(HFEC) to detect cracks at the flap idler hinge

fitting, per the service bulletin.

(i) Condition 1. If no crack is detected,

before further flight, install a new nut, plain

washer, and PLI washer, per the service

bulletin. Repeat the HFEC inspection every

1,000 landings until the replacement

specified in paragraph (a)(2)(ii) has been

done.

(ii) Condition 2. If any crack is detected,

before further flight, replace the flap idler

hinge fitting with a new like part, per the

service bulletin. Within 24,000 landings after

accomplishment of the replacement, do the

HFEC inspection required by paragraph (a)(2)

of this AD.

Alternative Methods of Compliance

(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. 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

(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.

Incorporation by Reference

(d) The actions shall be done in accordance

with Boeing Alert Service Bulletin DC9–

57A218, including Appendix, dated

September 20, 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, 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.

Effective Date

(e) This amendment becomes effective on

November 29, 2000.

Issued in Renton, Washington, on

November 1, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–28480 Filed 11–13–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–46–AD; Amendment

39–11970; AD 2000–22–22]

RIN 2120–AA64

Airworthiness Directives; Raytheon

Model Hawker 800XP and Hawker 800

(U–125A) Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Raytheon Model

Hawker 800XP and Hawker 800 (U–

125A) series airplanes, that requires

inspection of the wire bundle to relay

‘‘KT’’ on panel ‘‘JA’’ for correct routing,

adequate clearance from the fuel crossfeed valve operating lever, and the

presence of chafing; this amendment

also requires corrective action, if

necessary. The actions specified by this

AD are intended to detect and correct

chafing of the wire bundle exiting panel

‘‘JA’’ due to insufficient clearance from

the fuel cross-feed valve operating lever.

Such chafing of the wire bundle could

result in a fire in the area of the fuel

system in a confined space. This action

is intended to address the identified

unsafe condition.

DATES: Effective December 19, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of December

19, 2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Raytheon Aircraft Company, 9709

East Central, Wichita, Kansas 67206.

This information may be examined at

the Federal Aviation Administration

(FAA), Transport Airplane Directorate,

Rules Docket, 1601 Lind Avenue, SW.,

Renton, Washington; or at the FAA,

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:

Philip Petty, Aerospace Engineer,

Systems and Propulsion Branch, ACE–

116W, FAA, Wichita Aircraft

Certification Office, 1801 Airport Road,

Room 100, Mid-Continent Airport,

Wichita, Kansas 67209; telephone (316)

946–4139; fax (316) 946–4407.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain Model

Hawker 800XP and Hawker 800 (U–

125A) series airplanes was published in

the Federal Register on August 8, 2000

(65 FR 48404). That action proposed to

require inspection of the wire bundle to

relay ‘‘KT’’ on panel ‘‘JA’’ for correct

routing, adequate clearance from the

fuel cross-feed valve operating lever,

and the presence of chafing. That action

also proposed to require corrective

action, if necessary.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.