Federal Register / Vol. 62, No. 189 / Tuesday, September 30, 1997 / Rules and Regulations 51017

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

97–20–05 British Aerospace: Amendment

39–10143. Docket 97–NM–218–AD.

Applicability: All Model HS 748 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

otherwise 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 jamming or restricting of

the aileron cable, accomplish the

following:

(a) Within 6 months after the effective date

of this AD, install a modified aileron cable

pulley guard and rubbing strips in

accordance with British Aerospace Service

Bulletin HS 748–27–70, Revision 2, dated

May 20, 1994.

(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,

Standardization Branch, ANM–113, FAA,

Transport Airplane. Operators shall submit

their requests through an appropriate FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Standardization Branch, ANM–113.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(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 installation shall be done in

accordance with Jetstream Service Bulletin

HS 748–27–70, Revision 2, dated May 20,

1994. 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 AI(R) American Support, Inc., 13850

Mclearen Road, Herndon, Virginia 20171.

Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

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

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(e) This amendment becomes effective on

October 15, 1997.

Note 3: The subject of this AD is addressed

in British airworthiness directive 009–05–94,

dated May 9, 1994.

Issued in Renton, Washington, on

September 17, 1997.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–25165 Filed 9–29–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–215–AD; Amendment

39–10146; AD 97–20–08]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300, A300–600, and A310 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all Airbus Model A300,

A300–600, and A310 series airplanes,

that requires inspecting the bearings

located in the mechanical control

linkage of the nose landing gear (NLG)

free-fall mechanism for discrepancies,

replacing any discrepant bearings with

stainless steel bearings, and conducting

a test to ensure that the NLG free-fall

mechanism extends properly. This

amendment is prompted by a report

indicating that, during an operational

test of the NLG, the landing gear failed

to extend. The actions specified by this

AD are intended to prevent the bearings

from seizing, which could lead to the

loss of NLG free-fall extension

capability.

DATES: Effective November 4, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of November

4, 1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. 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 Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Charles Huber, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2589; fax (425) 227–1149.

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 all Airbus Model

A300, A300–600, and A310 series

airplanes was published in the Federal

Register on April 1, 1997 (62 FR 15441).

That action proposed to require

inspecting the bearings located in the

mechanical control linkage of the nose

landing gear (NLG) free-fall mechanism

for discrepancies, replacing any

discrepant bearings with stainless steel

bearings, and conducting a test to

ensure that the NLG free-fall mechanism

extends properly.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the two

comments received.

Both commenters support the

proposed rule.

Conclusion

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

The FAA estimates that 127 Model

A300, A300–600, and A310 airplanes of

U.S. registry will be affected by this AD,

that it will take approximately 14 work

hours per airplane to accomplish the

required actions, and that the average

labor rate is $60 per work hour.

Required parts will cost approximately

$552 per airplane. Based on these

figures, the cost impact of the AD on

U.S. operators is estimated to be

$176,784, or $1,392 per airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted.

Regulatory Impact

The regulations 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
51018 Federal Register / Vol. 62, No. 189 / Tuesday, September 30, 1997 / Rules and Regulations

implications to warrant the preparation

of a Federalism Assessment.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3)

will not have a significant economic

impact, positive or negative, on a

substantial number of small entities

under the criteria of the Regulatory

Flexibility Act. A final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it 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:

97–20–08 Airbus Industrie: Amendment 39–

10146. Docket 96–NM–215–AD.

Applicability: All Model A300, A300–600,

and A310 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

otherwise 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, unless

accomplished previously.

To prevent the bearings in the mechanical

control linkage of the nose landing gear

(NLG) free-fall mechanism from seizing,

which could lead to the loss of NLG free-fall

extension capability, accomplish the

following:

(a) Within 30 days after the effective date

of this AD, conduct an inspection to

determine whether carbon steel or stainless

steel bearings are installed in the mechanical

control linkage of the NLG free-fall

mechanism, in accordance with Airbus

Service Bulletin A300–32–0418 (for Model

A300 series airplanes), A300–32–6061 (for

Model A300–600 series airplanes), or A310–

32–2098 (for Model A310 series airplanes),

all Revision 1, all dated April 29, 1996.

(b) If stainless steel bearings are installed,

prior to further flight, conduct a test to

ensure that the NLG free-fall mechanism

extends properly, in accordance with Airbus

Service Bulletin A300–32–0418 (for Model

A300 series airplanes), A300–32–6061 (for

Model A300–600 series airplanes), or A310–

32–2098 (for Model A310 series airplanes),

all Revision 1, all dated April 29, 1996.

(c) If carbon steel bearings are installed,

prior to further flight, replace them with

stainless steel bearings, and conduct a test to

ensure that the NLG free-fall mechanism

extends properly, in accordance with Airbus

Service Bulletin A300–32–0418 (for Model

A300 series airplanes), A300–32–6061 (for

Model A300–600 series airplanes), or A310–

32–2098 (for Model A310 series airplanes),

all Revision 1, all dated April 29, 1996.

(d) 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,

Standardization Branch, ANM–113, 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, Standardization

Branch, ANM–113.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(e) 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.

(f) The actions shall be done in accordance

with the following Airbus service bulletins,

which contain the specified effective pages:

Service bulletin referenced and date Page No. Revision level

shown on page Date shown on page

A300–32–0418, Revision 1, April 29, 1996 ............. 1–6, 10–13

7–9, 14–23

1 Original .......... April 29, 1996.

October 5, 1995.

A310–31–2098, Revision 1, April 29, 1996 ............. 1–6, 8, 9, 11–14

7, 10, 15–25

1 Original .......... April 29, 1996.

October 5, 1995.

A300–32–6061, Revision 1, April 29, 1996 ............. 1–5, 8, 9, 11–14

6, 7, 10, 15–25

1 Original .......... April 29, 1996.

October 5, 1995.
Federal Register / Vol. 62, No. 189 / Tuesday, September 30, 1997 / Rules and Regulations 51019

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 Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

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

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(g) This amendment becomes effective on

November 4, 1997.

Issued in Renton, Washington, on

September 17, 1997.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–25167 Filed 9–29–97; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–CE–23–AD; Amendment 39–

10109; AD 96–12–03 R1]

RIN 2120–AA64

Airworthiness Directives; Aviat

Aircraft, Inc. Models S–1S, S–1T, S–2,

S–2A, S–2S, and S–2B Airplanes

(Formerly Known as Pitts Models S–

1S, S–1T, S–2, S–2A, S–2S, and S–2B

Airplanes); Correction

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; correction.

SUMMARY: This document corrects the

airworthiness directive (AD) number of

an amendment that was published in

the Federal Register on August 22, 1997

(62 FR 44535), and concerns Aviat

Aircraft, Inc. Models S–1S, S–1T, S–2,

S–2A, S–2S, and S–2B airplanes. The

referenced amendment revises AD 96–

12–03, but was inadvertently assigned

the number of AD 97–17–07 instead of

AD 96–12–03 R1. The AD currently

requires repetitively inspecting the aft

lower fuselage wing attach fitting on

both wings for cracks and modifying

any cracked aft lower fuselage wing

attach fitting. Modifying the aft lower

fuselage wing attach fitting on both

wings eliminates the repetitive

inspection requirement of the AD. This

action corrects the amendment to reflect

the right AD number throughout the

entire document.

EFFECTIVE DATE: October 3, 1997.

FOR FURTHER INFORMATION CONTACT: Mr.

Roger Caldwell, Aerospace Engineer,

FAA, Denver Aircraft Certification

Office, 26805 E. 68th Avenue, Room

214, Denver, Colorado 80249; telephone

(303) 342–1086; facsimile (303) 342–

1088.

SUPPLEMENTARY INFORMATION:

Discussion

On August 13, 1997, the FAA issued

Amendment 10109 (62 FR 44535,

August 22, 1997), which applies to

Aviat Models S–1S, S–1T, S–2, S–2A,

S–2S, and S–2B airplanes. This action

revises AD 96–12–03 by retaining the

requirements of repetitively inspecting

the aft lower fuselage wing attach fitting

on both wings for cracks, and modifying

any cracked aft lower fuselage wing

attach fitting; except the action

eliminates from the applicability those

airplanes that were equipped with aft

lower fuselage wing attach fittings,

either P/N 76090, 2–2107–1, or 1–210–

102, at manufacture. These aft lower

fuselage wing attach fittings were

incorporated at manufacture on the

Model S–2B airplanes beginning with

serial number 5349. AD 96–12–03

applied to all serial numbers of the

Model S–2B airplanes.

Need for the Correction

The AD number of this action is

incorrectly referenced as AD 97–17–07

instead of AD 96–12–03 R1 throughout

the document. Referencing the action as

AD 97–17–07 may not allow operators

of the affected airplanes that

accomplished the intent of AD 96–12–

03 to realize that the AD contains the

same actions as contained in the

original AD. The operators may spend

unnecessary time tracking down

information and approvals for ‘‘unless

already accomplished’’ credit for the AD

action.

Correction of Publication

Accordingly, the publication of

August 22, 1997 (62 FR 44535), of

Amendment 39–10109; AD 97–17–07,

which was the subject of FR Doc. 97–

22046, is corrected as follows:

§ 39.13 [Corrected]

On page 44535, in the third column,

5th line from the top of the column,

correct ‘‘AD 97–17–07’’ to ‘‘AD 96–12–

03 R1’’.

On page 44536, in the third column,

section 39.13, the sixth line in this

section and the 19th line from the top

of the column, correct ‘‘97–17–07’’ to

‘‘96–12–03 R1’’.

Action is taken herein to correct this

reference in Amendment 39–10109 and

to add this AD correction to section

39.13 of the Federal Aviation

Regulations (14 CFR 39.13).

The effective date remains October 3, 1997.

Issued in Kansas City, Missouri on

September 24, 1997.

Henry A. Armstrong,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 97–25831 Filed 9–29–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–15–AD; Amendment 39–

10148; AD 97–20–11]

RIN 2120–AA64

Airworthiness Directives; Socata—

Groupe Aerospatiale Model TBM 700

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain Socata—Groupe

Aerospatiale (Socata) Model TBM 700

airplanes. This AD requires removing

the main landing gear (MLG) inboard

doors and the door locking control

mechanism (MOD 70–065–32). This AD

is the result of an incident on one of the

affected airplanes where the MLG

inboard door locking hooks (hinges)

corroded, caused the doors to jam, and

prevented the MLG from extending. The

Federal Aviation Administration’s

analysis reveals that removing the MLG

inboard doors will not cause any

airplane safety or performance

problems. The actions specified by this

AD are intended to prevent the MLG

from failing to extend because of

corroded MLG inboard locking hinges,

which could result in loss of control of

the airplane during landing operations.

DATES: Effective November 13, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of November

13, 1997.

ADDRESSES: Service information that

applies to this AD may be obtained from

Socata—Groupe Aerospatiale, Socata

Product Support, Aeroport TarbesOssun-Lourdes, B P 930, 65009 Tarbes

Cedex, France; telephone 62.41.74.26;

facsimile 62.41.74.32; or the Product

Support Manager, Socata—Groupe

Aerospatiale, North Perry Airport, 7501

Pembroke Road, Pembroke Pines,

Florida 33023; telephone (954) 964–

6877; facsimile (954) 964–1668. This

information may also be examined at