63264 Federal Register / Vol. 62, No. 229 / Friday, November 28, 1997 / Rules and Regulations

accomplish the requirements of paragraph

(b)(2) of this AD.

(2) After accomplishing the requirements

of paragraph (b)(1) of this AD, modify rib 5.0

of the vertical stabilizer by installing new

stiffening, in accordance with Part 2 of the

Accomplishment Instructions of Fokker

Service Bulletin SBF100–55–018, Revision 1,

dated December 27, 1993. Accomplishment

of this modification constitutes terminating

action for the repetitive inspections required

by paragraph (a) of this AD.

(c) The following exceptions apply with

regard to the requirements of paragraphs (a)

and (b) of this AD:

(1) Accomplishment of the inspection

specified in paragraph (a) and (b)(1) of this

AD is not required if the modification

specified in paragraph (b)(2) is accomplished

prior to the accumulation of 7,300 total

landings on the airplane.

(2) Compliance with AD 91–18–15,

amendment 39–8018, is not required if the

requirements of paragraph (b)(2) of this AD

are accomplished prior to the accumulation

of 6,000 total landings on the airplane.

(d) For all airplanes: At the applicable

times specified in paragraph (d)(1) or (d)(2),

modify the Hi-lok bolt holes at rib 5.0 of the

vertical stabilizer by cold expansion, in

accordance with Fokker Service Bulletin

SBF100–55–023, dated January 3, 1995.

(1) For airplanes that have been modified

in accordance with the requirements of

paragraph (b) of this AD prior to the effective

date of this AD: Modify prior to the

accumulation of either 10,000 landings after

in-service modification, or 10,000 landings

after delivery with factory modification, as

applicable; or within 30 days after the

effective date of this AD, whichever occurs

later.

(2) For all other airplanes: Modify

concurrent with accomplishing the

requirements of paragraph (b) of this AD.

(e) 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,

International Branch, ANM–116. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(f) 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.

(g) The actions shall be done in accordance

with the following Fokker service bulletins,

which contain the following list of effective

pages:

Referenced service bulletin and date Page No. Revision level shown

on page Date shown on page

SBF100–55–018, Revision 1, December 27,

1993.

1–4, 8–16, 18, 19, 21–23, 25–28 ..................... 1 ................................ December 27, 1993.

5–7, 17, 20, 24, 29–31 ..................................... Original ...................... May 19, 1993.

SBF100–55–019, Revision 1, May 19, 1993 ... 1–3, 5, 9, .......................................................... 1 ................................ May 19, 1993.

4, 6–8, 10–12 ................................................... Original ...................... August 11, 1992.

SBF100–55–023, January 3, 1995 ................... 1–17 .................................................................. Original ...................... January 3, 1995.

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 Fokker Services B.V., Technical

Support Department, P.O. Box 75047, 1117

ZN Schiphol Airport, The Netherlands.

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.

Note 3: The subject of this AD is addressed

in Dutch airworthiness directive (BLA) 93–

069 (A), dated June 1, 1993.

(h) This amendment becomes effective on

January 2, 1998.

Issued in Renton, Washington, on

November 19, 1997.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–31029 Filed 11–26–97; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–189–AD; Amendment

39–10220; AD 97–24–13]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace BAe Model ATP Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain British Aerospace

BAe Model ATP airplanes, that requires

a detailed visual inspection of the flap

drive torque tubes in the wing root area

to detect inadequate clearance between

the torque tubes and surrounding

structure or scoring damage to the tubes;

and follow-on repetitive inspections or

corrective action, if necessary.

Accomplishment of certain

replacements and modifications would

constitute terminating action for the

repetitive inspections. This amendment

is prompted by reports of inadequate

clearance between flap drive torque

tubes and surrounding structures, and

possible scoring damage to the tubes.

The actions specified by this AD are

intended to prevent failure of the torque

tubes, which could result in an

asymmetric flap condition and reduced

controllability of the airplane.

DATES: Effective January 2, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 2,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from AI(R) American Support, Inc.,

13850 Mclearen Road, Herndon,

Virginia 20171. 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:

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

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 certain British

Aerospace BAe Model ATP airplanes

was published in the Federal Register
Federal Register / Vol. 62, No. 229 / Friday, November 28, 1997 / Rules and Regulations 63265

on August 25, 1997 (62 FR 44917). That

action proposed to require a detailed

visual inspection of the flap drive

torque tubes in the wing root area to

detect inadequate clearance between the

torque tubes and surrounding structure

or scoring damage to the tubes; and

follow-on repetitive inspections or

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.

Conclusion

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 10 British

Aerospace BAe Model ATP airplanes of

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

that it will take approximately 1 work

hour per airplane to accomplish the

required actions, and that the average

labor rate is $60 per work hour. Based

on these figures, the cost impact of the

AD on U.S. operators is estimated to be

$600, or $60 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

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:

97–24–13 British Aerospace Regional

Aircraft [Formerly Jetstream Aircraft

Limited, British Aerospace (Commercial

Aircraft) Limited]: Amendment 39–

10220. Docket 96–NM–189–AD.

Applicability: BAe Model ATP airplanes,

constructor numbers 2002 through 2063

inclusive; 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 (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 failure of the torque tubes,

which could result in an asymmetric flap

condition and reduced controllability of the

airplane, accomplish the following:

(a) Within 90 days after the effective date

of this AD, conduct a detailed visual

inspection of the flap drive torque tubes in

the left and right wing root areas to detect

inadequate clearance between the torque

tubes and surrounding structure or scoring

damage to the tubes, in accordance with

Jetstream Service Bulletin ATP–27–80, dated

April 23, 1996.

(1) If adequate clearance exists between all

flap drive torque tubes and surrounding

structure at the sites specified in the service

bulletin, with no scoring damage to any of

the tubes, no further action is required by

this AD.

(2) If inadequate clearance exists between

any flap drive torque tube and surrounding

structure at the sites specified in the service

bulletin, with no scoring damage to the tubes:

Accomplish the requirements of paragraphs

(a)(2)(i) and (a)(2)(ii) of this AD.

(i) At intervals not to exceed 250 hours

time-in-service, repeat the detailed visual

inspections required by paragraph (a) of this

AD.

(ii) Within 2,000 hours time-in-service after

the initial inspection required by paragraph

(a) of this AD, modify the structure to gain

the required minimum clearance in

accordance with the service bulletin.

Accomplishment of the modification

constitutes terminating action for the

repetitive inspection requirement of

paragraph (a)(2)(ii) of this AD.

(3) If any scoring damage to the torque

tubes is detected, accomplish the

requirements specified in paragraph (a)(3)(i),

(a)(3)(ii), or (a)(3)(iii) of this AD, as

applicable, in accordance with the service

bulletin, and at the time specified in the

applicable paragraph.

(i) If only one torque tube on one side or

both sides of the airplane is damaged, and

the scoring is within the maximum allowable

damage limits in the service bulletin: Within

250 hours time-in-service after any

inspection required by this AD in which the

damage was initially detected, modify the

surrounding structure to gain the required

minimum clearance and install a new torque

tube.

(ii) If both torque tubes on the same side

of the airplane are damaged, and the scoring

is within the maximum allowable damage

limits in the service bulletin: Prior to further

flight after any inspection required by this

AD in which damage was initially detected,

modify the surrounding structure to gain the

required minimum clearance and replace at

least one of the damaged torque tubes with

a new torque tube. Within 250 hours timein-service after any inspection in which

damage was initially detected, replace the

remaining damaged torque tube with a new

torque tube.

(iii) If any torque tube is damaged, and the

scoring is more than the allowable damage

limits described in the service bulletin: Prior

to further flight, modify the surrounding

structure to gain the required minimum

clearance and replace the damaged tube(s)

with a new torque tube(s).

(b) Accomplishment of the modification to

gain the required minimum clearance

between the torque tubes and surrounding

structure and the replacement of damaged

torque tube(s) with a new torque tube(s)

constitutes terminating action for the

requirements of this AD.

(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,

International Branch, ANM–116, 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, International Branch,

ANM–116.
63266 Federal Register / Vol. 62, No. 229 / Friday, November 28, 1997 / Rules and Regulations

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(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.

(e) The actions shall be done in accordance

with Jetstream Service Bulletin ATP–27–80,

dated April 23, 1996. 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.

Note 3: The subject of this AD is addressed

in British airworthiness directive 003–04–96.

(f) This amendment becomes effective on

January 2, 1998.

Issued in Renton, Washington, on

November 19, 1997.

Stewart R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–31027 Filed 11–26–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–187–AD; Amendment

39–10219; AD 97–24–12]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace Model BAC 1–11 200 and

400 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to all British Aerospace

Model BAC 1–11 200 and 400 series

airplanes, that currently requires a onetime inspection to determine the tension

of the control cables of the thrust

reversers, and to detect breakage,

damage, wear, or signs of corrosion; and

corrective actions, if necessary. This

amendment requires that the

inspections be repeated at certain

intervals. This amendment is prompted

by issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

actions specified by this AD are

intended to prevent failure of the

control cables, which may lead to the

inability of the thrust reverser to deploy

and/or an uncommanded deployment of

the thrust reverser while the airplane is

in flight.

DATES: Effective January 2, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 2,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from British Aerospace (Operations)

Ltd., trading as British Aerospace

Airbus Ltd., P.O. Box 77, Bristol BS99

7AR, England. 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:

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 94–17–02,

amendment 39–8997 (59 FR 41235,

August 11, 1994), which is applicable to

all British Aerospace Model BAC 1–11

200 and 400 series airplanes, was

published in the Federal Register on

September 22, 1997 (62 FR 49458). The

action proposed to require repetitive

inspections of the control cables of the

thrust reverser to determine the tension

of the control cables of the thrust

reversers, and to detect breakage,

damage, wear, or signs of corrosion; and

corrective actions, 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.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

There are approximately 42 Model

BAC 1–11 200 and 400 series airplanes

of U.S. registry that will be affected by

this AD.

The actions that are currently

required by AD 94–17–02 take

approximately 3 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour. Based

on these figures, the cost impact of the

previously required actions on U.S.

operators is estimated to be $7,560, or

$180 per airplane, per inspection cycle.

The new actions that are required by

this new AD will take approximately 3

work hours per airplane to accomplish,

at an average labor rate of $60 per work

hour. Based on these figures, the cost

impact of the new requirements of this

AD on U.S. operators is estimated to be

$7,560, or $180 per airplane, per

inspection cycle.

The cost impact figures discussed

above are 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

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: