20300 Federal Register / Vol. 63, No. 79 / Friday, April 24, 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:

98–09–04 Aerospatiale: Amendment 39–

10483. Docket 97–NM–263–AD.

Applicability: Model ATR72 series

airplanes on which Aerospatiale

Modification 2879 or Modification 2628 has

not been incorporated, 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 reduced structural integrity of

the airplane due to fatigue cracking in the

lower fuselage structure, accomplish the

following:

(a) Prior to the accumulation of 17,500 total

flight cycles, or within 500 flight cycles after

the effective date of this AD, whichever

occurs later: Except as provided in paragraph

(b) of this AD, perform a one-time high

frequency eddy current inspection to detect

fatigue cracking around the fastener holes in

the lower fuselage structure in the area of the

side brace fitting near frame 25 on the leftand right-hand sides, and modify crack-free

fastener holes, as required by paragraph (a)(1)

and/or (a)(2) of this AD, as applicable.

(1) For airplanes on which Aerospatiale

Modification 2879 has not been installed:

Perform the inspection and modification in

accordance with Aerospatiale Service

Bulletin ATR72–53–1022, Revision 2, dated

February 20, 1995.

(2) For airplanes on which Aerospatiale

Modification 2628 has not been installed:

Perform the inspection and modifications in

accordance with Aerospatiale Service

Bulletins ATR72–53–1034, Revision 1, and

ATR72–53–1053, Revision 1, both dated

March 28, 1995.

(b) If any crack or oversize hole is found

during the accomplishment of paragraph (a)

of this AD, and if any service bulletin listed

in paragraph (a) of this AD specifies to

contact the manufacturer for an appropriate

corrective action: Prior to further flight,

repair the discrepancy in accordance with a

method approved by the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate.

(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. 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.

(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 the following Aerospatiale service

bulletins, which contain the following list of

effective pages:

Service

bulletin

referenced

and date

Page number shown on page

Revision

level

shown on

page

Date shown on

page

ATR72–53–1034, Revision 1, March 28, 1995 ............ 1, 7, 9, 11–17, 20, 21, 23–25, 29, 30 ......................... 1 .............. March 28, 1995.

2–6, 8, 10, 18, 19, 22, 26–28 ..................................... Original .... November 4, 1994.

ATR72–53–1022, Revision 2, February 20, 1995 ....... 1, 11, 12, 16 ................................................................ 2 .............. February 20, 1995.

2 ................................................................................... 1 .............. November 10,

1994.

3–10, 13–15, 17–24 .................................................... Original .... July 29, 1994.

ATR72–53–1053, Revision 1, March 28, 1995 ............ 1, 6–8, 16, 19 .............................................................. 1 .............. March 28, 1995.

2–5, 9–15, 17, 18, 20 .................................................. Original .... November 7, 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 Aerospatiale, 316 Route de Bayonne,

31060 Toulouse, Cedex 03, 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.

Note 3: The subject of this AD is addressed

in French airworthiness directive 94–191–

022(B), dated August 17, 1994.

(f) This amendment becomes effective on

May 29, 1998.

Issued in Renton, Washington, on April 15,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–10478 Filed 4–23–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–226–AD; Amendment

39–10484; AD 98–09–05]

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

repetitive inspections to detect

corrosion of the brake hydraulic

accumulators in the vicinity of the

mounting straps; and corrective actions,

if necessary. 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 detect and correct corrosion

of the brake hydraulic accumulators,

which could lead to loss of hydraulic

pressure and consequent loss of braking

capability of the airplane.

DATES: Effective May 29, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 29,

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
Federal Register / Vol. 63, No. 79 / Friday, April 24, 1998 /Rules and Regulations 20301

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:

Norman B. Martenson, Manager,

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

on February 10, 1998 (63 FR 6682). That

action proposed to require repetitive

inspections to detect corrosion of the

brake hydraulic accumulators in the

vicinity of the mounting straps; and

corrective actions, if necessary.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

single comment received.

The commenter supports the

proposed rule.

Conclusion

After careful review of the available

data, including the comment 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 10 British

Aerospace BAe Model ATP airplanes of

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

that it will take approximately 2 work

hours per airplane to accomplish the

required inspection, 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 $1,200, or $120 per airplane, per

inspection cycle.

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:

98–09–05 British Aerospace Regional

Aircraft [Formerly Jetstream Aircraft

Limited, British Aerospace (Commercial

Aircraft) Limited]: Amendment 39–

10484. Docket 97–NM–226–AD.

Applicability: BAe Model ATP airplanes,

constructor’s numbers 2002 through 2063

inclusive, equipped with brake hydraulic

accumulators having APPH part number AIR

87342; 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 detect and correct corrosion of the brake

hydraulic accumulators, which could lead to

loss of hydraulic pressure and consequent

loss of braking capability of the airplane,

accomplish the following:

(a) Within 6 months after the effective date

of this AD, perform an inspection of the

brake hydraulic accumulators for corrosion,

in accordance with British Aerospace Service

Bulletin ATP–32–80, Revision 1, dated July

9, 1997. If any discrepancy is found, prior to

further flight, accomplish corrective actions,

as applicable, in accordance with the service

bulletin. Repeat the inspection thereafter at

intervals not to exceed 2 years.

(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,

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.

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.

(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 British Aerospace Service Bulletin

ATP–32–80, Revision 1, dated July 9, 1997,

which contains the following list of effective

pages:

Page No.

Revision

level shown

on page

Date shown

on page

1, 3 .............. 1 .................. July 9, 1997.

2, 4–7 .......... Original ........ June 19, 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 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 004–06–97

(undated).

(e) This amendment becomes effective on

May 29, 1998.
20302 Federal Register / Vol. 63, No. 79 / Friday, April 24, 1998 /Rules and Regulations

Issued in Renton, Washington, on April 15,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–10479 Filed 4–23–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–135–AD; Amendment

39–10485; AD 98–09–06]

RIN 2120–AA64

Airworthiness Directives; Saab Model

SAAB SF340A and SAAB 340B Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Saab Model SAAB

SF340A and SAAB 340B series

airplanes, that requires an inspection to

determine the serviceability of the fire

extinguisher of the forward lavatory

waste bin, and corrective actions, if

necessary. This amendment also

requires installation of a placard

adjacent to the fire extinguisher in the

forward lavatory waste bin. This

amendment is prompted by the issuance

of mandatory continuing airworthiness

information by a foreign civil

airworthiness authority. The actions

specified by this AD are intended to

prevent leakage of the fire extinguishing

agent, which could prevent proper

distribution of the agent within the

lavatory waste bin in the event of a fire.

DATES: Effective May 29, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 29,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from Saab Aircraft AB, SAAB Aircraft

Product Support, S–581.88, Linko ̈ping,

Sweden. 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:

Norman B. Martenson, Manager,

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 Saab Model

SAAB SF340A and SAAB 340B series

airplanes was published in the Federal

Register on October 29, 1997 (62 FR

56137). That action proposed to require

an inspection to determine the

serviceability of the fire extinguisher of

the forward lavatory waste bin, and

corrective actions, if necessary. The

action also proposed to require

installation of a placard adjacent to the

fire extinguisher in the forward lavatory

waste bin.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

single comment received.

The commenter supports the

proposed AD. However, the commenter

notes that unsafe condition addressed in

this proposed AD may be more

generally present in the transport

airplane fleet, and proposes a number of

requirements to address that problem:

—Since other installations with

capillary tubes may be subject to the

same type of failure, the suggests that

some sort of protection from

‘‘kinking’’ of similar capillary tubes

should be required.

—A feature should be added to the fire

extinguisher bottle to enable more

frequent inspection of lavatory fire

extinguisher bottles and their

contents.

—The fire bottle should be inspected in

place for proper pressure at least

every seven days and should be

removed at least annually and

weighed.

—Engine fire bottles that are low in

pressure result in an indication to the

flight crew; a similar indication may

be needed for this installation.

—A pressure indicator on the fire bottle

should be a required item; the

commenter states that, currently, it

has been removed on some airplanes.

The FAA acknowledges the concerns

of the commenter. The FAA has

determined that an unsafe condition

exists, and that the actions required by

this AD are adequate in order to ensure

the continued safety of the affected fleet.

While there may be merit to the

commenter’s suggestions, this AD is not

the appropriate context in which to

evaluate those suggestions. Since the

suggested changes would alter the

actions currently required by this AD,

additional rulemaking would be

required. The FAA finds that to delay

this action would be inappropriate in

light of the identified unsafe condition.

No change to this final rule is necessary.

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 141 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 2

work hours 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 $16,920, or $120 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.